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AGH University of Science and Technology

Faculty

of

Mechanical

Engineering

and

Robotics

Doctoral Thesis

Welding sequence Analysis

By

Isaac Hernández Arriaga

Co‐Advisor: Dr. Hab. Piotr Rusek, Prof. AGH

Dr. Eduardo Aguilera Gómez

September 2009

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Welding Sequence Analysis


ABSTRACT

This thesis has been divided in nine chapters.

Chapter 1 provides brief background and general and specific objectives of this work.

Chapter 2 presents the methods and advantages of reducing or controlling residual stresses and distortio

induced by the welding process as well as a definition and classification of the welding sequence. It als

presents a study of the welding sequence analysis, a survey of previous research in the field of weldin

sequences, and a discussion of its advantages, disadvantages, scope, and limitations.

The subject of Chapter 3 is the finite element modeling of the welding processes, defining the bounda

and initial conditions of the welding process and studying the effects of the welding sequence on the residu

stress distribution and distortion in symmetrical structures. It should be noted that the proposed numeric

model has general applicability and is not limited to symmetrical structures. The proposed sequentiall

coupled thermo-mechanical analysis involves two steps. A transient heat transfer analysis is performe

followed by a thermal elastic plastic analysis. This numerical simulation is performed in an I-type specime

subject to tension and validated with experimental data [25]. Finally, the chapter presents a numeric

simulation of the welding sequence in an L-type structure to demonstrate that the proposed numerical mod

accurately simulates the effects of the welding sequence on residual stresses and distortion.

Chapter 4 presents a study of the effects of the welding sequence on residual stresses and distortion in

stiffened symmetrical flat frame. Selected welding sequences reduce residual stresses, distortion, or th

relation between both parameters. These proper welding sequences are obtained from empirical weldin

rules, axis of symmetry, center of gravity of the frame, and concentric circles. The origin of the circles coincid

with the center of gravity of the frame, and the radius of the circles is formed by the center of gravity of th

frame with the center of gravity of each of the weld beads. The different welding sequences are analyzed wit

the numerical model developed in chapter 3. Finally, the chapter presents a procedure to determine th

proper welding sequences to reduce residual stress, distortion or the relation between both parameters for

dimensional symmetrical structures.

The main goal chapter 5 is to demonstrate that the procedure to determine the proper welding sequenc

to reduce residual stress, distortion or the relation between both parameters in 2-dimensional symmetric

structures can be applied to 3-dimensional symmetrical structures. This is done by studying the effects of th

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welding sequence on the residual stresses and distortion in a 3-dimensional unitary cell-type symmetric

structure. Now the weld bead circles become spheres. To demonstrate the procedure to determine the prop

welding sequence for 3-dimensional symmetrical structures, four numerical simulations are performed in th

proposed symmetrical structure. Two of these numerical simulations deal with the proper welding sequenc

to reduce residual stress and the other two deals with the proper welding sequence to reduce distortion. Alsthe numerical simulation of a special welding sequence is performed for comparison with the proper weldin

sequence to reduce distortion. This special welding sequence applies the external weld beads first and th

internal weld beads later. All the numerical simulations are based on the proposed numerical model of th

welding process developed in Chapter 3.

Chapter 6 presents a methodology for the development of the experimental tests. This methodology hel

to plan, execute, and control each of the stages of the experimental tests. The methodology starts with th

material selection of the specimen, configuration selection, welding process selection, metal transfer mod

selection, welding parameter selection, design and fabrication of the equipment needed to run the tedesign and fabrication of the mounting locks, residual stresses relief caused by the manufacturing proces

transportation, handling, storage and cutting of the plates, measurement of the initial distortion of the plate

design and fabrication of a holder-mounting device to hold the plates, design and fabrication of a squar

mounting device to square the holder-mounting device, application of welding tacks, measurement of th

distortion after applying the welding tacks, installation of the run-off tabs, application of the welding, remov

of the run-off tabs of the welded structure, measurement of the distortion after welding, and measurement

the final distortion induced by the welding process.

Chapter 7 covers the results of the experimental tests performed in 3-dimensional unitary cell-typsymmetrical specimens. In these experimental tests, the effects of the welding sequence on distortion a

studied. Eight symmetrical specimens are prepared. Four welding sequences are considered: two of them a

adequate to reduce distortion and the other two reduce residual stresses. The chapter also studies the effec

that occur when a welding bead is divided into 3 sub-weld beads, as well as the effects of relieving the residu

stresses caused by manufacturing process, transportation, storage and cutting of plates. Welding tacks a

applied to all specimens before the actual weld process begins. The measurement of the distortion

periodically performed to observe if rheological effects occur in the specimens after welding. The experiment

tests were performed in the Department of Machine Strength and Manufacturing in the Faculty of Mechanic

Engineering at the University of Science and Technology in Krakow, Poland.

Chapter 8 presents a comparison between the numerical results obtained in Chapter 5 and th

experimental results obtained in Chapter 7 for the 3-dimensional unitary cell-type symmetrical structure. Th

comparison discusses the distortion modes and the distortion in the 24 points of interest. The chapte

presents the procedures to determine the proper welding sequences to reduce the residual stresse

distortion, or a relation between both parameters in symmetrical and asymmetrical structures in 2 and

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dimensions. These procedures were developed in chapters 4 and 5 to determine the proper weldin

sequences to reduce residual stresses, distortion, or relation between both parameters in symmetric

structures in 2 and 3 dimensions.

Chapter 9 presents the conclusions, contributions and suggestions for future work.

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ACKNOWLEDGMENTS

I am extremely grateful for the support of the University of Guanajuato and AGH University of Science an

Technology. They provide employment and resources which made it possible for me to pursue this degree.

I wish to express my sincere appreciation to Dr. Eduardo Aguilera for his guidance, encouragement an

insight throughout the duration of this research.

I would also express my gratitude to Professor Piotr Rusek for his encouragement and support, h

influence extends far beyond my academic work.

I wish to tanks to Dr. Arturo Lara, Dr. Elias Ledesma, Professor Stanisław Wolny, and Professor Andrz

Skorupa for serving as dissertation committee members and providing positive suggestion and comments.

I acknowledge the Consejo Nacional de Ciencia y Tecnología (CONACYT), Dirección de Relacion

Academicas Internacionales e Interinstitucionales (DRAII), and Dirección de Investigación y Posgrado (DINPO

of the University of Guanajuato for the funding of doctoral studies, doctoral research and stay at AGH.

I would also like to express my gratitude to Director of the engineering division of the Irapuato-Salamanc

Campus; Dr. Oscar Ibarra, for his invaluable support in the completion of my doctoral studies.

I would especially like to thank the Authorities of the AGH University of Science and Technology; Recto

Professor Antoni Tajduś, Vice-Rector for Cooperation and Development, Professor Jerzy Lis, and Dean of th

faculty of Mechanical Engineering and Robotics, Professor Janusz Kowal for thier invaluable collaboration wi

the University of Guanajuato.

I am also grateful to Dr. Hector Plascencia for his interest and help to my research. Also, I would like thank to Dr. Pedro de Jesús García and to Dr. Rogelio Navarro for their initial help, interest and advice.

I am very grateful to Dr. Tomasz Góral for his help on experimental research. Thanks are also extended t

Drs. Jerzy Haduch and Andrzej Tyka for their assistance.

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During my stay at AGH, I was fortunate to have had a number of talented technical workers. Kazimie

Nawrot, Włodzimierz Rusek, and Artur Konopczak all helped with the fabrication of the equipment needed t

run the test.

My thanks to Salvador Martínez, for his friendly help in the experimental measurements at AGH. The samquality of special thanks goes to Mr. Guadalupe Negrete for his expertise and generous help in welding .

My special thanks go to Renato Sánchez for giving me their generous and solidary support.

To all my friends and classmates, especilly Hijinio Juárez, Alejandro León, Sergio Pacheco and M

Baldomero Lucero, thank you for your warm friendships.

To Ms. Ma. Eugenia Gallardo, secretary of our Mechanical Department, for helping me during my studies.

My academic achievements would have been impossible without the spiritual support of my family. Spec

thanks are due to my parents, Beny Arriaga and Daniel Hernández. Their sacrifice for my education made m

who I am. Thanks are also extended to my sister and brother; Ruth Hernández and Daniel Hernández, for the

understanding and support for my studies. Special love goes to my wife, Maria Victoria Cabrera who

boundless love and encouragement made my time at University of Guanajuato and AGH easy and pleasan

Also, my cute son, Samuel Isaac Hernández, enabled me to periodically escape the academic pressure with h

smiles.

Finally, I thank an anonymous editor for assisting with the English version of my thesis.

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TABLE OF CONTENTS

Abstract

Acknowledgments iv

Table of contents v

List of figures xi

List of tables xvi

Nomenclature xix

Chapter I INTRODUCTION

1.1 Background 1

1.2 General objective 2

1.3 Specific objectives 2

Chapter II WELDING SEQUENCE BACKGROUND AND METHODS FOR CONTROLLING RESIDUAL

STRESSES AND DISTORTION INDUCED BY WELDING

2.1 Introduction 3

2.2 Advantages of residual stress and distortion control 3

2.3 Methods to control welding-induced residual stress and distortion 4

2.3.1 Welding sequence 4

2.3.2 Definition of weld parameter 4

2.3.3 Weld procedure 5

2.3.4 Fixture design 5

2.3.5 Precambering 5

2.3.6 Prebending 6

2.3.7 Thermal tensioning 6

2.3.8 Heat sink welding 7

2.3.9 Preheating 7

2.10 Post-weld heat treatment 7

2.11 Post-weld corrective methods 7

2.4 Welding sequence definition 8

2.5 Welding sequence classification 8

2.5.1 Welding sequence for single pass welds 8

2.5.2 Welding sequence for multiple pass welds 9

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v


2.6 Welding sequence selection based on empiric rules 10

2.7 Welding sequence background 11

2.8 Summary of the welding sequence analysis background 43

2.9 Matrix of the welding sequence analysis background 44

Chapter III PROPOSAL OF A NUMERICAL SIMULATION OF THE WELDING PROCESS AND A NUMERICAL

SIMULATION OF THE WELDING SEQUENCE IN AN L-TYPE STRUCTURE

3.1 Introduction 45

3.2 Heat transfer in welding 45

3.2.1 Analytical solution for the temperature field 46

3.2.2 Thermal Initial and boundary Conditions 48

3.3 Thermal elastic plastic stress analysis in welding 50

3.3.1 Mechanical equations 503.3.2 Mechanical initial and boundary conditions 51

3.4 Finite element solution of the welding 51

3.4.1 Finite element solution of heat transfer in welding 51

3.4.2 Finite element solution of the thermal elastic plastic stress analysis in welding 52

3.5 Geometric configuration of I-type specimen subject to tension 55

3.6 Material selection for the I-type specimen subject to tension 56

3.7 Temperature-dependent thermal and mechanical properties of ASTM A36 56

3.8 Finite element model of the I-type specimen subject to tension 57

3.8.1 Definition and justification of the applied finite elements 58

3.8.2 Thermal initial and boundary conditions 61

3.8.3 Mechanical boundary condition 61

3.8.4 Body load 61

3.8.5. Solution of the finite element model 62

3.9 Points of interest in the finite element model of the I-type specimen subject to tension 62

3.10 Residual stresses in the I-type specimen subject to tension obtained in the numerical simulation 62

3.11 Comparison between the numerical and experimental results of an I-type specimen subject to

tension

63

3.12 Conclusions of the numerical simulation of the welding process in an I-type specimen subject to

tension

64

3.13 Numerical simulation of the welding sequence in an L-type structure 65

3.14 Geometric configuration of the L-type structure 65

3.15 Finite element model of the L-type structure 65


3.15.2 Mechanical boundary conditions 67

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3.15.3 Solution of the finite element model of the L-type structure 67

3.16 Configuration of welding sequences for the L-type structure 67

3.17 Localization of the point of interest in the L-type structure 68

3.18 Numerical results in the L-type structure 68

3.18.1 Distortion profile in the L-type structure 703.18.2 Residual stress distribution in the L-type structure 70

3.19 Experimental tests for the L-type structure 71

3.19.1 Selection of points of interest in the L-type structure 72

3.19.2 Configuration of the welding sequences in the L-type specimens 72

3.19.3 Measurement of distortion on L-type specimens 73

3.20 Conclusions of the welding sequence analysis of the L-type structure 75

Chapter IV WELDING SEQUENCE ANALYSIS IN A STIFFENED SYMMETRICAL 2-DIMENSIONAL FRAME

4.1 Introduction 76

4.2 Geometric configuration of a stiffened symmetrical flat frame 76

4.3 Welding configuration in the stiffened symmetrical flat frame 77

4.4 Finite element model of the stiffened symmetrical flat frame 80



4.4.3 Solution of the finite element model of the stiffened symmetrical flat frame 82

4.5 Numerical results in the stiffened symmetrical flat frame 82

4.5.1 Distribution of the residual stresses in the stiffened symmetrical flat frame 824.5.2 Distortion profile in the stiffened symmetrical flat frame 83

4.6 Analysis of residual stress-distortion relations analysis 83

4.7 Order of importance of the welding sequences to reduce residual stress, distortion, or the

relation between them in the stiffened symmetrical flat frame

84

4.8 Proper welding sequences to reduce the residual stress, distortion, or a relation between them

in the stiffened symmetrical flat frame

84

4.8.1 Proper welding sequence to reduce the residual stress in the stiffened symmetrical flat

frame

86

4.8.2 Proper welding sequence to reduce distortion in the stiffened symmetrical flat frame 87

4.8.3 Proper welding sequence to improve the relation between both critical parameters in the

stiffened symmetrical flat frame

87

4.9 Hypothesis to determine the proper welding sequence to reduce the residual stress, distortion,

or a relation between them in symmetrical flat structures

88

4.10 Experimental tests in a stiffened symmetrical flat frame specimen 89

4.10.1 Selection of points of interest in the stiffened symmetrical flat specimen 90

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4.10.2 Configuration of the welding sequence in the stiffened symmetrical flat specimen 90

4.10.3 Measurement of distortion on the stiffened symmetrical flat specimen 91

4.11 Conclusions of the welding sequence analysis of stiffened symmetrical flat frame 93

Chapter V WELDING SEQUENCE ANALYSIS IN A 3-DIMENSIONAL UNITARY CELL-TYPESYMMETRICAL STRUCTURE

5.1 Introduction 95

5.2 Hypothesis to determine the proper welding sequence to reduce the residual stress, distortion,

or a relation between them in 3-dimensional symmetrical structures

96

5.3 Geometric configuration of the 3-dimensional unitary cell 97

5.4 Selection of the number of weld beads in the 3-dimensional unitary cell 98

5.5 Symmetry axis selection and formation of the concentric spheres in the 3-dimensional unitary

cell

98

5.6 Proper welding sequence to reduce the residual stress and proper welding sequence to reduce

the distortion in the 3-dimensional unitary cell

100

5.7 Material selection of the 3-dimensional unitary cell 101

5.8 Fillet weld shape used in the 3-dimensional unitary cell 101

5.9 Finite element model of the 3-dimensional unitary cell 101



5.9.3 Solution of the finite element model of the 3-dimensional unitary cell 103

5.10 Localization of the points of interest in the 3-dimensional unitary cell 103

5.11 Configuration of the numerical simulation for the 3-dimensional unitary cell 104

5.12 Numerical results of the different welding sequences analyzed in the 3-dimensional unitary cell 105

5.12.1 Maximum von Mises residual stress in the 3-dimensional unitary cell 105

5.12.2 Distortion modes in the 3-dimensional unitary cell 106

5.12.3 Maximum distortion and distortion in 24 points of interest in the 3-dimensional unitary

cell

106

5.13 Numerical comparison between the proper welding sequence to reduce distortion and a special

welding sequence in the 3-dimensional unitary cell

107

5.14 Conclusions of the welding sequence analysis of the 3-dimensional unitary cell 109

Chapter VI METHODOLOGY OF EXPERIMENTAL TESTS

6.1 Introduction 110

6.2 Specimen material selection 110

6.3 Selection of specimen configuration 111

6.4 Selection of the welding process 111

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6.5 Selection of metal transfer mode 111

6.6 Selection of welding parameters (Operating variables) 112

6.6.1 Arc voltage and welding current 112

6.6.2 Welding speed 113

6.6.3 Wire feed rate 1136.6.4 Selecting of contact tip to work distance 114

6.6.5 Electrode orientation 114

6.6.6 Electrode diameter 115

6.6.7 Shielding gas composition 115

6.6.8 Gas flow rate 116

6.7 Design and fabrication of the equipment needed to run the test 116

6.8 Design and fabrication of the mounting locks 117

6.9 Relief of residual stresses caused by the manufacturing process, transportation, handling,

storage and cutting of the plates

118

6.10 Measurement of the initial plate distortion 119

6.11 Design and fabrication of a holder-mounting device to hold the plates 120

6.12 Design and fabrication of a square-mounting device 120

6.13 Application of the welding tacks 121

6.14 Distortion measurement after welding tack application 123

6.15 Installation of the run-off tabs 123

6.16 Application of the welding 124

6.17 Removing the run-off tabs from the welded structure 124

6.18 Measurement of the distortion after applying the welding 1256.19 Measurement of the final distortion 126

Chapter VII RESULTS OF THE EXPERIMENTAL TESTS IN 3-DIMENSIONAL UNITARY CELL-TYPE SPECIMENS


7.2 Configuration of the 3-dimensional unitary cell specimens 127

7.3 Localization of the points of interest in the 3-dimensional unitary cell specimens 128

7.4 Configuration of the experiment 128

7.5 Distortion after applying welding tacks in the 3-dimensional unitary cell specimens 128

7.6 Distortion after welding in the 3-dimensional unitary cell specimens 129

7.7 Distortion modes of the 3-dimensional unitary specimens 132

7.8 Final distortion of the 3-dimensional unitary cell specimens 133

7.9 Final Remarks for distortion of the 3-dimensional unitary cell specimens 135

7.10 Conclusions of the results of the experimental test in 3-dimensional unitary cell specimens 136

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Chapter VIII COMPARISON BETWEEN THE “3- DIMENSIONAL UNITARY CELL”-TYPE

STRUCTURES/SPECIMENS


8.2 Comparison of distortion modes 1378.3 Comparison of distortion 137

8.4 Conclusions of the comparison between numerical and experimental results 140

8.5 Procedures to determine the proper welding sequences to reduce residual stress, distortion, or

a relation between them in symmetrical and asymmetrical structures in 2 and 3 dimensions

140

8.5.1 Symmetrical structures in 2 and 3 dimensions 140

8.5.2 Asymmetrical structures in 2 and 3 dimensions 142

Chapter IX CONCLUSIONS, CONTRIBUTIONS, AND SUGGESTIONS FOR FUTURE RESEARCH

9.1 Conclusions 146

9.2 Contributions 147

9.3 Suggestion for future research 147

REFERENCES 149

APPENDIX

1 Plasticity theory applied to welding process and its formulation by finite element method 151

2 Definition and justification of the applied finite elements 171

3 Response to critical comments 179

4 Proper welding sequence to reduce residual stress and distortion in common symmetrical

structures in 2 and 3 dimensions based on the hypothesis developed in the sections 4.9 and 5.2.

188

5 Listing of commands of the numerical simulation of the welding process (I-type specimen

subject to tension)

191

6 Listing of commands of the numerical simulation of the welding sequence in an L-type structure

(Welding sequence No.1)

194

7 Listing of the commands of the numerical simulation of stiffened symmetrical flat frame

(welding sequence No.5 with welding tacks)

197

8 Listing of the commands of the numerical simulation of the 3-dimensional unitary cell-type

symmetrical structure (welding sequence most appropriate to reduce distortion with 24 weld

beads and welding tacks)

201

9 Construction drawings 205

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LIST OF FIGURES

CHAPTER II

Figure 2.1 Welded frame distortion [4]: (a) Without considering a proper welding sequence,

(b) considering a proper welding sequence

4

Figure 2.2 Rigid supports [4] 5

Figure 2.3 Precamber with a curved surface [2] 6

Figure 2.4 Pre-bending [2] 6

Figure 2.5 Welding with the thermal tensioning process [11] 6

Figure 2.6 Heat sink welding [1] 7

Figure 2.7 Sequences for thin-wall butt-welds [3]: (a) Progressive, (b) backstep, (c) symmetric, and

(d) jump

8

Figure 2.8 Built-Up welding sequence on thick-wall butt-weld [3] 9

Figure 2.9 Block welding sequence [3] 9

Figure 2.10 Cascade welding sequence [3] 9

Figure 2.11 Welding sequences for thin-wall butt-welds [16]: (a) Progressive, (b) backstep, and (c)

symmetric

11

Figure 2.12 Longitudinal residual stress distribution [16]: (a) Along the X-direction and (b) along the

Y-direction

12

Figure 2.13 Different welding sequence for thick-wall butt-welds [16] 13

Figure 2.14 Residual stresses distribution along the X-direction in various welding sequence for

thick-wall butt-welds [16]: (a) Longitudinal and (b) transverse

14

Figure 2.15 Geometry and various welding sequence for circular patch [16]: (a) Geometry of circular

patch welding, (b) Progressive sequence, (c) backstep sequence, and (d) jump sequence

15

Figure 2.16 Residual stresses distribution for various welding sequence [16]:(a) Circumferential and

(b) radial

16

Figure 2.17 Dimensions of the specimen, mm. [17] 17

Figure 2.18 Schematic of Weld bead´s delamination [17] 17

Figure 2.19 Comparison of transverse residual stress between in the same direction and welding in

the inverse direction [17]

18

Figure 2.20 Configuration of welded blocks in a multi-block welding sequence [18] 19

Figure 2.21 Structural boundary conditions of welded plates (clamp fixture at both sides) [18] 19

Figure 2.22 Resulted distortion profile for two different block sequences [18]: (a) Welding sequence

No. 1 and (b) welding sequence No. 2

20

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Figure 2.23 Resulted distribution of the Von Mises stress using different block sequences. [18]:

(a) Welding sequence No. 1 and (b) welding sequence No. 2

21

Figure 2.24 Configuration of a large-diameter multi-pass pass butt-welded pipe joints and its cross

section [19]

22

Figure 2.25 Welding sequences for a multi-pass Welded pipe joint [19] 22Figure 2.26 Comparison of circumferential residual stress in multi-pass welded pipe joints [19]: (a)

Inner surface and (b) outer surface

23

Figure 2.27 Comparison of axial residual stress in multi-pass welded pipe joints [19]: (a) Inner

surface and (b) outer surface

24

Figure 2.28 Comparison of residual stress across through-thickness along the heat-affected zone in

multi-pass welded pipe joints [19]: (a) Circumferential and (b) axial

25

Figure 2.29 Configuration of a multi-pass fillet Weld joint, mm. [20] 27

Figure 2.30 Different welding sequences in multi-pass fillet weld joint [20] 27

Figure 2.31 Comparison of residual stress in a multi-pass fillet weld joint [20]: (a) Case 1 and(b) case 2

28

Figure 2.32 Relation between nominal stress range and fatigue life in multi-pass fillet weld joints

[20]

29

Figure 2.33 Aluminum panel for study on welding sequence effect on angular distortion [21] 30

Figure 2.34 Welding sequences for angular distortion analysis of aluminum panel structure[21] 31

Figure 2.35 Distortion displacements at four cross sections of the panel from four welding

sequences [21]: (a) At x= 16 inch; (b) at x=32 inch; (c) at y= 9.3 inch; y (d) at y=30 inch.

32

Figure 2.36 Optimum welding sequence determined by JRM [21] 33

Figure 2.37 Comparison of distortion resulting from welding sequence and the optimum weldingsequence [21]: (a) at x= 16 inch, (b) at x=32 inch, (c) at y= 9.3 inch, and (d) at y=30 inch.

33

Figure 2.38 T-joint configuration [22]: (a) Finite element model and (b) dimensions of the cross

section of the hollow extrusions

34

Figure 2.39 Different welding sequences [22]: (a) Case 1 and (b) case 2 34

Figure 2.40 Comparison of measured (M) and calculated (S) distortion evolution for two welding

sequence [22]: (a) Case 1 and (b) case 2

35

Figure 2.41 Geometric configuration of a sub-assembly [15] 36

Figure 2.42 Simplified model with torsion springs [15] 36

Figure 2.43 Final exaggerated deformed shapes for different sequences [15] 37Figure 2.44 Geometric configuration and dimensions of weldment [23] 38

Figure 2.45 Code to designate the welding sequence and welding direction [23] 39

Figure 2.46 Radial displacement of the edge of plate with respect to θ for continuous welding and

the optimum sequence[23]

39

Figure 2.47 Tail bearing housing [24] 41

Figure 2.48 Finite element model of welding process and designation of welding paths showing 41

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positive orientation of weld and reference number in sequence [24]

Figure 2.49 Run 28 is the optimized displacement with a clamped structure [24] 42

Figure 2.50 The absolute values of the X displacement for all 28 sequences [24] 42

CHAPTER III

Figure 3.1 Eulerian frame and thermal initial and boundary conditions 49

Figure 3.2 Geometric configuration of I-type specimen subject to tension (mm) [25] 55

Figure 3.3 Thermal and mechanical properties of ASTM A36 as a function of temperature [34] 56

Figure 3.4 Stress-strain behavior of ASTM A36 carbon steel for different temperatures [Based in

figure 3.3]

57

Figure 3.5 Finite element mesh of the I-type specimen subject to tension 58

Figure 3.6 Weld thermal cycle of ASTM A36 carbon steel [34-35] 60

Figure 3.7 Localization of the points of interest on finite element model 62Figure 3.8 Distribution of residual stresses in the X-direction in the I-type specimen subject to

tension

63

Figure 3.9 Experimental tests: a) Localization of the points of interest in the I-type specimen

subject to tension, mm. b) welding parameters employed [25]

64

Figure 3.10 Geometric configuration of the L-type structure (mm) 65

Figure 3.11 Finite element model of the L-type structure 66

Figure 3.12 Localization of the node 1533 in the L-type structure 68

Figure 3.13 Maximum distortions in L-type structure for three different welding sequences 69

Figure 3.14 Maximum Von Mises residual stress in the L-type structure for three different welding

sequences

69

Figure 3.15 Distortion profile in the L-type structure corresponding to welding sequence 3 70

Figure 3.16 Distribution of Von Mises residual stress corresponding to the welding sequence 2 71

Figure 3.17 Localization of the interest points in the L-type specimen 72

Figure 3.18 L-type specimen 2 after applying the welding sequence 3 73

Figure 3.19 L-type specimen 2 (welding sequence 3) mounted on the coordinate measuring

machine

73

Figure 3.20 Comparison of the welding distortion (exaggerated) between two L-type specimens 75

CHAPTER IV

Figure 4.1 Geometric configuration of the stiffened symmetrical flat frame (mm) 77

Figure 4.2 Finite element model of the stiffened symmetrical flat frame 80

Figure 4.3 Distribution of Von Mises residual stresses corresponding to the welding sequence

(5 I-O)

82

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Figure 4.4 Distortion profile corresponding to the welding sequence 5 O-I WT 83

Figure 4.5 Centers of gravity of the structure, centers of gravity of the weld beads, axis of

symmetry and concentric circles in the stiffened symmetrical flat frame

86

Figure 4.6 Ranges of the values of P and W for welding sequence 1 I-O and combined welding

sequence

87

Figure 4.7 Localization of the point of interest in the stiffened symmetrical flat specimen 90

Figure 4.8 Stiffened symmetrical flat specimen after applying the welding sequence 5 O-I WT 91

Figure 4.9 Stiffened symmetrical flat specimen mounted on the coordinate measuring machine 91

Figure 4.10 Distortion profile in the stiffened symmetrical flat specimen corresponding to welding

sequence 5 O-I WT (exaggerated)

93

CHAPTER V

Figure 5.1 Panel used in the welding industry 97Figure 5.2 Configurations and dimensions of the 3-dimensional unitary cell (mm) 98

Figure 5.3 Axis of symmetry and concentric spheres of the 3-dimensional unitary cell formed by 24

fillet welds 99

Figure 5.4 Different welding sequences for the 3-dimensional unitary cell 100

Figure 5.5 Fillet weld shape used in the 3-dimensional unitary cell 101

Figure 5.6 Finite element model of the 3-dimensional unitary cell 102

Figure 5.7 Localization of the points of interest in the 3-dimensional unitary cell 104

Figure 5.8 Distribution of residual stresses corresponding to numerical simulation 2 105

Figure 5.9 Isometric view of the distortion profile corresponding to the numerical simulation 3 106Figure 5.10 Configuration of the special welding sequence 108

CHAPTER VI

Figure 6.1 Semiautomatic welding machine OPTYMAG 501 112

Figure 6.2 Typical zone of good short circuit welding conditions [37] 113

Figure 6.3 Contact tip to work distance [40] 114

Figure 6.4 Positioning of electrode gun with respect to the base metal plate [37] 114

Figure 6.5 Normal work angle for fillet welds [37] 115Figure 6.6 Arm-holder device 116

Figure 6.7 Welding torch holder device 117

Figure 6.8 Localization of the locks mounted on the traveler carriage 118

Figure 6.9 Electric oven used to initial residual stresses relief 119

Figure 6.10 Measurement of the initial distortion with standard gages 119

Figure 6.11 Holder-mounting device 120

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Figure 6.12 Square-mounting device 121

Figure 6.13 C-type clamps mounted on the specimen 122

Figure 6.14 Welding tacks application in the specimen 122

Figure 6.15 Installation of the run-off tabs on the specimen 123

Figure 6.16 Application of the welding to the specimen 124Figure 6.17 Removing of the run-off tabs of the specimen 125

Figure 6.18 Measurement of the distortion after applying welding using standard gages 125

CHAPTER VII

Figure 7.1 Distortion (exaggerated) after applying welding tacks and after welding for specimen T9 131

Figure 7.2 Distorted shape of the 3-dimensional unitary cell welded specimens 132

Figure 7.3 Final distortion (exaggerated) for welded specimen T9 134

CHAPTER VIII

Figure 8.1 Comparison between numerical (simulation 3) and experimental distortion (specimen

T9). Exaggerated distortion. 139

Figure 8.2 Flow Diagram of the analysis of the welding sequence for symmetrical and asymmetrical

structures in 2 and 3 dimensions

144

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xv


LIST OF TABLESCHAPTER II

Table 2.1 Different welding sequences used by Ji and Fang [17] 17

Table 2.2 Residual stress´s peak value for several cases [17] 18

Table 2.3 Welding sequences and orders applied into the multi-block model [18] 19

Table 2.4 Different welding sequence used by Bart, Deepak and Kyoung [15] 36

Table 2.5 for various welding conditions [23] 40

CHAPTER III

Table 3.1 Chemical composition of ASTM A36 carbon steel [33] 56Table 3.2 Residual stresses obtained in the numerical simulation of I-type specimen subject to

tension

63

Table 3.3 Comparison between numerical data and experimental data of two I-type specimen

subject to tension

64

Table 3.4 Welding sequence configuration in the L-type specimen 68

Table 3.5 Distortion at the points of interest in two L-type specimens 74

CHAPTER IV

Table 4.1 Welding sequences from the inside to the outside used in the stiffened symmetrical flat

frame

78

Table 4.2 Welding sequences from the outside to the inside used in the stiffened symmetrical flat

frame

79

Table 4.3 Order of importance of the analyzed welding sequences in the stiffened symmetrical flat

frame

85

Table 4.4 Configuration of welding sequence 5 O-I WT used in the stiffened symmetrical flat

specimen

90

Table 4.5 Distortion at the points of interest (mm) in the stiffened symmetrical flat specimen

corresponding to welding sequence 5 O-I WT

92

CHAPTER V

Table 5.1 Configuration of the numerical simulations for the 3-dimensional unitary cell 104

Table 5.2 Distortion at 24 points of interest (mm) corresponding to different welding sequences

In the 3-dimensional unitary cell 107

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xv


Table 5.3 Comparison of numerical results between both welding sequences In the

3-dimensional unitary cell

108

CHAPTER VI

Table 6.1 Electric settings used in the short circuit transfer mode [39] 113

Table 6.2 Common blends of shielding gas composition for short transfer mode [40] 115

CHAPTER VII

Table 7.1 3-dimensional unitary cell specimen configuration 128

Table 7.2 Distortion after application of the welding tacks for the different 3-dimensional unitary

cell specimens, mm.

129

Table 7.3 Distortion after welding for the different 3-dimensional unitary cell specimens 24 hrsafter welding, mm.

130

Table 7.4 Final distortion in the 24 points of interest of the 3-dimensional unitary cell specimens,

mm.

133

CHAPTER VIII

Table 8.1 Difference (%) between numerical and experimental results 138

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x


NOMENCLATURE

Mathematical symbols Units

Rectangular matrix -

Column vector, row vector -

Matrix transpose -

Matrix inverse -

, Partial differentiation if the following subscript is a letter -

Latin symbols

[ ] B Strain-displacement matrix for each element -

C Specific heat J/Kg°C

[ ]C

Damping matrix Kg/s

Power of viscoplastic straining 1/s

Increment of; for example ,Tot

ijd ε -

ep D Elastic-plastic stiffness matrix -

e

ije Deviation component of elastic strain tensor µε

E Young´s modulus N/m

ijkl E

2

Elastic tensor N/m

ep

ijkl E

2

Elastic-plastic tensor N/m

t

ijkl E

2

Tangent elastic tensor N/m

i f

2

Sum of the body force N

Elastic forces N

Inertia forces NDamping forces N

( ) 0 f = Yield surface -

{ }eF Element load vector N

{ }F Global load vector N

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x


{ }t F Global load vector corresponding at time t N

{ }i

t t F +∆

Nodal load vector corresponding to the state of stress for the time t ∆ -

( )2 1

E G

v

=

+

Shear modulus N/m

( ) 0G =

2

Plastic potential -

h Convection heat transfer coefficientc W/m

2

H

°C

Hardening modulus -

i Iteration number -

k x , k y , k Thermal conductivity in the x, y and z directions z W/m°C

( )3 1 2

E K

v=

−

Bulk modulus N/m

[ ]K

2

Global stiffness matrix N/m

[ ]eK Element stiffness matrices N/m

t K Stiffness matrix in the time N/m

[ ] M

Mass matrix Kg

n Number of nodal points for each element -

( , , )i

N x y z Shape functions -

N x , N y , N Cosine directors z -

q Boundary heat fluxs W/m

Q(x,y,z,t)

2

Source of heat generation W/m

{ }t R

3

Nodal point force corresponding at time t -

{ }s Stress deviation increment vector -

s Stress deviation tensorij N/m

T(x,y,z,t)

2

Current temperature °C

Prescribed surface temperature °C

T∞ Surrounding temperature °C

mT Melting temperature °C

{ }dT α Thermal dilatation vector -

t ∆ Time interval sec

cr t ∆ Critical time step sec

Displacement vector m

Velocity vector m/s

Acceleration vector m/s2

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x


,i ju Displacement gradient -

( )r U Radial distortion with respect to θ mm

Maximun radial distortion mm

{ }U ∆

Element nodal increments -

{ }iU ∆ Nodal increment vector in the iteration -

{ }U δ ∆ Admissible virtual nodal increase -

V Volume of the body m

3

Plastic work

Greek symbols

α Thermal expansion coefficient µm/m °Ci χ

Parameters that control the yield surface size -

δ Kronecker symbolij -

Emissivity

Cauchy strain tensor µε

Power of elastic straining -

e

ijd ε Elastic strain increment µε

e

kk ε Spherical component of elastic strain tensor µε

p

ijd ε

Plastic strain increment µε

tr

ijd ε Phase transformation strain increment µε

ijd

θ ε Thermal strain increment µε

pd ε Equivalent strain increment µε

ijd δ ε Variation in the strain increment µε

κ Parameter related with the strain hardening effects -

d λ Plastic multiplier -

v Poisson´s ratio -

ρ Density Kg/m

3

Stefan-Boltzmann constant

σ Cauchy stress tensorij N/m

σ

2

Hydrostatic stress tensorkk N/m

2

Spherical invariant N/m

2

Radial residual stress N/m2

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xx


Von Mises stress N/m

or

2

Transverse residual stresses N/m

σ

2

Yield stressy N/m

2

Longitudinal residual stress N/m

2

Axial residual stress N/m or

2

Circumferential residual stress N/m

2

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CHAPTER

INTRODUCTION

1.1 Background

During the heating and cooling cycle in the welding process, thermal strain occurs in the filler material an

in the base metal regions close to the weld. The strain produced during heating is accompanied by plast

deformation. The non-uniform plastic deformation that occurs in the weld structure is what leads to residu

stresses. These residual stresses react to produce internal forces which must be equilibrated and caus

distortion [1].

The residual stress and distortion in weldments depend on several interrelated factors such as therm

cycle, material properties, structural restraints, welding conditions and geometry [2]. Of these parameters, th

thermal cycle has the greatest influence on the thermal loads in the welded structures. At the same time, th

temperature distribution is a function of parameters such as welding sequence, welding speed, energy of th

source, and environmental conditions.

A high level of tensile residual stresses near the seam can induce brittle fracture, cracking due to corrosio

stress, and reduced fatigue strength. Compressive residual stresses in the base metal located some distan

away from the weld line can substantially decrease the critical buckling stress [3]. The main effects o

distortion are the loss of tolerance in the welded components and deformation of structural elements th

results in inadequate support to transfer applied loads [4]. Therefore, residual stresses and distortion shou

be reduced to meet all geometry and strength requirements.

Some of the most popular methods for reducing residual stresses and distortion in weld fabrication ar

welding sequence, definition of weld parameters, definition of weld procedure, use of precambering fixture

prebending, thermal tensioning, heat sink welding, post-weld treatment, control of weld consumables, an

post-weld corrective methods [1].

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1.2 General objective

• Develop a welding sequence-based methodology to reduce residual stresses, distortion, or a relatio

between both parameters in symmetrical structures.

1.3 Specific Objectives

• Obtain temperature-dependent material properties of ASTM A36 steel used in this investigation.

• Conduct a literature survey on welding sequences.

• Investigate the theory of plasticity applied to the welding process and its finite element formulation.

• Perform a finite element simulation of the welding process through a thermo-mechanical analys

based on the von Mises criterion and flow rule, assuming a lineal isotropic hardening and temperatu

dependent materials while neglecting micro-structural evolution.

• Validate the proposed numerical model of the welding process with experimental data to determin

model accuracy.

• Apply the proposed numerical model of the welding process to determine whether the weldin

sequence in an L-type structure affects the residual stresses and distortion.

• Apply the proposed numerical model of the welding process in a welding sequence analysis in 2 and


• Analyze the effects of the welding sequence on residual stresses and distortion in 2 and 3 dimension

symmetrical structures.

• Analyze the relationship between residual stress and distortion due to the welding sequence in


• Determine the proper welding sequence to reduce residual stresses, distortion, or a relation betwee

both parameters in 2 and 3 dimensional symmetrical structures.

• Verify if the proper welding sequence for 2-dimensional symmetrical structures is applicable to

dimensional symmetrical structures, considering appropriate modifications.

• Develop a methodology for experimental tests.

• Perform experimental tests of the proper welding sequence to reduce distortion in a 2-dimension

symmetrical structure.

• Compare the numerical and experimental results on the proper welding sequence to reduce residu

stresses or distortion in a 3-dimensional symmetrical structure.

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CHAPTER

WELDING SEQUENCE BACKGROUND AND

METHODS FOR CONTROLLING RESIDUAL STRESSES AND

DISTORTION INDUCED BY WELDING

2.1 Introduction

This chapter presents the methods and advantages of reducing or controlling residual stresses an

distortion induced by the welding process as well as a definition and classification of the welding sequence.

also includes a study of the welding sequence analysis, as well as a summary of previous welding sequenc

research, and a discussion of its advantages, disadvantages, scope, and limitations.

2.2 Advantages of residual stress and distortion control

Controlling the residual stress and distortion in weldments provides two main advantages: (1) reducefabrication costs by minimizing or controlling distortion, and (2) increased service life of the welded structu

by controlling the induced residual stress.

The benefits of distortion control are [1]:

1. Eliminate the need of expensive distortion correction and loss of accuracy.

2. Reduce machining requirements

3. Improve quality

And residual stress control benefits are no less important [2]:

1. Maximize fatigue performance.

2. Minimize costly service problems.

3. Improve resistance to environmental damage.

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2.3 Methods to control welding-induced residual stress and distortion

Some of the most popular methods used in the industry to control welding-induced residual stress an

distortion include: welding sequence, definition of weld parameters, weld procedure, fixture desig

precambering, prebending, thermal tensioning, heat sink welding, post-weld heat treatment, control of weconsumables and post-weld corrective methods [2].

2.3.1 Welding sequence

The proper welding sequence can minimize distortion and affect the distribution of the residual stress [4

Figure 2.1 shows two welded frames. In the first frame (a) a proper welding sequence was not performed an

a large distortion was produced. The second frame (a) shows a proper welding sequence which leads to le

distortion.

Figure 2.1 Welded frame distortion [4]: (a) without considering a proper welding sequence,

(b) considering a proper welding sequence

2.3.2 Definition of weld parameter

This method is based on control of weld parameters such as heat input, weld groove geometry, single-pa

versus multiple pass welds, and type of joint [5]. The input heat is the most influential parameter in wel

induced distortion. Reducing welding heat input decreases all kinds of weld-induced distortions [2]. The he

input can be controlled through the welding speed and weld size. Faster welding not only reduces the amou

of adjacent material affected by the heat of the arc, but also progressively decreases the residual stress. Th

important difference lies in the fact that faster welding produces a slightly narrower isotherm. The width o

the isotherm influences the transverse shrinkage of butt welds, explaining why faster welding generally resu

in less residual stress [6]. When the specimen thickness decreases, the weld size also decreases, and

reduction in the volume of weld metal usually results in less residual stresses and distortion. However, whe

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the specimen thickness decreases, the tensile residual stress in the areas near the fusion zone and distortio

increase [6]. This is because thin weldments absorb more energy per unit volume. The use of small groov

angles and root openings decrease the volume of weld metal, resulting in lower transverse shrinkage. F

example, the use of a U-groove instead of a V-groove should reduce the amount of weld metal [3]. Welding

frequently performed in one pass, especially for thin plates. However, when welding is performed in multippasses, particularly when welding thick plates, shrinkage accumulates [3].

2.3.3 Weld procedure

Welding procedures have considerable effect on distortion. Fusion welding often leads to the large

distortion, while laser (LBW), electron beam (EBW), and stir welding (FRW) result in lower distortion. Howeve

friction stir welding can impart large plastic strains to the structure. These large strains, which locally strai

harden the material, can influence the fracture response of the structure [8]. In fusion welding, residual stres

distributions are similar; this is true when the design and relative size of the weldments are also similar. Thmost important fusion welding processes are Shield Metal Arc Welding (SMAW), Gas Metal Arc Weldin

(GMAW), Submerged Arc Welding (SAW), and Gas Tungsten Arc Welding (GTAW). However, the automatic o

semiautomatic welding processes present more advantages in the residual stresses and distortion control du

to their repeatability.

2.3.4 Fixture design

This method is based on the design of clamps, jigs and rigid supports that restrain displacements an

rotations of some portions of the welded components or the complete structure. However, the use of thedevices increases residual stresses [7,9-10]. Figure 2.2 shows a rigid support formed by a back plate and tw

clamps. The clamps restrain the angular distortion of the welded joint.

Figure 2.2 Rigid supports [4]

2.3.5 Precambering

This method consists on elastically bending some of the components (usually in a specially designed fixtur

in a predefined manner before welding. After welding, the precamber is released and the fabricated structu

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“springs back” to minimally distorted shape [2]. Figure 2.3 shows a precamber with a curved surface. Th

structure is fixed to the device by clamps.

Figure 2.3 Precamber with a curved surface [2]

2.3.6 Prebending

This method consists of plastically bending some of the components before welding, and possibly befo

placing them in a fixture. After welding, the desired “non-distorted” shape result. The welding is performe

with or without a fixture [2]. Figure 2.4 shows a prebending in a fillet weld.

Figure 2.4 Pre-bending [2]

2.3.7 Thermal tensioning

This method consist on strategically moving a heat source ahead of, beside, behind, (or combinations

these) the moving weld torch. This method can control distortions and residual stresses during welding b

controlling the heating and cooling rates [11,12]. Figure 2.5 shows thermal tensioning welding.

Figure 2.5 Welding with the thermal tensioning process [11]

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2.3.8 Heat sink welding

This method is similar to thermal tensioning, except that a cooling source is strategically moved (or ke

stationary) during welding (Figure 2.6).

Figure 2.6 Heat sink welding [1]

2.3.9 Preheating

Preheating the components being welded reduces residual stresses and distortion by reducing therm

gradients around the weld bead. Preheating has beneficial effects when welding steels by reducing cracks

the heat affected zones and weld metal [3].

2.3.10 Post-weld heat treatment

Heating all or parts of the welded fabrication to high temperatures (depending on the material) for a perio

on time may relieve welding stresses. Often the stresses cannot be fully relieved, i.e., some level of residustress remains. This method is expensive and is often used to prevent service fracture problems such a

corrosion, fatigue, creep, or combinations of them.

2.3.11 Post-weld corrective methods

Corrective methods may reduce distortion or residual stresses in a welded component. Corrections mad

“after weld” are often expensive and time consuming. The most important post-weld corrective methods a

press straightening, shot peening, laser shock peening, vibratory stresses relief, and hammer peening [3].

Remark: The control methods previously described can increase the production costs due to energ

consumption, time, and/or expensive equipment. Other methods slow down production by requiring fixtu

devices.

Welding sequence is inexpensive because it directly affects the temperature field of the welde

structure, and consequently the residual stresses and distortion. Therefore, sequence analysis

fundamental for controlling residual stresses and distortion in welded structures.

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2.4 Welding sequence definition

The American Welding Society (AWS) defines welding sequence as the order of making welds in

weldment [13].

2.5 Welding sequence classification

Welding sequences are classified by the number of passes: single pass and multiple pass weld sequence

However, single pass sequences can be applied to multiple pass welds between beads [3].

2.5.1 Welding sequence for single pass welds

For thin components (up to ¼ inch) welding is performed in a single pass [3]. The weld bead is divided

short sections and welded considering the order and direction of the welds [3,14]. The more common weldinsequences for single pass welds are: progressive, backstep, symmetric, and jump (Figure 2.7).

Figure 2.7 Sequences for thin-wall butt-welds [3]: (a) Progressive, (b) backstep, (c) symmetric, and (d) jump

Figure 2.7 (a) corresponds to progressive welding, where the weld beads are set down continually from on

end of the joint to the other. In the backstep sequence (Figure 2.7 b), the weld beads are deposited in th

opposite direction to the welding progress. Figure 2.7 (c) is the symmetric welding sequence, where the we

beads are deposited from the axis of symmetry of the joint. In the jump welding sequence (Figure 2.7 d) th

weld beads are deposited in intermittent form.

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2.5.2 Welding sequence for multiple pass welds

For thick components (over 1/4 inch), welding sequences are classified as [3]:

• Built-Up: The first layer is completed along the entire weld length through the previously describesingle pass sequences (progressive, backstep, symmetric, jump sequences, etc.), followed by th

second, third, etc. (Figure 2.8). This sequence applies to large-diameter butt-welded pipe join

frequently used in boiling water reactors, oil pipe transport systems, and steam piping systems.

Figure 2.8 Built-Up welding sequence on thick-wall butt-weld [3]

• Block welding: A given block of the joint is welded completely and then the next block is welded, an

so on. This kind of welding sequence is applied mainly to very long joints (e.g., ship hulls). Figure 2

shows the block welding sequence on thick-wall butt-weld, where first the end blocks of the joint a

welded in, and later the central block is added to the joint.

Figure 2.9 Block welding sequence [3]

• Cascade welding: It is similar to the block welding sequence; the main difference is that the ends of th

blocks overlap. An application of this sequence is welding of long thick plates (Figure 2.10).

Figure 2.10 Cascade welding sequence [3]

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2.6 Welding sequence selection based on empirical rules

For complex geometries, several empirical rules useful to decide the welding sequence have bee

introduced [15]:

Rule 1. The weld bead closest to the previous can be selected next.

Rule 2. The weld bead farthest from the current can be next.

Rule 3. Weld beads with greater restraint should be chosen next.

Rule 4. Weld beads symmetric to the neutral axis are selected next.

Rule 5. Weld beads originate from the center points of a structure progressing outwards.

Rule 6. Weld beads that are not adjacent to the current can be next.

Optimizing welding productivity demands minimization of the torch moving distance between weld bead

as in rule 1. However, rule 1 is not appropriate for welding quality because successively welding close bead

can generate a very high heat flux that results in serious thermal distortion. Rules 2, 3 and 4 can improv

welding quality at the expense of welding time. To tackle both issues simultaneously, rules 5 and 6 a

introduced.

Remark: The authors in [15] do not clearly define "weld quality,” nor do they mention what specific we

parameters improve or worsen with the previously mentioned algorithms.

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2.7 Welding sequence background

Teng and Peng [16] investigated the reduction in residual stresses caused by welding by analyzing th

effects of welding sequence on residual stress distribution in single and multi-pass butt-welded plates ancircular patch welds. The research was conducted through finite element-based thermo elastic plastic analys

and simulated weld thermal cycles. The test specimen dimensions and the different welding sequences use

in the thin-wall butt-weld analysis are shown in figure 2.11. The authors worked with three different weldin

sequences: (1) progressive, (2) backstep, and (3) symmetric.

Figure 2.11 Welding sequences for thin-wall butt-welds [16]:

(a) Progressive, (b) backstep, and (c) symmetric

Figure 2.12 (a) and (b) show the distribution of the longitudinal residual stresses along the X-direction (a

Y=150 mm) and Y-direction obtained with progressive, backstep, and symmetric sequences. These figure

reveal that the symmetric sequence produced the lowest residual stresses.

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Figure 2.12. Longitudinal residual stress distribution [16]:

(a) Along the X-direction and (b) along the Y-direction

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Reference [16] also considered butt-welded thick plate joints (figure 2.13). Three different cases a

considered. Case (A): welding half of the upper groove, the whole lower groove and then the remaining uppe

groove. Case (B): welding half of the upper groove, half of the lower groove, the remaining of the uppe

groove and then the remaining lower groove. Case (C): welding the whole lower groove before the whoupper groove.

Figure 2.13 Different welding sequence for thick-wall butt-welds [16]

Figure 2.14 (a) and (b) depict the distribution of the longitudinal and transverse residual stresses obtaine

with various types of welding sequences. Longitudinal residual stresses between various welding sequence

did not appear to differ significantly. However, the transverse residual stresses of case (A) were smaller thathose of the other welding sequences. This difference might be attributed to two reasons: (1) the symmetr

welding sequence can reduce the residual shrinkage or (2) the symmetric welding sequence has pre-heatin

and post-heating effects.

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Figure 2.14 Residual stresses distribution along the X-direction in various welding sequences

for thick-wall butt-welds [16]: (a) Longitudinal and (b) transverse

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Finally, the effect of sequences on residual stresses for circular plates is reported [16]. Figure 2.15 show

the various welding sequences for circular patch welds.

Figure 2.15 Geometry and various welding sequence for circular patch [16]:

(a) Geometry of circular patch welding, (b) Progressive sequence,

(c) backstep sequence, and (d) jump sequence

Figure 2.16 (a) depicts the distribution of circumferential residual stresses and reveals that the variou

welding sequences do not appear to differ significantly. Figure 2.16 (b) depicts the distribution of radi

residual stress and reveals that the backstep sequence has smaller radial residual stresses than the oth

welding sequences. This is because the post-weld treatment and the pre-heating effect of backstep sequenc

are better than in the other welding sequences.

Remark: Reference [16] is applicable only to simple structures, and the numerical simulations do no

consider the welding direction. No experiments were conducted for validating the numerical results for th

different welding sequences.

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Figure 2.16 Residual stress distribution for various welding sequences [16]:

(a) Circumferential and (b) radial

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Ji and Fang [17] investigated the influence of welding sequence on the residual stresses of a thick plat

Authors worked with double V-groove multiple-pass butt-welds and adopted the converse welding metho

between adjacent layers, or between adjacent weld beads in every layer. They analyzed a coupled therm

mechanical model using finite element and an ellipsoidal heat source. The numerical results were validate

against experimental results (the x-ray method). Figure 2.17 depicts the dimensions of the analyzed specimeand the double V-groove configuration. In the numerical simulation the weld was divided into nine laye

(figure 2.18).

Figure 2.17 Dimensions of the specimen, mm. [17] Figure 2.18 Schematic of Weld bead´s

delamination [17]

Table 2.1 displays several welding sequences analyzed to study the effect on residual stresses. Th

converse welding method, consisting of applying the opposite direction between adjacent layers in multi-lay

welds, or between beads in every layer [17], was adopted between adjacent layers.

Welding sequence

Case (A) 2 3 1 4 8 5 9 6 7

Case (B) 2 3 4 1 5 8 6 9 7

Case (C) 2 3 1 4 5 8 6 7 9

Case (D) 1 2 8 3 9 4 5 6 7

Case (E) 1 2 3 8 4 5 9 6 7

Case (F) 1 2 3 8 9 4 5 6 7

Case (G) 1 2 3 4 5 8 6 9 7

Case (H) 2 3 4 5 1 6 8 7 9

Table 2.1 Different welding sequences used by Ji and Fang [17]

Table 2.2 shows the resulting peak value of the residual stresses. It can be seen from the table that th

peak values of transverse residual stress or longitudinal residual stress obtained from case (C) are lowest. Th

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is because the filler metal is being more uniformly applied, the angular deformation is minimized, and th

residual stress is low.

Parameter Case

(A) (B) (C) (D) (E) (F) (G) (H)

Equivalent residual stress (MPa) 701 712 571 885 653 658 921 912

Transverse residual stress (MPa) 623 544 405 718 505 511 829 857

Longitudinal residual stress (MPa) 634 636 507 823 592 607 879 865

Table 2.2 Residual stress´s peak value for several cases [17]

To validate if the residual stress obtained by the converse welding method between adjacent layers is th

minimum, the authors studied the welding stress of the double V-groove plate under classic and conver

welding. The simulation results show that the peak value of the transverse residual stress by the method oconverse welding is 18.2 % less than the stress obtained by the method of classic welding (Figure 2.19

Longitudinal residual stresses behave similar to the results shown in figure 2.19, but the peak value decrease

by 16.9%. When converse welding is adopted, the residual stresses have an opposite distribution to th

previous weld bead, reducing the residual stress value. Therefore, the beads produce a relatively unifor

residual stress distribution and a lower residual stress value.

Figure 2.19 Comparison of transverse residual stress between welding in the

same direction and welding in the inverse direction [17]

Remark: An important disadvantage of [17] is the computational cost to simulate the welding proce

because the model considered the effects of phase transformation and the type of heat source.

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Nami, Kadivar and Jafarpur [18] studied the welding sequence in multiple blocks for the effect on th

thermal and mechanical response of thick plate weldments by the use of a 3-D thermo-viscoplastic mode

Anand´s viscoplastic model was used to simulate the rate dependent plastic deformation of welded materia

Also, they considered the temperature dependence of thermal and mechanical properties of material, weldinspeed, welding lag, and the effect of the filling material added to the weld. The model was compared with th

results of two analytical and experimental works.

Figure 2.20 depicts the configuration and dimensions of the welded blocks. The length of the welded str

was divided into seven parts and welded by different sequences. The arc was allowed to move in a forwar

(+X3) or in a backward direction (-X3). Figure 2.21 depicts the structural boundary conditions of the welde

plates.

Figure 2.20 Configuration of welded blocks in Figure 2.21 Structural boundary conditions of welded

a multi-block welding sequence [18] plates (clamp fixture at both sides) [18]

The selected welding sequences in table 2.3 are commonly used in practice. In the first sequence th

joining was done inwardly (toward the center of the plates) and in second sequence the joining happene

toward the edge of the plates (outwardly).

Table 2.3 Welding sequences and orders applied into

the multi-block model [18]

Welding sequence Configuration

1 +1, +7, +2, +6, +3, +5, -4

2 +2, +4, +6, +1, +3, +5,+7

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2


Figure 2.22 shows the final distortion profile in weldments, indicating the magnitude and location of th

maximum plate distortion. As can be seen, the maximum distortion in sequence 1 is greater than in sequenc

2.

Figure 2.22 Resulted distortion profile for two different block sequences [18]:


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2


Figure 2.23 shows two very different residual stress contours. The magnitude of the maximum von Mis

stress that has been generated by sequence No.2 is greater than produced by sequence No.1. A large stre

variation occurs in the region close to the welding pattern. In the region between the welding pattern and th

edges, a small variation in the stress value is observed. In the region close to the edges, the bounda

conditions introduce large residual stresses with sharp variations.

Figure 2.23 Distribution of the Von Mises stress using different block sequences. [18]:


Remark: Reference [18] does not research the effects of the welding sequence on the relationsh

between distortion and residual stresses. The proposed methodology is computationally expensive becaus

it considers visco-plastic effects.

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2


Mochizuki and Hayashi [19] investigated the residual stress in large-diameter, multi-pass, butt-welded pip

joints for various welding sequences. The pipe joints had an x-shaped groove. The mechanism that produc

residual stress in the welded pipe joints was studied in detail using a simple prediction model. The autho

worked with a thermo-elastic-plastic analysis using finite element method with an axisymmetric model. Als

they determined an optimum welding sequence for preventing stress-corrosion cracking from the residustress distribution.

The configuration of a large-diameter, multi-pass, butt-welded pipe joint and its cross section is shown

figure 2.24.

Figure 2.24 Configuration of a large-diameter multi-pass Figure 2.25 Welding sequences for a multi-pass

pass butt-welded pipe joints and its cross section [19] Welded pipe joint [19]

The authors [19] proposed six welding sequences (figure 2.25) to study the dependence of the residu

stress on the welding sequence. In case 1 the inner side of the groove is welded before the outer surface o

the groove. In case 2, the outer side of the groove is welded before the inner surface of the groove. In case

half of the inner side of the groove is welded, then the whole outer side, and later the remaining inner sid

groove. In case 4, half of the outer side of the groove is welded, then the whole inner side of the groove, an

later the remaining outer groove. In case 5, half of the inner side of the groove is welded, then half of th

outer groove, later the remaining inner groove, and lastly the remaining outer groove. In case 6, half of th

outside groove is welded, then half of the inside groove, later the remaining outside groove and at the end th

remaining inside groove.

Figure 2.26 (a) and (b) show a comparison between the circumferential residual stresses on the inner an

outer surfaces of the groove; Figure 2.27 (a) and (b) show a comparison of the axial residual stresses on th

inner and outer surfaces of the groove; and Figure 2.28 (a) and (b) show a comparison between th

circumferential and axial residual stresses through the plate thickness along the heat-affected zone. All thes

figures consider multi-pass, butt-welded, pipe joints.

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Figure 2.26 Comparison of circumferential residual stress in multi-pass welded

pipe joints [19]: (a) Inner surface and (b) outer surface

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Figure 2.27 Comparison of axial residual stress in multi-pass welded

pipe joints [19]: (a) Inner surface and (b) outer surface

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Figure 2.28 Comparison of residual stress across through-thickness along the heat-affected zone

in multi-pass welded pipe joints [19]: (a) Circumferential and (b) axial

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In figures 2.26 (a), 2.26 (b) and 2.28 (a), the circumferential residual stresses behaved similarly: tensi

circumferential stresses are distributed near the welding deposit on the inner and outer surfaces. Th

maximum stress occurs near the welded metal. Tensile stress then decreases and finally becomes compressiv

about 40 mm from the center of welded metal.

In figures 2.27 (a), 2.27 (b) and 2.28 (b), the distribution of the axial residual stress near the welding depo

differs depending on the welding sequence. Stresses in the heat-affected zone vary with the weldin

sequence, both on the surface and through the thickness, but the axial residual stress distribution away fro

the welded metal is not affected by the welding sequence.

Through-thickness axial residual stresses along the heat-affected zone have a big influence in th

generation and propagation of stress-corrosion cracking in multi-pass, welded pipe joints. The inner surface

exposed to a more severe environment than the outer surface because the pipe may contain corrosivsubstances. There are two steps in selecting an optimum welding sequence for preventing stress-corrosio

cracking: (i) lowering the axial residual stress on the inner surface along the heat-affected zone, because crac

generation should be prevented first; and (ii) lowering the through-thickness axial stress near the inner surfa

to reduce or eliminate crack propagation rate, even if a crack begins to propagate.

According to figure 2.28 (b), cases 2, 3, and 6 are good candidates since they produced lower stresses o

the inner surface of the heat affected zone. Among these, case 6 was the best because the axial throug

thickness stress near the inner surface is almost zero up to a depth of 6 mm. This welding sequence shou

have the lowest probability of generating and propagating stress-corrosion cracking.

Remark: In the work performed by Mochizuki and Hayashi [19], the analytical method proposed t

determine the residual stresses through-thickness is only applicable to multi-pass, welded pipe joint

Therefore, the method is not valid for pipe joints of small diameter (single pass joints). The metho

presented has a good qualitative correlation with experimental and numerical data. However, quantitativ

correlation was not good.

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Mochizuki, Hattori and Nakakado [20] studied the effect of residual stress on fatigue strength at a weld to

in a multi-pass fillet weld joint. The residual stress in the specimen was varied by controlling the weldin

sequence. They calculated the residual stresses by thermo-elastic-plastic analysis and compared them to stra

gage and X-ray diffraction measurements.

A weld joint was fabricated to evaluate the residual stress and fatigue strength. Two attachments we

fillet-welded on both sides of a main plate, as shown in figure 2.29.

Figure 2.29 Configuration of a multi-pass fillet Weld joint, mm. [20]

Two joints were fabricated by changing the welding sequence, as shown in figure 2.30. In case 1, the fin

welding pass was set down in the attachment side, and in case 2 the final welding pass was set down in th

main plate side.

Figure 2.30 Different welding sequences in multi-pass fillet weld joint [20]

Figure 2.31 depicts the experimental and numerical results for transverse residual stresses for the tw

welding sequences. The measured and analytical distributions of residual stress agree well. Therefore, th

results from the thermo-elastic-plastic analysis were used to define the residual stress needed to evalua

fatigue strength. The transverse residual stress in the weld toe of the main plate was 170 MPa for the we

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joint whose final welding pass was deposited on the attachment side (case 1), and 80 MPa for the joint wi

the final pass on the main plate (case 2).

Figure 2.31 Comparison of residual stress in a multi-pass fillet

weld joint [20]: (a) case 1 and (b) case 2

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Figure 2.32 compares the fatigue strength curves for the two multi-pass fillet weld joints. The vertical ax

shows the nominal stress range along the loading direction,∆σy, and the horizontal axis shows the number o

cycles to failure, Nf. It was confirmed from observation during the fatigue test that the initial surface crac

nucleated at the center of the weld toe and propagated as a semi-elliptical crack. The fatigue streng

resulting from the two welding sequences was nearly the same in the low cycle range. A clear differenappears around 10

5

Figure 2.32 Relation between nominal stress range and fatigue

life in multi-pass fillet weld joints [20]

Remark: In the work presented by Mochizuki, Hattori and Nakakado [20], the methodology is valid fo

simple fillet joints only. Two similar welding sequences were used, differing only in the order of applicatio

of two weld beads.

cycles, indicating that high cycle fatigue strength can be improved by varying the weldin

sequence. Therefore, the welding sequence corresponding to case 2 is better for multi-pass, fillet weld joints.

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Tsai and Park [21] studied the distortion mechanisms and the effect of the welding sequence on pan

distortion. In this study, distortion behaviors, including local plate bending and buckling, as well as glob

girder bending, were investigated using finite element analysis. It was found that buckling does not occur

structures with a skin-plate thickness of more than 1.6 mm, unless the stiffening girder bends excessively. Thapplied the joint rigidity method (JRM) to determine the optimum welding sequence for minimum pan

warping. The JRM consists of starting with more rigid joints and progressively moving toward less rigid join

[21].

Figure 2.33 shows the geometrical configuration of the panel structure. This panel is formed by one sk

plate, three longitudinal, and three transverse T-stiffeners. The welding sequence simulation includes: i) layin

tack welds along the joints and, ii) laying structural welds at various joints with different sequences.

Figure 2.33 Aluminum panel for study on welding sequence effect on angular distortion [21]

Four welding sequences were investigated in this study (figure 2.34). Sequence No. 1 deposits the we

from the inner panels moving outward. Sequence No. 2 lays the weld from the outer panels moving inwar

Sequences No. 3 and 4 are respectively similar to sequences 1 and 2. Sequence No. 3 searches for the joi

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with the highest constraint to deposit the next weld as the welding process progresses. Sequence No. 4 lay

the next weld at the least constrained joint.

Figure 2.34 Welding sequences for angular distortion analysis of aluminum panel structure [21]

Figure 2.35 shows the vertical displacement along the cross section of the four panels for the four weldin

sequences being investigated. The origin of the coordinates is at the lower left corner (point A in figure 2.34

The global distortion of the panel in all cases shows a downward movement and tilting toward th

unsupported corner due to the structural weight. The high peak values in the displacement curves indica

the location of the stiffeners.

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Figure 2.35 Distortion displacements at four cross sections of the panel from four welding sequences [21]:

(a) At x= 16 inch; (b) at x=32 inch; (c) at y= 9.3 inch; y (d) at y=30 inch.

Sequences No. 2 and No. 4 result in greater angular bending curvatures than the other sequences. Th

angular distortions of the skin plate from sequences No. 1 and No. 3 are similar in magnitude and shape.

appears that the welding sequence that follows the most restrained joint for depositing the next weld durin

the welding process results in smaller angular distortion of the skin plate. Therefore, welding sequences No.

and No. 3, which deposit the weld from the inner panels to the outward direction, are better for th

production of structural panels.

Joint rigidity can be defined as the resistance to angular bending of a T-joint under a unit moment applie

to the joint. The welding sequence that starts with more rigid joints and moves progressively towards less rig

joints would result in less bending of the skin plate. Using the concept of JRM, the optimum welding sequen

(figure 2.36) begins welding both sides of the middle stiffener in any order, then welding the inside joint of th

edge stiffeners in any order, and finally, welding the outer joints of the edge stiffeners in any order.

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Figure 2.36 Optimum welding sequence determined by JRM [21]

Figure 2.37 depicts a comparison of the distortion values between sequence No. 1 and the optimu

sequence. The optimum welding sequence produces a significant reduction in angular distortion in the sk

plate.

Figure 2.37 Comparison of distortion resulting from welding sequence No. 1 and the optimum welding sequence [21]:

(a) at x= 16 inch, (b) at x=32 inch, (c) at y= 9.3 inch, and (d) at y=30 inch.

Remark: The work performed by Tsai and Park [21] did not consider the welding in the perpendicul

direction and between the T-stiffeners. Therefore, the proposed method to optimize the welding sequenc

is limited to rigid, co-lineal joints.

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Hackmair and Werner [22] investigated the welding sequence and its effect on distortion in a T-joi

structure. The T-joint structure is formed by two hollow extrusions of a 6060 T6 aluminum alloy. Th

extrusions are joined by four weld operations, whose order of application defines the two different weldin

sequences. Figure 2.38 shows the finite element mesh of the T-joint and the dimensions of the holloextrusions. The T-joint was clamped on both ends of the horizontal tube. The evolution of the deformations

the x-direction was measured on the upper end of the vertical tube with an inductive measuring device. Th

different welding sequences are shown in figure 2.39.

Figure 2.38 T-joint configuration [22]: (a) Finite Figure 2.39 Different welding sequences [22]:

element model and (b) dimensions of the (a) Case 1 and (b) case 2

cross section of the hollow extrusions

Figure 2.40 (a) shows the good qualitative agreement obtained when comparing measured (M) an

numerical (S) distortion values for the welding sequence of case 1. Quantitatively, however, the numeric

results show less pronounced peaks. The difference may be due to the FE-mesh of the T-joint not considerin

two separate extrusions. The T-joint in the simulation was considered as one continuous part, whereas the

are two extrusions being joined in the welding experiment, separated by an unavoidable gap. Figure 2.40 (

shows the comparison of measured (M) and calculated (S) distortion values for the welding sequence of ca

2. Similar to case 1, there was a difference in the magnitude of the distortions.

Case 2 resulted in higher distortion. The average experimental distortion increased from 0,4 mm for case

to 2.8 mm for case 2 – 7 times more. In the simulation, however, distortion increased from 0.2 mm for case

to 0,4 mm for case 2, a factor of 2. Therefore, further research is necessary to improve the quantitative mod

predictions through detailed modeling of the gap between the two extrusions.

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Figure 2.40 Comparison of measured (M) and calculated (S) distortion evolution

for two welding sequences [22]: (a) Case 1 and (b) case 2

Remark: the modeling performed by Hackmair and Werner [22] does not consider the gap between tw

separate extrusions, therefore producing a quantitative difference with experimental results. The autho

performed an analysis of the optimum welding sequence and applied it to a component of an automotiv

front axle carrier. However, the optimum sequence was not shown. The proposed methodology is on

applied to simple joints. Therefore, a local/global method is required for more complex structures, whi

implies a high computational cost.

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Bart, Deepak and Kyoung [15] investigated the effect of the welding sequence on a sub-assemb

composed of thin-walled aluminum alloy extruded beams. The main factor considered was the quality of th

assembly after welding, which was measured by the deformation at pre-defined critical locations. Th

aluminum alloy extruded beam structure was modeled with a 2-D beam element model. Their methodologconsisted of applying pre-estimated angular shrinkages for each welding step, thus eliminating the use of

complex nonlinear transient analysis, which would require consideration of thermo-mechanical interaction

and plasticity. Two distortion modes (angular shrinkage and tilting shrinkage) were investigated and applied

model the welding distortion.

Figure 2.41 depicts the geometric configuration of a sub-assembly composed of thin-walled aluminum allo

extruded beams. These beams have a rectangular cross section and were joined by 2 weld seams (top an

bottom) per joint. Figure 2.42 shows a simplified model with torsion springs (stiffness k) to model the pr

calculated angular shrinkage.

Figure 2.41 Geometric configuration of a sub-assembly [15] Figure 2.42 Simplified model with torsion springs [15]

Four representative welding sequences based on empirical algorithms (table 2.4) were selected to simula

the effect of welding sequence on welding deformation,


Case 1 1, 6, 4, 3, 2, 5

Case 2 6, 1, 3, 4, 2, 5

Case 3 1, 6, 2, 5, 3, 4

Case 4 1, 2, 4, 3, 5, 6

Table 2.4 Different welding sequences used

by Bart, Deepak and Kyoung [15]

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Figure 2.43 depicts the final (exaggerated) deformed shapes for the different sequences. Case 3 resulted

minimum final distortion. This is because weld seams on joints with greater restraint were applied first.

Figure 2.43 Final exaggerated deformed shapes for different sequences [15]

Remark: the work performed by Bart, Deepak and Kyoung [15] does not consider the contact betwee

the beams and does not analyze the effect of the welding sequence on the distribution of the residu

stresses. This study is of great importance because it shows that the residual stress has a critical effect

constrained structures.

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Kadivar, Jafarpur and Baradaran [23] utilized a genetic algorithm method with a thermo-mechanical mod

to determine an optimum welding sequence. The thermo-mechanical model developed for this purpo

predicts the residual stress and distortion in thin plates. The thermal history of the plate was computed with

transient, two dimensional finite element model which serves as an input to the mechanical analysis. Th

mechanical response of the plate was estimated through a thermo-elastic, viscoplastic finite element modeThe proposed model was verified by comparison with experimental data where available. The autho

observed that the welding sequence changes the distribution of residual stress, but has little influence on th

maximum residual stress levels. However, the welding sequence does have an effect on the weldme

distortion. Therefore, the authors chose the minimization of distortion as the target function.

Figure 2.44 depicts the geometric configuration and dimensions of a weldment chosen to investigate th

best welding sequence. In the optimization procedure, the circular weld line was divided into eight parts. Th

order of welding for these parts, and the direction of welding for each part, were considered as the proble

variables. It was assumed that the plate was welded by one welder; i.e., eight parts of weld line were weldeone after another, not simultaneously. Two different types of restraints were considered. In one, several tac

welds with equal distances among them were employed to hold the inner circular plate in place. In the oth

type (full restrain), all of the weld line elements were considered active at the beginning of the computatio

In other words, it was assumed that the workpiece is continuous and the region associated with the weld lin

is heated to the melting temperature. To eliminate the rigid body motion, the central node of the plate wa

considered fixed and the vertical freedom of the edge node at θ=0° was suppressed.

Figure 2.44 Geometric configuration and dimensions of weldment [23]

For the problem under consideration, a typical welding sequence was coded in the form of a string with 1

digits as shown in figure 2.45. The first eight digits in the string (1, 4, 3, 2, 5, 7, 6, 8) represent the sequence

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welding. The second eight digits (1, 2, 2, 2, 1, 2, 2, 1) represent the direction of welding, where 1 and

respectively mean clockwise or counterclockwise.

Figure 2.45 Code to designate the welding sequence

and welding direction [23]

As stated earlier, the effects of the welding sequence on the maximum residual stress values are negligib

Therefore, the distortion of the weldment was considered as the objective function. Because the plate w

thin, and its deformation was modeled with an in-plane model, the maximum radial displacement at the edg

of the plate ( )maxr

U represented the maximum radial weldment distortion.

Figure 2.46 shows the variation of ( )r U with respect to θ when using tack welds. The displaceme

produced by the optimum sequence is nearly uniform. In other words, when the optimum sequence is applie

the deformed shape of the plate remains circular with a small contraction; whereas using a continuo

sequence the deformed shape of the plate is irregular and with a distorted shape. The maximum displaceme

at the edge of the plate ( )maxr

U for the optimum sequence was about 70% less than that of the continuou

sequence. Similar results were obtained for the case of welding with full restrain (without tack welds).

Figure 2.46 Radial displacement of the edge of plate with respect to θ

for continuous welding and the optimum sequence[23]

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In table 2.5, the values of for the two cases of restraint are compared with the condition of th

“perfect heat sink”. This table shows that the distortion obtained by the optimum sequence is smaller tha

that of the “perfect heat sink” condition. It should be noted that the generation of a perfect heat sin

condition is almost impossible, and a real heat sink would produce a considerably larger deformation.

Welding

condition

Full restraint With tack welds Welding with

perfect heat sink

(Continuous seq)

1 2 3 4 5 6 7 8

1 1 1 1 1 1 1 1

Continuous

sequence

1 2 3 4 5 6 7 8

1 1 1 1 1 1 1 1

Optimum

sequence

1 4 7 6 2 5 8 3

1 2 1 2 2 2 2 2

Continuous

sequence

1 2 3 4 5 6 7 8

1 1 1 1 1 1 1 1

Optimum

sequence

1 4 7 2 6 5 8 3

1 1 1 1 2 2 2 2

0.409 0.137 0.371 0.110 0.145

Table 2.5 for various welding conditions [23]

Remark: in the work performed by Kadivar, Jafarpur and Baradaran [23], the applied genetic algorith

method is valid for simple joints only. Therefore, the use of other genetic algorithms is required for comple

joints. In addition, experimental tests to check the optimum sequence obtained by genetic algorithm we

not performed.

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Voutchkov, Keane, Bhaskar and Olsen [24] proposed a surrogate model that substantially reduces th

computational expense in sequential combinatorial finite element problems. The model was applied to a we

path planning problem in a tail bearing housing (TBH). The TBH is a crucial component of most gas turbine

and is used to help mount the engine to the body of the aircraft. The welding sequence used to attach th

vanes to the inner ring was chosen to minimize distortion during the welding process.

Figure 2.47 depicts the tail bearing housing. Its major structural components are the outer ring, the inn

ring, and the vanes. The vanes are welded to the rings using the process of Gas Tungsten Arc Welding. Th

welds are broken down into six sub-weld segments, considering the order and direction of the welds. Figu

2.48 shows the finite element model of the welding process and designation of the welding paths showing t

number in the sequence. The arrows indicate the positive direction of each path. The point of interest

measure the distortion was located at the top of the vane (node 10). Only the component in the X-direction

node 10 was used for the optimization process.

Figure 2.47 Tail bearing housing [24] Figure 2.48 Finite element model of welding process and designation

of welding paths showing positive orientation of weld and

reference number in sequence [24]

To study the effects of the welding sequence, the authors applied a design of experiments (DOE) an

proposed a combinatorial model to obtain an optimum sequence. The final optimization result is illustrated figure 2.49, which shows the FE simulation for Run 28 (displacement versus time). The curve reaches ze

displacement just before 300 s, when the clamps were released. Run 28 is shown together with some previo

runs (numbers 1, 5, 6, 16, 24, 26) for comparison purposes. The figure illustrates the improvement of the

displacement in comparison to run 1, which is the standard sequence adopted in most TBH production.

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Figure 2.49 Run 28 is the optimized displacement with a clamped structure [24]

The values for the displacement for all 28 runs are shown in figure 2.50, showing that the optimized ru

produces minimal displacement.

Figure 2.50 The absolute values of the X displacement for all 28 sequences [24]

Remark: Although Voutchkov, Keane, Bhaskar and Olsen [24] applied a surrogate model to reduce th

computational expense in determining the optimum welding sequence, the numerical models th

calculated the response for the design of experiments were too computationally expensive. For example,

single run required 32 hrs and 28 runs were analyzed. If the authors had worked with the sequenti

combinatorial model and with a simplified model of the welding process, the required computation

processing time for the analysis of the welding sequence could have been considerably shorter.

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2.8 Summary of the welding sequence analysis background

• Previous research [15-24] has demonstrated that the welding sequence is an efficient method fo

controlling residual stresses and distortion.• When the welding sequence is combined with the converse welding method, the residual stre

distribution and distortion are considerably reduced.

• To date, there is no study showing the residual stress-distortion relation due to welding sequence.

• The values of residual stresses and distortion obtained by numerical simulation (without considerin

micro-structural evolution) of a welding process applied to the analysis of the welding sequence sho

good agreement with experimental measurements.

• Except for the work of Tsai, Park and Cheng [21], analyses of the welding sequences presente

correspond to simple structures with no more than two components.

• Previous research did not consider the contact effects between the welded components.

• The process of welding sequence optimization depends on the specifics of the restraint and joint typ

and therefore needs to be carried out for each structure.

• The welding sequence analysis background is summarized in the next table. This matrix summarizes th

work and investigations performed for the welding sequence analysis, as well as the main topics th

are to be performed in this investigation.

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CHAPTER I

PROPOSAL OF A NUMERICAL SIMULATION

OF THE WELDING PROCES

AND

A NUMERICAL SIMULATION OF THE WELDING

SEQUENCE IN AN L-TYPE STRUCTUR3.1 Introduction

This chapter presents a finite element simulation of the welding processes with the objective of definin

the initial and boundary conditions and studying the effects of the welding sequence on the residual stre

distribution and distortion in symmetrical structures in 2 and 3 dimensions. Although the analysis focuses o

symmetrical structures, the proposed numerical model is applicable to asymmetrical structures. The propose

sequentially-coupled thermo-mechanical analysis involves two steps: a transient heat transfer analysis

performed followed by a thermal elastic plastic analysis. This numerical simulation is performed in an I-typspecimen subject to tension and validated with experimental data [25] to check the accuracy of the propose

numerical model. The end of this chapter presents a numerical simulation of the welding sequence in an

type structure to test whether the proposed numerical model can simulate the effects of the weldin

sequence on residual stresses and distortion, with respective adaptations.

3.2 Heat transfer in welding

The temperature distribution in a weldment is mainly determined by the total heat input, the prehe

temperature, the welding process, and the type and geometry of joint. The latent heat released during phastransformation only marginally affects the temperature distribution. The temperature field in the molten po

is in general assumed to be governed by the same equation as is applied to the solid metal. In mo

metallurgical and structural studies of welding, the energy transfer from the electrode to the weld metal

represented either by a surface heat source or by momentarily deposited energy that gives the weld metal a

initial temperature distribution.

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In general the temperature field should be taken as thermodynamically coupled to the mechanical fiel

The governing equation of the heat flow follows the first law of thermodynamics (conservation of energy). Th

law states that the rate of change of internal energy and conduction must be in equilibrium wi

the heat production and the power of elastic and viscoplastic straining and , respectively [26]:

(1)

The parameter takes on the value of 1 if all inelastic dissipation is converted into heat. Th

mechanical coupling terms in (1) are in most cases not considered because their influence on the temperatu

field is very small [27]. It is therefore possible to divide the thermo-mechanical analysis of a welding proce

into two main parts: the analysis of the temperature field and subsequent analysis of the mechanical fields.

3.2.1 Analytical solution for the temperature field

Neglecting the mechanical coupling terms in Eq. (1), the energy equation becomes [27]:

(2)

Equations (1) and (2) are statements of the First Law of Thermodynamics [28]. Fourier’s law of heat transf

[28] defines a relationship between the heat flux and the gradient of the temperature field . For a

isotropic material this relationship is the Fourier heat conduction Law:

(3)

Where is the thermal conductivity for the material. Equation (2) and (3) give

(4)

In Cartesian coordinates x, y, z, equation (4) becomes

(5)

Where: is the thermal conductivity in the , and directions, respectively, is th

temperature, is the density, is the specific heat and is time. Equation (5) becomes nonlinear if mater

properties and C are a function of temperature. The first term is conduction of heat through th

material. The second term is the source of heat generation. The last term is the rate of change

internal energy.

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There are only three terms in the heat equation (with zero velocity) that can be “manipulated” in additio

to the associated boundary conditions of either prescribed flux or prescribed temperature type. Therefore an

model of a weld heat source based on the heat equation must specify something about one or more terms

this heat equation or its BCs.

Suppose that a heat source is moving at a constant speed in the positive direction. We can define a

Eulerian (moving) frame with origin at the center of the source (i.e., a welding arc), and coordinates

The transformation from to is given by [29]:

(6)

Where: is time. Noting that the material time derivate in equation (4) becomes:

(7)

We obtain the equation of conservation of energy in the Eulerian frame:

(8)

Here, represents the time derivate of temperature at a point fixed with respect to the heat source.

steady state, this derivate is zero, and so equation (8) becomes:

(9)

When and are constant, equation (9) can be solved more easily by applying the transformation:

(10)

Substituting equation (10) into (9), we have:

(11)

(12)

Equation (12) is symmetric positive definite. After properly transforming the boundary conditions fro

to function, it is easy to solve this equation with standard Lagrangian FEM code th

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contains a solver for positive definite symmetric matrix. Equation (12) applies only to linear systems (i.e.,

independent of ) because of equation (11).

3.2.2 Thermal initial and boundary Conditions

The solution of the heat conduction equation (4), involves a number of arbitrary constants to b

determined by specified initial and boundary conditions. These conditions are necessary to translate the re

physical conditions into mathematical expressions [28].

Initial conditions are required only when dealing with transient heat transfer problems (in which th

temperature field changes with time). The common initial condition in a material can be expresse

mathematically as [28]:

(13)

On the boundary of the domain either the essential (prescribed temperature) or natural (prescribed flu

boundary conditions must be satisfied. Five common types of boundary conditions are [28]:

Essential boundary condition:

a) Prescribed surface temperature, it is often necessary to prescribe a surface temperature for a structur

The mathematically expression takes the form:

(14)

Natural boundary condition

b) Prescribed heat input , many structures, particularly in the case of welding, have the boundary surfac

exposed to a heat source or sink. Let denote the outward normal to the surface at the point , the

the mathematical formulation for the heat input across a solid boundary is:

(15)

(c) Perfectly insulated surface, by definition, a perfectly insulated surface is one across which there is n

heat flux. Equation (15) becomes:

(16)

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(d) Convection boundary condition, most structures have surfaces which are in contact with fluids, eith

gases or liquids. The heat flux across a bounding surface may be taken as proportional to the differenc

between the surface temperature and the known temperature of the surrounding medium

Equation (15) then takes the form:

(17)

Where: is the convection heat transfer coefficient.

(e) Radiation heat exchange, when the rate of the heat flow across a boundary is specified in terms of th

emitted energy from the surface and the incident radiant thermal energy emitted and reflected from oth

solids and /or fluids, the boundary condition is:

(18)

Where: is the Stefan-Boltzmann constant and is the emissivity.

If the partial differential equation (4), the initial conditions (13) and the boundary conditions (14), (15

(16), (17), and (18) are consistent, the problem is well posed and a unique solution exists.

The most convenient domains in which to apply equations (11) and (12) are prisms with constant cros

sections, as found in the plate shown in figure 3.1. The temperature of the boundary between the weld po

and the solid is prescribed to the solidus temperature. The flux due to complex radiation and convection o

the surface of the weld pool is not taken into account.

Figure 3.1 Eulerian frame and thermal initial and boundary conditions

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3.3 Thermal elastic plastic stress analysis in welding

In the mechanical analysis, the temperature history obtained from the thermal analysis is introduced as

thermal loading. Thermal strains and stresses can be calculated at each time increment, and the final state

residual stresses will be accumulated by thermal strains and stresses. Residual stresses in each temperatuincrement are added to those at nodal points to update the behavior of the model before the ne

temperature increment.

3.3.1 Mechanical equations

Three basic sets of equation relating to the mechanical model, the equilibrium and compatibility equation

and the constitutive equations for thermal elastic plastic material, are considered as follows [1]:

, 0ij j i f σ + = (19)

Where: i f is the sum of the body force and

ijσ is the Cauchy stress tensor. To ensure that the bod

remains continuous during the deformation, the compatibility equations must be satisfied [2].

, , , , 0ij kl kl ij ik jl jl ik ε ε ε ε + − − = (20)

The thermal elastic plastic material model will be derived assuming isotropic material, von Mises yie

criterion and the associated flow rule and linear isotropic hardening. Thermal and mechanical properties of th

selected material are a function of temperature. The micro-structural evolution is not considered. The initi

assumption is that the total strain increment can be decomposed as (valid for small strains and rotations) [1]:

e p

ij ij ij ijd d d d θ ε ε ε ε = + + (21)

Stress-strain relations can be written as

22

31 12

3 1 2 313

ij kl kl

ij ij kk ij ij kk

VM

Gs s d E d d Gd K dT dK

H v K G

ε σ δ ε ε δ α σ

σ

= + − − +

− +

11

1 13 3

ijij

VM

f s dT

s T dG

H H G

G Gσ

∂ ∂ + − +

+ +

(22)

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The variation of the material properties dG and dK in equation (22) is due to the temperature only [2].

These equations are treated in more detail in appendix No.1

3.3.2 Mechanical initial and boundary conditions

Initial conditions are necessary only when the analysis is transient [30] and therefore will not be specifie

in the static mechanical analysis described here.

In a mechanical problem, the boundary conditions can be specified in three different ways:

Type I: Specification of the primary variable (degree of freedom).

Type II: Specification of variables related to the derivative of the primary variable.Type III: Specification of a linear combination of the primary variable and its derivate.

The primary variables are the displacement components. When Type I boundary conditions are used, th

displacement constraints are specified along a segment of the boundary. Rotations at the boundary are Type

because rotations are related to the derivatives of the displacement components.

3.4 Finite element solution of the welding

We have selected finite element modeling has over existing alternatives for detailed analysis (finidifference and boundary element) for its capability for nonlinear analysis in complex geometries. Finit

element is also most compatible with modern CAD/CAM software systems. For thermal analysis alone,

strong argument can be made in favor of finite difference methods. However, for thermal elastic plast

analysis finite element analysis holds an advantage. The boundary element method is not well developed f

nonlinear analysis. Briefly, these considerations led to the choice of FEA as the most effective numeric

method for developing a complete analysis capability for computer modeling or simulation of welds. Finit

element is a generalized Rayleigh-Ritz method, which uses interpolation to express the variables in terms of i

values in a finite number of nodes.

3.4.1 Finite element solution of heat transfer in welding

The finite element method FEM usually imposes a piece-wise polynomial approximation of the temperatu

field within each element [29]:

(23)

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Where: are basis functions dependent only on the type element and its size and shape. Physically

is the value of the temperature at node at time .

(24)

Where: is abbreviated to .

The next question is how to evaluate ? Garlekin´s FEM is among the most convenient and general of th

methods available for this purpose. If equation (23) is substituted into equation (4), a residual or error ter

must be added. Otherwise equation (23) would be the exact solution. Indeed when equation (23) is the exa

solution, the error in the FEM solution is zero.

Garlekin´s FEM method requires [29]:

(25)

Mathematically is the residual from equation (4); in equation (25) is a test function and the terms

equation (23) are the trial functions. Since there are nodes, equation (25) creates a set of ordina

differential equations which are integrated to form a set of algebraic equations for each time step:

(26)

This set of equations is solved for the nodal temperatures at the end of the time step. Usually some for

of Newton-Raphson method together with a Gaussian elimination and back substitution would be employed.

3.4.2 Finite element solution of the thermal elastic plastic stress analysis in welding

In welding, no external force is applied to the welded structure. Thermal loads are the only source

residual stress and distortion [1-3]. Therefore, the principle of virtual work in this case, without mechanic

loading, is written as [26]:

0ij ij

V

d d dV δ ε σ =∫ (27)

Where:ijd δ ε is the variation in the strain increment ijd ε . The stress increment

ijd σ is given in equatio

(22).

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In matrix notation, the thermal elastic plastic constitutive equation (eqn. 22) becomes [26]:

{ } { } { } { }epd D d C s M dT σ ε α = − − (28)

Where:ep

D is the elastic plastic stiffness matrix, { }C s and { } M dT α are terms related with th

distortion and volume change due to the temperature.

The virtual work equation (27) is now written as:

{ } { } 0T

V

d d dV δ ε σ =∫ (29)

Where: is the volume of the body to be analyzed and is the transpose of . The straidisplacement for three-dimensional problem can be written in matrix form as [26]:

{ } { }

0 0

0 0

0 0

0

0

0

x

y

z d du

y x

z y

z x

ε

∂ ∂

∂ ∂

∂ ∂

=

∂ ∂ ∂ ∂

∂ ∂ ∂ ∂

∂ ∂ ∂ ∂

(30)

In the finite element solution, the increments in the displacements for each element are approximated a

[30]:

{ } ( ){ }1

, ,n

i

i

du N x y z U =

= ∆∑ (31)

Where: n is the number of nodal points for each element, ( , , )i N x y z are the shape functions and { U∆

are element nodal increments.

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Substituting equation (31) into equation (32) produces the following expresion:

{ } [ ]{ }d B U ε = ∆ (32)

Where: [ ] [ ] ( )1

, ,n

i

i

B N x y z =

= ∂ ∑ is the strain-displacement matrix for each element.

Using equation (31) and equation (32) yields:

{ } { } [ ]T T T

d U Bδ ε δ = ∆ (33)

Substituting equations (27), (28) and (32) into equation (29) yields

{ } [ ] [ ][ ] { } [ ] { } [ ] { } 0T T T T

V V V

U B D B dV U C B s dV M B d dV θ

δ ε ∆ ∆ − − = ∫ ∫ ∫ (34)

The vectors { }U δ ∆ and { }U ∆ are not included in the integrals because they are not a function of th

coordinates. Equation (34) must be valid for any admissible virtual nodal increase { }U δ ∆ of equilibriu

configuration. Therefore, equation (34) becomes:

{ } [ ]

{ } { }{ }

0T

U K U F ∆ ∆ − = (35)

Now, the expressions inside the braces must be zero, therefore:

[ ]{ } { } K U F ∆ = (36)

Where:[ ] K is the global stiffness matrix for the assembly of elements and is formed as a sum of th

element stiffness matrices and is the global load vector, formed as the sum of the element loa

vectors .

The stiffness matrix for each element is:

[ ] [ ] [ ]e

T ep

e

V

K B D B dV = ∫ (37)

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And the element load vector is:

{ } [ ] { } [ ] { }e e

T T

e

V V

F M B dT dV C B s dV α = +∫ ∫ (38)

Equation (36) is solved for each load (time) increment. The stiffness matrix is in most cases updated

every load increment. It is often advantageous to use the elastic stiffness matrix only, computed at th

beginning of each time step in a modified Newton-Raphson approach. The non-linearities are compensated f

by equilibrium iterations and the stress increment during each load (time) increment are often calculate

using the subincrement technique. The matrix element in is typically integrated with Gauss quadratur

The reader is referred to Appendix 1 for detailed treatment of this set of equations.

3.5 Geometric configuration of I-type specimen subject to tension

The finite element welding simulation is performed with a commercial code on an I-type specimen subje

to tension. This geometry is selected due to the availability of experimental data [25]. A static linear model w

used with a shrinkage force (transverse to weld bead) applied in the boundary between the weld metal an

the base metal to simulate the effects of the welding process. In the present work, a thermo-mechanic

analysis that includes plastic behavior and temperature distribution will be developed. The I-type specime

subject to tension consists of a central bar and two lateral bars (restraining members). When the weld met

solidifies and shrinks, tensile residual stresses are induced in the central bar, while in the lateral ba

compression residual stresses are induced. This is due to the balance conditions and geometry [3]. Figure 3depicts the geometric configuration of an I-type specimen subject to tension.

Figure 3.2 Geometric configuration of I-type specimen subject to tension (mm) [25]

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3.6 Material selection for the I-type specimen subject to tension

The material selected is ASTM A36 steel because of its common use in the welding industry. The chemic

composition of ASTM A36 is shown in table 3.1.

Chemical composition of ASTM A36 (%)

C Mn P S Si Fe

0.21-0.29 1.0 0.04 0.05 0.28 98.0 min

Table 3.1 Chemical composition of ASTM A36 carbon steel [33]

3.7 Temperature-dependent thermal and mechanical properties of ASTM A36

Temperatures vary widely within the welded part. Therefore, thermal and mechanical properties of weldematerials vary significantly [34]. The thermal and mechanical properties of ASTM A36 due to temperature a

shown in figure 3.3.

Figure 3.3 Thermal and mechanical properties of ASTM A36 as a function of temperature [34]

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As this previous figure indicates, when temperature increases, the modulus of elasticity, modulus o

tangent, yield stress and thermal conductivity decrease while the thermal expansion and specific he

increase. Autogeneous weldment is assumed. This means that weld metal, heat affected zone (HAZ), and bas

metal share the same mechanical and thermal properties. Figure 3.4 depicts the stress-strain behavior ASTM A36 carbon steel for different temperatures.

Figure 3.4 Stress-strain behavior of ASTM A36 carbon steel

for different temperatures [Based on figure 3.3]

3.8 Finite element model of the I-type specimen subject to tension

We simulate welding with a sequentially coupled thermo-mechanical analysis. The thermo-mechanic

analysis involves two steps. First, a transient heat transfer analysis is performed. The calculated transien

temperatures are applied as a step-by-step thermal load. In the second step, a thermal elastic plastic analys

(quasi-static) computes the cumulative thermal stresses for each time step. The end result is residual streand distortion. All numerical simulations in this investigation were performed in a PC with an Intel® Core™

Duo processor T5300 running at 1.73 GHz, configured with 3072MB of SDRAM memory.

Due to the symmetry of the I-type specimen subject to tension, only a quarter of the model is analyze

The finite element mesh is shown in figure 3.5. The weld region is finely meshed, and the zones away from th

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weld bead have a relatively coarse mesh. This guarantees accuracy while reducing the calculation time. Th

numerical model is divided into 1536 hexahedral elements and 2420 nodes.

Figure 3.5 Finite element mesh of the I-type specimen subject to tension

3.8.1 Definition and justification of the applied finite elements

To perform the thermal analysis, it is necessary to select an element type that is able to simulate:

• A transient thermal analysis.

• The weld thermal cycle [figure 3.6, page 60], which determines the temperature as a function of th

time in the weld bead (i.e., all elements belonging to the weld bead).

• The conduction phenomenon that occurs in the base metal as primary mode of heat transfer.

• The phenomenon of heat loss by convection to the surrounding in the base metal, moreover it

required to calculate the rate of change of internal energy.

• Activation and de-activation of the weld bead elements.

To perform the structural analysis, it is necessary to select an element type that is able to simulate:

• Homogeneous and isotropic material.

• Elastic-plastic material´s behavior following the von Mises yield criterion and the associated flow ru

with linear isotropic hardening by strain.

• Small strains.


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Furthermore, it is necessary to select an element type that with the temperature in each node and th

thermal expansion coefficient, it can couple these data with the structural unitary strain.

ANSYS offers a broad variety of elements for the analysis of two and three-dimensional thermal an

structural problems. In table 1 and 2 some common element used by ANSYS are presented. In general, aelements have the same characteristics (degree of freedom, input data, and output data), only there are tw

main differences: 1) the order of elements: higher order elements achieve better results and greater accurac

however, these elements require more computational time. This time requirement is because numeric

integration of elemental matrices is more involved, also, these elements are well suited to model problem

with curved boundaries. 2) The shape of element: quadrilateral and brick element present better meshin

control than triangular and tetrahedral elements.

For these two reasons, PLANE55 and SOLID70 elements are selected for two and three dimensional therm

analysis, respectively. Both elements have a single degree of freedom, temperature and isotropic materiproperties. These elements alloy simulate these thermal conditions mentioned early without complication

which is necessary to introduce the thermal conductivity and specific heat as a function of temperature [F

3.3, page 56], the convective heat transfer coefficient (natural convection), this coefficient is considere

constant and is equal to 10 W/m2 ºC. Heat loss by convection is a boundary condition and is applied only t

surfaces in contact with the surrounding. It is also required to introduce the temperature of the surroundin

which is a boundary condition (20°C) and the initial condition of base metal, which is considered as th

ambient temperature (20°C).

The elements PLANE42 and SOLID45 are selected for two and three dimensional structural analysirespectively. PLANE 42 and SOLID45 elements have two and three degrees of freedom at each nod

respectively: translation in the nodal directions and isotropic material properties. Both elements couple th

temperature with strain, for this reason it is necessary to introduce the thermal expansion coefficien

elasticity modulus, tangent modulus, yield stress and Poisson´s ratio dependent on temperature as shown

figure 3.3 [page 56]. Finally, to transfer the thermal loads obtained in the transient thermal analysis to th

structural analysis, the concept of body load is used through load step. PLANE 42 and SOLID45 elements hav

this capability because the temperatures may be input as body loads at the nodes. The elements PLANE42 an

SOLID55, and SOLID70 and SOLID45 are equivalent to perform coupled thermo-mechanical analysis. Definitio

and justification of the applied finite elements are treated in more detail in appendix No.2.

3.8.2 Thermal initial and boundary conditions

As mentioned early, these conditions are necessary to express the real physical conditions in

mathematical expressions. For all numerical simulation developed in the present research, the initial an

boundary conditions are equal, unless otherwise noted.

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a) Initial condition:

Because the thermal model consists of a transient heat transfer analysis, it is required an initial condition

the base metal, which is considered as the surrounding temperature ( =20°C).

b) Boundary conditions (see figure 3.5, page 58):

Symmetrical plane:

Plane y-z in x=0; and plane x-z in y=0;

Surfaces in contact with the surrounding except surfaces belonging to weld metal:

Nodes belonging to weld metal:

Prescribed heat input: heat loading is simulated via weld thermal cycle curves shown in figure 3.6. Th

input heat is applied to all surfaces between the weld metal and the base metal.

Figure 3.6 Weld thermal cycle of ASTM A36 carbon steel [34-35]

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3.8.3 Mechanical boundary condition

In the structural analysis, the parameters and are the displacements in the X, Y, and Z-directio

respectively. , , and are the strain in the X, Y, and Z-direction, respectively. , , and are th

rotation with respect to X, Y, and Z axis, respectively.

a) Symmetrical plane (see figure 3.5, page 58):

Plane y-z in x=0;

and

; ← due to Poisson´s ratio and pure tension

Plane x-z in y=0;

and

← due to Poisson´s ratio and pure tension

b) Surfaces in contact with the surrounding (see figure 3.5, page 58):

The normal stresses to the surfaces in contact with the surrounding and the shear stresses are zero (i.e.,

the plane x-z in y=50.8 mm, ).

c) For all surfaces including the surfaces belonging to symmetrical planes, the shearing strain is zero due t

pure tension.

3.8.4 Body load

Body loads can be generated internally or externally as the result of physical fields acting volumetrically o

the body. Gravity, inertial loads, and temperature changes represent body loads in a mechanical problem [26

In the present research, we use the concept of body load to transfer the transient thermal loads to the stat

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structural analysis. The use of load steps is necessary to calculate the response of the structure t

temperatures obtained from transient thermal analysis at specific points in time.

3.8.5. Solution to the finite element model

After completing the finite element mesh and specifying the loading conditions (boundary, initial and bod

loads), the solution can be initiated.

In the transient thermal analysis, the time to complete the weld bead is 6 seconds, and the time to retur

to its initial temperature is 1200 seconds [25]. The thermal elastic plastic analysis requires 15 load steps t

complete the weld thermal cycles (1, 3, 10, 20, 35, 50, 75, 100, 200, 300, 400, 600, 750, and 1200 seconds). A

the computational analysis was done using ANSYS®.

3.9 Points of interest in the finite element model of the I-type specimen subject to tension

Experimental data was taken from an I-type specimen subject to tension [25]. Residual stresses in the

direction were obtained in two points of interest. The same points (Figure 3.7) are selected on the finit

element model to carry out a quantitative comparison

Figure 3.7 Localization of the points of interest on finite element model

3.10 Residual stresses in the I-type specimen subject to tension obtained in the numerical simulation

The results of interest are the residual stresses in the two selected points. Table 3.2 depicts the values o

the residual stresses in the X-direction obtained in the numerical simulation.

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Node Residual stresses in the X direction (MPa)

126 204.53 (Tensile)

2001 12.78 (Compressive)

Table 3.2 Residual stresses obtained in the numerical simulation

of I-type specimen subject to tension

Figure 3.8 depicts the distribution of residual stresses in the X-direction at the end of the thermal cycle o

the weld bead. High tensile residual stresses occur in the region between the weld bead and the metal bas

due to resistance to contraction of the material as the cooling begins. This contraction produces tensi

residual stresses in the central bar. Therefore, for self-equilibrium purposes, compressive residual stresse

occur in the lateral bars.

Figure 3.8 Distribution of residual stresses in the X-direction

in the I-type specimen subject to tension

3.11 Comparison between numerical and experimental results of an I-type specimen subject to tension

Experimental and numerical results are compared for four locations [figure 3.9(a)] in I-type specime

subject to tension. Points 1 and 3 are located in the central zone of the lateral bars, while points 2 and 4 a

located in the central zone of the central bar.

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Figure 3.9 (b) shows welding parameters employed.

Figure 3.9 Experimental tests: a) Localization of the points of interest in the I-type specimen


Table 3.3 depicts the comparison between numerical and experimental data for two I-type specimen

subject to tension. Due to the symmetry of the specimens, points 1 and 3, and 2 and 4 have equal numeric

residual sresses. The table shows that of the 6 comparison points, 2 of them present a difference of 1%,

points present a difference of 5% and the 2 remaining points present a difference of 10%.

Point Numerical

Residual

stress

(MPa)

Specimen 1 Specimen 2

Experimental

residual stress

(MPa)

Difference

(%)

Experimental

residual stress

(MPa)

Difference

(%)

1 -12,78 -11,72 8,29 -11,79 7,74

2 204,53 194,43 4,93 195,66 0,628

3 -12,78 -12,18 4,69 -------- --------

4 204,53 205,38 0,41 -------- --------

Table 3.3 Comparison between numerical data and experimental data

of two I-type specimen subject to tension

3.12 Conclusions of the numerical simulation of the welding process in an I-type specimen subject to tension

• The maximum residual stress occurs in the region between the weld bead and the metal base.

• Tensile residual stresses occur at the central bar, while compressive residual stresses occur at the later

bars.

• The tensile residual stresses at the central bar remain constant through all of its length.

• The compressive residual stresses at the lateral bars remain constant in all their length.

• The numerical values show a good agreement with the experimental measurements.

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3.13 Numerical simulation of the welding sequence in an L-type structure

We are modeling the effects of the welding sequence on the residual stress distribution and distortion in

L-type structure to check if we can predict residual stresses and distortion with respective adaptations.

3.14 Geometric configuration of the L-type structure

The L-type structure consists of two bars and a rigid base. The bars are joined by a weld bead betwee

them and two weld beads to a rigid base (figure 3.10). This configuration is selected because it contains fe

weld beads and the optimum welding sequence is well known through experience: minimum distortion

produced by first applying the weld bead that joins the two bars and then applying the two weld beads th

join the two bars to the rigid base.

Figure 3.10 Geometric configuration of the L-type structure (mm)

3.15 Finite element model of the L-type structure

The numerical simulation of the welding sequence in an L-type structure is based on the proposed mod

of the welding process developed in the previous section. The model considers the time between th

application of a weld bead and the next. To simulate the structure with welding tacks, the elements of th

welded region are activated during the analysis. The welding region has a fine mesh and the zones away fro

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the weld bead are meshed coarser, reducing the processing time while still guaranteeing computation

accuracy. Figure 3.11 shows the finite element model of the L-type structure.

Figure 3.11 Finite element model of the L-type structure





b) Boundary conditions(see figure 3.11):

Surfaces in contact with the surrounding except surfaces belonging to the weld beads (Plane x-y in z=0):

Nodes belonging to weld beads (according to the welding sequence):

Prescribed heat input: heat loading is simulated via weld thermal cycle curves (figure 3.6, page 60). Heat

applied on all surfaces between the weld metal and the base metal according to welding sequence.

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3.15.2 Mechanical boundary conditions

Three boundary conditions are applied to structural model: a) those just sufficient to prevent rigid bod

motion and rotations of the model and b) stress-free on Z-direction (plane-stress problem), which imply th

all out-of-plane stresses vanish, and c) the normal stresses to the surfaces in contact with the surrounding an

the shear stresses are zero.

a) The nodes belonging to the element attached to coordinate systems (X=0 and Y=0) [see figure 3.1

page 66) are selected to prevent rigid body motion and rigid body rotations:

and

b) In the plane-stress problem, the normal stresses to the plane X-Y ( ) and shearing stress acting in th

plane ( and ) are zero on face of the structure (see figure 3.11). Therefore, .

c) Surfaces in contact with the surrounding (see figure 3.11, page 66)


x=0, ).

3.15.3. Solution of the finite element model of the L-type structure


loads), the solution can be initiated.

In the transient thermal analysis, the time to complete each weld bead is 6 seconds, and the time to retu

to its initial temperature is 1200 seconds [25]. The thermal elastic plastic analysis for each simulation require

15 load steps to complete the weld thermal cycles (2, 5, 15, 32, 35, 45, 62, 65, 75, 100, 200, 300, 400, 60

1200 seconds).

3.16 Configuration of welding sequences for the L-type structure

Due to the number of weld beads and the diagonal symmetry of the L-type structure, there are only thre

different welding sequences (Table 3.4). The first welding sequence applies the weld bead counterclockwis

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The second welding sequence first applies the weld beads that join the bars with the rigid base, and then th

weld bead that joins the two bars. The third welding sequence first applies the weld bead that joins the tw

bars, and then the weld beads that join the two bars with the rigid base.

Welding sequence Configuration1 1-2-3

2 1-3-2

3 2-1-3

Table 3.4 Welding sequence configuration

in the L-type specimen

3.17 Localization of the point of interest in the L-type structure

It has been demonstrated in the previous section that the maximum residual stress in the metal bas

occurs in the weld metal boundary. For the L-type structure, this maximum occurs in node 1533 (figure 3.12).

Figure 3.12 Localization of the node 1533 in the L-type structure

3.18 Numerical results in the L-type structure

The maximum von Mises residual stress in the base metal and the maximum distortion in the L-typ

structure are the parameters of interest in this analysis. Figure 3.13 depicts the maximum distortion for thre

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different welding sequences. The figure shows that sequence 2 produces highest distortion and sequence

reduces distortion by 32%

Figure 3.13 Maximum distortions in L-type structure for

three different welding sequences

Figure 3.14 depicts the maximum von Mises residual stress in the base metal for three different weldin

sequences. Welding sequence 3 produces highest residual stress and sequence 2 reduces stress by 5%.

Figure 3.14 Maximum Von Mises residual stress in the L-type structure

for three different welding sequences

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3.18.1 Distortion profile in the L-type structure

The maximum distortion occurs mainly in the Z-direction in the region near weld bead 2, and the

decreases near weld beads 1 and 3 (Figure 3.15, welding sequence 3).

Figure 3.15 Distortion profile in the L-type structure corresponding

to welding sequence 3

3.18.2 Residual stress distribution in the L-type structure

The von Mises residual stress in the base metal is maximum at the boundary between the weld bead 2 an

the vertical bar. High residual stresses also occur near the rigid base, close to weld beads 1 and 3. Thes

residual stresses occur because weld beads 1 and 3 are highly constrained. In addition, these residual stress

change little with the welding sequence. Therefore, they are not considered for the welding sequence analys

Figure 3.16 depicts the distribution of Von Mises residual stresses corresponding to welding sequence 2.

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Based on the variation of the maximum distortion values and on the Von Mises residual stresses in the ba

metal, it is demonstrated that the proposed numerical model of the welding process can accurately simula

the effects of the welding sequence on residual stress and distortion in welded structures.

Figure 3.16 Distribution of Von Mises residual stress corresponding to the welding sequence 2

3.19 Experimental tests for the L-type structure

To qualitatively confirm the results obtained in the numerical simulation of the different weldin

sequences, two experimental tests are performed. The L-type specimen 1 follows the sequence that produc

the most distortion, and specimen 2 follows the sequence that produces the least amount of distortion. A

welding parameters used in the numerical simulations are reproduced in the experimental tests. Welding tac

are applied to all the L-type specimens before the welding process starts. Measurements of the distortion

both specimens are performed in a BH-V504 MITUTOYO coordinate measuring machine (resolutio

0.0001mm) located in the Manufacturing Processes Laboratory at the Salamanca-Irapuato campus of th

University of Guanajuato.

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3.19.1 Selection of points of interest in the L-type structure

To measure structure distortion, 26 points of interest are selected. These points are located on the edg

of both bars (figure 3.17). A reference frame at the rigid base is marked to locate the specimen.

Figure 3.17 Localization of the points of interest in the L-type specimen

3.19.2 Configuration of the welding sequences in the L-type specimens

As mentioned earlier, specimen 1 follows welding sequence 2, first joining the bars with the rigid base an

then joining the two bars. Specimen 2 (Figure 3.18) is welded with sequence 3, .first applying the weld bea

that joins the two bars and then applying the weld beads that join the two bars to the rigid base.

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Figure 3.18 L-type specimen 2 after applying the welding sequence 3

3.19.3 Measurement of distortion on L-type specimens

The final distortion induced by the welding process is determined by subtracting the distortion aft

applying the weld tacks from the distortion after applying the weld beads. Figure 3.19 shows specimen

(welding sequence 3) mounted on the coordinate measuring machine.

Figure 3.19 L-type specimen 2 (welding sequence 3) mounted on

the coordinate measuring machine

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The maximum distortion in specimen 1 occurs in point 7 and in specimen 2 occurs in point 8, both nea

weld bead 2 (table 3.5). However, specimen 1 has higher distortion than specimen 2. This behavior agrees wi

the numerical simulation. The experimental data (Table 3.5) indicate that distortion decreases near weld bea

1 and 3. This is also consistent with the numerical simulations.

Point L-type specimen No.1 L-type specimen No.2

1 0,25 0,14

2 0,51 0,26

3 0,63 0,59

4 0,92 0,81

5 1,05 1,06

6 1,34 1,20

7 1,77 1,34

8 1,58 1,42

9 1,38 1,22

10 1,24 1,06

11 1,02 0,98

12 0,82 0,59

13 0,51 0,36

14 0,32 0,33

15 0,25 0,17

16 0,42 0,3017 0,52 0,53

18 0,79 0,81

19 1,05 0,98

20 1,32 1,10

21 1,41 1,10

22 1,25 0,99

23 0,96 0,89

24 0,79 0,59

25 0,65 0,38

26 0,41 0,22

Table 3.5 Distortion at the points of interest in two L-type specimens

The experimental difference in the maximum distortion between the two specimens is about 20%, whi

the numerical difference is about 32%. This difference is attributed to the lack of an automatic welder leadin

to geometric irregularities in the weld beads.

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Figure 3.20 depicts the comparison of the welding distortion between the two L-type specimens. This figu

shows that specimen 1 (welding sequence 2), results in the highest distortion.

Figure 3.20 Comparison of the welding distortion (exaggerated) between two L-type specimens

3.20 Conclusions of the welding sequence analysis of the L-type structure

• The maximum residual stresses occur in the boundary between the weld metal and the base metal.

• The welding sequence that produces the lowest distortion also produces the highest residual stress

the base metal.

• The welding sequence that produces the lowest residual stress in the base metal also produces thhighest distortion.

• Numerical predictions for distortion are consistent with experimental results.

• The welding sequence that produces the lowest distortion in the numerical simulations also produc

the lowest distortion in the experimental tests.

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CHAPTER IV

WELDING SEQUENCE ANALYSIS

IN A STIFFENED SYMMETRICA

2-DIMENSIONAL FRAME

4.1 Introduction

This chapter presents a study of the effects of the welding sequence on residual stresses and distortion instiffened symmetrical flat frame. The proper welding sequences obtained in this analysis are chosen to reduc

residual stresses, distortion, or the relation between them. These proper welding sequences are obtained wi

the help of empirical welding rules: the axis of symmetry, center of gravity of the frame, and concentric circl

The origin of the circles coincides with the center of gravity of the flat frame, and the radius of the circles

formed by the center of gravity of the flat frame with the center of gravity of each of the weld beads. To car

out the different welding sequences, the numerical model developed in chapter 3 is used with the help of

commercial code. At the end of this chapter we propose and demonstrate a hypothesis to determine th

proper welding sequences to reduce residual stress, distortion, or the relation between them for


4.2 Geometric configuration of a stiffened symmetrical flat frame

The proposed symmetrical flat structure has the shape of a stiffened frame consisting of four external ba

and three internal bars joined by ten weld beads (Figure 4.1). This configuration is selected due to its multip

symmetries. The numbering of the weld beads is random.

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Figure 4.1 Geometric configuration of the stiffened symmetrical flat frame (mm)

4.3 Welding configuration in the stiffened symmetrical flat frame

The number of possible welding sequences depends on the number of weld beads [24]:

(39)

Applying equation (39), the number of possible welding sequences for the frame in figure 4.1 is 10!

3,628,800. A possible approach is to run all possible combinations and select the sequence that produces th

lowest distortion, the lowest residual stress or an appropriate relation between them. This is not feasible wodue to the large number of possible combinations. Symmetry reduces the number of welding sequences

1,088,640 – still impossibly large for analysis of all options. We therefore consider empirical rules: applying th

weld beads from the inside to the outside of the structure produces 9 sequences; and applying weld bead

from the outside to the inside of the structure produces 9 more sequences. Therefore, only eighteen weldin

sequences need to be considered.

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Welding

sequence

Weld beads

1 and 2

Weld beads

3, 4, 5 and 6

Weld beads

7, 8, 9 and 10

Configuration

1 I-O

1-2-3-4-5-6-7-8-9-10

2 I-O

1-2-5-3-4-6-8-7-10-9

3 I-O

1-2-3-6-4-5-7-8-9-10

4 I-O1-2-3-4-5-6-7-9-8-10

5 I-O

1-2-5-3-4-6-8-10-7-9

6 I-O

1-2-3-4-6-5-9-7-8-10

7 I-O

1-2-3-4-5-6-7-10-8-9

8 I-O

1-2-5-3-4-6-8-7-9-10

9 I-O

1-2-3-6-4-5-7-10-8-9

Table 4.1 Welding sequences from the inside to the outside used in the stiffened symmetrical flat frame

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Welding

sequence

Weld beads

7, 8, 9 Y 10

Weld beads

3, 4, 5 Y 6

Weld beads

1 Y 2

Configuration

1 O-I

10-9-8-7-6-5-4-3-2-1

2 O-I

9-10-7-8-6-4-3-5-2-1

3 O-I

10-9-8-7-5-4-6-3-2-1

4 O-I

10-8-9-7-6-5-4-3-2-1

5 O-I

9-7-10-8-6-4-3-5-2-1

6 O-I

10-8-7-9-5-6-4-3-2-1

7 O-I

9-8-10-7-6-5-4-3-2-1

8 O-I

10-9-7-8-6-4-3-5-2-1

9 O-I

9-8-10-7-5-4-6-3-2-1

Table 4.2 Welding sequences from the outside to the inside used in the stiffened symmetrical flat frame

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In these welding sequences, the weld beads are split in 3 groups according to their relative position to th

center of gravity. A sequence is specified by the bead order 1,2,.. 9 and the letters I-O (starting from the insid

or O-I (starting from the outside). The term WT means that welding tacks are used to keep the structure fixe

while performing the welding process. Experience shows that the welding tacks (WT), together with th

welding sequence, have important effects on residual stresses and distortion in the welded structureTherefore, each of the 18 welding sequences will be considered with and without welding tacks, for a total

36 numerical simulations – a tractable problem. The configurations of these welding sequences are shown

tables 4.1 and 4.2.

4.4 Finite element model of the stiffened symmetrical flat frame

The numerical simulations of the different welding sequences are based on the numerical model of th

welding process developed in chapter 3, considering the time between the application of a weld bead and th

next. To simulate the structure with welding tacks, the elements of the welded region are activated during athe analysis. To simulate the structure without welding tacks, the elements of the welded region are fir

deactivated and then activated in accordance with the welding sequence. Thermal and mechanical propertie

are deactivated by means of a reduction factor (1e-6). The welding region has a fine mesh and the zones awa

from the weld bead are meshed coarser. This consideration reduces the processing time and still guarantee

computational accuracy. Figure 4.2 shows the finite element model of the stiffened symmetrical flat frame.

Figure 4.2 Finite element model of the stiffened symmetrical flat frame

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Because the thermal model consists of a transient heat transfer analysis, it is required an initial condition the base metal, which is considered as the surrounding temperature ( =20°C).

b) Boundary conditions (see figure 4.2, page 80):

Surfaces in contact with the surrounding except surfaces belonging to the weld beads (Plane x-y in z=0):





Three boundary conditions are applied to structural model: a) those just sufficient to prevent rigid bod

motion and rotations of the model and b) stress-free on Z-direction (plane-stress problem), which imply thall out-of-plane stresses vanish, and c) the normal stresses to the surfaces in contact with the surrounding an

the shear stresses are zero.

a) The nodes belonging to the element attached to its center of gravity of the structure are selected

prevent rigid body motion and rigid body rotations (see figure 4.2, page 80):

; ; ; and

b) In the plane-stress problem, the normal stresses to the plane X-Y ( ) and shearing stress acting in th

plane ( and ) are zero on face of the structure (see figure 4.2, page 80). Therefore,

c) Surfaces in contact with the surrounding (see figure 4.2, page 80):


x=0, ).

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4.4.3 Solution of the finite element model of the stiffened symmetrical flat frame


loads), the solution can be initiated. In the transient thermal analysis, the time to complete each weld bead

6 seconds. Thermal elastic plastic analysis for each simulation requires 33 load steps to complete the wethermal cycles.

4.5 Numerical results in the stiffened symmetrical flat frame

The parameters of interest are maximum von Mises residual stress in the base metal and maximu

distortion in the stiffened symmetrical flat frame.

4.5.1 Distribution of the residual stresses in the stiffened symmetrical flat frame

The maximum von Mises residual stress in the metal base occurs at the boundary of weld bead 6 and a

internal bar (node 681). This is expected because the internal bars have a high degree of constraint due to th

connection to the external bars. In the central part of all the bars the magnitude of the von Mises residu

stress is almost zero. Welding sequence 5I-O shows the lowest von Mises residual stress (199.84 MPa) of a

the welding sequences analyzed (Figure 4.3).

Figure 4.3 Distribution of Von Mises residual stresses corresponding to welding sequence 5 I-O

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4.5.2 Distortion profile in the stiffened symmetrical flat frame

The maximum distortion occurs in different areas of the external bars depending on the welding sequenc

The internal bars have low distortion because they are restricted by the external bars. Welding sequence 5 OWT results in the lowest distortion (Figure 4.4).

Figure 4.4 Distortion profile corresponding to welding sequence 5 O-I WT

Analyzing the results, it is observed that the maximum Von Mises residual stress can be reduced by 15

while the maximum distortion can be reduced by 35% by applying a proper welding sequence.

4.6 Analysis of residual stress-distortion relations analysis

The following equation is proposed for quantitative comparison of the effects of the welding sequence o

residual stress, distortion, or the relation between them:

(40)

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Where: and are the residual stress and distortion for each welding sequence. The residu

stress corresponds to one selected point on the structure and the distortion corresponds to the maximu

distortion that occurs in each welding sequence. The highest residual stress that occurs in all weldin

sequences is accompanied by lowest distortion. The highest distortion that occurs in all weldinsequences , is accompanied by lowest residual stress. Weight factors W and P can be assigned

residual stress and distortion, respectively. For the case when the welding sequence only reduces the residu

stress, and . When the welding sequence only reduces distortion, and . When th

welding sequence reduces the relation between both parameters, .

4.7 Order of importance of the welding sequences to reduce residual stress, distortion, or the relatio

between them in the stiffened symmetrical flat frame

Applying equation (40) [page 83] to the results of the residual stress and distortion obtained in the 3numerical simulations, the order of importance of the different welding sequences to reduce residual stres

distortion, or a relation between them is obtained (table 4.3).

Analyzing these results, the proper welding sequence to reduce residual stress is 5 I-O (from the inside

the outside of the structure), and the proper welding sequence to reduce the distortion is 5 O-I WT (from th

outside to the inside using welding tacks). This implies that the proper welding sequence to reduce th

residual stresses is inappropriate to reduce the distortion and vice versa. Finally, welding sequence 1 I-

(welding sequence in growing spiral) shows the best overall performance: it is ranked number 4 in reducin

stress and 19 in reducing distortion. Therefore, welding sequence 1 I-O is the proper welding sequence improve the relation between the selected critical parameters.

4.8 Proper welding sequences to reduce the residual stress, distortion, or a relation between them in th

stiffened symmetrical flat frame

To formulate the proper welding sequences obtained in table 4.3, the axis of symmetry and the center

gravity of the flat frame are used. We draw concentric circles centered on the center of gravity of the fram

and extending to the center of gravity of the weld beads. The weld beads located at the same distance fro

the center of gravity of the frame fall on the same circle. The circles are numbered from the smallest to thlargest. Weld beads 1 and 2 belong to circle 1, weld beads 3, 4, 5, and 6 belong to circle 2, and weld beads 7,

9, and 10 belong to circle 3 (Figure 4.5).

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Welding

sequence

Parameters Order of importance of welding sequence to reduce:

Residual stress Distortion

Umax

(mm)

σvm W=1, P=0Node

681 (MPa)

proper = 1

inappropriate= 36

W=0, P=1 proper = 1

inappropriate= 36

1 I-O 0.286 205.48 0.872 4 0.905 192 I-O 0.314 201.29 0.854 2 0.994 35

3 I-O 0.293 208.27 0.883 12 0.927 25

4 I-O 0.305 205.73 0.873 6 0.965 32

5 I-O 0.316 199.84 0.848 1 1 36

6 I-O 0.297 207.6 0.881 10 0.940 28

7 I-O 0.309 206.46 0.876 8 0.978 33

8 I-O 0.312 201.72 0.856 3 0.987 34

9 I-O 0.290 208.54 0.885 14 0.918 23

1 O-I 0.277 206.3 0.875 7 0.877 17

2 O-I 0.220 223.64 0.949 31 0.696 8

3 O-I 0.228 216.30 0.918 30 0.722 10

4 O-I 0.278 205.52 0.872 5 0.880 18

5 O-I 0.214 224.22 0.951 33 0.677 3

6 O-I 0.230 215.32 0.913 27 0.728 11

7 O-I 0.277 210.90 0.895 18 0.877 16

8 O-I 0.223 223.70 0.949 32 0.706 9

9 O-I 0.235 214.29 0.909 24 0.744 12

1 I-O WT 0.296 210.33 0.892 15 0.937 26

2 I-O WT 0.299 208.1 0.883 13 0.946 30

3 I-O WT 0.290 212.3 0.901 23 0.918 22

4 I-O WT 0.289 210.53 0.893 16 0.915 21

5 I-O WT 0.300 206.79 0.877 9 0.949 31

6 I-O WT 0.291 211.95 0.899 22 0.921 24

7 I-O WT 0.297 211.43 0.897 20 0.940 27

8 I-O WT 0.298 207.8 0.881 11 0.943 29

9 I-O WT 0.287 214.67 0.911 26 0.908 20

1 O-I WT 0.260 211.05 0.895 19 0.823 14

2 O-I WT 0.212 231.75 0.983 35 0.671 2

3 O-I WT 0.219 214.58 0.910 25 0.693 74 O-I WT 0.266 210.45 0.893 17 0.842 15

5 O-I WT 0.206 235.74 1 36 0.652 1

6 O-I WT 0.216 215.20 0.913 28 0.684 5

7 O-I WT 0.260 211.52 0.897 21 0.823 13

8 O-I WT 0.215 231.39 0.982 34 0.680 4

9 O-I WT 0.217 215.75 0.915 29 0.687 6

Table 4.3 Order of importance of the analyzed welding sequences in the stiffened symmetrical flat frame

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Figure 4.5 Centers of gravity of the structure, centers of gravity of the weld beads, axis of symmetry,

and concentric circles in the stiffened symmetrical flat frame

4.8.1 Proper welding sequence to reduce the residual stress in the stiffened symmetrical flat frame

This welding sequence begins by selecting the weld beads belonging to the smallest circle and the

continuing with the weld beads belonging to the larger circle until the largest circle is reached. Weld bead

within the same circle should be selected symmetrically. First, the weld beads with diagonal symmetry a

selected. If the weld bead with diagonal symmetry has already been selected, then the farthest symmetric

weld bead is selected next. When a current weld bead has more than one farthest symmetrical weld bea

(weld beads with the same radius); the adjacent weld bead in counter-clockwise is selected next. Finally,

move from one circle to the other, the farthest weld bead to the current weld bead is selected next. If

current weld bead has more than one farthest weld bead, the adjacent weld bead in counter-clockwise

selected.

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4.8.2 Proper welding sequence to reduce distortion in the stiffened symmetrical flat frame

This welding sequence requires applying weld tacks to the structure. The sequence begins by selecting th

weld beads belonging to the largest circle, and then continuing with the weld beads belonging to the adjacen

smaller circle until the smallest circle is reached. The application of the weld beads belonging to the samcircle should be selected in a symmetrical form. First, the weld beads with diagonal symmetry are selected.

the weld bead with diagonal symmetry has already been selected previous to the current weld bead, then th

farthest symmetrical weld bead is selected next. When a current weld bead has more than one farthe

symmetrical weld bead, the adjacent weld bead in counter-clockwise is selected next. Finally, to move fro

one circle to the other, the farthest weld bead to the current is selected next. If a current weld bead has mor

than one farthest weld bead, the adjacent bead in a clockwise manner is selected.

4.8.3 Proper welding sequence to improve the relation between both critical parameters in the stiffene

symmetrical flat frame

It is observed in table 4.3 that the welding sequence 1 I-O shows the best stress-distortion relation, rankin

number 4 in stress reduction and 19 in distortion reduction. Therefore, welding sequence 1 I-O is selected

improve the relation between the two parameters. However, to understand the mechanism leading to th

residual stresses and distortion observed in the numerical simulations, a combined welding sequence

proposed. Therefore, a comparison between welding sequence 1 I-O and the combined welding sequence w

be performed. Figure 4.6 depicts the ranges of the values of P and W for the welding sequence 1 I-O, and th

combined welding sequence. This figure shows that a welding sequence is better than the other depending o

the values of P and W.

Figure 4.6 Ranges of the values of P and W for welding sequence 1 I-O

and combined welding sequence

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For: and

This welding sequence starts with the beads in the smallest circle and then continuing with the beads in th

larger adjacent circle until the largest circle is reached. Weld beads within the same circle should be applied counter-clockwise direction. To move from one circle to the next, the closest weld bead is selected.

For: and

In this welding sequence, welding tacks are required only on the circle next to the larger adjacent circl

The sequence begins by selecting the weld beads on the smallest circle, and then continuing with the we

beads on the circle next to the larger adjacent circle and continuing with the beads on the smaller adjacen

circle. The application of the beads on the same circle should be symmetrical. First, the weld beads wit

diagonal symmetry are applied. If the weld bead with diagonal symmetry has already been applied, then thfarthest symmetrical weld bead is selected next. When a current weld bead has more than one farthe

symmetrical bead, the adjacent bead in counter-clockwise direction is selected next. Finally, to move from on

circle to the other, the farthest weld bead to the current bead is selected next. If a current weld bead has mo

than one farthest bead, the adjacent bead in counter-clockwise direction is selected.

4.9 Hypothesis to determine the proper welding sequence to reduce the residual stress, distortion, or

relation between them in symmetrical flat structures

To determine the proper welding sequences to reduce the residual stress, distortion, or a relation betweethem in flat symmetrical structures, it is necessary to determine the axis of symmetry and the center of gravi

of the structure. We next draw concentric circles centered on the center of gravity of the structure an

extending to the center of gravity of the weld beads. Weld beads that are located at the same distance fro

the center of gravity of the structure fall on the same circle. Circles are numbered from the smallest to th

largest diameter.

a) To reduce residual stress: Start with the weld beads on the smallest circle and then continue with th

beads on the larger adjacent circle until the largest circle is reached. The weld beads on the same circle shou

be selected in a symmetrical form. First, the weld beads with diagonal symmetry are selected. If the bead witdiagonal symmetry has already been selected, then the farthest symmetrical bead is selected. When a we

bead has more than one farthest symmetrical weld bead, the adjacent weld bead in counter-clockwi

direction is selected. Finally, to move from one circle to the other, the farthest weld bead to the current we

bead is selected. If a current weld bead has more than one farthest weld bead, the adjacent weld bead

counter-clockwise direction is selected.

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b) To reduce distortion: Apply welding tacks to the structure before welding. First, the weld beads in th

largest circle are selected and then the beads on the adjacent smaller circle are selected until the smalle

circle is reached. Beads on the same circle should be applied symmetrically. Beads with diagonal symmetry a

selected first. If the weld bead with diagonal symmetry has already been previously selected, then the farthesymmetrical bead is selected next. When a current weld bead has more than one farthest symmetrical we

bead, the adjacent weld bead in counter-clockwise direction is selected next. Finally, to move from one circ

to the other, the farthest weld bead is selected. If a current bead has more than one farthest bead, th

adjacent bead in a clockwise manner is selected.

c) To improve the relation between residual stress and distortion:

i) Favoring the residual stress: Start with the weld beads belonging to the smallest circle and the

continuing with the beads on the larger adjacent circle until the largest circle is reached. The application oweld beads belonging to the same circle should counterclockwise into adjacent beads. To move from on

circle to the other, the closest weld bead to the current weld bead is selected.

ii) Favoring the distortion: This welding sequence requires application of welding tacks only on the circ

next to the larger adjacent circle. The welding sequence starts by selecting the beads on the smallest circl

and then continuing with the beads on the circle next to the larger adjacent circle, and later going back to th

beads on the smaller adjacent circle. The application of the weld beads on the same circle should be in

symmetrical form. First, the beads with diagonal symmetry are applied. If the weld bead with diagon

symmetry has already been applied, then the farthest symmetrical bead is selected next. When a current beahas more than one farthest symmetrical bead, the adjacent bead in counter-clockwise direction is selecte

next. Finally, to move from one circle to the other, the farthest bead to the current is selected next. If a curre

weld bead has more than one farthest bead, the adjacent bead in counter-clockwise direction is selected.

For the stiffened symmetrical flat frame, the hypothesis to determine the proper welding sequence

reduce residual stress, distortion, or the relation between them in symmetrical structures in the plane

verified.

4.10 Experimental tests in a stiffened symmetrical flat frame specimen

We conducted an experiment to validate the numerical results. All welding parameters used in th

numerical simulations are reproduced in the experiment. Welding tacks are applied to a stiffened symmetric

flat specimen before the welding process starts. Measurement of the distortion in the stiffened symmetric

plane specimen is performed in a BH-V504 MITUTOYO coordinate measuring machine (resolution: 0.000

mm). This machine is located in the manufacture laboratory at the University of Guanajuato camp

Salamanca-Irapuato.

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4.10.1 Selection of points of interest in the stiffened symmetrical flat specimen

To measure distortion, 88 points of interest are selected (Figure 4.7). These points are located on the edg

of all bars. A reference frame at the internal horizontal bar is marked to position the stiffened symmetrical fl

specimen.

Figure 4.7 Localization of the point of interest in the stiffened symmetrical flat specimen

4.10.2 Configuration of the welding sequence in the stiffened symmetrical flat specimen

As previously mentioned, the stiffened symmetrical flat specimen follows the welding sequence th

minimizes distortion (5 O-I WT, Table 4.4 and figure 4.8). This sequence first applies beads at locations farthefrom the center and then moves progressively inward. Weld beads at equal distance from the center of th

specimen are selected symmetrically.


5 O-I WT 9-7-10-8-6-4-3-5-2-1

Table 4.4 Configuration of welding sequence 5 O-I WT

used in the stiffened symmetrical flat specimen

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Figure 4.8 Stiffened symmetrical flat specimen after applying

the welding sequence 5 O-I WT

4.10.3 Measurement of distortion on the stiffened symmetrical flat specimen

The distortion induced by the welding process is determined by subtracting the distortion after applyin

the weld tacks from the distortion after applying the weld beads. Figure 4.9 shows the stiffened symmetric

flat specimen mounted on the coordinate measuring machine.

Figure 4.9 Stiffened symmetrical flat specimen mounted

on the coordinate measuring machine

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The maximum distortion in the specimen occurs in the external bars and drops in value as the locatio

moves progressively inwards to the structure (Table 4.5), in agreement with the numerical results.

Point Distortion Point Distortion

1 0,82 45 0,44

2 0,84 46 0,10

3 0,79 47 0,07

4 0,94 48 0,10

5 0,90 49 0,25

6 0,94 50 0,19

7 0,84 51 0,24

8 0,84 52 0,37

9 0,74 53 0,68

10 0,64 54 0,62

11 0,76 55 0,53

12 0,64 56 0,55

13 0,61 57 0,44

14 0,58 58 0,51

15 0,54 59 0,30

16 0,58 60 0,14

17 0,54 61 0,09

18 0,48 62 0,32

19 0,47 63 0,41

20 0,51 64 0,53

21 0,74 65 0,12

22 0,59 66 0,19

23 0,41 67 0,34

24 0,29 68 0,60

25 0,37 69 0,47

26 0,43 70 0,32

27 0,32 71 0,37

28 0,24 72 0,40

29 0,25 73 0,23

30 0,40 74 0,50

31 0,45 75 0,21

32 0,28 76 0,14

33 0,67 77 0,20

34 0,17 78 0,10

35 0,22 79 0,06

36 0,20 80 0,15

37 0,29 81 0,18

38 0,39 82 0,15

39 0,62 83 0,30

40 0,64 84 0,30

41 0,59 85 0,15

42 0,38 86 0,23

43 0,64 87 0,15

44 0,51 88 0,07

Table 4.5 Distortion at the points of interest (mm) in the stiffened symmetrical flat

specimen corresponding to welding sequence 5 O-I WT

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The maximum measured distortion is four times higher in the Z-direction. This is probably because th

welding process was not automated, producing geometric irregularities in the weld bead. Figure 4.10 depic

the measured distortion profile, indicating that the maximum distortion occurs on the external bars an

progressively decreases as it approaches to center of the specimen.

Figure 4.10 Distortion profile in the stiffened symmetrical flat specimen

corresponding to welding sequence 5 O-I WT (exaggerated)

4.11 Conclusions of the welding sequence analysis of stiffened symmetrical flat frame

• The maximum residual stress in the metal base occurs in the boundary with the welded metal in th

internal bars.

• For the stiffened symmetrical flat frame, the distortion is reduced by 35 %, while the maximum vo

Mises residual stress is reduced by 15% when applying the proper welding sequence to respective

reduce distortion or residual stress. The welding sequence is twice as effective for reducing distortio

than for reducing residual stresses.

• Welding tacks are not recommended when trying to reduce residual stress.

• Welding tacks are necessary to reduce distortion.

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• Welding tacks followed by weld bead application from the outside to the inside of the structure reduc

distortion but increases residual stresses.

• Applying the weld beads from the inside to the outside of the structure without welding tacks reduce

the residual stress but increases the distortion.

• The welding sequence that produces the lowest distortion also produces the highest residual stress.

• The welding sequence that produces the lowest residual stress also produces the highest distortion.

• The relation between P=0,5 and W=0,5 does not mean that both parameters are reduced by the sam

percentage, because the proper welding sequence reduces the distortion twice as much as residu

stresses.

• There is good qualitative agreement between the measured and numerical results. Quantitative

however, the numerical results show lower maximum peak values. The difference is probably due to th

lack of an automated welder.

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CHAPTER V

WELDING SEQUENCE ANALYSIS IN A

3-DIMENSIONAL UNITARY CELL-TYPE

SYMMETRICAL STRUCTURE

5.1 Introduction

This chapter describes a study of the effects of the welding sequence on the residual stresses and distortio

in a 3-dimensional unitary cell, with the purpose of demonstrating that the methodology for determining th

proper welding sequences to reduce residual stress, distortion, or the relation between them in 2-dimension

symmetrical structures can be applied to 3-dimensional symmetrical structures, where weld bead circle

become spheres. The methodology is demonstrated by conducting four numerical simulations in the propose

symmetrical structure. Two of the numerical simulations deal with the proper welding sequence to reduc

residual stress and the other two deals with the proper welding sequence to reduce distortion. A speciwelding sequence is also analyzed for comparison with the proper sequence to reduce distortion. This speci

welding sequence applies the external beads first and the internal beads later. All the numerical simulation

are based on the proposed numerical model of the welding process developed in Chapter 3 with a commerc

software code.

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5.2 Hypothesis to determine the proper welding sequence to reduce the residual stress, distortion, or

relation between them in 3-dimensional symmetrical structures

To determine the proper welding sequences to reduce the residual stress, distortion, or a relation betweethem in 3-dimensional symmetrical structures, we start by identifying the axis of symmetry and the center

gravity of the structure. Next, we draw concentric spheres centered on the center of gravity of the structur

and extending to the center of gravity of each of the weld beads. Weld beads located at the same distanc

from the center of gravity of the structure will fall on the same sphere. The spheres are numbered from th

smallest to the largest.

a) To reduce residual stress: Start with the weld beads belonging to the smallest sphere and then continu

with the weld beads belonging to the larger adjacent sphere until the largest sphere is reached. The we

beads belonging to the same sphere should be symmetrical. First, the beads with diagonal symmetry aselected. If the weld bead with diagonal symmetry has already been selected, then the farthest symmetric

weld bead is selected next. When a current weld bead has more than one farthest symmetrical bead, th

adjacent weld bead in counter-clockwise is selected. Finally, to move from one sphere to the other, th

farthest weld bead to the current bead is selected. If a current bead has more than one farthest weld bea

the adjacent bead in counter-clockwise is selected. The converse welding method between weld beads

adopted.

b) To reduce distortion: Apply welding tacks to the structure before welding. First, the weld beads in th

largest sphere are selected and then the weld beads belonging to the adjacent smaller sphere are selecteuntil the smallest sphere is reached. The application of the weld beads on the same sphere should be

symmetrical form. The weld beads with diagonal symmetry are selected first. If the weld bead with diagon

symmetry has already been selected, then the farthest symmetrical bead is selected next. When a weld bea

has more than one farthest symmetrical bead, the adjacent weld bead in counter-clockwise direction

selected next. Finally, to move from one sphere to the other, the farthest weld bead to the current is selecte

If a weld bead has more than one farthest bead, the adjacent bead in a clockwise direction is selected. Th

converse welding method between beads is adopted.

c) To improve the relation between residual stress and distortion:

i) Favoring residual stress: Start with the weld beads on the smallest sphere and then continue with th

weld beads on the larger adjacent sphere until the largest sphere is reached. The application of weld beads o

the same sphere should be in an adjacent form in counter-clockwise direction. To move from one sphere

the other, the closest weld bead to the current bead is selected. The converse welding method between we

beads is adopted.

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ii) Favoring distortion: In this welding sequence, the application of welding tacks is required only on th

sphere next to the larger adjacent sphere. The welding sequence begins by selecting the weld beads on th

smallest sphere, and then continuing with the weld beads on the sphere next to the larger adjacent spher

Then, going back to the weld beads on the smaller adjacent sphere. The application of the weld beads on thsame sphere should be symmetrical. First, the weld beads with diagonal symmetry are applied. If the we

bead with diagonal symmetrical has already been applied, then the farthest symmetrical weld bead is selecte

next. When a current weld bead has more than one farthest symmetrical bead, the adjacent bead in counte

clockwise direction is selected next. Finally, to move from one sphere to the other, the farthest weld bead t

the current weld bead is selected next. If a current weld bead has more than one farthest weld bead, th

adjacent weld bead in counter-clockwise direction is selected. The converse welding method between we

beads is adopted.

5.3 Geometric configuration of the 3-dimensional unitary cell

A 3-dimensional unitary cell configuration is selected because it is a common structural arrangement

industry, used in the construction of panels, ships, bridges, etc. This configuration keeps the requirement

symmetry in the space. Figure 5.1 depicts a structural panel used in the welding industry, where a segme

takes the form of a 3-dimensional unitary cell.

Figure 5.1 Panel used in the welding industry

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The 3-dimensional unitary cell consists of two horizontal and two vertical plates joined by fillet welds a

shown in figure 5.2. The thickness of the plates is 3 mm.

Figure 5.2 Configurations and dimensions of the 3-dimensional unitary cell (mm)

5.4 Selection of the number of weld beads in the 3-dimensional unitary cell

The 3-dimensional unitary cell is joined by eight fillet welds. The effect of dividing a fillet weld into su

welds is studied. For the present investigation, each of the fillet welds is divided in 3 sub-welds.

5.5 Symmetry axis selection and formation of the concentric spheres in the 3-dimensional unitary cell

Due to the multiple symmetry (symmetry and diagonal symmetry axis) of the 3-dimensional unitary ce

the center of mass coincides with the centroid of the structure, which is also the center of the spheres.

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Two concentric spheres are formed with 8 weld beads and four concentric spheres with 24 weld bead

(Figure 5.3).

Figure 5.3 Axis of symmetry and concentric spheres of the 3-dimensional

unitary cell formed by 24 fillet welds

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5.6 Proper welding sequence to reduce the residual stress and proper welding sequence to reduce th

distortion in the 3-dimensional unitary cell

Figures 5.4 (a) and (c) depict the proper welding sequence to reduce distortion with 8 and 24 fillet weldrespectively. Figures 5.4 (b) and (d) depict the proper welding sequence to reduce the residual stresses with

and 24 fillet welds, respectively.

Figure 5.4 Different welding sequences for the 3-dimensional unitary cell

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5.7 Material selection of the 3-dimensional unitary cell

Structural steel S235JR is selected to define the material properties of the 3-dimensional unitary cell. Th

steel is widely used in Europe (Poland: steel ST3S) for construction of ships, buildings, bridges and machine[36]. This steel is easy to weld because of its carbon content (0.22% C), and its chemical compositio

mechanical and thermal properties are similar to ASTM A36 structural steel. Steel S235JR is therefore modele

using properties of ASTM A36 structural steel.

5.8 Fillet weld shape used in the 3-dimensional unitary cell

Because the 3-dimensional unitary cell is joined with fillet welds, it is important to model the shape of th

fillet weld as close as possible to reality. For this reason, a common shape found in the welding literature

proposed [1]. Figure 5.5 depicts the shape of the fillet weld used in the 3-dimensional unitary cell.

Figure 5.5 Fillet weld shape used in the 3-dimensional unitary cell

5.9 Finite element model of the 3-dimensional unitary cell

The numerical simulations of the welding sequences for the 3-dimensional unitary cell are based on th

numerical model of welding process developed in Chapter 3. To simulate the structure with welding tacks, th

elements of the welded region are activated during all of the analysis. To simulate the structure witho

welding tacks, the elements of the welded region are originally turned off and then activated in accordance t

the welding sequence. This is accomplished by reducing thermal and mechanical properties of the elements b

multiplying them by 1e-6. The analysis considers the time between the application of weld beads and th

welding direction. The region being welded has a fine mesh and the zones away from the weld beads a

meshed coarser. This consideration reduces the processing time and still guarantees computationally accurac

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The numerical model of the 3-dimensional unitary cell is divided into 29,362 hexahedral elements and 41,20

nodes. Figure 5.6 shows the finite element model of the 3-dimensional unitary cell.

Figure 5.6 Finite element model of the 3-dimensional unitary cell





b) Boundary conditions (see figure 5.6):

Surfaces in contact with the surrounding except surfaces belonging to the weld beads:


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a) The specified mechanical boundary conditions are those just sufficient to prevent rigid body motion an

rotations of the model, the nodes belonging to the element localized in the center of one lateral edge at th

bottom horizontal plate are selected to prevent rigid body motion and rigid body rotations (see figure 5.

page 102):

; ;

; ;

b) Surfaces in contact with the surrounding (see figure 5.6):


the plane y-z in x=0, ).

5.9.3 Solution of the finite element model of the 3-dimensional unitary cell


loads), the solution can be initiated. In the transient thermal analysis, the time to complete each weld bead

6 seconds. Thermal elastic plastic analysis for each simulation requires 55 load steps to complete the we

thermal cycles.

5.10 Localization of the points of interest in the 3-dimensional unitary cell

The selected points of interest belong to important areas in the 3-dimensional unitary cell (Figure 5.7

Points 1 and 3 are located in the center of the horizontal plates, while points 2 and 4 are located in the cent

of the vertical plates. Points 5 and 8 and points 6 and 7 are located in the central part of the lower and upp

flanges, respectively. Points 9, 12, 15 and 18, and points 11, 14, 17 and 20 are respectively located in the edg

of the lower and upper flanges. Points 10, 13, 16 and 19 are located in the central part of the lateral edges o

the vertical plates, while points 21, 22, 23 and 24 are located in the central part of the lateral edges of th

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horizontal plates. The magnitude of the distortion is positive when the displacement direction is inwards to th

structure.

Figure 5.7 Localization of the points of interest in the 3-dimensional unitary cell

5.11 Configuration of the numerical simulation for the 3-dimensional unitary cell

To demonstrate the hypothesis proposed in Section 5.2, four numerical simulations will be performed. Tw

of them deal with the proper welding sequence to reduce the distortion with 8 and 24 weld beads, and th

other two deals with the proper welding sequence to reduce the residual stress with 8 and 24 weld beads. Th

numerical simulations for reduced distortion include the effects of the welding tacks. Table 5.1 depicts th

configuration of the numerical simulations for the 3-dimensional unitary cell.

Numerical

simulation

Proper welding sequence

to reduce:

Number of

welds

Welding

tacks

figure

1 Distortion 8 Yes 5.4 (a)

2 Residual stress 8 No 5.4 (b)

3 Distortion 24 Yes 5.4 (c)

4 Residual stress 24 No 5.4 (d)

Table 5.1 Configuration of the numerical simulations for the 3-dimensional unitary cell

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5.12 Numerical results of the different welding sequences analyzed in the 3-dimensional unitary cell

The numerical results of interest are the maximum von Mises residual stresses in the base metal, th

distortion modes, the maximum distortion, and the distortion in the 24 points selected in the unitary 3dimensional unitary cell.

5.12.1 Maximum von Mises residual stress in the 3-dimensional unitary cell

The maximum von Mises residual stress in the base metal occurs in the central internal weld beads, at th

boundary with the weld metal. Compressive residual stress occurs in the central region of the vertical an

horizontal plates, while tensile residual stress occurs in the weld metal and nearby areas. Numerical simulatio

2 (Figure 5.8) results in the lowest residual stress, therefore confirming the hypothesis proposed in Section 5.

Figure 5.8 Distribution of residual stresses in numerical simulation 2

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5.12.2 Distortion modes in the 3-dimensional unitary cell

All the numerical simulations produce the same distortion mode. However, the magnitude of the distortio

varies. The lower and upper flanges rotate inward to the structure, while the center plates bend towards th

inside of the structure. The central regions of the vertical and horizontal flanges also bend inward towards thstructure. Numerical simulation 3 (Figure 5.9) results in the lowest distortion. This simulation deals with th

proper welding sequence to reduce distortion, therefore confirming the hypothesis proposed in section 5.2.

Figure 5.9 Isometric view of the distortion profile corresponding to numerical simulation 3

5.12.3 Maximum distortion and distortion in 24 points of interest in the 3-dimensional unitary cell

In all the simulations, the maximum distortion occurs in the central region of the upper and lower flange

(points 5, 6, 7 and 8). Table 5.2 depicts the distortion at the 24 points of interest for the different weldin

sequences.

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The table shows that simulation 3 produces the lowest distortion. However, this welding sequence results

the highest von Mises residual stress. Once again, the proper welding sequence to reduce the residual stre

results in highest distortion.

Point Node Simulation1 2 3 4

1 15756 0,08 0,05 0,06 0,04

2 17536 0,11 0,01 0,21 0,05

3 19015 0,08 0,07 0,06 0,04

4 17238 0,11 0,02 0,21 0,05

5 14571 1,85 1,87 1,68 1,65

6 20554 2,0 2,0 1,75 1,85

7 20508 1,82 1,83 1,67 1,64

8 14498 1,99 1,98 1,73 1,80

9 11 1,36 1,70 1,52 1,12

10 386 0,31 0,18 0,35 0,19

11 758 1,54 1,92 1,53 1,13

12 35172 1,49 1,86 1,55 1,11

13 38137 0,08 0,07 0,2 0,19

14 41155 1,57 1,95 1,74 1,24

15 35099 1,51 1,88 1,50 1,08

16 37839 0,39 0,10 0,3 0,08

17 41109 1,33 1,65 1,54 1,13

18 1 1,56 1,94 1,74 1,2119 361 0,19 0,10 0,16 0,08

20 754 1,47 1,83 1,56 1,01

21 167 0,57 0,25 0,66 0,29

22 36357 0,59 0,34 0,59 0,34

23 591 0,57 0,31 0,6 0,33

24 39616 0,52 0,22 0,68 0,29

Maximum distortion 2,97 3,05 2,04 2,10

Table 5.2 Distortion at 24 points of interest (mm) corresponding to different welding sequences

In the 3-dimensional unitary cell.

5.13 Numerical comparison between the proper welding sequence to reduce distortion and a special weldin

sequence in the 3-dimensional unitary cell

The proper welding sequence to reduce distortion (Figure 5.4 (c), page 100) recommends starting with th

weld beads on sphere 4 (Figure 5.3, page 99), located in the lateral edges of the outside of the structure. Nex

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the weld beads on sphere 3 are applied. These weld beads are located at the lateral edges, on the inside of th

structure. Next, the weld beads located at the center box, on the outside of the structure are applied (sphe

2). Finally, the weld beads on sphere 1, located in the center box, on the inside of the structure, are applie

The sequence involves applying alternating external and internal weld beads. For this reason, a special weldin

sequence (figure 5.10) that involves applying first the external and then internal weld beads is proposed. Thwelding sequence is commonly used to reduce the distortion in this type of joints. Weld beads belonging t

the same sphere are applied in the same way in both welding sequences.

Figure 5.10 Configuration of the special welding sequence

Table 5.3 shows the comparison of the numerical results between both welding sequences. It can be see

that the proper welding sequence results in the lowest distortion, verifying the original hypothesis.

Welding sequence Maximum distortion (mm) Difference (%)

Proper welding sequence

to reduce distortion

2,04

6.4

Special welding sequence 2.18

Table 5.3 Comparison of numerical results between both welding sequences in the

3-dimensional unitary cell

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5.14 Conclusions of the welding sequence analysis of the 3-dimensional unitary cell

• Numerical simulations using 24 weld beads reduce distortion by up to 31% and residual stress by up t

18% with respect to numerical simulations using 8 weld beads.• Numerical simulations of the proper welding sequence to reduce residual stress confirm the hypothes

in Section 5.2 by delivering minimum stress.

• Numerical simulations of the welding sequence to reduce distortion also confirm the hypothes

proposed in Section 5.2 by producing minimum distortion

• It has been demonstrated that the hypothesis to determine the proper welding sequences for fl

symmetrical structures is also valid for symmetrical 3-dimensional structures.

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CHAPTER V

METHODOLOGY O

EXPERIMENTAL TESTS

6.1 Introduction

This chapter presents a methodology for helping plan, execute, and control each of the stages of th

experimental tests. The methodology starts with the material selection of the specimen, configuratio

selection, welding process selection, metal transfer mode selection, welding parameters selection, design an

fabrication of the equipment needed to run the test, design and fabrication of the mounting locks, residu

stresses relief caused by the manufacturing process, transportation, handling, storage and cutting of th

plates, measurement of the initial distortion of the plates, design and fabrication of a holder-mounting devic

to hold the plates, design and fabrication of a square-mounting device to square the holder-mounting devic

application of welding tacks, measurement of the distortion after applying the welding tacks, installation

the run-off tabs, welding, removal of the run-off tabs of the welded structure, measurement of the distortio

after welding, and measurement of the final distortion induced by the welding process.

6.2 Specimen material selection

The specimen material is of great importance because it determines the selection of the welding proces

parameters and material [35]. For this experiment, structural steel S235JR is selected. This steel is widely use

in Europe (Poland: steel ST3S) for construction of ships, buildings, bridges and machinery [36]. This steel is ea

to weld because of its carbon content (0.22% C), and its chemical composition, mechanical and therm

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properties are similar to ASTM A36 structural steel. Steel S235JR is therefore modeled using properties

ASTM A36 structural steel.

6.3 Selection of specimen configuration

The configuration of the specimen determines the joint geometries, mounting configuration and th

devices needed to adapt the components of the welding equipment. For this experiment a "three-dimension

unitary cell" configuration is selected because of its common applicability in industry for construction o

panels, ships and bridges. The three-dimensional unitary cell consists of two horizontal and two vertical plate

joined by fillet welds (figure 5.2, page 98). The thickness of the plates is 3 mm.

6.4 Selection of the welding process

The appropriate selection of the welding process will produce an efficient application of the welding in thspecimen. To produce the correct application, it is necessary to control the welding parameters, direction, an

position of the welding torch. This implies that the selected welding process has to be semiautomatic o

automatic. For this experiment, the Gas Metal Arc Welding (GMAW) process is selected because it can b

automated. Furthermore, the welding laboratory of the Machine Strength and Manufacturing Department

the University of Sciences and Technology AGH, where the experiment took place, has a semiautomat

OPTYMAG 501, welding machine (Figure 6.1, page 112). This machine is equipped with a microprocesso

controlled electrode wire feeder PDE-5, to fully adjust all of the welding process parameters (continuous

indicated in a multifunctional LCD display). It also has an MG-2 gas mixer and a RTU-10-300 rotameter with

computerized system for process monitoring. The OPTYMAG 501 welding machine enables welding processwith the following methods: MIG/MAG standard, MIG/MAG pulse/synergic and manual mode and a MM

method for welding processes with coated electrodes.

6.5 Selection of metal transfer mode

The operating features of the welding process are largely determined by the form in which the weld met

transfer takes place from the electrode to the weld pool [37]. The main metal transfer modes are: sho

circuiting transfer, globular transfer, spray transfer, and pulsed transfer. For this experiment we select sho

circuiting transfer for low current operation with small electrode diameters leading to a small, fast-coolinweld pool that is generally well suited for joining thin sections. In short circuiting transfer mode, also calle

“dip” transfer, the molten metal formed on the tip of the electrode wire is transferred by the wire dipping in

the molten weld pool, thus causing a momentary short circuit. Metal is therefore transferred only when th

electrode tip is in contact with the weld pool, and no metal is transferred across the arc gap.

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Figure 6.1 Semiautomatic welding machine OPTYMAG 501

6.6 Selection of welding parameters (Operating variables)

The weld geometry, depth of penetration, and overall quality of the weld process depends on the weldin

parameters [38]. These parameters are determined from the welding process, metal transfer mode, bas

metal, metal thickness and joint geometries. These parameters are: arc voltage, welding current, weldin

speed, wire feed rate, contact tip to work distance, electrode orientation, electrode diameter, shielding ga

composition, and gas flow rate.

6.6.1 Arc voltage and welding current

The arc voltage and welding current depend mainly on the metal transfer mode and the diameter of th

electrode. According to Rao [39], the ranges of voltage and current recommended for different electrod

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diameters with short circuit transfer mode for carbon and alloy steels are shown in table 6.1. In th

experiment, a voltage of 22V and a current of 160A are selected.

Electrode

diameter(mm)

Carbon steel and low alloy steels

Short circuit transfer modeVoltage (V) Current (A)

0.8 15-21 70-130

0.9 16-22 80-190

1.2 17-22 100-225

1.6 ---- ----

2.4 ---- ----

Table 6.1 Electric settings for short circuit transfer mode [39]

6.6.2 Welding speed

The welding speed determines the quantity of deposition of filler metal [40]. The welding speed depend

mainly on the cross section of the weld bead (6.3 mm2), and the wire feed volume (31.80 mm

3

Figure 6.2 Typical regions of good short circuit welding conditions [37]

/s). For th

experiment, the calculated welding speed is 5 mm/s.

6.6.3 Wire feed rate

Several combinations of open circuit voltages and wire feed rates can produce short circuiting transfer o

metal. However, an optimum combination of arc voltage and wire feed rate will produce the best result. Figu

6.2 shows arc voltage vs. wire feed rate [37]. The region of good short circuiting or dip transfer arc is about 2

wide. This graph shows that for a voltage of 22 V, there is a corresponding wire feed rate of 50 mm/s.

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6.6.4 Selecting of contact tip to work distance

The contact tip to work distance (CTWD, Figure 6.3) determines the arc efficiency [40]. According to th

Lincoln Electric Company, for short circuiting metal transfer mode, the CTWD should be held between 10 an

12 mm. For this experimental investigation, the selected CTWD is 11 mm.

Figure 6.3 Contact tip to work distance [40]

6.6.5 Electrode orientation

The electrode orientation with respect to the weld joint affects the weld bead shape as well as the we

penetration. According to Mandal [37], the electrode orientation is defined in two ways:

• By the electrode axis orientation with respect to the direction of travel. This is known as the trav

angle. The three possible ways to positioning the welding gun (figure 6.4), are called forehan

perpendicular and backhand. In this experimental investigation, the perpendicular positioning of th

electrode gun with respect to the base metal plate is selected.

Figure 6.4. Positioning of electrode gun with respect to the base metal plate [37]

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• The angle between the electrode axis and the adjacent work surface. This is called work angle. For fill

welds in the horizontal position, the electrode should be positioned at about 45° to the vertical plan

(figure 6.5).

Figure 6.5 Normal work angle for fillet welds [37]

6.6.6 Electrode diameter

The appropriate diameter of the electrode depends on the base metal composition, metal thickness, an

the metal transfer mode [38]. In this experiment, the base material is carbon steel with a thickness of 3mm

and the metal transfer mode is by short circuit. Therefore, according to the AWS, the electrode diamet

should be 0,9 mm.

6.6.7 Shielding gas composition

The primary function of the shielding gas is to protect the arc and the molten weld pool from th

atmospheric oxygen and nitrogen. The selection of the shielding gas composition depends on the bas

material and the metal transfer mode [39]. According to the Lincoln Electric Company, there are two commo

blends of shielding gases for short circuit transfer mode for carbon steels (Table 6.2). The blend 80% Argon

20%CO2

Common short circuiting transfer shielding gas blends

is selected for this investigation.

75% Argon + 25%CO2- reduces spatter and improves weld bead appearance in

carbon steel applications.

80% Argon + 20%CO2- Another popular blend, which further reduces spatter

and enhances weld bead appearance in carbon steel applications.

Table 6.2 Common blends of shielding gas composition for short transfer mode [40]

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6.6.8 Gas flow rate

Gas flow rate eliminates and prevents defects in the weld bead [40]. According to the Lincoln Electr

Company , the rate flow for short circuiting transfer mode with either CO 2

• Must be a rigid device.

or a mixed shielding gas is usua

12-17 L/min. For this experiment, 12 L/min is selected.

6.7 Design and fabrication of the equipment needed to run the test

Due to the configuration of the three-dimensional unitary cell with fillet welds, it is necessary to design an

fabricate an arm-holder and a welding-torch-holder to efficiently apply the welding fillet. Figure 6.6 depicts th

configuration of the arm-holder mounted in the main-support. See Appendix 9 for the construction drawing

of the arm-holder.

The requirements for the arm-holder device are:

• Should have a positioning system (two positions) for the welding torch holder.

• Should be easy to mount on the main-support.

Figure 6.6 Arm-holder device

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The requirements for the welding-torch-holder device are:

• Must have a rigid arm.

• Must have a system to rotate the welding torch from one position to another 90° apart.

• Must have a system to perform a zig-zag rotary motion for the welding torch.

• Should be easy to mount and remove on the arm-holder.

Figure 6.7 depicts the configuration of the welding torch holder device. See Appendix 9 for the constructio

drawings of the welding torch holder device.

Figure 6.7 Welding torch holder device

6.8 Design and fabrication of the mounting locks

The mounting locks position the specimen with respect to a reference point. The locks constrain th

specimen in the X, Y and Z-directions. Figure 6.8 depicts the localization of the mounting locks on the travel

carriage.

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Figure 6.8 Localization of the locks mounted on the traveler carriage

6.9 Relief of residual stresses caused by the manufacturing process, transportation, handling, storage an

cutting of the plates.

The manufacturing process results in residual stresses and distortion. For example, in the rolled plate

tensile residual stresses are developed near the edges, while compressive residual stresses are developed

the interior of the plates. In addition, transportation, handling and storage of the plates can alter the state o

initial residual stresses and distortion. The cutting processes also induce residual stresses near the edges of th

plates.

To study the effects of the initial residual stresses and distortion due to the manufacturing proces

transportation, handling, storage and cutting of the plates, four plate specimens are subject to a he

treatment for stress relief. The main objective is to compare the effect of applying or not applying a he

treatment for stresses relief. The distortion is the parameter of comparison. The duration of the treatment an

the temperature of the electric oven depend on the geometric characteristics and material properties of th

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plates. For the present study, the heating time is 5 Hrs at 250 °C. Figure 6.9 depicts the electric oven used

relief the initial residual stresses.

Figure 6.9 Electric oven used to initial residual stresses relief

6.10 Measurement of the initial plate distortion

It is important to measure the initial distortion of the plates to avoid errors in the measurements

distortion after welding, because, in many cases, the distortion due to the manufacturing proces

transportation, handling, storage and cutting of the plates is larger than the distortion induced by the weldin

process. A series of standard gages are used to measure the initial distortion on a polished table. Thes

standard gages have a minimum precision of 0.05 mm. Figure 6.10 depicts the measurement of the initi

distortion on a polished table with standard gages.

Figure 6.10 Measurement of the initial distortion with standard gages

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6.11 Design and fabrication of a holder-mounting device to hold the plates

To assemble and hold together the plates with the specimen configuration before applying the weldin

tacks to the specimen, a holder-mounting device is required (figure 6.11 and Appendix 9).

The requirements for the holder-mounting device are:

• Must be rigid.

• Must be a precision device.

• Must have a system that reduces the work-volume to remove the specimen after the application of th

welding tacks.

Figure 6.11 Holder-mounting device

6.12 Design and fabrication of a square-mounting device

Because the holder-mounting device will be removed of each specimen after applying the welding tacks,

device to square the holder-mounting device is required (Figure 6.12). The construction drawings of th

square-mounting device are in Appendix 9.

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The requirements for the square-mounting device are:

• Must be rigid.

• Must be a precision device.

• Must have a system that increases the work-volume to remove the holder-mounting device.

Figure 6.12 Square-mounting device

6.13 Application of the welding tacks

The welding tacks are used to hold the specimen together before welding. Before applying the weldin

tacks, C-type clamps are used to temporarily hold the plates together to the holder-mounting device. Once a

the welding tacks are applied, it is necessary to wait 15 minutes to allow solidification before removing the

type clamps. Figure 6.13 depicts the C-type clamps mounted on the specimen and figure 6.14 depicts th

application of the welding tacks on the specimen.

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Figure 6.13 C-type clamps mounted on the specimen

Figure 6.14 Welding tack application on the specimen

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6.14 Distortion measurement after welding tack application

Initial distortion can considerably affect the value of the final distortion induced by the welding process.

is therefore necessary to measure distortion after welding tack application to consider the initial distortion the specimen. In this experiment, 24 points of interest have been selected to measure the initial distortio

(figure 5.7, page 104). For some of the points, the measurement is performed with standard gages and

polished rule. For the remaining points, distortion is measured by tracing the contour of the four faces of th

welded structure (front, back, top and bottom) using a pencil with a sharp tip on a special paper sheet fixed o

a polished table. The sheets with the contours are scanned and save in a BMP format. The BMP files a

converted to a DWG format to be read by a CAD program. Once the file is opened, measurement of th

distortion can be performed by using CAD program tools. The measurements have a dimensional tolerance o

0,2 mm.

6.15 Installation of the run-off tabs

In some applications, it is necessary to completely fill out the groove right to every end of the joint. In suc

cases, run-off tabs are used. They, in effect, extend the groove beyond the ends of the members to be welde

The weld is carried over in tabs. This ensures that the entire length of the joint is filled to the necessary dept

with weld metal. Run-off tabs are excellent appendages on which to start and stop welding. Figure 6.15 depic

the run-off tabs installed on the specimen.

Figure 6.15 Installation of the run-off tabs on the specimen

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6.16 Application of the welding

The application of the welding is made by following a sequence. The selection of the welding sequenc

depends on the critical parameter or parameters to reduce – residual stress, distortion or a relation betweeboth. Chapters 4 and 5 described the proper welding sequences to reduce residual stress, distortion or

relation between both for symmetrical structures in 2 and 3 dimensions. For this experiment, we selected th

welding sequence to reduce residual stress and distortion for symmetrical structures in the space. Figure 6.1

depicts the specimen welding.

Figure 6.16 Application of the welding to the specimen

6.17 Removing the run-off tabs from the welded structure

The run-off tabs should be removed to be able to perform the distortion measurements. These run-off ta

are removed once the welding process is completed. Care must be taken when removing them to not induc

residual stresses, or distortion, or both. First the run-off tab material close to the specimen is removed. Th

can be performed with an abrasive disc. Then, each of the run-off tabs is removed, and at the end, th

irregular edges are taken out with a grinder. Figure 6.17 depicts the removal of the run-off tabs from th

specimen.

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Figure 6.17 Removing the run-off tabs from the specimen

6.18 Measurement of the distortion after applying the welding

The same procedure used in the measurement of the distortion after application of the welding tacks

used to measure the distortion after application of the welding. The measurement of the distortion should b

performed 24 hrs, 48 hrs, 96 hrs and 384 hrs after the welding process to detect possible rheological effect

Figure 6.18 depicts the distortion measurement after the welding process using standard gages.

Figure 6.18 Measurement of the distortion after welding using standard gages

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6.19 Measurement of the final distortion

The final distortion, or the distortion induced by the welding process, is obtained by adding or subtractin

the distortion after applying the welding tacks, and the distortion after welding.

Final distortion = Distortion after applying Distortion after applying (41)

the welding tacks welding

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CHAPTER VI

RESULTS OF THE EXPERIMENTAL TESTS IN

3-DIMENSIONAL UNITARY CELL-TYPE

SPECIMENS

7.1 Introduction

This chapter covers the results of the experimental tests performed in 3-dimensional unitary ce

specimens. In these experimental tests, the effects of the welding sequence on distortion are studied. Eig

symmetrical specimens are prepared. Four welding sequences are considered: two of them are appropriate

reduce distortion and the others are appropriate to reduce residual stresses. Also, the effects that occur whe

a welding bead is divided into 3 sub-weld beads are studied, as well as the effects of relieving the residu

stresses caused by manufacturing process, transportation, storage and cutting of plates. Welding tacks a

applied to all specimens before the actual weld process begins. The measurement of the distortion

periodically performed to observe if rheological effects occur in the specimens after welding. The experiment

tests were performed in the Department of Machine Strength and Manufacturing in the Faculty of Mechanic

Engineering at the University of Science and Technology in Krakow, Poland.

7.2 Configuration of the 3-dimensional unitary cell specimens

The 3-dimensional unitary cell specimens have the same configuration analyzed in Chapter 5. The ma

objective of using the same configuration is performing a quantitative and qualitative comparison betwee

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numerical and experimental results. The 3-dimensional unitary cell specimen consists of two horizontal an

two vertical plates joined together by fillet welds (figure 5.2, page 98). The thickness of the plates is 3 mm.

7.3 Localization of the points of interest in the 3-dimensional unitary cell specimens

The points of interest in the 3-dimensional unitary cell specimens are the same points selected in Chapt

5 (figure 5.7, page 104) to perform a quantitative and qualitative comparison between the numerical an

experimental results.

7.4 Configuration of the experiment

Eight specimens and four welding sequences are studied: two of them are appropriate to reduce distortio

and the other two are appropriate to reduce residual stress (Table 7.1). Other parameters considered in thes

experiments are: the number of weld beads (8 or 24) and whether a relief of the residual stresses induced bmanufacture, transportation, handling, storage and cutting is performed. Welding tacks are applied to a

specimens before welding. The specimen number represents the order in which they are fabricate

Specimens T1, T2 and T3 were discarded due to measurement errors.

Specimen Number of

the Weld

beads

Welding sequence most

appropriate to reduce:

Residual stress relief Welding

tacks

T7 8 Distortion No Yes

T11 8 Distortion Yes Yes

T8 8 Residual stress No Yes

T4 8 Residual stress Yes Yes

T9 24 Distortion No Yes

T5 24 Distortion Yes Yes

T10 24 Residual stress No Yes

T6 24 Residual stress Yes Yes

Table 7.1 3-dimensional unitary cell specimen configuration

7.5 Distortion after applying welding tacks in the 3-dimensional unitary cell specimens

Distortion is measured after application of the welding tacks and it represents the initial specimen distorte

shape. Table 7.2 lists the values of the distortion after application of the welding tacks for the differe

specimens.

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Point

Specimen

T7 T11 T8 T4 T9 T5 T10 T6

1 0,15 0,55 0,25 0,10 0,40 0,20 0,20 0,30

2 0,15 0,20 0,25 0,30 0,10 0,05 0,20 0,20

3 0,25 0,05 0,2 0,15 0,15 0,20 0,10 0,10

4 0,20 0,20 0,05 0,35 0,15 0,10 0 0,05

5 0,95 0,60 0,25 0,93 0,5 0,55 0,55 0,75

6 0,65 0,38 0,60 1,15 0,43 0,95 0,35 0,93

7 0,93 0,60 0,63 1,43 0,80 0,60 0,80 0,45

8 0,92 0,63 0,28 1,38 0,15 0,58 0,45 0,80

9 (-) 1,10 (-) 1,00 (-) 0,40 (-) 1,70 (-) 1,15 (-) 0,45 (-) 0,30 (-) 0,70

10 (-) 0,15 (-) 0,25 0,10 0,10 0 (-) 0,20 0,25 0,25

11 (-) 0,10 (-) 0,20 (-) 0,10 (-) 1,25 (-) 0,70 (-) 0,50 (-) 0,15 (-) 0,20

12 (-) 0,20 (-) 0,35 0 (-) 0,95 (-) 0,30 (-) 0,55 (-) 0,60 (-) 0,30

13 (-) 0,05 (-) 0,15 (-) 0,05 0,05 0 0,20 0,05 0,20

14 (-) 0,40 (-) 0,45 (-) 1,10 (-) 1,10 (-) 0,55 (-) 1,20 0,30 (-) 1,25

15 (-) 0,85 (-) 0,65 (-) 0,45 (-) 1,45 (-) 0,10 (-) 0,25 0 (-) 0,55

16 (-) 0,10 0,35 0,45 0 (-) 0,15 (-) 0,20 0,35 0,15

17 (-) 0,50 0,30 (-) 0,35 (-) 0,95 (-) 0,50 (-) 0,25 (-) 0,60 (-) 0,20

18 (-) 0,20 (-) 0,10 (-) 0,20 (-) 1,50 (-) 0,60 (-) 0,90 (-) 0,30 (-) 0,65

19 0,25 0,05 0,15 0,10 0,25 (-) 0,10 0,50 0,35

20 (-) 0,65 (-) 1,00 (-) 0,70 (-) 1,80 (-) 0,80 (-) 1,05 (-) 1,10 (-) 0,80

21 (-) 0,50 (-) 0,25 (-) 0,05 (-) 0,05 (-) 0,15 (-) 0,40 0,15 0

22 (-) 0,45 (-) 0,30 (-) 0,05 (-) 0,10 (-) 0,30 (-) 0,35 (-) 0,10 (-) 0,10

23 (-) 0,20 (-) 0,35 0,05 (-) 0,10 (-) 0,20 (-) 0,25 0 0

24 (-) 0,40 (-) 0,35 0,15 0,05 (-) 0,20 (-) 0,25 (-) 0,15 0

Table 7.2 Distortion after application of the welding tacks for the

different 3-dimensional unitary cell specimens, mm.

7.6 Distortion after welding in the 3-dimensional unitary cell specimens

Distortion is measured after welding and it represents the final distorted specimen shape. It is necessary

note that these measurements do not represent the distortion induced by the welding process because th

specimens were originally distorted by the application of the welding tacks.

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The measurements were performed periodically (24, 48, 96 and 384 hours) after welding to observ

possible rheological effects. However, the distortion did not show any variation with time. Therefore, th

rheological effects are discarded in the experimental tests. Table 7.3 lists the values of the distortion aft

welding for the different three dimensional unitary cell specimens 24 hours after welding.

Point

Specimen

T7 T11 T8 T4 T9 T5 T10 T6

1 0,05 0,45 0,30 0,05 0,35 0,25 0,15 0,25

2 0,30 0,35 0,25 0,30 0,10 0,15 0,25 0,15

3 0,15 0,15 0,25 0,10 0,20 0,15 0,05 0,05

4 0,10 0,35 0,05 0,35 0,05 0,30 0,05 0,10

5 0,80 1,30 1,65 1,0 1,05 1,0 0,50 0,93

6 1,28 1,5 1,25 0,70 1,15 0,75 1,30 0,90

7 0,87 1,45 1,20 0,50 0,83 0,93 0,85 1,30

8 0,93 1,35 1,55 0,55 1,50 0,95 1,15 1,05

9 0,30 0,45 1,30 0,10 0,35 1,10 0,85 0,50

10 0,15 0,10 0,25 0,30 0,40 0,10 0,40 0,40

11 1,40 1,30 1,60 0,55 0,75 1,0 0,95 1,20

12 1,10 1,30 1,90 0,90 1,10 0,80 0,85 0,95

13 0,05 0,25 0,05 0,15 0,25 0,45 0,20 0,35

14 0,95 1,0 0,70 0,70 0,95 0,40 0,80 0

15 0,45 1,0 1,30 0,45 1,40 1,0 1,10 0,65

16 0,25 0,05 0,55 0,10 0,10 0,20 0,45 0,25

17 0,95 2,0 1,30 0,85 1,0 1,20 0,45 1,10

18 1,30 1,40 1,50 0,35 1,0 0,70 0,70 0,65

19 0,45 0,30 0,25 0,25 0,45 0,10 0,60 0,45

20 0,70 0,60 1,10 0,05 0,65 0,35 0,05 0,40

21 0 0,20 0,20 0,20 0,35 0,30 0,40 0,30

22 0,10 0,20 0,25 0,20 0,25 0,25 0,20 0,20

23 0,30 0,10 0,30 0,20 0,40 0,35 0,30 0,30

24 0,10 0,10 0,35 0,35 0,35 0,35 0,20 0,30

Table 7.3 Distortion after welding for the different 3-dimensional

unitary cell specimens 24 hrs after welding, mm.

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Figure 7.1 shows a comparison between the distortion after applying welding tacks and the distortion aft

welding for specimen T9, illustrating the distorted shape before and after welding.

Figure 7.1 Distortion (exaggerated) after applying welding tacks and after

welding for specimen T9

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7.7 Distortion modes of the 3-dimensional unitary specimens

All welded specimens present the same distortion mode. However, the magnitude of the distortion varie

The lower and upper flanges rotate inward to the specimen, and the plates of the central box bend toward th

center of the specimen (Figure 7.2).

Figure 7.2 Distorted shape of the 3-dimensional unitary cell welded specimens

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7.8 Final distortion of the 3-dimensional unitary cell specimens

The final distortion is calculated with equation (41) [page 126] and tables 7.2 (page 129) and 7.3 (pag

130). Table 7.4 lists the final distortion in the 24 points of interest of the 3-dimensional unitary cell specimens

Point

Specimen

T7 T11 T8 T4 T9 T5 T10 T6

1 0,10 0,10 0,05 0,05 0,05 0,05 0,05 0,05

2 0,15 0,15 0 0 0,2 0,2 0,05 0,05

3 0,10 0,10 0.05 0,05 0,05 0,05 0,05 0,05

4 0,10 0,15 0 0 0,2 0,2 0,05 0,05

5 1,75 1,90 1,90 1,93 1,55 1,55 1,90 1,68

6 1,93 1,88 1,85 1,85 1,58 1,70 1,65 1,83

7 1,80 2,05 1,83 1,93 1,63 1,53 1,65 1,75

8 1,85 1,98 1,83 1,93 1,65 1,53 1,60 1,85

9 1,40 1,45 1,70 1,80 1,50 1,55 1,15 1,20

10 0,30 0,35 0,15 0,20 0,40 0,30 0,15 0,15

11 1,50 1,50 1,70 1,80 1,45 1,50 1,10 1,40

12 1,30 1,65 1,90 1,85 1,40 1,35 1,45 1,25

13 0,10 0,10 0,10 0,10 0,25 0,25 0,15 0,15

14 1,35 1,45 1,80 1,80 1,50 1,60 1,10 1,25

15 1,30 1,65 1,75 1,90 1,50 1,25 1,10 1,20

16 0,35 0,40 0,10 0,10 0,25 0,40 0,10 0,10

17 1,45 1,70 1,65 1,80 1,50 1,45 1,05 1,30

18 1,50 1,50 1,70 1,85 1,60 1,60 1,00 1,30

19 0,20 0,25 0,10 0,15 0,20 0,20 0,10 0,10

20 1,35 1,60 1,80 1,85 1,45 1,40 1,15 1,20

21 0,50 0,45 0,25 0,25 0,50 0,70 0,25 0,30

22 0,55 0,50 0,30 0,30 0,55 0,60 0,30 0,30

23 0,50 0,45 0,25 0,30 0,60 0,60 0,30 0,30

24 0,50 0,45 0,20 0,30 0,55 0,60 0,35 0,30

Table 7.4 Final distortion in the 24 points of interest of the 3-dimensional

unitary cell specimens, mm.

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Figure 7.3 depicts the comparison of the non-distorted and distorted shape of specimen T9, showing

general agreement with distortions in Section 7.7.

Figure 7.3 Final distortion (exaggerated) for welded specimen T9

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7.9 Final Remarks for distortion of the 3-dimensional unitary cell specimens

For the points located at the center of the plates (points 1, 2, 3 and 4):

• There is symmetry with respect to the horizontal (points 1 and 3) and vertical (points 2 and 4) axes.

• Welding with 24 beads results in higher distortion than welding with 8 beads.

• When following a welding sequence from the outside to the inside of the structure, specimens with

weld beads develop higher distortion.

• Little variation is observed between welded specimens with or without stress-relief.

For points 5, 6, 7 and 8 located at the central part of the lower and upper flanges:

• Specimens with 8 weld beads result in higher distortion than specimens with 24 weld beads.

• Welded specimens with stress-relieved plates develop a slight increase in distortion.

• Specimens welded with 24 weld beads that use a sequence from the outside to the inside of th

structure developed less distortion than specimens using the opposite sequence. In specimens welde

with 8 weld beads no significant trend was identified.

For points 9, 11, 12, 14, 15, 17, 18 and 20 located at the edges of the lower and upper flanges:

• There is no distortion symmetry in any axis.

• Specimens with 8 weld beads show higher distortion than specimens with 24 beads.

• Welded specimens with stress-relieved plates develop higher distortion than specimens without stres

relief.

• In 8 bead specimens, following a welding sequence from the outside to the inside of the structur

produces less distortion than using the converse sequence. However, 24 bead specimens using a

inside-to-outside sequence developed less distortion than specimens using the converse sequence.

For points 10, 13, 16 and 19 located at the central part of the lateral edges of the vertical plates:

• Welding sequences starting from the inside to the outside of the structure developed less distortio

than specimens using the opposite welding sequence.

• Distortion is slightly higher in the specimens welded with 24 beads.

• Little difference is observed between specimens with and without stress-relieved plates.

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For points 21, 22, 23 and 24 located at the central part of the lateral edges of the horizontal plates:

• Specimens welded with 24 beads develop higher distortion than specimens with 8 weld beads.

• Specimens without stress-relief develop higher distortion than specimens with stress-relievef.

7.10 Conclusions of the results of the experimental test in 3-dimensional unitary cell specimens

• In all welded specimens, the maximum distortion occurs at the central part of the lower and uppe

flanges (points 5, 6, 7 and 8).

• The specimens with 8 weld beads show higher distortion than specimens with 24 weld beads.

• Little difference is observed between specimens with or without stress-relieved plates.

• Specimens with 24 beads following a welding sequence starting from the outside to the inside of th

structure, show the lowest distortion without taking into account the stress-relief in the plates.

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CHAPTER VI

COMPARISON BETWEEN TH

3- DIMENSIONAL UNITARY CELL-TYP

STRUCTURES/SPECIMEN

8.1 Introduction

This chapter presents a comparison between numerical (Chapter 5) and experimental (Chapter 7) resul

for the 3-dimensional unitary cell structure. The comparison discusses the distortion modes, and distortion

the 24 points of interest. The end of this chapter presents the procedures to determine the proper weldin

sequences to reduce the residual stresses, distortion, or a relation between them in symmetrical an

asymmetrical structures in 2 and 3 dimensions. These procedures are based on the demonstrated hypothesdeveloped in Chapters 4 and 5.

8.2 Comparison of distortion modes

The distortion modes of all the numerical simulations (figure 5.9, page 106) agree with the experiment

results (figure 7.2, page 132). The lower and upper flanges rotate inward towards the specimen, and th

central area of the flange bends towards the specimen. The central areas of the vertical and horizontal plate

bend inward to the structure.

8.3 Comparison of distortion

Numerical distortion at the 24 points of interest (table 5.2, page 107) can be directly compared with th

experimental results (table 7.4, page 133). It is important to mention that the numerical simulations do n

consider relief of the initial residual stresses. For this reason, only four numerical simulations were develope

vs. eight experiments. Therefore, each of the simulations will be compared against two experiments: with o

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without stress relief. Equation 42 is used to determine the percentage difference between numerical an

experimental results for each of the 24 points of interest:

(42)

Table 8.1 depicts the difference percentage between numerical and experimental results.

Point Specimen

T7 T11 T8 T4 T9 T5 T10 T6

1 20 20 0 0 -20 -20 20 202 26,6 26,6 --- --- -5 -5 0 0

3 20 20 -40 -40 -20 -20 20 20

4 -10 26,6 --- ---- -5 -5 0 0

5 -5,7 2,6 1,6 3,1 -8,4 -8,4 13,1 1,8

6 -3,6 -6.4 -8,1 -8,1 -10,7 -2,9 -12,2 -1,1

7 -1,1 11,2 0 5,2 -2,4 -9,1 0,6 6,3

8 -7.5 -0,5 -8.2 -2.6 -4,8 -13 -12,5 2,7

9 2,8 6,2 0 5,5 -1,3 1,9 2,6 6,6

10 -3,3 11,4 -20 10 12,5 -16,6 -26,6 -26,6

11 -2,6 -2,6 -12,9 -6,6 -5,5 -2 -2,7 19,3

12 -14,6 9,7 2,1 -0,5 -10,7 -13,3 23,4 11,2

13 20 20 30 30 20 20 -26,6 -26,6

14 14 -8,2 -8,3 -8,3 -16 -8,7 -12,7 0,8

15 -16,2 8,5 -7.4 1 0 -20 1,8 10

16 -11,4 2,5 0 0 -20 25 20 20

17 8,2 21,7 0 8,3 -2,6 -6,2 -7,6 13

18 -4 -4 -14,1 -4,8 -8,7 -8,7 -21 6,9

19 5 24 0 33 20 20 20 20

20 -8,8 8,1 -1,6 1,1 -7,6 -11,4 12,1 15,821 -14 -26.6 0 0 -32 5,7 -16 3,3

22 -7,2 -18 -13,3 -13,3 -7,2 1,6 -13,3 -13,3

23 -14 -26.6 -24 -3,3 0 0 -10 -10

24 -4 -15,5 -10 26,6 -23.6 -13,3 17,1 3,3

Table 8.1 Difference (%) between numerical and experimental results

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Figure 8.1 shows a comparison between numerical (table 5.2-simulation 3, page 107) and experiment

distortion (table 7.4 -specimen T9, page 133). The figure shows good correlation between both results.

Figure 8.1 Comparison between numerical (simulation 3) and experimental

distortion (specimen T9). Exaggerated distortion.

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8.4 Conclusions of the comparison between numerical and experimental results

• Of the 192 points of interest, 17 points show a good correlation in distortion between numerical an

experimental results, 87 points present a difference between 0,1-10%, 61 points differ by 10,1-20%, 1points are different by 20,1-30%, 2 points present a difference between 30,1-40%, and 4 points canno

be compared. The resulting comparison is considered acceptable.

• Welded specimens without stress-relief present smaller differences than specimens fabricated wit

stress-relief, with the exception of specimen T10.

• The maximum differences in distortion occur in the points located at the center of the horizontal an

vertical plates because the magnitude of the distortion in these points is very small. As an exampl

variations as small as 0,01 mm result in large percentage differences.

8.5 Procedures to determine the proper welding sequences to reduce residual stress, distortion, or a relatiobetween them in symmetrical and asymmetrical structures in 2 and 3 dimensions

Based on the demonstrated hypotheses to determine the proper welding sequence to reduce the residu

stress, distortion, or a relationship between them in symmetrical structures in 2 (Chapter 4) and 3 dimension

(Chapter 5), the following procedures are obtained to determine proper welding sequences. Hypotheses fo

symmetrical structures are also adapted to asymmetrical structures. However, this hypothesis was n

demonstrated.

8.5.1 Symmetrical structures in 2 and 3 dimensions

To determine the proper welding sequence to reduce the residual stress, distortion, or a relation betwee

them in symmetrical structures in the plane/space, the procedure is as follows: Determine the axis

symmetry and the center of gravity of the structure. Draw concentric circles/spheres centered on the center

gravity of the structure and extending to the center of gravity of each of the weld beads. The weld bead

located at the same distance from the center of gravity of the structure fall on the same circle/sphere. Th

circles/spheres are numbered from the smallest to the largest.

Procedure No.1- To reduce residual stress:

Start with the weld beads on the smallest circle/sphere and then continue with the weld beads on th

larger adjacent circle/sphere until the largest circle/sphere is reached. The weld beads on the sam

circle/sphere should be symmetrical. First, the weld beads with diagonal symmetry are selected. If the we

bead with diagonal symmetry has already been selected, then the farthest symmetrical weld bead is selecte

next. When a current weld bead has more than one farthest symmetrical weld bead, the adjacent weld bead

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counter-clockwise direction is selected. Finally, to move from one circle/sphere to the other, the farthest we

bead to the current weld bead is selected. If a current weld bead has more than one farthest weld bead, th

adjacent weld bead in counter-clockwise direction is selected. The converse welding method between we

beads is adopted.

Procedure No.2- To reduce distortion:

Apply welding tacks to the structure before welding. First, the weld beads in the largest circle/sphere ar

selected, followed by the weld beads on the adjacent smaller circle/sphere, until the smallest circle/sphere

reached. The application of the weld beads on the same circle/sphere should be in symmetrical form. The we

beads with diagonal symmetry are selected first. If the weld bead with diagonal symmetry has already bee

selected, then the farthest symmetrical weld bead is selected next. When a current weld bead has more tha

one farthest symmetrical weld bead, the adjacent weld bead in counter-clockwise direction is selected nex

Finally, to move from one circle/sphere to the other, the farthest weld bead to the current is selected. If current weld bead has more than one farthest weld bead, the adjacent weld bead in a clockwise direction

selected. The converse welding method between weld beads is adopted.

Procedure No.3- To improve the residual stress-distortion relation while prioritizing the reduction

residual stresses:

First, the weld beads on the smallest circle/sphere are selected and then continuing with the weld beads o

the larger adjacent circle/sphere until the largest circle/sphere is reached. The application of weld beads o

the same circle/sphere should be in an adjacent form in counter-clockwise direction. To move from oncircle/sphere to the other, the closest weld bead to the current is selected. The converse welding metho

between weld beads is adopted.

Procedure No.4- To improve the residual stress-distortion relation while prioritizing the reduction

distortion:

Welding tacks are required only on the circle/sphere next to the larger adjacent circle/sphere. The weldin

sequence begins by selecting the weld beads on the smallest circle/sphere, and then continuing with the we

beads on the circle/sphere next to the larger adjacent circle/sphere. Then, going back to the weld beads on thsmaller adjacent circle/sphere. The application of the weld beads on the same circle/sphere should be in

symmetrical form. First, the weld beads with diagonal symmetry are applied. If the weld bead with diagon

symmetrical has already been applied, then the farthest symmetrical weld bead is selected. When a curre

weld bead has more than one farthest symmetrical weld bead, the adjacent weld bead in counter-clockwis

direction is selected. Finally, to move from one circle/sphere to the other, the farthest weld bead is selecte

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next. If a current weld bead has more than one farthest weld bead, the adjacent weld bead in counte

clockwise direction is selected. The converse welding method between weld beads is adopted.

8.5.2 Asymmetrical structures in 2 and 3 dimensions

The procedure to determine the proper welding sequence to reduce the residual stress, distortion, or

relation between them in asymmetrical structures is as follows: Find the center of gravity of the structure an

draw concentric circles/spheres centered on the center of gravity of the structure and extending to the cent

of gravity of each of the weld beads. The weld beads that are located at the same distance from the center o

gravity of the structure will fall on the same circle/sphere. The circles/spheres are numbered from the smalle

to the largest.

Procedure No.5- To reduce the residual stress:

First, the weld beads on the smallest circle/sphere are selected and then continuing with the weld bead

on the adjacent larger circle/sphere until the largest circle/sphere. Next, the farthest weld bead to the curre

weld bead on the same circle/sphere is selected. When a current weld bead has more than one farthest we

bead in the same circle/sphere, the adjacent weld bead in counter-clockwise direction is selected. Finally, t

move from one circle/sphere to the other, the farthest weld bead to the current weld bead is selected. If

current weld bead has more than one farthest weld bead, the adjacent weld bead in counter-clockwis

direction is selected. The converse welding method is adopted between weld beads.

Procedure No.6- To reduce the distortion:

Apply welding tacks to the structure. First, the weld beads belonging to the largest circle/sphere a

selected and then the weld beads belonging to the adjacent smaller circle/sphere, until the smalle

circle/sphere is reached. Next, the farthest weld bead to the current weld bead on the same circle/sphere

selected. When a current weld bead has more than one farthest weld bead in the same circle/sphere, th

adjacent weld bead in counter-clockwise direction is selected. Finally, to move from one circle/sphere to th

other, the farthest weld bead to the current is selected. If a current weld bead has more than one farthe

weld bead, the adjacent weld bead in a clockwise direction is selected. The converse welding method

adopted between weld beads.

Procedure No.7- To improve the residual stress-distortion relation while prioritizing the reduction o

residual stresses.

First, the weld beads on the smallest circle/sphere are selected, and then continuing with the weld bea

on the larger adjacent circle/sphere until the largest circle/sphere is reached. The application of the we

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beads on the same circle/sphere should be in an adjacent form in counter-clockwise direction. Finally, to mov

from one circle/sphere to the other, the closest weld bead to the current weld bead is selected. The convers

welding method is adopted between weld beads.

Procedure No.8- To improve the residual stress-distortion relation while prioritizing the reduction odistortion:

The application of welding tacks is required only on the circle/sphere next to the larger adjace

circle/sphere. The welding sequence begins by selecting the weld beads on the smallest circle/sphere, an

then continuing with the weld beads on the circle/sphere next to the larger adjacent circle/sphere. Then, goin

back to the weld beads on the smaller adjacent circle/sphere. Next, the farthest weld bead to the current we

bead on the same circle/sphere is applied. When a current weld bead has more than one farthest weld bea

the adjacent weld bead in counter-clockwise direction is selected next. Finally, to move from one circle/sphe

to the other, the farthest weld bead to the current weld bead is selected next. If a current weld bead has mothan one farthest weld bead, the adjacent weld bead in counter-clockwise direction is selected. The convers

welding method is adopted between weld beads.

Figure 8.2 depicts the flow diagram of the analysis of the welding sequence for symmetrical an

asymmetrical structures in 2 and 3 dimensions. The main goal of this flow diagram is to facilitate reading by

welder, for determining the proper welding sequences to reduce the required critical parameter, an

additionally, to be used by the weld-cognizant engineer in the design stage to check the welding sequenc

with a finite element code.

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Welding sequence analysis


Figure 8.2 Flow Diagram of the analysis of the welding sequence for symmetrical and asymmetric

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CHAPTER IX

CONCLUSIONS, CONTRIBUTIONS

AND SUGGESTIONS FOR

FUTURE RESEARCH

9.1 Conclusions

The following conclusions are limited to analyzed cases in this thesis:

• The maximum residual stress occurs in the base metal, at the boundary with the welded metal.

• Validation of the numerical simulation of the welding process vs. experimental results show

satisfactory results, with less than 8.3% difference.

• The welding sequence considerably affects the residual stresses and the distortion in welded structure

• The welding sequence that produces the lowest distortion also produces the highest residual stress anvice versa.

• The welding sequence has a bigger effect on distortion than on residual stresses.

• The comparison between numerical results of the 3-dimensional unitary cell with experimental tes

shows satisfactory results, with less than 40% difference.

• Dividing a weld bead in several sub-welds reduces distortion but increases residual stresses.

• Combining the welding sequence and converse welding method considerably reduces distortion an

residual stresses.

• To reduce distortion it is necessary to apply welding tacks to the structure before welding begins.

• To reduce the residual stresses, welding tacks are not recommended.• Application of the weld beads from the inside to the outside of the structure, without the use o

welding tacks results in the lowest residual stress, but the highest distortion.

• Application of the weld beads from the outside to the inside of the structure, with the use of weldin

tacks, results in the lowest distortion, but in the highest residual stresses.

• Application of the weld beads from the inside to the outside of the structure with the use of weldin

tacks reduces distortion, but increases residual stress.

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• Application of the weld beads from the outside to the inside of the structure without the use of weldin

tacks, reduces residual stresses, but increases distortion.

• The hypothesis to determine the proper welding sequences for 2-dimensional symmetrical structures

valid for 3-dimensional symmetrical structures.

9.2 Contributions

• A finite element-based simulation of the welding process. A sequentially coupled thermo-mechanic

analysis is proposed. A transient heat transfer analysis is first performed, followed by a thermo elast

plastic analysis. The material is assumed to follow the von Mises yield criterion and the associated flo

rule, lineal isotropic hardening, and the temperature-dependent thermal and mechanical properties

the selected material. The micro-structural evolution is not considered

• A comparison of the numerical simulation of the welding process to experimental tests.

• A study of the effects of the welding sequence on the residual stress and distortion on particulasymmetrical structures in 2 and 3 dimensions.

• A residual stress-distortion relation analysis due to the welding sequence for 2-dimension

symmetrical structures.

• An equation to determine the residual stress-distortion relation:

• A hypothesis to determine the proper welding sequence to reduce the residual stress, distortion or

relation between them for 2-dimensional symmetrical structures (Chapter 4, Section 4.9).• A hypothesis to determine the proper welding sequence to reduce the residual stress, distortion or

relation between them, for 3-dimensional symmetrical structures (Chapter 5, Section 5.2).

• Validation of the hypotheses to determine the proper welding sequence to reduce the residual stres

distortion or a relation between them, for symmetrical structures in 2 and 3 dimensions.

• Procedures to select the proper welding sequence to reduce the residual stress, distortion, or a relatio

between them for symmetrical structures in 2 and 3 dimensions.

• Development of a methodology to perform experimental tests.

• Experimental comparison of the proper welding sequences to reduce the distortion and/or the residu

stress in a 3-dimensional symmetrical structure.

9.3 Suggestion for future research

• Include the effects of micro-structural evolution in the numerical simulation of the welding process.

• Measurement of the residual stress in the 3-dimensional unitary cell specimens.

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• Application of this methodology to determine the proper welding sequence to reduce the residu

stress, distortion or a relation between them, for other common structures in the welding industr

Appendix 4 proposes some welding sequences to reduce the residual stresses and distortion

common symmetrical structures. These welding sequences have not been numerically verified.

• Develop a family-group classification of the symmetrical structures in 2 and 3 dimensions to determinthe proper welding sequence to reduce the residual stress, distortion or a relation between them.

• Develop a computer program to automatically determine the proper welding sequences to reduc

residual stress, distortion or a relation between them, for symmetrical structures in 2 and 3 dimension

• Develop a methodology to determine the proper welding sequence to reduce the residual stres

distortion or a relation between them for asymmetrical structures.

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REFERENCES

[1] Zhili, F., 2005, “Processes and Mechanisms of Welding Residual Stress and Distortion”, CRC Press.

[2] Masubuchi, K., 1980, “Analysis of Welded Structures: Residual Stresses, Distortion, and their

Consequences”, Pergamon Press.

[3] Masubuchi, K., 2001, “Welding Handbook: Residual Stress and Distortion”, American Welding Society

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Messler, R., 1999, “Principles of Welding: Processes, Physics, Chemistry, and Metallurgy”, John Wiley

and Sons, Inc.

[5] Murugan, V., Gunaraj, V., 2005, “Effects of Process parameters on angular distortion of gas metal arcwelded structural steel plates”, Weld. J. 84 (11): 165s-171s.

[6] Tso-Liang Teng., Ching-Cheng Lin., 1998, “Effect of welding condition on residual stress due to butt

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[7] Jang, B., Kim, H. K., Kang S., 2001, “Effects of root opening on mechanical properties, deformation and

residual stress of weldments”, Weld. J. 80 (7): 80s-88s.

[8] Bhide, S. R., Michaleris, P., Posada, M., Deloach, J., 2006, “Comparison of buckling distortion

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[9] Wahab, M. A., Alam, M. S., Painter, M. J., Stafford, P. E., 2006, “Experimental and numerical simulation

of restraining forces in gas metal arc welded joints”, Weld. J. 85 (2): 35s-43s.

[10] Muhammad, Abid., Muhammad, Siddique., 2005, “Numerical simulation of the effect of constraints on

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Weld Buckling Distortion”, Weld. J. 76(11): 451s-457s.

[12] Michaleris, P., Dantzig, J., Tortorelli, D., 1999, “Minimization of welding residual stress and distortion in

large structures” Weld. J. 78 (11): 361-366.

[13] Holdren, R. L., Greer, J. E., 2001, “Welding Handbook: Terms and definition, Appendix A.”, American

Welding Society , 9th

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edition,

The Lincoln Electric Company , 1933, “Procedure handbook of arc welding design and practice”,

Cleveland, Ohio, U.S.A.

[15] Bart, O. N., Deepak, G., Kyoung, Y. K., 2004, “Welding distortion minimization for an aluminum alloyextruded beam structure using a 2D model”, ASME J. Manufacturing Science and Engineering, 126: 52-

63.

[16] Tso, L. T., Peng, H. C., Wen, C. T., 2003, “Effect of welding sequence on residual stresses”, Compute

and Structures, 81: 273-286.

[17] Ji, S. D., Fang, H. Y., Liu, X. S., Meng, Q. G., 2005, “Influence of a welding sequence on the welding

residual stress of a thick plate”, Modeling and Simulation in Materials Science and Engineering, 13

553-565.

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[18] Nami, M. R., Kadivar, M. H., Jafarpur, K., 2004, “3D thermo-viscoplastic modeling of welds: Effect o

piece-wise welding on thermo-mechanical response of thick plate weldments”, Iranian Journal of

Science and Technology, Transaction B, Vol. 28, No. B4, 467-478.

[19] Mochizuki, M., Hayashi, M., 2000, “Residual stress distribution depending on welding sequence in mult

pass welded joints with X-shaped groove”, ASME J. Pressure Vessel Technology. 122: 27-32.

[20] Mochizuki, M., Hattori, T., Nakakado, K., 2000 , “Residual stress reduction and fatigue strength

improvement by controlling welding pass sequence”, ASME J. Engineering Materials and Technology,

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[21] Tsai, C. L., Park, S. C., Cheng, W. T., 1999, “Welding distortion of a thin-plate panel structure”, Weld. J

78 (11): 156s-165s.

[22] Hackmair, C., Werner, E., Pönisch, M., 2003, “Application of welding simulation for chassis components

within the development of manufacturing methods”, Computational materials Science, 28: 540-547.

[23] Kadivar, M. H., Jafarpur, K., Baradaran, G. H., 2000, “Optimizing welding sequence with genetic

algorithm”, Computational Mechanics. 26: 514-519.

[24] Voutchkov, I., Keane, A. J., Bhaskar, A., Olsen, T. M., 2005, “Weld sequence optimization: the use ofsurrogate models for solving sequential combinatorial problems”, Computer methods in applied

mechanics and engineering, 194: 3535-3551.

[25] Hernández, A. I., 2005, “Análisis de distorsión y esfuerzos residuales en estructuras soldadas”, Tesis de

maestría, Universidad de Guanajuato.

[26] Karlsson, L., 1986, “Thermal Stresses I-Chapter 5: Thermal Stresses in welding”, Edited by Hetnarski R

B., Elsevier Science Publishers B.V.

[27] Argyris, J. H., Szimmat, J., William, K. J., 1982, “Computational aspect of welding stress analysis”

Computer methods in applied mechanics and engineering, 33: 635-666.

[28] Boley, B., Weiner, J., 1962, “Theory of thermal stresses”, John Wiley and Sons, Second Edition.

[29] Goldak, J.A., Akhlaghi Mehdi., 2005, “Computational Welding Mechanics”, Springer.

[30] Cook, R., Malkus, D., Plesha, M., Witt, R., 2002, “Concepts and Application of Finite Element Analysis”

John Wiley and Sons, Fourth Edition.

[31] Doghri, I., 2000, “Mechanics of Deformable Solid: Linear and Nonlinear, Analytical and Computationa

Aspects”, Springer.

[32] Malvern, L., 1969, “Introduction to the Mechanics of a Continuous Medium”, Prentice Hall, Inc.

[33] William, D., Callister, Jr., 2000, “Materials Science and Engineering an Introduction”, John Wiley and

Sons, inc. Fifth Edition.

[34] Chang, P. H., 2003, “Numerical and experimental investigation on residual stresses of the butt-welded

joints”, Computation Material Science, 29: 511-522.

[35] Tso-Liang Teng., Ching-Cheng Lin., Peng-Hsiang Chang., 2002, “Effect of weld geometry and residua

stresses on fatigue in butt-welded joints”, Int. J. Pressure Vessels and Piping, 79: 467-482.[36] Pilarczyk, J., 2003, “Poradnik inżyniera Spawalnictwo część 1”, Wydawnictwa Naukowo-Techniczne

Polska. (In polish)

[37]

Mandal, N. R., 2004, “Welding and distortion control”, Alpha Science International Ltd.

[38] Holdren, R. L., Greer, J. E., 2001, “Welding Handbook: Volume 2.”, American Welding Society , 9th

[39]

edition,

Rao, P. N., 2001, “Manufacturing Technology: Foundry, Forming and Welding”, McGraw-Hil

International, Second Edition.

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[40] Nadzam, J., 2006, “Gas Metal Arc Welding Guidelines”, The Lincoln Electric Company , Cleveland, Ohio

U.S.A.

[41] Słuzalec, A., 2005, “Theory of Thermomechanical Processes in Welding”, Springer.

[42] Prat, P., Gens, A., 2000, “Leyes de comportamiento de materiales” Métodos Numéricos para Cálculo y

Diseño en Ingeniería, Barcelona.

[43] Simo, J., Hugnes T., 1998, “Computational Inelasticity”, Interdisciplinary Applied Mathematics, Vol. 7,

Springer-Verlag, New York, Inc.

[44] Makhnenko, V. I., Veliokoivanenko, E. A., 1999, “Numerical Methods for the Predictions of welding

stresses and distortions”, E. O. Paton Electric Welding Institute, Volume 13, Part 1.

[45] Nicholson, D., 2003, “Finite Element Analysis: Thermomechanics of Solid”, CRC Press.

[46] Klaus-Jurgen Bathe, 1996, “Finite Element Procedures”, Prentice Hall.

[47] Swanson Analysis Systems, Inc. “ANSYS user´s manual: Elements”, Vol. III.

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APPENDIX 1

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Plasticity theory applied to welding process and its formulation by finite element method

1. Plasticity theory applied to welding process

Plasticity-based analysis provides an engineering basis for study of residual stress and distortion [1]. Th

temperature of the metal in welds varies from melting temperature ( )mT to room temperature ( )ambT . Th

domain includes the liquid weld pool and the far field of solid near room temperature. The material´s behavi

depends on the temperature range encountered in the different regions in the weld. At temperatures abov

0.8 mT , the solid can be considered to be linear viscous. Between 0.5 and 0.8 mT , the material is ra

dependent. For 0.5 mT , the solid can be considered to be viscoplastic and characterized by an elasticity tenso

viscosity and deformation resistance. Below 0.5 mT , the solid can be considered to be rate independent plast

material characterized by an elasticity tensor, yield strength and isotropic hardening modulus [29].

Most thermal stress analyses have used thermal elastic plastic constitutive models with rate independen

plasticity. Rate independent plasticity implies zero viscosity and therefore zero relaxation time. This means th

stress relaxes instantly to the yield stress. A rate independent model is certainly not valid in the liquid regio

and is suspected near the melting point where the viscous effects are expected to be important [29

Furthermore, the mechanical and thermal properties of weld and base metal are dependent on temperatu

[1,29,41].

2. Mathematical considerations in the modeling of the welding process

Welding process simulation considers small displacements [2,41]. Therefore, the infinitesimal strain

defined as:

( ), ,

1

2ij i j j iu uε = + (4

The strain in equation (43) is known as the Cauchy strain tensor. Changes in stress caused by deformatio

are also assumed to travel slowly compared to the speed of sound. So, at any instant, an observed group o

material particles is approximately in static equilibrium [1]:

, 0ij j i f σ + = (19

Where: i f is the sum of the body force and ijσ is the Cauchy stress tensor.

To ensure that the body remains continuous during the deformation, the compatibility equations must b

satisfied [2].

, , , , 0

ij kl kl ij ik jl jl ik ε ε ε ε + − − = (20

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3. Rate independent isotropic plasticity in the modeling of the welding process

Rate independent plasticity occurs at low temperatures, roughly below 0.5 mT . The deformation is due

dislocation glide and strain rate due to fluctuations plays no significant role. The relaxation time is zero. In th

simulation of the welding process it is important to assume the appropriate material behavior of the weld anbase metal. The additive decomposition of strain, yield surface, flow rule and the hardening hypothesis shou

be assumed in such a way to describe the welding process as realistic as possible [41].

3.1 Additive decomposition of total strain

This section shows a derivation of the constitutive equations in differential (increment) form for therm

elastic plastic isotropic material, assuming that total strain increment can be decomposed (valid for sma

strains and small rotations) as [1]:

Tot e p tr

ij ij ij ij ijd d d d d θ ε ε ε ε ε = + + + (44

Where:e

ijd ε is the elastic strain increment, p

ijd ε is the plastic strain increment, ijd θ ε is the thermal stra

increment, andtr

ijd ε is the phase transformation strain increment. The metallurgical evolution may develo

stresses due to strain incompatibility during solid-state phase transformation. This strain incompatibili

results in stresses between the grains of different phases, which may have a significant influence on the sta

of residual stresses in the weld metal and heat affected zone in joining certain types of materials such

martensitic weldments. However, this phase transformation stress is usually ineffective in influencing the fin

state of weld distortion. Equation (44) is therefore reduced to:

e pij ij ij ijd d d d θ ε ε ε ε = + + (2

Equation (21) represents the additive decomposition of total strain increment considered in th

investigation. Figure 1 depicts the decomposition of total strain into elastic, plastic and thermal.

Figure 1. Stress-strain curve of thermal elastic plastic material [42,43]

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From figure 1, two fundamental relations are obtained:

( )e p

ij ijkl kl ijkl kl kl kl d E d E d d d θ σ ε ε ε ε = = − − (4

t ep

ij ijkl lk ijkl lk d E d E d σ ε ε = = (46

where: ijkl E is the elastic tensor,t

ijkl E is the tangent elastic tensor andep

ijkl E is the elastic-plastic tensor.

If the elastic strain increment is zero ( )0ijd θ ε = , the material is known as rigid- perfectly plastic (figu

2(a)). If the strain increases with no limit when the stress reaches the yield point, the material is known a

elastic-perfectly plastic (figure 2 (b)). If the stress does not remain constant beyond the yield point, increasin

or decreasing with strain, the material is known elastic-plastic with hardening (figure 2(c)) or elastic-plast

with softening (figure 2(d)). This investigation considers that materials behave as elastic plastic with hardenin

Figure 2. Stress-strain idealized curves in plasticity [42]. (a) Rigid-perfectly plastic, (b) elastic-perfectly plastic,

(c) elastic-plastic with hardening and (d) elastic-plastic with softening.

3.2 Yield surface

A yield criterion is a basic assumption for determining the onset of plastic strain. If a stress state at a poin

satisfies the yield criterion, then this point deforms plastically; otherwise, it undergoes elastic strain [30

Figure 3 depicts the yield surface for isotropic materials.

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The general expression of the yield surface is written as [42]:

( ), 0ij i f σ χ = (4

where: i χ are parameters that control the yield surface size

Figure 3. Yield surface for isotropic materials [42]

Generalizing the different material behavior showed in figure 2, the yield surface becomes [42]:

• Perfect plasticity: the yield surface only depends on the magnitudes of the stress, not changed in siz

during the load process. In this case, equation (47) reduces to:

( ) 0ij f σ = (4

• Rigid Plasticity: the yield surface expands during the load process.

• Soften Plasticity: the yield surface contracts during the load process.

When the body is under plastic domain, the stress state should be on the yield surface. Thus, given

defined stress state ijσ and parameters, i χ , yields [42]:

( ), 0ij i

f σ χ < ⇒ for elastic deformation domain

( ), 0ij i

f σ χ = ⇒ for plastic deformation domain

( ), 0ij i f σ χ > ⇒ impossible

For the general case of modeling of the welding process, the yield surface has the form [2]:

( )( ), , , 0 p p

ij ij f T σ ε κ ε = (4

Where: κ is the parameter related with the strain hardening effects and T is the temperature.

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3.3 Flow rule

The flow rule relates the stress state with components of the plastic strain increment [8]. In general there

a function of the stress and other parameters that [42]:

( ), 0ij iG σ ξ = (50

The term is known as plastic potential, so that plastic strain increment is obtained as [42]:

p

ij

ij

Gd d ε λ

σ

∂=

∂ (5

Where d λ is a scalar that determines the magnitude of the plastic strain increment and is called plast

multiplier. The plastic strain increment is parallel to the gradient of the plastic potential. Therefore, thdirection of the plastic strain is tangent to the surface of G (figure 4).

Figure 4. Plastic potential and direction of plastic strain increment [42]

When the yield surface and the plastic potential coincide ( ) ( )ij ij f Gσ σ = , the plasticity is called associa

and no-associate plasticity for the oppositecase [42]. The associate plasticity is used in ductile metals while th

no-associate plasticity is more appropriate for granular materials [31]. For associate plasticity equation (5

becomes:

p

ij

ij

f d d ε λ

σ

∂=

∂ (5

Applying the consistency condition to equation (49) yields:

0df = (53

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0 p

ij ij p

ij ij

f f f f d d d dT

T σ ε κ

σ ε κ

∂ ∂ ∂ ∂+ + + =

∂ ∂ ∂ ∂ (5

The consistency condition means that if yield occurs during a time interval, the solution should alwa

remain on the yield surface [32].

Since p

ij p

ij

d d κ

κ ε ε

∂=

∂ and the flow rule is p

ij

ij

f d d ε λ

σ

∂=

∂, substituting these expressions into equation (54

produces:

kl

kl

f f d Q d dT

T λ σ

σ

∂ ∂= +

∂ ∂ (5

The plastic multiplier takes specific values to remain on the yield surface at all times:

0d λ = if 0 f < (Elastic strain)

0d λ > if 0 f = and 0df = (Yielding)

0d λ = if 0 f = and 0df < (Unloading)

If 0d λ > , the plastic strain increments are determined from the flow rule. If equation (55) is introduce

into equation (51), the plastic strain increment becomes:

p

ij kl

ij kl ij

f f f f d Q d dT

T

ε σ

σ σ σ

∂ ∂ ∂ ∂= + ∂ ∂ ∂ ∂

(56

Where;1

p p

ij ij ij

Q f f f κ

ε κ ε σ

= − ∂ ∂ ∂ ∂

+ ∂ ∂ ∂ ∂

(5

3.4 Hardening hypothesis

The hardening hypothesis describes how the yield surface is modified by the plastic strain beyond the init

yield [8]. Under this hypothesis, the yield surface is not constant but may change in size, shape and/or positio

during the process of plastic strain [6].

There are three fundamental hardening hypotheses [30-33,42-43]:

a) Null hardening. The hardening energy is absent in an ideally plastic material (perfect plasticity). The yie

surface for this material is not changed by the presence of plastic strain as illustrated in figure 5 (a). If th

stress state remains on the yield surface in the path 1-2, then the evolution of the plastic strain occurs, th

path 2-3 corresponds to elastic unload.

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b) Isotropic hardening. Assumes that the subsequent yield surface is a uniform expansion of the initial yie

surface, as shown in figure 5(b), and that the material´s isotropic response to yielding remains unchange

during plastic strain. Thus the center of initial and subsequent yield surface is the same. In isotropic hardenin

the variable κ depends on the plastic strain or plastic work.

For the case of strain hardening, ( ) p F d κ ε = ∫ where pd ε is the equivalent strain increment defined as:

2

3

p p p

ij ijd d d ε ε ε = (58

For the case of work hardening, ( ) p F dW κ = ∫ where pdW is the work plastic increment defined as:

p p

ij ijdW d σ ε = (59

c) Kinematic hardening. Assumes that the yield surface moves as a rigid body in the stress space durin

plastic strain. As a result the shape of the subsequent yield surface during plastic strain remains unchange

This hardening is more appropriate for cyclic plasticity, because isotropic hardening cannot predict th

Bauschingers effect which is observed experimentally [31].

For this investigation, isotropic strain hardening (Figure 5 (b)) is selected.

(a) (b) (c)

Figure 5. Three fundamental hypothesis of hardening [42]. (a) Null hardening,

(b) isotropic hardening, and (c) kinematic hardening.

4. Von Mises model applied to the welding process

Welding process simulation is based on two important considerations [1, 2, 26,27]: 1) Welding is for duct

metals (associate plasticity) and 2) Deformations occur without volume change (independent of the spheric

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invariant,1

3ij kk ij pδ σ δ = ). Due to these considerations, the Von Mises model is adopted. Figure 6 depicts th

Von Mises yield surfaces for one, two and three dimensions.

(a) (b) (c)

Figure 6. Von Mises yield surface [42]. (a) One-dimensional,

(b) Two-dimensional and (c) Three-dimensional

For this investigation, the three-dimensional Von Mises yield surface is selected.

The yield surface of Von Mises has the following equivalent forms [1, 2, 42, 44]:

( )( )21 1, 0

2 3

p

ij ij Y f s s T σ κ ε = − = (6

( )( )3

, 02

p

ij ij Y f s s T σ κ ε = − =

(6

Where ij ij ij s pσ δ = − is the stress deviation tensor.

From equation (61), the gradient of the yielding surface is:

3

2

ij

ij VM

s f

σ σ

∂=

∂ (62

Introducing equation (62) in equation (52) produces the plastic strain increment for the Von Mises model.

3

2

p

ij ij

VM

d d sε λ σ

= ⇔ 3

22

2

2

p x x

p y y

p z z

p xy xy VM

p xz xz

p yz yz

sd

sd

sd d

d

d

d

ε

ε

ε λ

τ γ σ

τ γ

τ γ

=

(63

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and then, using equation (61), equation (57) becomes:

1

p

ij ij

Q f f

ε σ

= − ∂ ∂

∂ ∂

(6

In the Von Mises yield criterion, the plastic multiplier is equal to the equivalent strain increment [30-3

42]:

pd d λ ε = (65

Equation (65) into equation (52) becomes:

1 p

pij ij

f ε

σ ε

∂ ∂=

∂ ∂ (66

Equation (66) into equation (64) becomes:

1 1 1 p

ij p p p

ij

Q f H f ε

ε ε ε

= − = − =∂∂∂

∂∂ ∂

(6

Where: H is the hardening modulus.

If 0 H = →

Perfect plasticity.0 H > → Rigid plasticity.

0 H < → Soft plasticity.

Finally, using equations (62), (67), and (56) the plastic strain increment becomes:

1 3 3 3

2 2 2

ij ij p kl ij kl

VM VM VM

s s s f d d dT

H T ε σ

σ σ σ

∂= +

∂ (6

or

1 3 3

2 2

ij ij p

ij VM

VM VM

s s f d d dT

H T ε σ

σ σ

∂= +

∂ (69

Equations (68) and (69) indicates that if the temperature dependency of the yield surface is expressed as

(60) or (61), the effect of temperature is indicated by an additional term in the well-known relationsh

between strain and stress.

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The elastic strain tensor can be divided by deviation and spherical components [1]:

1

3

e e e

ij ij ij kk eε δ ε = + (70

The relationship between stress and strain into their deviation and spherical components are, respective

[1]:

2

ije

ij

se

G= (7

1

3

e

kk kk K

ε σ = (72

Where:( )2 1

E G

v=

+ is the shear modulus and

( )3 1 2

E K

v=

− is the bulk modulus.

The incremental forms of equations (71) and (72) are:

2

1 1

2 2

e

ij ij ijde ds s dGG G

= − (73

2

1 2 1

3

e

kk kk kk

vd d dK

E K ε σ σ

− = −

(7

Introducing equations (73) and (74) into equation (70), the elastic strain increment becomes:

2

2

1 1 1 1 2 1 2

2 2 3

e

ij ij ij ij kk ij kk

v vd ds s dG d dK

G G E E ε δ σ δ σ

− − = − + −

(7

For the case of elastic condition, the thermal strain is defined as the thermal expansion of the material [45

ijd dT θ ε α = (7

Where: α is the thermal expansion coefficient of material.

Substituting equations (69), (75) and (76) into equation (21), the total strain increment becomes:

2

2

1 1 1 1 2 1 2

2 2 3ij ij ij ij kk ij kk

v vd ds s dG d dK

G G E E ε δ σ δ σ

− − = − + −

3 3

2 2

ij ij

ij VM

VM VM

s s f dT d dT

H H T α δ σ

σ σ

∂+ + +

∂ (7

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The inverse relationship of equation (77) becomes:

2

2

31 12

3 1 2 31

3

ij kl kl

ij ij kk ij ij kk

VM

Gs s d E d d Gd K dT dK

H v K G

ε σ δ ε ε δ α σ

σ

= + − − + −

+

11

1 13 3

ijij

VM

f s dT

s T dG

H H G

G Gσ

∂ ∂ + − +

+ +

(22

The variation of the material properties dG and dK in equation (22) is due to temperature only [2]. In th

case of elastic conditions, the change in the stress can be written as:

2

1 12

3 1 2 3

ij

ij ij kk ij ij kk

s E d d Gde dG K dT dK

v G K σ δ ε δ α σ

= + − − + −

(78

5. Formulation by finite element method of the welding process

The finite element method is a generalized Rayleigh-Ritz method, which uses interpolation to express th

variables in terms of its values in a finite number of nodes [30]. In the welding process, no external force

applied to the welded structure. Thermal loads are the only source of residual stress and distortion [1-3Therefore, The principle of virtual work without mechanical loading, is written as [26]:

0ij ij

V

d d dV δ ε σ =∫ (27

whereij

d δ ε is the variation in the strain increment ijd ε . The stress incrementij

d σ is given in equatio

(22).

In matrix notation, the thermal elastic plastic constitutive equation (eqn. 22) becomes [26]:

{ } { } { } { }epd D d C s M dT σ ε α = − − (28

where: ep D is the elastic plastic stiffness matrix, { }C s and { } M dT α are terms related with th

distortion and volume change due to the temperature.

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In extended notation, equation (28) can be expressed as:

2

2

2

1

1 2 1 2 1 21

1 2 1 2 1 2

1

1 2 1 2 1 22

x y x xy x yz x x z x zx

x y y y z y xy y yz y zx

x

x y z z xy z x z z

x

xy

yz

zx

s s s s s s s s s s sv v v

v L v L v L L L L s s s s s s s s s s sv v v

d v L v L v L L L Ld s s s s s s s sv v v

d v L v L v L LG

d

d

d

σ

σ

σ

τ

τ

τ

−− − − − − −

− − −−

− − − − − − − − −

− − − − − − − − −

=

2

2

2

21

22

1

2

12

x

y yz z zx

z

xy x xy y xy z xy xy xy yz xy zx

y

x yz y yz z yz xy yz yz yz zx

y zx xy zx yz zx x zx z zx zx

d

d s s s

d L L

d s s s s s s s s s s s

d L L L L L L

s s s s s s s s s s s

L L L L L L

s s s s s s s s s s s L L L L L L

ε

ε

ε

γ

γ

−

− − − − − −

− − − − − −

− − − − − −

2

z

zxd γ

1

1

1

0

0

0

x

y

z

xy

yz

zx

s

s

sC M

s

s

s

− −

(79

Where:

21 2 21

3 3

VM VM f C dG dT

G L L T

σ σ ∂ = − + ∂

(80

23

kk M K dT dK K

σ α

= +

(8

22 13 3

VM H LG

σ = +

(82

The virtual work equation (27) is now written as:

{ } { } 0T

V

d d dV δ ε σ =∫ (29

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where: is the volume of the body to be analyzed and is the transpose of . The strai

displacement for three-dimensional problem can be written in matrix form as [26]:

{ } { }

0 0

0 0

0 0

0

0

0

x

y

z d du

y x

z y

z x

ε

∂ ∂ ∂ ∂

∂ ∂

= ∂ ∂

∂ ∂

∂ ∂ ∂ ∂

∂ ∂ ∂ ∂

(3

In the finite element solution, the increments in the displacements for each element are approximated a

[30]:

{ } ( ){ }1

, ,n

ii

du N x y z U =

= ∆∑ (3

where: n is the number of nodal points for each element, ( , , )i N x y z are the shape functions and { U∆

are element nodal increments.

Substituting equation (31) into equation (30) becomes:

{ } [ ]{ }d B U ε = ∆ (3

Where [ ] [ ] ( )1

, ,n

i

i

B N x y z =

= ∂ ∑ is the strain-displacement matrix for each element.

Using equation (31) and equation (32) becomes:

{ } { } [ ]T T T

d U Bδ ε δ = ∆ (3

Substituting equation (27), (28) and (32) into equation (29) becomes:

{ } [ ] [ ][ ] { } [ ] { } [ ] { } 0T T T T

V V V

U B D B dV U C B s dV M B d dV θ δ ε

∆ ∆ − − = ∫ ∫ ∫ (34

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The vectors { }U δ ∆ and { }U ∆ are not included in the integrals because they are not function of th

coordinates. Equation (34) must be valid for any admissible virtual nodal increase { }U δ ∆ of equilibriu

configuration. Therefore, equation (34) becomes:

{ } [ ]{ } { }{ } 0T

U K U F ∆ ∆ − = (35

Now, the expressions inside the braces must be zero, therefore:

[ ]{ } { } K U F ∆ = (36

Where [ ] K is the global stiffness matrix for the assembly of elements and is the sum of the eleme

stiffness matrices , and is the global load vector equal to the sum of the element load vectors .

The stiffness matrix for each element is:

[ ] [ ] [ ]e

T ep

e

V

K B D B dV = ∫ (3

And the element load vector is:

{ } [ ] { } [ ] { }e e

T T

e

V V

F M B dT dV C B s dV α = +∫ ∫ (38

Equation (36) is non-linear and can be rewritten as [30]:

{ } { } { }1t i i i

t t t t K U F F −+∆ +∆

∆ = − (8

{ } { } { }1i i i

t t t t U U U −

+∆ +∆= + ∆ (8

where is the iteration number, t K is the stiffness matrix in the time , { }iU ∆ is the nodal increme

vector in the iteration , and { }i

t t F +∆ is the nodal load vector corresponding to the state of stress for the tim

t ∆ .

6. Solution of the equilibrium equations by finite element method

The equations of equilibrium governing the linear dynamic response of a system of finite element are [46

[ ]{ } [ ]{ } [ ]{ } { } M U C U K U F + + = (8

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Where: [ ] M ,[ ]C and are the mass, damping and stiffness matrices; is the external load vecto

and and are the displacement, velocity, and acceleration vectors of the finite element assemblag

Equation (68) is a linear differential equation of second order and is derived from Newton´s second law o

motion. Therefore, equation (85) can be rewritten as:

(8

where: are the inertia forces, are the damping forces an

are the elastic forces , all of them time-dependent.

In finite element analysis, the system of equations (eqn. 85) is solved with two methods of solution [46

direct integration and mode superposition. For this investigation we consider the direct integration methods.

6.1 Direct integration methods

In direct integration the equations in (85) are integrated using a numerical step-by-step procedure, th

term “direct” meaning that prior to the numerical integration the equations are not transformed into

different form [46]. Direct numerical integration is based on two ideas. First, instead of trying to satisfy (85) a

any time t, it attempts to satisfy (85) only at discrete time intervals t ∆ apart. Second, it assumes a variation

displacements, velocities and acceleration within each time interval t ∆ .

Direct integration assumes that the displacement, velocity and acceleration vectors at time 0 are know

and the solution to (85) is required from time 0 to time . In the solution the time interval , is divided into

equal time intervals t ∆ , and the integration scheme establishes an approximate solution at times 0 , t ∆ , 2∆,….., t , t t + ∆ ,…, . Since an algorithm calculates the solution at the next required time from the solution at th

previous time, the algorithms assume that the solution at times 0, t ∆ , 2 t ∆ ,.., t , is known and the solution

time t t + ∆ is required next.

The central difference method and the Newmark method are the most common method of dire

integration [30, 31, 46].

The central difference method

To approximate the velocities and accelerations in terms of displacement, appropriate finite differencexpressions can be used. This method assumes that the velocity and acceleration are given by:

{ } { } { } { }( )2

12t t t t t t U U U U

t −∆ +∆= − +

∆ (87

{ } { } { }( )1

2t t t t t U U U

t +∆ −∆= −

∆ (88

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Expressing equation (85) in terms of the time ,

[ ]{ } [ ]{ } [ ]{ } { }t t t t M U C U K U F + + = (8

Introducing equations (87) and (88) into equation (89) and grouping the terms { } { },t t t U U +∆ , and { }t t U −∆

[ ] [ ] { } { } [ ] [ ] { } [ ] [ ] { }2 2 2

1 1 2 1 1

2 2t t t t t t

M C U F K M U M C U t t t t t

+∆ −∆

+ = − − − − ∆ ∆ ∆ ∆ ∆

(9

The term { }t t U +∆ is determined from equation (90), the solution of { }t t U +∆ is thus based on using th

equilibrium conditions at time t . The integration procedure is therefore called explicit, and it is noted th

such integration scheme does not require factorization of the stiffness matrix [ ] K in the step-by-step solutio

Newmark Method

This method considers that the displacement, velocity and acceleration are now in time t t + ∆ . Th

following assumptions are used:

{ } { } { }( ) { } { }2

1 1 11

2t t t t t t t U U U U U

t t α α α +∆ +∆

= − − − − ∆ ∆

(9

{ } { } ( ){ } { }1t t t t t t U U U U t δ δ +∆ +∆ = + − + ∆

(92

{ } { } { } { } { } 21

2t t t t t t t U U U t U U t α α +∆ +∆

= + ∆ + − + ∆

(93

Now, expressing equation (85) for the time t t + ∆ ,

[ ]{ } [ ]{ } [ ]{ } { }t t t t t t t t M U C U K U F +∆ +∆ +∆ + ∆+ + = (94

Introducing equations (91), (92) and (93) into equation (94),

[ ] { } { }( ) { } { }2

1 1 11

2t t t t t M U U U U

t t α α α +∆

− − − − + ∆ ∆

[ ] { } ( ){ } { }1t t t t C U U U t δ δ +∆ + − + ∆ +

[ ] { } { } { } { } { }21

2t t t t t t t K U U t U U t F α α +∆ +∆

+ ∆ + − + ∆ =

(9

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Introducing equation (91) into equation (95),

[ ] { } { }( ) { } { }2

1 1 11

2

t t t t t M U U U U

t t α α α

+∆

− − − − +

∆ ∆

[ ] { } ( ){ } { } { }( ) { } { }2

1 1 11 1

2t t t t t t t C U U U U U U t

t t δ δ

α α α +∆

+ − + − − − − ∆ + ∆ ∆

[ ] { } { } { } { } { }( ) { } { } { }2

2

1 1 1 11

2 2t t t t t t t t t t K U U t U U U U U t F

t t α α

α α α +∆ +∆

+ ∆ + − + − − − − ∆ = ∆ ∆

(9

Factorizing the term t t U +∆ in equation (96) and grouping terms,

[ ] [ ] [ ] { } [ ] { } { } { }2 2

1 1 1 11

2t t t t t M C K U M U U U

t t t t

δ

α α α α α +∆

+ + = − − − − − ∆ ∆ ∆ ∆

[ ] { } ( ) { } { }1 1

1 1 12 2

t t t C U t U U t

δ δ δ

α α α

− − + − − − ∆ + − ∆

[ ] { } ( ){ } ( ){ } { }

2

2

2

1 1

1 1 12 2t t t t t

t

K U t U t U F t

α α

α α α α α +∆

∆

− − + − − − ∆ + − ∆ + ∆

(97

Parameters α and δ can be determined to obtain integration accuracy and stability. If these paramete

satisfy the following conditions, the solution of the equations is inconditionally stable [46].

21 1

4 2α δ

≥ +

,

1

2δ ≥ , y

10

2δ α + + > (9

With1

4

α = and1

2

δ = , the Newmark method becomes a constant-average-acceleration metho

Introducing these values into equation (97),

[ ] [ ] [ ] { } { } [ ] { } { } { } [ ] { } { }2 2

4 4 4 4 2t t t t t t t t t M C K U F M U U U C U U

t t t t t +∆ +∆

+ + = + + + + + ∆ ∆ ∆ ∆ ∆

(9

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The term { }t t U +∆ is determined from equation (82). The solution of { }t t U +∆ is thus based on the equilibriu

conditions at time t t + ∆ . The integration procedure is therefore called implicit. It is noted that su

integration scheme requires factorization of the stiffness matrix [ ] K in the step-by-step solution.

6.2 Solution of nonlinear equations in dynamic analysis

Solving the nonlinear dynamic response of a finite element system requires a similar procedure to

nonlinear static analysis. The main difference is adding the integration algorithms at time .

Explicit integration

As in linear analysis, the equilibrium of the finite element system is considered at time in order

calculate the displacements at time t t + ∆ . Neglecting the effect of a damping matrix, the equations

equilibrium governing the system for each discrete time step are [46]:

[ ]{ } { } { }t t t M U F R= − (100

where: { }t R is the nodal point force at time t .

The solution for the nodal point displacements at time t t + ∆ is obtained using the central differenc

approximation for the accelerations at the time t . The main restriction in the use of the central differenc

method is the time step size. For stability, the time step size t ∆ must be smaller than a critical time step ct ∆

This critical time step can be calculated from the stiffness and mass properties of the finite element model an

element size.

Implicit integration

As in linear analysis, the implicit integration considers the equilibrium of the system at time t t + ∆ . Th

requires an iterative procedure for nonlinear analysis. Using the modified Newton-Raphson and neglecting th

effects of a damping, the governing equilibrium equations are [46]:

[ ]{ } [ ]{ } { } { }1i i i i

t t t t t t t M U K U F R −+∆ +∆ +∆+ ∆ = − (10

6.3 Comparison between explicit and implicit integration

There are two main differences between explicit an implicit integration: (1) in explicit integration (eqn. 73

the stiffness matrix does not require factorization in the step-by-step solution, (2) The time step size t ∆ in th

explicit integration is restricted by critical time step cr t ∆ .

In finite element welding process simulation, the effects of inertia and damping are ignored [1-3

Furthermore, the welding process simulation is performed by nonlinear transient analysis. Therefore,

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commercial finite element code with explicit integration is not appropriate because the time step siz

limitation may considerably slow down calculations. Also, equation (83), which is obtained by finite eleme

method for a thermal elastic plastic model has the form of the implicit integration equation (eqn. 101) negle

the effects of inertia and damping. Therefore, a commercial package that uses the implicit integration is mo

appropriate for the simulation of the welding process.

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APPENDIX 2

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Definition and justification of the applied finite elements

The proposed sequentially-coupled thermo-mechanical analysis involves two steps. In the first step

transient heat transfer analysis is performed followed by a thermal elastic plastic analysis.

To perform the thermal analysis, it is necessary to select an element type that can simulate:

• Transient thermal analysis.

• The weld thermal cycle [figure 3.6, page 58], which determines the temperature as a function of tim

in the weld bead (i.e., all elements belonging to the weld bead).

• Conduction heat transfer in the base metal.

• Heat loss by convection and radiation to the surroundings in the base metal.


To perform the structural analysis, it is necessary to select an element type that can simulate:

• Homogeneous and isotropic material.

• Elastic-plastic material behavior following the von Mises yield criterion and the associated flow ru

with linear isotropic hardening by strain.

• Small strains.


An important factor for the selection of the structural element is the stress state for each analyze

structure, as determined below (figures 7 to 10). The analysis reveals that all structures develop bendinstiffness effects, except for the I-type structure subject to tension.

ANSYS offers a broad variety of elements for the analysis of two and three-dimensional thermal an

structural problems such as BEAM, SHELL, PLANE and SOLID elements. All these elements can simulat

mechanical and thermal effects in addition to bending stiffness. The plane and solid elements solved th

bending condition with the link between several elements.

Beam elements are appropriate for structural members whose cross-sectional dimensions are sma

compared to its length. They are also commonly subjected to transverse loading. Shell elements are designe

to efficiently model thin structures and bending capability. Otherwise, these elements present initial instabiliin perfectly flat plates. Avoiding this effect requires an initial displacement. Beam and shell elements a

therefore discarded while the plane and solid elements are selected for the numerical simulation.

1.- I-type structure subject to tension.

This structure consists of a central bar and two lateral bars (three parallel bars joined together). Due to th

symmetry of the structure, only a quarter of the model is analyzed as is shown in figure 7(a). The stress state

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obtained in two points of interest. Both points are located on the upper surface. Points 1 and 2 a

respectively located on the geometric center of the central bar and the lateral bar. When the weld therm

cycle is completed, element 1 is subject to pure tension while element 2 is subject to pure compression, bot

in the X-direction (figure 7b). Due to Poisson ratio effects, element 1 undergoes contraction while element

undergoes expansion, both in the Y and Z-direction (figure 7c).

(a)

(b)

(c)

Figure 7. Stress state in the I-type structure subject to tension

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2.- L-type structure

The L-type structure consists of an L-shaped rigid base and two perpendicularly attached thin bars (figu

8a). Due to the symmetry of the structure, the thin bars develop the same stress state, and only the vertic

bar is analyzed. Figure 8(b) shows the load and moment applied to the vertical bar as a result of the we

thermal cycles. The stress state is obtained in two points of interest located on the upper surface. The fir

point is located in the geometric center of the bar and the second is located on the lateral border in the midd

of the bar. Element 1 undergoes pure shearing due to bending and tension in the Y-direction due to we

shrinkage (figure 8c). Element 2 undergoes tension in the Y-direction due to weld shrinkage and bendin

(figure 8d).

Figure 8. Stress state in the L-type structure

The next equation is used to determine the shearing stress

(10

And the Y-direction stress is.

(10

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3.- Stiffened symmetrical flat frame (flat stress condition)

Stiffened symmetrical flat frame consists of four external bars and three internal bars joined by ten weld

(figure 9a). Figure 9(b) shows the load and moment applied to one half of the external vertical bar as a resu

of the weld thermal cycles. The stress state is obtained in two points of interest. Both points are located on th

upper surface. The first is located in the geometric center of the extracted segment from the external vertic

bar and the second is located on the lateral border in the middle of the extracted segment. Element

undergoes pure shearing due to bending and tension in the Y-direction due to the weld shrinkage (figure 9c

Element 2 undergoes tension in the Y-direction due to weld shrinkage and bending (figure 9d). The shearin

stress ( ) and stress ( ) are respectively determined by equations (120) and (103).

Figure 9. Stress state in the stiffened symmetrical flat frame

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4.- 3-Dimensional unitary cell - type symmetrical structure

The 3-dimensional unitary cell consists of two horizontal and two vertical plates joined by fillet weld

(figure 10a). Figure 10(b) shows the moments applied to a segment of the vertical plate as a result of the we

thermal cycles. This segment is delimited in the Y-direction by the weld beads and in the Z-direction by th

plate´s lateral borders. The stress state is obtained in one point of interest located on the upper surface in th

geometric center of the segment from the vertical plate. Element 1 undergoes shearing and tension in the

and Z-direction due to bending and to the weld shrinkage (figure 10c). The shearing stress ( ) and stre

( ) are respectively determined by equations (120) and (103).

Figure 10. Stress state in the 3-Dimensional unitary cell

Tables 1 and 2 show some plane and solid elements commonly used by ANSYS. In general, all elemen

have the same characteristics (degree of freedom, input data, and output data), except for two ma

differences: 1) the order of elements: higher order elements achieve better results and greater accurac

however, these elements require more computational time because numerical integration of element

matrices is more involved. Higher order elements are well suited to problems with curved boundaries. 2) Th

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shape of element: quadrilateral and brick element present better meshing control than triangular an

tetrahedral elements.

For these two reasons, PLANE55 and SOLID70 elements are respectively selected for two and thre

dimensional thermal analysis. Both elements have isotropic material properties and a single degree

freedom: temperature. These elements allow straightforward thermal modeling of the welding procesincluding thermal conductivity and specific heat as a function of temperature (Fig 3.3, page 56). The convecti

heat transfer coefficient is considered constant at 10 W/m2

THERMAL ELEMENTS

ºC (natural convection). Heat loss by convection

a boundary condition and is applied only to surfaces in contact with the surrounding air – assumed at 20°

same as the initial temperature of the base metal.

The elements PLANE42 and SOLID45 are respectively selected for two and three dimensional structur

analysis. PLANE 42 and SOLID45 elements have isotropic material properties and respectively two and thre

degrees of freedom at each node: translation in the nodal directions. Both elements couple temperatures wi

strain, therefore requiring the thermal expansion coefficient, elasticity modulus, tangent modulus, yield stre

and Poisson´s ratio dependent on temperature (figure 3.3 page 56). Finally, thermal loads are transferred t

the structural analysis through the concept of body load used through load step. PLANE 42 and SOLID4

elements have this capability because the temperatures may be specified as body loads at the nodes. Th

elements PLANE42 and SOLID55, and SOLID70 and SOLID45 are equivalent to performing coupled therm

mechanical analysis.

Element Dimension Number

of nodes

Main

application

Degree of

freedom

Input data Output data Comments

PLANE35 2-D

triangular

element

6 Steady-state

and transient

conduction

Heat transfer

Temperature - Convection or heat fluxes

may be applied to the

element´s surfaces.

- Nodal temperatures.

- Thermal gradients.

- Thermal fluxes components.

-This element is

compatible with

the PLANE77

element.

PLANE55 2-Dquadrilater

al element

4 Steady-stateand transient

conduction

Heat transfer

Temperature - Convection or heat fluxesmay be applied to the


- Nodal temperatures.- Thermal gradients.


- Better meshingcontrol

PLANE77 2-D

quadrilater

al element

8 Steady-state

and transient

conduction

Heat transfer





- Thermal gradients.


- This element is

well suited to

model problems

with curved

boundaries.

SOLID70 3-D brick

element

8 Steady-state

and transient

conduction

Heat transfer




-Heat generation rates may

be applied at the nodes.


- Average face temperature.

- Temperature-gradient

components.

- Vector sum at the centroid of

the element.

- Heat flux components.

- Better meshing

control

SOLID90 3-D brickelement

20 Steady-stateand transient

conduction

Heat transfer

Temperature - Convection or heat fluxesmay be applied to the


-Heat generation rates may

be applied at the nodes.

- Nodal temperatures.- Average face temperature.

- Temperature-gradient

components.

- Vector sum at the centroid of

the element.

- Heat flux components.

- This element iswell suited to

model problems

with curved

boundaries.

Table 1. Thermal (conduction) elements used by ANSYS

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STRUCTURAL ELEMENTS

Element Dimension Number

of nodes

Main

application

Degree of

freedom

Input data Output data Comments

PLANE42 2-D

quadrilateral

element

4 Isotropic solid

problems

Translation in

the nodal x

and y-

directions

-Distributed surface load may

be applied to element´s

surfaces.

-Temperatures may be input

as element body loads at the

nodes.

- Nodal displacements.

- Directional stress and

principal stresses.

- Better meshing

control.

-This element

may be used to

analyze large-

deflection, large

strain, plasticity,

and creep

problems

PLANE82 2-D

quadrilateral

element

8 Isotropic solid

problems

Translation in

the nodal x

and y-

directions

-Distributed surface load may


surfaces.



nodes.


- Directional stress and

principal stresses.

- This element is

well suited to

model problems

with curved

boundaries.

-This element

may be used to

analyze large-

deflection, large

strain, plasticity,and creep

problems

SOLID45 3-D brick

element

8 Isotropic solid

problems

Translation in

the nodal x, y,

and z-

directions

- Distributed surface load may


surfaces.



nodes.


- Normal components of the

stress in x, y, and z-

directions; shear stress and

principal stresses.

-This element

may be used to

analyze large-

deflection, large

strain, plasticity,

and creep

problems

SOLID92 3-D

tetrahedral

element

10 Isotropic solid

problems

Translation in

the nodal x, y,

and z-

directions

- Distributed surface load may


surfaces.



nodes.


- Normal components of the

stress in x, y, and z-

directions; shear stress and

principal stresses.

-This element

may be used to

analyze large-

deflection, large

strain, plasticity,

and creep

problems

Table 2. Structural elements used by ANSYS

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APPENDIX 3

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Response to critical comments

1) Even though the I and L- structures are considered only in a qualitative sense in order to validate th

numerical model, their absolute dimensions should be given. The same applies to the flat frame analyzed

chapter IV, which plays a crucial role in the thesis.

The absolute dimensions for the structures analyzed are:

a) I-type structure subject to tension consists of a central bar and two lateral bars (three parallel bars joine

together).

Figure 11. Dimensions of the I-type structure [mm]

b) L-type structure consists of an L-shaped rigid base and two perpendicularly attached thin bars. The thickne

of the rigid base is 12.7 mm and the thickness of the bars is 3.175 mm.

Figure 12. Dimensions of the L-type structure [mm]

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c) Stiffened symmetrical plane frame consists of four external bars and three internal bars joined by ten weld

Figure 13. Dimensions of stiffened symmetrical plane frame [mm]

2) No information is given on how the welding parameters were converted into the heat conditions applied a

the input to the FE analyses.

The heat condition applied was obtained from [Y. Higashida, J. D. Burk, and F.V. Lawrence, JR.]. While the

authors did not determine heat transfer as a function of time, they did measure the thermal cycle at HA

adjacent to the fusion line. Chromel-alumel thermocouples (0.51 mm diameter) were spot welded onto thsurface of an ASTM A36 steel plate near the fusion line. The localization of the thermocouple was determine

by preliminary measurements to define the fusion line position. The thermocouples were electrically an

thermally shielded and were connected to an oscilloscope. The thermal cycle was photographically recorded.

The amount of energy available in a heat source is called its energy capacity. For an electrical arc, th

available heat at the source is:

(104

Where E is the arc voltage (volts), and I is the arc current (Amperes). There are similar relationships fo

electrical resistance sources, laser beams, etc. Net heat input in welding is the quantity of energy introduce

per unit length of weld from a traveling heat source, whether a flame, electric arc, plasma, or beam. The n

energy input is computed as the ratio of the power of the heat source (in Watts) to its travel speed:

(105

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Where H is the net energy input (in watt-seconds or joules per mm or inch), P is the total input power

the heat source (in watts), and is the welding velocity (in mm per second or inch per minute). For a

electrical arc (considering the heat transfer efficiency):

(106

This heat could be introduced in FEM to obtain temperature in function of time; neglecting phase chang

effects.

3) Based on the data in table 4.3, in page 85 the Author claims that procedure 1 I-O (welding sequence fro

the inside to the outside) should be used to improve the stress-distortion relation. However, the data sugge

that procedure 1 O-I yields the same stress-distortion behavior.

Welding sequences 1 I-O and 1O-I present similar results. However, welding sequence 1 I-O was selected the best because the order of importance to reduce the residual stress is slightly better than 1O-I as shown

the table below. Taking in account that the welding sequence for the case of the stiffened symmetrical fl

frame reduces the distortion twice as much as the residual stress, the change from one position to another

the improvement of the residual stress has greater importance than a change from one position to another

the improvement of the distortion.

Welding

sequence

Parameters Order of importance of welding sequence to reduce:

Residual stress Distortion

Umax

(mm)

σvm W=1, P=0Node 681

(MPa)

proper = 1

inappropriate= 36

W=0, P=1 proper = 1

inappropriate= 36

1 I-O 0.286 205.48 0.872 4 0.905 19

1 O-I 0.277 206.30 0.875 7 0.877 17

Table 3. Comparison between welding sequences 1 I-O and 1O-I

4) From distortion measurement for the “three dimensional cell” the Author concludes in p. 136 that laying

weld beads produces more distortion than 24 beads. However, as revealed in table 7.3, the sum of th

measured distortion is greater for 24 welds (14.98 mm) than for 8 welds (12.93 mm). Also the maximu

distortion value is smaller for 8 welds than for 24 welds (1.40 and 1.50 mm, respectively). The same

indicated by the computed distortion data in table 5.2. In this context it cannot be overlooked that electrod

craters unfavorably affect the fatigue properties of a structure. Therefore, laying 8 welds seems to be mo

appropriate than 24 sub-welds.

• Table 7.3 [page 130] depicts the distortion measured after application of the weld and it represents th

final distorted shape of the specimens. It is necessary to note that this distortion does not represe

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the distortion induced by the welding process because the specimens were originally distorted by th

application of the welding tacks. The final distortion (distortion induced by welding) is determined by:

Final distortion = Distortion after applying Distortion after applying (41)

the welding tacks welding

• Table 4 depicts the values of the final distortion in the 24 points of interest of the 3-dimensional unita

cell specimens (the final distortion is calculated with equation (41) [page 126] and tables 7.2 [page 12

and 7.3 [page 130]). The data in the table show that the sum of the measured distortion is lower in th

specimens with 24 weld beads than specimens with 8 weld beads with the exception of specimen T7.

Point

Specimen

8 Weld beads 24 Weld beads

T7 T11 T8 T4 T9 T5 T10 T6

1 0,10 0,10 0,05 0,05 0,05 0,05 0,05 0,05

2 0,15 0,15 0 0 0,2 0,2 0,05 0,05

3 0,10 0,10 0.05 0,05 0,05 0,05 0,05 0,05

4 0,10 0,15 0 0 0,2 0,2 0,05 0,05

5 1,75 1,90 1,90 1,93 1,55 1,55 1,90 1,68

6 1,93 1,88 1,85 1,85 1,58 1,70 1,65 1,83

7 1,80 2,05 1,83 1,93 1,63 1,53 1,65 1,75

8 1,85 1,98 1,83 1,93 1,65 1,53 1,60 1,85

9 1,40 1,45 1,70 1,80 1,50 1,55 1,15 1,20

10 0,30 0,35 0,15 0,20 0,40 0,30 0,15 0,15

11 1,50 1,50 1,70 1,80 1,45 1,50 1,10 1,4012 1,30 1,65 1,90 1,85 1,40 1,35 1,45 1,25

13 0,10 0,10 0,10 0,10 0,25 0,25 0,15 0,15

14 1,35 1,45 1,80 1,80 1,50 1,60 1,10 1,25

15 1,30 1,65 1,75 1,90 1,50 1,25 1,10 1,20

16 0,35 0,40 0,10 0,10 0,25 0,40 0,10 0,10

17 1,45 1,70 1,65 1,80 1,50 1,45 1,05 1,30

18 1,50 1,50 1,70 1,85 1,60 1,60 1,00 1,30

19 0,20 0,25 0,10 0,15 0,20 0,20 0,10 0,10

20 1,35 1,60 1,80 1,85 1,45 1,40 1,15 1,20

21 0,50 0,45 0,25 0,25 0,50 0,70 0,25 0,30

22 0,55 0,50 0,30 0,30 0,55 0,60 0,30 0,30

23 0,50 0,45 0,25 0,30 0,60 0,60 0,30 0,30

24 0,50 0,45 0,20 0,30 0,55 0,60 0,35 0,30

Sum of the measured distortion 21.93 23.76 22.96 24.39 22.11 22.16 17.8 19.11

Table 4. (Table 7.4) Final distortion in the 24 points of interest

of the 3-dimensional unitary cell specimens, mm.

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• Table 5 depicts the computed distortion at the 24 points of interest for the different weldin

sequences. The table shows that simulations 3 and 4 (with 24 weld beads) produce lower distortio

than the others (with 8 weld beads).

Point Node Simulation

8 weld beads 24 weld beads

1 2 3 4

1 15756 0,08 0,05 0,06 0,04

2 17536 0,11 0,01 0,21 0,05

3 19015 0,08 0,07 0,06 0,04

4 17238 0,11 0,02 0,21 0,05

5 14571 1,85 1,87 1,68 1,65

6 20554 2,0 2,0 1,75 1,85

7 20508 1,82 1,83 1,67 1,64

8 14498 1,99 1,98 1,73 1,80

9 11 1,36 1,70 1,52 1,12

10 386 0,31 0,18 0,35 0,19

11 758 1,54 1,92 1,53 1,13

12 35172 1,49 1,86 1,55 1,11

13 38137 0,08 0,07 0,2 0,19

14 41155 1,57 1,95 1,74 1,24

15 35099 1,51 1,88 1,50 1,08

16 37839 0,39 0,10 0,3 0,08

17 41109 1,33 1,65 1,54 1,13

18 1 1,56 1,94 1,74 1,21

19 361 0,19 0,10 0,16 0,08

20 754 1,47 1,83 1,56 1,01

21 167 0,57 0,25 0,66 0,29

22 36357 0,59 0,34 0,59 0,34

23 591 0,57 0,31 0,6 0,33

24 39616 0,52 0,22 0,68 0,29

Maximum

distortion

2,97 3,05 2,04 2,10

Table 5. (Table 5.2) Distortion at the 24 points of interest corresponding to different welding sequences

In the 3-dimensional unitary cell structure, mm.

• Structures with a greater number of sub-welds are more appropriate to reduce distortion, but als

reduce fatigue performance due to higher residual stresses which may reach the yield point in norm

operating conditions. Therefore, to avoid the loss of stability, laying 8 weld beads seems to be mo

appropriate than 24 sub-welds.

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5) The term “converse welding method” used in pages 140-143 in the context of the welding procedu

description is not explained.

The converse welding method consists of applying the opposite direction between adjacent layers in mul

layer weld, or between beads in every layer [17].

6) What is the relationship between the residual stress state in a structure made of several welded elements

various types and strain in the structural elements?

For symmetrical structures with rigid elements, distortion tends to decrease more than residual stress. Fo

example, for the stiffened symmetrical flat frame, the welding sequence reduces the distortion twice as muc

as residual stress. This relationship would tend to be equaled and with elements even more rigid it would ten

to reverse the relationship among residual stress-distortion. On the other hand, the curves of the ranges of th

values of P and W for the welding sequence 1 I-O, and the combined welding sequence, the intersection poinwould tend to move toward the left as is shown in figure 14.

Figure 14. (Figure 4.7) Ranges of the values of P and W for welding sequence 1 I-O

and combined welding sequence

For symmetrical structures made from several welded element of various types (e.g., welding of I-typ

beams with beams of rectangular cross section), it is not possible to make a preliminary conclusion of th

relationship between residual stress-distortion, however, the proposed numerical model of the weldinprocess in the present investigation can analyze this type of configuration of structures.

7) How is the residual stress state measured in the I-type structure after welding?

In the I-type specimen, the stress relaxation method was used. These techniques are based on the know

fact that the strains that occur during unloading are elastic even when the material has undergone plast

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deformation. The determination of residual stress takes places when the stress is relaxed by cutting th

specimen. Four electrical strain gauges were mounted to measure the strain release as shown in figure 15 (a

Strain gauges 1 and 3 are located in the central zone of the lateral bars, while strain gauges 2 and 4 are locate

in the central zone of the central bar. Figure 15 (b) shows welding parameters employed.

Figure 15. (Figure 3.11) Experimental tests: a) Localization of the points of interest in the I-type specimen


Procedure followed to obtain residual stress on the I-type specimen:

1.- Preparation of the specimen (e.g., machined operations).

2.- Welding application.

3.- Mounting of the electrical strain gauges.

4.- Cutting of the specimen, the cut was performed between the strain gauge 4 and weld bead.5.- Measurement of the strain relaxation with the Wheatstone bridge.

6.- Application of the generalized Hooke´s law to obtain the residual stress state.

Tensile residual stresses were obtained in the central bar, while in the lateral bars compression residu

stresses were obtained. This is due to the balance conditions and geometry [3].

8) What about stability of the welded structure, particularly made from plate elements?

Buckling results from the loss of stability of the elements under compression stress induced in thperipheral areas away from welds. The mechanism of buckling is hidden in the action of the inheren

(incompatible residual plastic) strains formed during welding. Welding-induced buckling differs from bendin

distortion by its much greater out-of-plane deflections and several stable patterns. Buckling patterns depen

much more on the geometry of the elements, and types of weld joint especially depend on the thickness

sheet materials under certain conditions.

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Buckling distortion caused by longitudinal welds in plates (see figure above), in panels or in shells is main

dominated by longitudinal compressive stress produced in areas away from the weld, but the bucklin

distortions caused by circular welds either in plates or in shells are mainly determined by transverse shrinkag

of welds in the radial direction whereby compressive stresses are produced in the tangential direction. Th

buckling pattern depend much more on rigidity (thickness, dimensions and shape) of the elements to bwelded, as well as on the type of weld joint and welding heat inputs.

Figure 16. Buckling distortion

The most important stage in eliminating buckling distortion is rational design of welded structur

elements: plates, panels and shells. Buckling can be controlled by a variety of methods and technologic

measures for removal, mitigation or prevention. In the design state, rational selection of geometry, thickne

of materials and type of weld joint is essential. In the fabrication stage, technological measures and techniqu

to eliminating buckling can be classified as:

1.- Methods applied before welding.

2.- Methods adopted during welding operation.

3.- Methods applied after welding.

In the methods applied before welding, e.g. predeformation, post-weld buckling is compensated b

counterdeformation formed in the elements prior to welding by a specially designed fixture die. In th

methods applied after welding, once buckling is in existence, warpage is removed by special flattenin

processes, using manual hammer, applying a mechanized weld-rolling technique or utilizing an electri

magnetic pulse shock. These methods both before welding and after welding are arranged as speci

operations on a production line and specific installations or fixtures are needed, resulting in increasing co

and variable quality of welded elements.

Pretensioning can be classified in the category of methods applied either before or during welding. Fo

each particular structural design of panels, a device for mechanical tensile loading is required. Owing to the

complexity and reduced efficiency in practical execution, application of these methods is limited. In this sens

the thermal tensioning is more flexible in stiffened panel fabrication.

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APPENDIX 4

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Proper welding sequence to reduce residual stress and distortion in common symmetrical structures in

and 3 dimensions based on the hypothesis developed in the sections 4.9 and 5.2.

Welding of the collinear tubes with 8 weld beads

Collinear tubes Welding Proper welding sequence to reduce

residual stress and/or distortion

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Welding of tubes to 90° with 8 weld beads

Welding of tubes to 90° (Isometric view)

(top view) (top view)

Proper welding sequence to reduce Proper welding sequence to reduceresidual stress distortion

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APPENDIX 5

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Listing of commands of the numerical simulation of the welding process (I-type specimen subject to tension

Transient thermal analysis

/title,transient thermal analysis

/PREP7

k,1,0,0

k,2,0.0015,0k,3,0.003,0

k,4,0.00635,0

k,5,0.0127,0

k,6,0.0254,0

k,7,0.0381,0

k,8,0.0508,0

k,9,0.06985,0

k,10,0.101575,0

k,11,0.1100840,0

k,12,0.1365,0

k,13,0,0.00635

k,14,0.0015,0.00635

k,15,0.003,0.00635

k,16,0.00635,0.00635

k,17,0.0127,0.00635

k,18,0.0254,0.00635k,19,0.0381,0.00635

k,20,0.0508,0.00635

k,21,0.06985,0.00635

k,22,0.101575,0.00635

k,23,0.1100840,0.0115944

k,24,0.1365,0.01159443

k,25,0.1096109,0.0209887

k,26,0.1365,0.0381

k,27,0.101575,0.0254

k,28,0.101575,0.0381

k,29,0.101575,0.0508

k,30,0.1365,0.0508

k,31,0,0.0254

k,32,0,0.0381

k,33,0,0.0508

k,34,0.101575,0.015875

k,35,0.0889,0

k,36,0.0889,0.00635

l,1,2

l,2,3

l,3,4

l,4,5

l,5,6

l,6,7

l,7,8

l,8,9

l,9,35

l,35,10

l,10,11

l,11,12

l,13,14l,14,15

l,15,16

l,16,17

l,17,18

l,18,19

l,19,20

l,20,21

l,21,36

l,36,22

larc,22,23,34,0.009525

l,1,13

l,2,14

l,3,15

l,4,16

l,5,17

l,6,18l,7,19

l,8,20

l,9,21

l,35,36

l,10,22

l,11,23

l,12,24

l,23,24

larc,23,25,34,0.009525

l,24,26

l,25,26

larc,25,27,34,0.009525

l,27,28

l,28,26

l,26,30

l,29,30l,28,29

l,31,27

l,32,28

l,33,29

l,31,32

l,32,33

al,1,25,13,24

al,2,26,14,25

al,3,27,15,26

al,4,28,16,27

al,5,29,17,28

al,6,30,18,29

al,7,31,19,30

al,8,32,20,31

al,9,33,21,32

al,10,34,22,33

al,11,35,23,34

al,12,36,37,35

al,37,39,40,38

al,40,43,42,41

al,43,44,45,46

al,47,42,48,50

al,48,46,49,51

aglue,all

ET,1,PLANE55

ET,2,SOLID70

lesize,1,,,4

lesize,2,,,4

lesize,3,,,4

lesize,4,,,4

lesize,5,,,4lesize,6,,,4

lesize,7,,,4

lesize,8,,,4

lesize,9,,,4

lesize,10,,,4

lesize,38,,,4

lesize,41,,,4

lesize,47,,,10

lesize,12,,,4

lesize,51,,,4

lesize,24,,,4

MSHAPE,0,2D

MSHKEY,1

amesh,all

TYPE,2

EXTOPT,ESIZE,3,0,EXTOPT,ACLEAR,1

EXTOPT,ATTR,0,0,0

VEXT,all,, ,0,0,-0.003175,,,,

TYPE,2

EXTOPT,ESIZE,2,0,

EXTOPT,ACLEAR,1

EXTOPT,ATTR,0,0,0

VEXT,83,,,0,0,0.0047625,,,,

VEXT,79,,,0,0,0.0047625,,,,

VEXT,75,,,0,0,0.0047625,,,,

VEXT,71,,,0,0,0.0047625,,,,

VEXT,67,,,0,0,0.0047625,,,,

VEXT,63,,,0,0,0.0047625,,,,

VEXT,17,,,0,0,0.0047625,,,,

VEXT,16,,,0,0,0.0047625,,,,

VEXT,15,,,0,0,0.0047625,,,,VEXT,14,,,0,0,0.0047625,,,,

VEXT,13,,,0,0,0.0047625,,,,

VEXT,12,,,0,0,0.0047625,,,,

nummrg,all

eplot

/VIEW,1,1,1,1

/ANG,1

/REP,FAST

TOFFST,273

MPTEMP,,,,,,,,

MPTEMP,1,20

MPTEMP,2,90

MPTEMP,3,200

MPTEMP,4,314

MPTEMP,5,423.5

MPTEMP,6,533

MPTEMP,7,643

MPTEMP,8,753

MPTEMP,9,863

MPTEMP,10,972.5

MPTEMP,11,1090

MPTEMP,12,1216

MPTEMP,13,1321.5

MPTEMP,14,1423.5

MPTEMP,15,1500

MPDATA,KXX,1,,51.82

MPDATA,KXX,1,,50.73

MPDATA,KXX,1,,48.78

MPDATA,KXX,1,,45.73

MPDATA,KXX,1,,42.07

MPDATA,KXX,1,,37.80MPDATA,KXX,1,,33.53

MPDATA,KXX,1,,28.04

MPDATA,KXX,1,,25

MPDATA,KXX,1,,26.82

MPDATA,KXX,1,,28.04

MPDATA,KXX,1,,29.87

MPDATA,KXX,1,,31.09

MPDATA,KXX,1,,40.24

MPDATA,KXX,1,,40.85

MPTEMP,,,,,,,,

MPTEMP,1,20

MPTEMP,2,90

MPTEMP,3,200

MPTEMP,4,314

MPTEMP,5,423.5

MPTEMP,6,533MPTEMP,7,643

MPTEMP,8,753

MPTEMP,9,863

MPTEMP,10,972.5

MPTEMP,11,1090

MPTEMP,12,1216

MPTEMP,13,1321.5

MPTEMP,14,1423.5

MPTEMP,15,1500

MPDATA,C,1,,451.21

MPDATA,C,1,,487.8

MPDATA,C,1,,518.29

MPDATA,C,1,,560.97

MPDATA,C,1,,628.04

MPDATA,C,1,,713.41

MPDATA,C,1,,829.26MPDATA,C,1,,920.73

MPDATA,C,1,,1051.21

MPDATA,C,1,,1158.53

MPDATA,C,1,,1262.19

MPDATA,C,1,,1384.14

MPDATA,C,1,,1500

MPDATA,C,1,,1603.6

MPDATA,C,1,,1670

MP,DENS,1,7850

SFA,116,1,CONV,10,20

*DIM,timevstemp,TABLE,9,1,1,time,tem

*SET,TIMEVSTEMP(0,1,1) , 20





*SET,TIMEVSTEMP(3,0,1) ,3














SAVEFINISH

/SOL

ANTYPE,4

TRNOPT,FULL

LUMPM,0

NSUBST,990,990,990

OUTRES,ERASE

OUTRES,ALL,1

LNSRCH,1

TIME,990

DA,22,TEMP, %TIMEVSTEMP%

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IC,all,TEMP,20,

/STATUS,SOLU

SOLVE

Thermal elastic plastic analysis

/title,thermal elastic plastic analysis/PREP7

%Commands of the geometric model and

mesh equal to transient thermal

analysis% TOFFST,273

MPTEMP,,,,,,,,

MPTEMP,1,20

MPTEMP,2,90

MPTEMP,3,200

MPTEMP,4,314

MPTEMP,5,423.5

MPTEMP,6,533

MPTEMP,7,643

MPTEMP,8,753

MPTEMP,9,863

MPTEMP,10,972.5MPTEMP,11,1090

MPTEMP,12,1216

MPTEMP,13,1321.5

MPTEMP,14,1423.5

MPTEMP,15,1500

MPDATA,EX,1,,207e9

MPDATA,EX,1,,198e9

MPDATA,EX,1,,198e9

MPDATA,EX,1,,186e9

MPDATA,EX,1,,168e9

MPDATA,EX,1,,118e9

MPDATA,EX,1,,54e9

MPDATA,EX,1,,6e9

MPDATA,EX,1,,6e9

MPDATA,EX,1,,6e9

MPDATA,EX,1,,6e9

MPDATA,EX,1,,6e9

MPDATA,EX,1,,6e9

MPDATA,EX,1,,6e9

MPDATA,EX,1,,6e9

MPDATA,PRXY,1,,0.3

MPDATA,PRXY,1,,0.308









MPDATA,PRXY,1,,0.423MPDATA,PRXY,1,,0.447




TB,BISO,1,6,2,

TBTEMP,20

TBDATA,,250e6,11.032e9,,,,

TBTEMP,90

TBDATA,,238.8e6,10.894e9,,,,

TBTEMP,423.5

TBDATA,,172.56e6,9.584e9,,,,

TBTEMP,643

TBDATA,,74.39e6,5.171e9,,,,

TBTEMP,753

TBDATA,,18.29e6,1.862e9,,,,

TBTEMP,1500

TBDATA,,9.75e6,0.069e9,,,,

MPTEMP,,,,,,,,

MPTEMP,1,20MPTEMP,2,90

MPTEMP,3,200

MPTEMP,4,314

MPTEMP,5,423.5

MPTEMP,6,533

MPTEMP,7,643

MPTEMP,8,753

MPTEMP,9,863

MPTEMP,10,972.5

MPTEMP,11,1090

MPTEMP,12,1216

MPTEMP,13,1321.5

MPTEMP,14,1423.5

MPTEMP,15,1500

UIMP,1,REFT,,,20

MPDATA,ALPX,1,,11.7e-6MPDATA,ALPX,1,,11.7e-6

MPDATA,ALPX,1,,12.3e-6

MPDATA,ALPX,1,,13e-6












MP,DENS,1,7850

/VIEW,1,1,1,1

/ANG,1

/REP,FAST

DA,82,SYMM

DA,85,SYMM

DA,90,SYMM

DA,95,SYMM

DA,120,SYMM

DA,125,SYMM

DA,22,SYMM

DA,19,SYMM

DA,24,SYMM

DA,28,SYMM

DA,32,SYMM

DA,36,SYMM

DA,40,SYMMDA,44,SYMM

DA,48,SYMM

DA,52,SYMM

DA,56,SYMM

DA,60,SYMM

DA,142,SYMM

DA,64,SYMM

DA,112,SYMM

TREF,20,

FINISH

/SOL

LDREAD,TEMP,,,1, , 'transient thermal

analysis ','rth',' '

LSWRITE,1,

BFDELE,all,TEMP

LDREAD,TEMP,,,3, , 'transient thermal


LSWRITE,2,

BFDELE,all,TEMPLDREAD,TEMP,,,10,, 'transient thermal


LSWRITE,3,

BFDELE,all,TEMP

LDREAD,TEMP,,,20,, 'transient thermal


LSWRITE,4,

BFDELE,all,TEMP



LSWRITE,5,

BFDELE,all,TEMP



LSWRITE,6,

BFDELE,all,TEMPLDREAD,TEMP,,,75,, 'transient thermal


LSWRITE,7,

BFDELE,all,TEMP

LDREAD,TEMP,,,100,,'transient thermal


LSWRITE,8,

BFDELE,all,TEMP



LSWRITE,9,

BFDELE,all,TEMP



LSWRITE,10,

BFDELE,all,TEMP



LSWRITE,11,

BFDELE,all,TEMP



LSWRITE,12,

BFDELE,all,TEMP



LSWRITE,13,

BFDELE,all,TEMP



LSWRITE,14,LSSOLVE,1,14,1,

FINISH

/SOLU

8/22/2019 Full 10088



19


APPENDIX 6

8/22/2019 Full 10088



19


Listing of commands of the numerical simulation of the welding sequence in an L-type structure (weldin

sequence 1)


/title,transient thermal analysis WS1

/PREP7

k,1,0,0k,2,0.1,0

k,3,0.227,0

k,4,0.23,0

k,5,0.25,0

k,6,0.2627,0

k,7,0.2827,0

k,8,0.2857,0

k,9,0.32,0

k,10,0.23,0.097

k,11,0.25,0.097

k,12,0.2627,0.097

k,13,0.2827,0.097

k,14,0,0.1

k,15,0.1,0.1

k,16,0.227,0.1

k,17,0.25,0.1

k,18,0.2627,0.1

k,19,0.2857,0.1

k,20,0.32,0.1

k,21,0.25,0.103

k,22,0.2627,0.103

k,23,0,0.227

k,24,0.1,0.227

k,25,0,0.23

k,26,0.097,0.23

k,27,0.25,0.24575736

k,28,0,0.25

k,29,0.097,0.25

k,30,0.1,0.25

k,31,0.103,0.25

k,32,0.24575736,0.25k,33,0.25,0.25

k,34,0,0.2627

k,35,0.097,0.2627

k,36,0.1,0.2627

k,37,0.103,0.2627

k,38,0.25845736,0.2627

k,39,0.2627,0.2627

k,40,0,0.2827

k,41,0.097,0.2827

k,42,0,0.2857

k,43,0.1,0.2857

k,44,0,0.32

k,45,0.1,0.32

k,46,0.2627,0.25845736

l,1,2

l,2,3

l,3,4

l,4,5

l,5,6

l,6,7

l,7,8

l,8,9

l,1,14

l,2,15

l,3,16

l,4,10

l,5,11

l,6,12

l,7,13l,8,19

l,9,20

l,16,10

l,10,11

l,11,12

l,12,13

l,13,19

l,14,15

l,15,16

l,16,17

l,17,18

l,18,19

l,19,20

l,14,23

l,15,24

l,17,21

l,18,22

l,21,22

l,21,27

l,22,46

l,23,24

l,23,25

l,24,26

l,25,26

l,25,28

l,26,29

l,24,30

l,27,33

l,27,46

l,28,29

l,29,30l,30,31

l,31,32

l,32,33

l,33,39

l,46,39

l,28,34

l,29,35

l,30,36

l,31,37

l,32,38

l,34,35

l,35,36

l,36,37

l,37,38

l,38,39

l,34,40

l,35,41

l,36,43

l,40,41

l,40,42

l,41,43

l,42,43

l,42,44

l,43,45

l,44,45

l,11,17

l,12,18

lplot

al,1,10,23,9al,2,11,24,10

al,3,12,18,11

al,4,13,19,12

al,5,14,20,13

al,6,15,21,14

al,7,16,22,15

al,8,17,28,16

al,19,72,25,18

al,20,73,26,72

al,21,22,27,73

al,23,30,36,29

al,26,32,33,31

al,33,35,44,34

al,36,38,39,37

al,39,41,45,40

al,44,51,50,43

al,45,53,57,52

al,46,54,58,53

al,47,55,59,54

al,48,56,60,55

al,49,50,61,56

al,57,63,65,62

al,58,64,67,63

al,65,67,68,66

al,68,70,71,69

al,38,42,46,41

aglue,all

ET,1,PLANE55

ET,2,SOLID70

lesize,5,,,6


lesize,72,,,3

lesize,73,,,3

lesize,31,,,3

lesize,32,,,3

lesize,43,,,3

lesize,51,,,3

lesize,49,,,3

lesize,61,,,3

lesize,46,,,3

lesize,58,,,3

lesize,47,,,3

lesize,59,,,3

lesize,25,,,6

lesize,4,,,6

lesize,27,,,6

lesize,6,,,6

lesize,42,,,6

lesize,40,,,6

lesize,62,,,6

lesize,64,,,6

lesize,66,,,3

lesize,37,,,3

lesize,3,,,3

lesize,7,,,3

lesize,9,,,20

lesize,17,,,20

lesize,1,,,20


lesize,8,,,3

lesize,70,,,3

lesize,69,,,3

lesize,2,,,10

lesize,24,,,10

lesize,29,,,10

lesize,30,,,10

lesize,2,,,10

lesize,24,,,10

lesize,29,,,10

lesize,30,,,10

lesize,34,,,30

lesize,35,,,30

lesize,48,,,30

lesize,60,,,30

MSHAPE,0,2D

MSHKEY,1

amesh,all

nummrg,all

%Thermal properties dependent on

temperature used in numerical weld

process of the I-type specimen to

tension%

TYPE,2

EXTOPT,ESIZE,2,0,

EXTOPT,ACLEAR,1

EXTOPT,ATTR,0,0,0

MAT,1

VEXT,1, , ,0,0,-0.003175,,,,

VEXT,2, , ,0,0,-0.003175,,,,VEXT,3, , ,0,0,-0.003175,,,,

VEXT,4, , ,0,0,-0.003175,,,,

VEXT,5, , ,0,0,-0.003175,,,,

VEXT,6, , ,0,0,-0.003175,,,,

VEXT,7, , ,0,0,-0.003175,,,,

VEXT,8, , ,0,0,-0.003175,,,,

VEXT,9, , ,0,0,-0.003175,,,,

VEXT,11, , ,0,0,-0.003175,,,,

VEXT,12, , ,0,0,-0.003175,,,,

VEXT,14, , ,0,0,-0.003175,,,,

VEXT,15, , ,0,0,-0.003175,,,,

VEXT,16, , ,0,0,-0.003175,,,,

VEXT,27, , ,0,0,-0.003175,,,,

VEXT,18, , ,0,0,-0.003175,,,,

VEXT,21, , ,0,0,-0.003175,,,,

VEXT,23, , ,0,0,-0.003175,,,,

VEXT,24, , ,0,0,-0.003175,,,,

VEXT,25, , ,0,0,-0.003175,,,,

VEXT,26, , ,0,0,-0.003175,,,,

VEXT,10, , ,0,0,-0.003175,,,,

VEXT,13, , ,0,0,-0.003175,,,,

VEXT,17, , ,0,0,-0.003175,,,,

VEXT,22, , ,0,0,-0.003175,,,,

VEXT,19, , ,0,0,-0.003175,,,,

VEXT,20, , ,0,0,-0.003175,,,,

8/22/2019 Full 10088



19


eplot

SFA,1,1,CONV,10,20

SFA,2,1,CONV,10,20

SFA,3,1,CONV,10,20

SFA,4,1,CONV,10,20

SFA,5,1,CONV,10,20

SFA,6,1,CONV,10,20

SFA,7,1,CONV,10,20SFA,8,1,CONV,10,20

SFA,9,1,CONV,10,20

SFA,11,1,CONV,10,20

SFA,12,1,CONV,10,20

SFA,14,1,CONV,10,20

SFA,15,1,CONV,10,20

SFA,16,1,CONV,10,20

SFA,27,1,CONV,10,20

SFA,18,1,CONV,10,20

SFA,21,1,CONV,10,20

SFA,23,1,CONV,10,20

SFA,25,1,CONV,10,20

SFA,24,1,CONV,10,20

SFA,26,1,CONV,10,20

SFA,83,1,CONV,10,20

SFA,108,1,CONV,10,20SFA,128,1,CONV,10,20

SFA,123,1,CONV,10,20

SFA,118,1,CONV,10,20

SFA,113,1,CONV,10,20

SFA,103,1,CONV,10,20

SFA,98,1,CONV,10,20

SFA,93,1,CONV,10,20

SFA,88,1,CONV,10,20

SFA,78,1,CONV,10,20

SFA,28,1,CONV,10,20

SFA,33,1,CONV,10,20

SFA,38,1,CONV,10,20

SFA,43,1,CONV,10,20

SFA,48,1,CONV,10,20

SFA,53,1,CONV,10,20

SFA,58,1,CONV,10,20

SFA,63,1,CONV,10,20

SFA,68,1,CONV,10,20

SFA,73,1,CONV,10,20

*DIM,TIMEVSTEMP01,TABLE,9,1,1,TIM

E,TEMP,

*SET,TIMEVSTEMP01(0,1,1) , 20
















*SET,TIMEVSTEMP01(8,1,1) , 20*SET,TIMEVSTEMP01(9,0,1) , 930



E,TEMP,




















E,TEMP,




















FINISH

/SOL

ANTYPE,4

TRNOPT,FULL

LUMPM,0

NSUBST,990,990,990

OUTRES,ERASE

OUTRES,ALL,1

LNSRCH,1

TIME,990DA,51,TEMP, %TIMEVSTEMP01%

DA,136,TEMP, %TIMEVSTEMP01%








IC,all,TEMP,20,

/STATUS,SOLU

SOLVE


/title,thermal elastic plastic WS1

/PREP7

%Commands of the geometric modeland mesh equal to transient thermal

analysis% %Mechanical properties dependent on

temperature used in numerical welding


tension%

FINISH

/SOL

D,1,all,0

D,3,all,0

D,62,all,0

D,2595,all,0

D,2656,all,0

D,2597,all,0

D,3036,all,0

D,3040,all,0

D,3059,all,0

TREF,20,

%Application of the load thermal from

transient thermal analysis, 15 load step

are required%

LDREAD,TEMP,,,2, ,'analisis transiente

termico S1','rth',' '

LSWRITE,1,

BFDELE,all,TEMP

LSSOLVE,1,15,1,

FINISH

8/22/2019 Full 10088



19


APPENDIX 7

8/22/2019 Full 10088



19


Listing of the commands of the numerical simulation of the stiffened symmetrical flat frame (weldin

sequence 5 O-I WT)



S5 O-I WT

/PREP7k,1,0,0

k,2,0.004243,0

k,3,0.053175,0

k,4,0.08365,0

k,5,0.08865,0

k,6,0.09365,0

k,7,0.10635,0

k,8,0.11135,0

k,9,0.11635,0

k,10,0.146825,0

k,11,0.195757,0

k,12,0.2,0

k,13,0.08865,0.0097

k,14,0.09365,0.0097

k,15,0.10635,0.0097

k,16,0.11135,0.0097k,17,0.0127,0.0127

k,18,0.016943,0.0127

k,19,0.053175,0.0127

k,20,0.08365,0.0127

k,21,0.09365,0.0127

k,22,0.10635,0.0127

k,23,0.11635,0.0127

k,24,0.146825,0.0127

k,25,0.183057,0.0127

k,26,0.1873,0.0127

k,27,0.0127,0.016943

k,28,0.09365,0.0157

k,29,0.10635,0.0157

k,30,0.1873,0.016943

k,31,0,0.053175

k,32,0.0127,0.053175

k,33,0.09365,0.053175

k,34,0.10635,0.053175

k,35,0.1873,0.053175

k,36,0.2,0.053175

k,37,0,0.08365

k,38,0.0127,0.08365

k,39,0.1873,0.08365

k,40,0.20,0.08365

k,41,0,0.08865

k,42,0.0097,0.08865

k,43,0.1903,0.08865

k,44,0.2,0.08865

k,45,0.09365,0.09065

k,46,0.10635,0.09065

k,47,0,0.09365k,48,0.0097,0.09365

k,49,0.0127,0.09365

k,50,0.0157,0.09365

k,51,0.0227,0.09365

k,52,0.0537175,0.09365

k,53,0.08365,0.09365

k,54,0.09365,0.09365

k,55,0.10635,0.09365

k,56,0.11635,0.09365

k,57,0.146825,0.09365

k,58,0.1773,0.09365

k,59,0.1843,0.09365

k,60,0.1873,0.09365

k,61,0.1903,0.09365k,62,0.2,0.09365

k,63,0.08865,0.09665

k,64,0.09365,0.09665

k,65,0.10635,0.09665

k,66,0.11135,0.09665

k,67,0.08865,0.10335

k,68,0.09365,0.10335

k,69,0.10635,0.10335

k,70,0.11135,0.10335

k,71,0,0.10635

k,72,0.0097,0.10635

k,73,0.0127,0.10635

k,74,0.0157,0.10635

k,75,0.0227,0.10635

k,76,0.0537175,0.10635

k,77,0.08365,0.10635k,78,0.09365,0.10635

k,79,0.10635,0.10635

k,80,0.11635,0.10635

k,81,0.146825,0.10635

k,82,0.1773,0.10635

k,83,0.1843,0.10635

k,84,0.1873,0.10635

k,85,0.1903,0.10635

k,86,0.2,0.10635

k,87,0.09365,0.10935

k,88,0.10635,0.10935

k,89,0,0.11135

k,90,0.0097,0.11135

k,91,0.1903,0.11135

k,92,0.2,0.11135

k,93,0,0.11635

k,94,0.0127,0.11635

k,95,0.1873,0.11635

k,96,0.2,0.11635

k,97,0,0.146825

k,98,0.0127,0.146825

k,99,0.09365,0.146825

k,100,0.10635,0.146825

k,101,0.1873,0.146825

k,102,0.2,0.146825

k,103,0.0127,0.183057

k,104,0.1873,0.183057

k,105,0.09365,0.1843

k,106,0.10635,0.1843

k,107,0.0127,0.1873

k,108,0.016943,0.1873k,109,0.053175,0.1873

k,110,0.08365,0.1873

k,111,0.09365,0.1873

k,112,0.10635,0.1873

k,113,0.11635,0.1873

k,114,0.146825,0.1873

k,115,0.183057,0.1873

k,116,0.1873,0.1873

k,117,0.08865,0.1903

k,118,0.09365,0.1903

k,119,0.10635,0.1903

k,120,0.11135,0.1903

k,121,0,0.2

k,122,0.004243,0.2k,123,0.053175,0.2

k,124,0.08365,0.2

k,125,0.08865,0.2

k,126,0.09365,0.2

k,127,0.10635,0.2

k,128,0.11135,0.2

k,129,0.11635,0.2

k,130,0.146825,0.2

k,131,0.195757,0.2

k,132,0.2,0.2

k,133,0,0.004243

k,134,0.2,0.004243

k,135,0,0.195757

k,136,0.2,0.195757

l,1,2

l,2,3l,3,4

l,4,5

l,5,6

l,6,7

l,7,8

l,8,9

l,9,10

l,10,11

l,11,12

l,1,133

l,1,17

l,2,18

l,3,19

l,4,20

l,5,13

l,6,14

l,7,15

l,8,16

l,9,23

l,10,24

l,11,25

l,12,26

l,12,134

l,133,27

l,134,30

l,13,20

l,13,14

l,14,15

l,15,16

l,16,23

l,17,18l,18,19

l,19,20

l,20,21

l,21,22

l,22,23

l,23,24

l,24,25

l,25,26

l,17,27

l,21,28

l,22,29

l,26,30

l,133,31

l,27,32l,28,33

l,29,34

l,30,35

l,134,36

l,31,32

l,33,34

l,35,36

l,31,37

l,32,38

l,33,45

l,34,46

l,35,39

l,36,40

l,37,38

l,45,46

l,39,40l,37,41

l,38,42

l,38,49

l,39,60

l,39,43

l,40,44

l,41,47

l,41,42

l,42,48

l,45,54

l,46,55

l,43,61

l,43,44

l,44,62

l,47,48

l,48,49

l,49,50

l,50,51

l,51,52

l,52,53

l,53,54

l,54,55

l,55,56

l,56,57

l,57,58

l,58,59

l,59,60

l,60,61

l,61,62

l,47,71

l,48,72l,49,73

l,50,74

l,51,75

l,52,76

l,53,77

l,63,67

l,64,68

l,65,69

l,66,70

l,56,80

8/22/2019 Full 10088



19


l,57,81

l,58,82

l,59,83

l,60,84

l,61,85

l,62,86

l,63,64

l,64,65l,65,66

l,53,63

l,56,66

l,67,77

l,67,68

l,68,78

l,68,69

l,69,79

l,69,70

l,70,80

l,54,64

l,55,65

l,71,72

l,72,73

l,73,74

l,74,75l,75,76

l,76,77

l,77,78

l,78,79

l,79,80

l,80,81

l,81,82

l,82,83

l,83,84

l,84,85

l,85,86

l,71,89

l,72,90

l,73,94

l,78,87

l,79,88

l,84,95

l,85,91

l,86,92

l,89,93

l,89,90

l,90,94

l,91,95

l,91,92

l,92,96

l,93,94

l,87,88

l,95,96

l,93,97

l,94,98

l,87,99l,88,100

l,95,101

l,96,102

l,97,98

l,99,100

l,101,102

l,97,135

l,98,103

l,99,105

l,100,106

l,101,104

l,102,136

l,135,103

l,103,107

l,107,108

l,108,109

l,109,110

l,110,111l,105,111

l,105,106

l,106,112

l,112,113

l,113,114

l,114,115

l,115,116

l,116,104

l,104,136

l,135,121

l,121,107

l,122,108

l,109,123

l,110,124

l,117,125

l,110,117l,117,118

l,118,111

l,111,112

l,112,119

l,118,119

l,118,126

l,119,127

l,120,128

l,119,120

l,120,113

l,113,129

l,114,130

l,115,131

l,116,132

l,132,136

l,121,122

l,122,123

l,123,124

l,124,125

l,125,126

l,126,127

l,127,128

l,128,129

l,129,130

l,130,131

l,131,132

l,14,21

l,15,22

l,28,29

lplot

al,1,14,33,13al,2,15,34,14

al,3,16,35,15

al,4,17,28,16

al,5,18,29,17

al,29,220,36,28

al,6,19,30,18

al,30,221,37,220

al,7,20,31,19

al,8,21,32,20

al,31,32,38,221

al,9,22,39,21

al,10,23,40,22

al,11,24,41,23

al,24,25,27,45

al,27,51,54,50

al,54,60,63,59

al,63,69,76,68

al,76,77,92,75al,68,75,91,67

al,92,110,139,109

al,91,109,138,108

al,139,147,152,146

al,152,153,156,151

al,138,146,151,145

al,156,162,165,161

al,165,171,186,170

al,186,208,207,185

al,207,219,206,184

al,183,206,218,205

al,182,205,217,204

al,181,203,202,197

al,203,204,216,201

al,202,201,215,200

al,198,200,214,199al,196,197,198,195

al,177,195,194,193

al,194,199,213,192

al,193,192,212,191

al,176,191,211,190

al,175,190,210,189

al,174,189,209,188

al,172,173,188,187

al,163,167,172,166

al,154,158,163,157

al,149,150,154,148

al,125,141,149,140

al,126,142,150,141

al,78,94,125,93

al,79,95,126,94

al,71,72,78,70

al,61,65,71,64

al,65,66,79,72

al,52,56,61,55

al,26,47,52,46

al,13,42,26,12

al,80,96,127,95

al,81,97,128,96

al,82,98,129,97

al,83,99,130,98

al,84,123,111,114

al,114,100,116,99

al,111,101,117,100

al,117,118,131,116

al,85,124,112,123

al,112,102,119,101al,119,120,132,118

al,86,115,113,124

al,113,103,121,102

al,121,122,133,120

al,115,104,122,103

al,87,105,134,104

al,88,106,135,105

al,89,107,136,106

al,90,108,137,107

al,132,144,155,143

al,155,160,164,159

al,164,169,179,168

al,179,180,196,178

al,62,74,85,73

al,53,58,62,57

al,222,49,53,48

al,37,44,222,43

aglue,all%Thermal properties %

ET,1,PLANE55

/REPLOT,RESIZE

TYPE, 1

MAT, 1

REAL,

ESYS, 0

SECNUM,

FLST,5,116,4,ORDE,59

FITEM,5,2

FITEM,5,-3

FITEM,5,6

FITEM,5,9

FITEM,5,-10

FITEM,5,14

FITEM,5,-23FITEM,5,26

FITEM,5,-27

FITEM,5,30

FITEM,5,34

FITEM,5,-35

FITEM,5,39

FITEM,5,-40

FITEM,5,46

FITEM,5,-63

FITEM,5,71

FITEM,5,76

FITEM,5,78

FITEM,5,82

FITEM,5,-83

FITEM,5,87

FITEM,5,-88

FITEM,5,92

FITEM,5,-94

FITEM,5,96

FITEM,5,-107

FITEM,5,109

FITEM,5,-110

FITEM,5,112

FITEM,5,119

FITEM,5,125

FITEM,5,129

FITEM,5,-130

FITEM,5,134

FITEM,5,-135

FITEM,5,139

FITEM,5,149FITEM,5,152

FITEM,5,154

FITEM,5,-172

FITEM,5,175

FITEM,5,-176

FITEM,5,179

FITEM,5,182

FITEM,5,-183

FITEM,5,186

FITEM,5,189

8/22/2019 Full 10088



20


FITEM,5,-192

FITEM,5,198

FITEM,5,-201

FITEM,5,204

FITEM,5,-206

FITEM,5,210

FITEM,5,-211

FITEM,5,214FITEM,5,217

FITEM,5,-218

FITEM,5,222

CM,_Y,LINE

LSEL, , , ,P51X

CM,_Y1,LINE

CMSEL,,_Y

LESIZE,_Y1, , ,4, , , , ,1

CLRMSHLN

FLST,5,32,4,ORDE,30

FITEM,5,4

FITEM,5,8

FITEM,5,28

FITEM,5,32

FITEM,5,64


FITEM,5,-69

FITEM,5,79

FITEM,5,91

FITEM,5,114

FITEM,5,-116

FITEM,5,118

FITEM,5,120

FITEM,5,122

FITEM,5,-124

FITEM,5,126

FITEM,5,138

FITEM,5,148

FITEM,5,150

FITEM,5,-151

FITEM,5,153

FITEM,5,193

FITEM,5,195

FITEM,5,197

FITEM,5,203

FITEM,5,212

FITEM,5,216

FITEM,5,220

FITEM,5,-221

CM,_Y,LINE

LSEL, , , ,P51X

CM,_Y1,LINE

CMSEL,,_Y

LESIZE,_Y1, , ,2, , , , ,1

CLRMSHLN

TYPE, 1MAT, 1

REAL,

ESYS, 0

SECNUM,

MSHAPE,0,2D

MSHKEY,1

FLST,5,63,5,ORDE,25

FITEM,5,2

FITEM,5,-7

FITEM,5,9

FITEM,5,-13

FITEM,5,16

FITEM,5,-21

FITEM,5,23

FITEM,5,-27

FITEM,5,30

FITEM,5,-35

FITEM,5,37FITEM,5,-41

FITEM,5,44

FITEM,5,-49

FITEM,5,51

FITEM,5,-55

FITEM,5,58

FITEM,5,-64

FITEM,5,66

FITEM,5,68

FITEM,5,-74

FITEM,5,77

FITEM,5,-78

FITEM,5,81

FITEM,5,-82

CM,_Y,AREA

ASEL, , , ,P51XCM,_Y1,AREA

CHKMSH,'AREA'

CMSEL,S,_Y

AMESH,_Y1

CMDELE,_Y

CMDELE,_Y1

CMDELE,_Y2

TYPE, 1

MAT, 2

REAL,

ESYS, 0

SECNUM,

FLST,5,4,4,ORDE,4

FITEM,5,13

FITEM,5,24

FITEM,5,188

FITEM,5,207

CM,_Y,LINE

LSEL, , , ,P51X

CM,_Y1,LINE

CMSEL,,_Y

LESIZE,_Y1, , ,4, , , , ,1

CLRMSHLN

FLST,5,28,4,ORDE,25

FITEM,5,1

FITEM,5,11

FITEM,5,-12

FITEM,5,25

FITEM,5,33

FITEM,5,41


FITEM,5,-74

FITEM,5,80

FITEM,5,90

FITEM,5,127

FITEM,5,137

FITEM,5,143

FITEM,5,-144

FITEM,5,173

FITEM,5,-174

FITEM,5,178

FITEM,5,180

FITEM,5,184

FITEM,5,-185

FITEM,5,187

FITEM,5,208

FITEM,5,-209

FITEM,5,219CM,_Y,LINE

LSEL, , , ,P51X

CM,_Y1,LINE

CMSEL,,_Y

LESIZE,_Y1, , ,2, , , , ,1

CLRMSHLN

TYPE, 1

MAT, 2

REAL,

ESYS, 0

SECNUM,

FLST,5,20,5,ORDE,20

FITEM,5,1

FITEM,5,8

FITEM,5,14


FITEM,5,28

FITEM,5,-29

FITEM,5,36

FITEM,5,42

FITEM,5,-43

FITEM,5,50

FITEM,5,56

FITEM,5,-57

FITEM,5,65

FITEM,5,67

FITEM,5,75

FITEM,5,-76

FITEM,5,79

FITEM,5,-80

FITEM,5,83

CM,_Y,AREA

ASEL, , , ,P51X

CM,_Y1,AREA

CHKMSH,'AREA'

CMSEL,S,_Y

AMESH,_Y1

CMDELE,_Y

CMDELE,_Y1

CMDELE,_Y2

/DIST,1,0.924021086472,1

/REP,FAST

eplot

SAVE

/PNUM,KP,0

/PNUM,LINE,0/PNUM,AREA,0

/PNUM,VOLU,0

/PNUM,NODE,0

/PNUM,TABN,0

/PNUM,SVAL,0

/NUMBER,1

/PNUM,MAT,1

/REPLOT

/UI,MESH,OFF

SFA,2,1,CONV,10,20

% Weld bead thermal cycle, from w

bead No. 1 to weld bead No.10

written%


E,TEMP,


















*SET,TIMEVSTEMP01(9,1,1) , 20FINISH

/SOL

ANTYPE,4

TRNOPT,FULL

LUMPM,0

NSUBST,990,990,990

OUTRES,ERASE

OUTRES,ALL,1

LNSRCH,1

TIME,990

%Application of the weld bead therm

cycle to all areas corresponding to

each weld bead, from weld bead No.

to weld bead No.10 %

DA,29,TEMP,%TIMEVSTEMP01%



IC,all,TEMP,20,

/STATUS,SOLU

SOLVE


/title,thermal elastic plastic S5 OI WT

/PREP7

%Commands of the geometric mode

and mesh equal to transient thermal

analysis% %Mechanical properties dependent o

temperature used in numerical weld


tension%

D,778,all,0D,784,all,0

TREF,20,

%Application of the load thermal from

transient thermal analysis, 33 load st

are required%

LDREAD,TEMP,,,2, ,'analisis transient

termico S5','rth',' '

LSWRITE,1,

LSSOLVE,1,33,1,

FINISH

8/22/2019 Full 10088



20


APPENDIX 8

8/22/2019 Full 10088



20


Listing of the commands of the numerical simulation of the 3-dimensional unitary cell (proper weldin

sequence to reduce distortion with 24 weld beads and welding tacks)



/PREP7

k,1,0,0k,2,0.003,0

k,3,0.203,0

k,4,0.206,0

k,5,0,0.014

k,6,0.003,0.014

k,7,0.203,0.014

k,8,0.206,0.014

k,9,0,0.034

k,10,0.003,0.034

k,11,0.203,0.034

k,12,0.206,0.034

k,13,0,0.044

k,14,0.003,0.044

k,15,0.203,0.044

k,16,0.206,0.044

k,17,0.0045,0.0455

k,18,0.2015,0.0455

k,19,0,0.046

k,20,0.003,0.046

k,21,0.004,0.046

k,22,0.202,0.046

k,23,0.203,0.046

k,24,0.206,0.046

k,25,0,0.047

k,26,0.003,0.047

k,27,0.004,0.047

k,28,0.006,0.047

k,29,0.016,0.047

k,30,0.036,0.047

k,31,0.17,0.047

k,32,0.19,0.047k,33,0.2,0.047

k,34,0.202,0.047

k,35,0.203,0.047

k,36,0.206,0.047

k,37,0,0.05

k,38,0.003,0.05

k,39,0.004,0.05

k,40,0.006,0.05

k,41,0.016,0.05

k,42,0.036,0.05

k,43,0.17,0.05

k,44,0.19,0.05

k,45,0.2,0.05

k,46,0.202,0.05

k,47,0.203,0.05

k,48,0.206,0.05

k,49,0,0.051

k,50,0.003,0.051

k,51,0.004,0.051

k,52,0.202,0.051

k,53,0.203,0.051

k,54,0.206,0.051

k,55,0.0045,0.0515

k,56,0.2015,0.0515

k,57,0,0.053

k,58,0.003,0.053

k,59,0.203,0.053

k,60,0.206,0.053

k,61,0,0.063k,62,0.003,0.063

k,63,0.203,0.063

k,64,0.206,0.063

k,65,0,0.083

k,66,0.003,0.083

k,67,0.203,0.083

k,68,0.206,0.083

k,69,0,0.167

k,70,0.003,0.167

k,71,0.203,0.167

k,72,0.206,0.167

k,73,0,0.187

k,74,0.003,0.187

k,75,0.203,0.187

k,76,0.206,0.187

k,77,0,0.197

k,78,0.003,0.197

k,79,0.203,0.197

k,80,0.206,0.197

k,81,0.0045,0.1985

k,82,0.2015,0.1985

k,83,0,0.199

k,84,0.003,0.199

k,85,0.004,0.199

k,86,0.202,0.199

k,87,0.203,0.199

k,88,0.206,0.199

k,89,0,0.2

k,90,0.003,0.2

k,91,0.004,0.2

k,92,0.006,0.2k,93,0.016,0.2

k,94,0.036,0.2

k,95,0.17,0.2

k,96,0.19,0.2

k,97,0.2,0.2

k,98,0.202,0.2

k,99,0.203,0.2

k,100,0.206,0.2

k,101,0,0.203

k,102,0.003,0.203

k,103,0.004,0.203

k,104,0.006,0.203

k,105,0.016,0.203

k,106,0.036,0.203

k,107,0.17,0.203

k,108,0.19,0.203

k,109,0.2,0.203

k,110,0.202,0.203

k,111,0.203,0.203

k,112,0.206,0.203

k,113,0,0.204

k,114,0.003,0.204

k,115,0.004,0.204

k,116,0.202,0.204

k,117,0.203,0.204

k,118,0.206,0.204

k,119,0.0045,0.2045

k,120,0.2015,0.2045

k,121,0,0.206k,122,0.003,0.206

k,123,0.203,0.206

k,124,0.206,0.206

k,125,0,0.216

k,126,0.003,0.216

k,127,0.203,0.216

k,128,0.206,0.216

k,129,0,0.236

k,130,0.003,0.236

k,131,0.203,0.236

k,132,0.206,0.236

k,133,0,0.25

k,134,0.003,0.25

k,135,0.203,0.25

k,136,0.206,0.25

l,1,2

l,3,4

l,1,5

l,2,6

l,3,7

l,4,8

l,5,6

l,7,8

l,5,9

l,6,10

l,7,11

l,8,12

l,9,10

l,11,12

l,9,13

l,10,14l,11,15

l,12,16

l,13,14

l,15,16

l,13,19

l,14,20

l,14,17

l,15,18

l,15,23

l,16,24

l,19,20

l,20,21

l,21,17

l,17,28

l,18,33

l,18,22

l,22,23

l,23,24

l,19,25

l,20,26

l,21,27

l,22,34

l,23,35

l,24,36

l,25,26

l,26,27

l,27,28

l,28,29

l,29,30l,30,31

l,31,32

l,32,33

l,33,34

l,34,35

l,35,36

l,25,37

l,26,38

l,27,39

l,28,40

l,29,41

l,30,42

l,31,43

l,32,44

l,33,45

l,34,46

l,35,47

l,36,48

l,37,38

l,38,39

l,39,40

l,40,41

l,41,42

l,42,43

l,43,44

l,44,45

l,45,46

l,46,47

l,47,48

l,37,49

l,38,50l,39,51

l,40,55

l,45,56

l,46,52

l,47,53

l,48,54

l,49,50

l,50,51

l,51,55

l,52,56

l,52,53

l,53,54

l,49,57

l,50,58

l,55,58

l,56,59

l,53,59

l,54,60

l,57,58

l,59,60

l,57,61

l,58,62

l,59,63

l,60,64

l,61,62

8/22/2019 Full 10088



20


l,63,64

l,61,65

l,62,66

l,63,67

l,64,68

l,65,66

l,67,68

l,65,69l,66,70

l,67,71

l,68,72

l,69,70

l,71,72

l,69,73

l,70,74

l,71,75

l,72,76

l,73,74

l,75,76

l,73,77

l,74,78

l,75,79

l,76,80

l,77,78l,79,80

l,77,83

l,78,84

l,78,81

l,79,82

l,79,87

l,80,88

l,83,84

l,84,85

l,81,85

l,82,86

l,86,87

l,87,88

l,83,89

l,84,90

l,85,91

l,81,92

l,82,97

l,86,98

l,87,99

l,88,100

l,89,90

l,90,91

l,91,92

l,92,93

l,93,94

l,94,95

l,95,96

l,96,97

l,97,98

l,98,99l,99,100

l,89,101

l,90,102

l,91,103

l,92,104

l,93,105

l,94,106

l,95,107

l,96,108

l,97,109

l,98,110

l,99,111

l,100,112

l,101,102

l,102,103

l,103,104

l,104,105

l,105,106l,106,107

l,107,108

l,108,109

l,109,110

l,110,111

l,111,112

l,101,113

l,102,114

l,103,115

l,104,119

l,109,120

l,110,116

l,111,117

l,112,118

l,113,114

l,114,115l,115,119

l,116,120

l,116,117

l,117,118

l,113,121

l,114,122

l,119,122

l,120,123

l,117,123

l,118,124

l,121,122

l,123,124

l,121,125

l,122,126

l,123,127

l,124,128

l,125,126

l,127,128

l,125,129

l,126,130

l,127,131

l,128,132

l,129,130

l,131,132

l,129,133

l,130,134

l,131,135

l,132,136

l,133,134

l,135,136

lplotal,1,4,7,3

al,2,6,8,5

al,7,10,13,9

al,8,12,14,11

al,13,16,19,15

al,14,18,20,17

al,19,22,27,21

al,23,29,28,22

al,24,25,33,32

al,20,26,34,25

al,27,36,41,35

al,28,37,42,36

al,29,30,43,37

al,31,32,38,49

al,33,39,50,38

al,34,40,51,39

al,41,53,64,52

al,42,54,65,53al,43,55,66,54

al,44,56,67,55

al,45,57,68,56

al,46,58,69,57

al,47,59,70,58

al,48,60,71,59

al,49,61,72,60

al,50,62,73,61

al,51,63,74,62

al,64,76,83,75

al,65,77,84,76

al,66,78,85,77

al,72,80,86,79

al,73,81,87,80

al,74,82,88,81

al,83,90,95,89al,84,85,91,90

al,87,93,92,86

al,88,94,96,93

al,95,98,101,97

al,96,100,102,99

al,101,104,107,103

al,102,106,108,105

al,107,110,113,109

al,108,112,114,111

al,113,116,119,115

al,114,118,120,117

al,119,122,125,121

al,120,124,126,123

al,125,128,133,127

al,129,135,134,128

al,130,131,137,136

al,126,132,138,131

al,133,140,147,139

al,134,141,148,140

al,142,149,141,135

al,143,136,144,155

al,137,145,156,144

al,138,146,157,145

al,147,159,170,158

al,148,160,171,159

al,149,161,172,160

al,150,162,173,161

al,151,163,174,162

al,152,164,175,163

al,153,165,176,164

al,154,166,177,165al,155,167,178,166

al,156,168,179,167

al,157,169,180,168

al,170,182,189,181

al,171,183,190,182

al,172,184,191,183

al,178,186,192,185

al,179,187,193,186

al,180,188,194,187

al,189,196,201,195

al,190,191,197,196

al,193,199,198,192

al,194,200,202,199

al,201,204,207,203

al,202,206,208,205

al,207,210,213,209

al,208,212,214,211

al,213,216,219,215al,214,218,220,217

aplot

aglue,all

ET,1,PLANE55

ET,2,SOLID70

lesize,1,,,2

lesize,2,,,2

lesize,219,,,2

lesize,220,,,2

lesize,52,,,2

lesize,63,,,2

lesize,158,,,2

lesize,169,,,2

lesize,21,,,2

lesize,35,,,2


lesize,42,,,2

lesize,65,,,2

lesize,26,,,2

lesize,40,,,2

lesize,82,,,2

lesize,94,,,2

lesize,50,,,2

lesize,73,,,2

lesize,127,,,2

lesize,139,,,2

lesize,181,,,2

lesize,195,,,2

lesize,148,,,2

lesize,171,,,2

lesize,132,,,2

lesize,146,,,2

lesize,188,,,2

lesize,200,,,2

lesize,155,,,2

lesize,178,,,2

lesize,15,,,4

lesize,18,,,4

lesize,97,,,4

lesize,100,,,4

lesize,121,,,4

lesize,124,,,4

lesize,203,,,4

lesize,206,,,4

lesize,44,,,4


lesize,177,,,4

lesize,9,,,4

lesize,12,,,4

lesize,103,,,4

lesize,106,,,4

lesize,115,,,4

lesize,118,,,4

lesize,209,,,4

lesize,212,,,4

8/22/2019 Full 10088



20


lesize,45,,,4

lesize,174,,,4

lesize,47,,,4

lesize,176,,,4

lesize,3,,,2

lesize,6,,,2

lesize,215,,,2


lesize,112,,,13

lesize,46,,,19

lesize,175,,,19

MSHAPE,0,2D

MSHKEY,1

amesh,all

TYPE,2

EXTOPT,ESIZE,8,0,

EXTOPT,ACLEAR,1

EXTOPT,ATTR,0,0,0

VEXT,all, , ,0,0,-0.023,,,,

nummrg,all

/VIEW,1,1,1,1

/ANG,1

/REP,FASTeplot

ASEL,S,LOC,Z,-0.023

aplot

TYPE,2

EXTOPT,ESIZE,1,0,

EXTOPT,ACLEAR,1

EXTOPT,ATTR,0,0,0

VEXT,all, , ,0,0,-0.0024,,,,

ALLSEL,ALL

aplot

ASEL,S,LOC,Z,-0.0254

aplot

EXTOPT,ESIZE,8,0,

EXTOPT,ACLEAR,1

EXTOPT,ATTR,0,0,0

VEXT,all, , ,0,0,-0.023,,,,

ALLSEL,ALL

aplot


aplot

EXTOPT,ESIZE,1,0,

EXTOPT,ACLEAR,1

EXTOPT,ATTR,0,0,0

VEXT,all, , ,0,0,-0.0024,,,,

ALLSEL,ALL

aplot


aplot

EXTOPT,ESIZE,8,0,

EXTOPT,ACLEAR,1

EXTOPT,ATTR,0,0,0

VEXT,all, , ,0,0,-0.023,,,,

ALLSEL,ALL

aplot


aplotEXTOPT,ESIZE,1,0,

EXTOPT,ACLEAR,1

EXTOPT,ATTR,0,0,0

VEXT,all, , ,0,0,-0.0024,,,,

ALLSEL,ALL

aplot


aplot

EXTOPT,ESIZE,8,0,

EXTOPT,ACLEAR,1

EXTOPT,ATTR,0,0,0

VEXT,all, , ,0,0,-0.023,,,,

ALLSEL,ALL

aplot


aplotEXTOPT,ESIZE,1,0,

EXTOPT,ACLEAR,1

EXTOPT,ATTR,0,0,0

VEXT,all, , ,0,0,-0.0024,,,,

ALLSEL,ALL

aplot


aplot

EXTOPT,ESIZE,8,0,

EXTOPT,ACLEAR,1

EXTOPT,ATTR,0,0,0

VEXT,all, , ,0,0,-0.023,,,,

ALLSEL,ALL

aplot


aplot

EXTOPT,ESIZE,1,0,

EXTOPT,ACLEAR,1

EXTOPT,ATTR,0,0,0

VEXT,all, , ,0,0,-0.0024,,,,

ALLSEL,ALL

aplot

ASEL,S,LOC,Z,-0.127

aplot

EXTOPT,ESIZE,8,0,

EXTOPT,ACLEAR,1

EXTOPT,ATTR,0,0,0

VEXT,all, , ,0,0,-0.023,,,,

ALLSEL,ALL

aplot

eplot

nummrg,all

/VIEW,1,1,1,1

/ANG,1

/REP,FAST

eplot%Thermall properties dependent

on temperature used in

numerical welding process of the

I-type specimen to tension%

SFA,386 AREA,1,CONV,10,20

% Weld bead thermal cycle, from

weld bead No. 1 to weld bead

No.24 is written%

*DIM,TIMEVSTEMP01,TABLE,9,1,

1,TIME,TEMP,






*SET,TIMEVSTEMP01(3,0,1) , 4*SET,TIMEVSTEMP01(3,1,1) ,

1245


*SET,TIMEVSTEMP01(4,1,1) ,

1245









*SET,TIMEVSTEMP01(9,0,1) ,

1000


FINISH

/SOL

ANTYPE,4

NLGEOM,1

DELTIM,2,2,2

OUTRES,ERASE

OUTRES,ALL,1

TIME,1980

%Application of the weld bead

thermal cycle to all areas

corresponding to each weld

bead, from weld bead No. 1 to

weld bead No.24 %

DA,1483,TEMP,

%TIMEVSTEMP01%

DA,1501,TEMP,

%TIMEVSTEMP01%

DA,1502,TEMP,

%TIMEVSTEMP01%DA,1506,TEMP,

%TIMEVSTEMP01%

DA,1505,TEMP,

%TIMEVSTEMP01%

DA,1486,TEMP,%TIMEVSTEMP

%

IC,all,TEMP,20,

/STATUS,SOLU

SOLVE

Thermal elastic plastic analysi

/title,thermal elastic pla

/PREP7

%Commands of the geometric

model and mesh equal to

transient thermal analysis% %Mechanical properties

dependent on temperature us

in numerical welding process o

the I-type specimen to tension

FINISH

/SOL

ANTYPE,0

ANTYPE,0

NLGEOM,1

NSUBST,10,20,5

PSTRES,1

D,166,all,0

D,167,all,0

D,2139,all,0

D,2146,all,0

TREF,20,

%Application of the load therm

from transient thermal analysi

53 load step are required%

LDREAD,TEMP,,,8, ,'analisis

transiente termico 1','rth',' '

LSWRITE,1,

BFDELE,all,TEMP

LSSOLVE,1,53,1,

FINISH

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