Upload
others
View
12
Download
0
Embed Size (px)
Citation preview
Mechanisms Based ModelingApproaches to Multiaxial Fatigue
of Wind Turbine Rotor Blades
Ramesh Talreja
Department of Aerospace Engineering
Texas A&M University, College Station, Texas
Marino Quaresimin
Department of Management and Engineering, University of Padova, Italy
Contents
• Introduction & Background
• The dismal state of multiaxial fatigue in composites
• A rational way forward – mechanisms based
• Results & Status
• Future direction
• Conclusion
Multiaxial Fatigue
Cruciform Tubular
Test samples
Stress Biaxiality Ratios
In material coordinates:
λ1=σ2/1 (normal)
λ2= σ6/1 (shear)
12= σ6/2 (shear)
x
q
y
1
z3
O
2
x
y
z
O
x
y
z
O
x
y
z
O
X
Y
Z=3
1
2
The dismal state of multiaxial fatigue
• Most current approaches are essentially modified “metal fatigue”, lacking THINK COMPOSITES content.
• Schemes, formulas, ad-hoc ideas with poor, uncertain predictive capability.
References:• Fatigue behaviour and life assessment of composite laminates under
multiaxial loadings, M. Quaresimin, L.Susmel, R. Talreja International Journal of Fatigue, 32 (2010) 2–16
• M. Quaresimin, R. Talreja “Fatigue of fiber reinforced composites under multiaxial loading” in Fatigue life prediction of composites and composite structures, A.Vassilopoulos Ed. , 2010 WoodheadPublishing Ltd,, 2010, p. 334-389.
Current approaches:Phenomenological failure criteria
• Tsai-Hill criterion
• Smith-Pascoe criterion
• Fewaz-Ellyin Criterion
Polynomial function based criterion
s s s
1 2 1 s 6
Nf Nf
1Õ 1Ó 2Õ
2Ó
Static
failure
envelope
s1=f1(Nf) s6=f6(Nf)
s1=f1(Nf) s2=f2(Nf)
Fatigue
failure
envelopes
- M. J. Owen, J. R. Griffiths, M.S. Found, I. C. C. M. (1975)
- M.J. Owen, J.R. Griffiths. Journal of Materials Science 1978
- M. J. Owen, J. R. Griffiths, M. S. Found 35th SPI (1980)
- D.F. Sims, V.H. Brogdon. ASTM STP 636 (1997)
Smith & Pascoe (1989)
0%
-200%
-400%
200%400%
100
1000
10000
100000
1000000
10000000
100 1000 10000 100000 1000000 10000000
Nf,e [cycles]
Nf
[cycle
s]
.
Aboul Wafa et al.[1]
Amijima et al.[2]
Kawakami et al.[3]
Kawai Taniguchi [16]
Smith Pascoe [4]
2
f6
2
fSE
2
21
12
21
1
12
1
2a,1
NfNf2
EEEE
1
1
s
Fawaz & Ellyin (1994)
0%
-200%
-400%
200%400%
10
100
1000
10000
100000
1000000
10000000
10 100 1000 10000 100000 1000000 1000000
0Nf,e [cycles]
Nf [
cycl
es]
Aboul Wafa et al.[1]
Amijima et al. [2]
Kawai Taniguchi [16]
Kawakami et al.[3]
Smith Pascoe [4]
external multiaxiality
s(T, C, q, R, N)=f(T, C, q[br+g(R) mr log(N) ]
Our Approach
Step 1. Develop mechanisms based Fatigue Life Diagrams to clarify:
• Effects of multiaxial loading• Conditions governing long fatigue life ( > 107 cycles)Step 2. Develop mechanics models guided by Step 1 to
quantitatively predict:• Effects of shear on tension-tension, tension-
compression and compression-compression fatigue• Effects of normal stresses on torsional fatigueStep 3. Develop failure criteria for long term fatigue life
under multiaxial loading.
The Team
Texas A&M University
• Aerospace Engineering (Talreja, Huang)
University of Padova – Vicenza, Italy
• Mechanical Engineering (Quaresimin, Carraro)
Technical University of Denmark
• Risø Laboratory for Sustainable Energy (Brøndsted, Sørensen)
Luleå University, Sweden
• Polymer Engineering (Varna)
Step 1. Mechanisms based Fatigue Life Diagram
Log N
max Noprogressive damage
Noevovig damage
Case 1: Unidirectional composites, on-axis loading
Fiber-bridged matrix cracking
On-axis fatigue life diagram modified by λ1 and λ2
Log N
1 > 0 2 > 0
max Noprogressive damage
Noevovig damage
Fiber-bridged matrix cracking
1 s 2, a
s1, a
2 s 6, a
s1, a
12 s 6, a
s 2, a
Off-axis fatigue life diagram modified by λ1, λ2 and λ12
λ1 , λ2
λ12
Experimental Programat University of Padova (Quaresimin)
• Start with cyclic transverse stress, σ2, and study the effect of λ12=σ6/σ2
• Specimen type: tubular
Fiber layups:
UD tubes: [904]
TU tubes [0F/90U,3]
TUT tubes: [0F/90U,3/0F]
Three fiber lay-ups
• UD tubes: [904]• Sudden failure, no damage evolution, damage
initiation from surface defects
• TU tubes [0F/90U,3] • Stable crack propagation and multiple cracking,
some influence of surface defects
• TUT tubes: [0F/90U,3/0F]• Stable crack propagation and multiple cracking,
negligible influence of surface defects
Specimen manufacturing
Samples produced by mandrel wrapping of glass/epoxy UD tapes and fabrics then cured in autoclave (1 hour at 140ºC and 6 bars) without
vacuum bag:some resin rich areas but no voids
Ext diameter 22 mmInt diameter 19 mmTab diameter 24 mm
5
50
100 1000 10000 100000 1000000 10000000
Tra
nsv
erse
str
ess
on
90°
pli
es [
MP
a]
Number of cycles, N
L
0L
1
λ12 = 0
λ12 = 1
λ12 = 2λ12
Fatigue curves (6 on 2 ) at R=0 [90]4 tubes
final failure ≈ crack initiation
WOHLER CURVES - tubes with one inner layer of fabric and three layer of 90 UD Tapes
0
5
10
15
20
25
30
35
40
45
50
55
60
65
70
75
10 100 1000 10000 100000 1000000 10000000
Log(Nf)
б2
[M
Pa
]
120
120.5
121
122
12
Fatigue testing (6 on 2 ) at R=0 [0F/903]
0.631.252.5
final failure fiber controlled
LED internal lighting of tubes damage observation
Fatigue curves (6 on 2 ) at R=0 – [0F/903]
5
50
10 100 1000 10000 100000 1000000 10000000
tran
sver
se s
tres
s s
2in
90°p
lies
[MP
a]
cycles for nucleation of cracks
l12=0
l12=0.63
λ12 = 0
λ12 = 0.63
λ12 = 1.25
λ12 = 2.5
12
Fatigue curves (6 on 2 ) at R=0 [0F/903/0F]
5
50
100 1000 10000 100000 1000000 10000000
Tran
sverse
str
ess
on
90
pli
es
[MP
a]
Number of cycles, N
l 1 2 = 0
l 1 2 = 1
l 1 2 = 2
λ12 = 0
λ12 = 1
λ12 = 212
Cycles for crack initiation
Comparison between [904] and [0F/903/0F]
5
50
100 1000 10000 100000 1000000 10000000
tra
nsv
erse
str
ess
on
90
pli
es [
MP
a]
number of cycles, N
: TUT tubes
dashed lines: UD tubes
λ12 = 0
λ12 = 1
λ12 = 2
Cycles for crack initiation
Crack propagation
0
20
40
60
80
100
0 50000 100000 150000
cycles of crack propagation, Np
λ12 = 0
λ12 = 0.5
λ12 = 1
λ12 = 1.5
cra
ck a
ng
le[d
egre
es]
2α
σ2 on 90º plies = 30 MPa
3-step Approach
Step 1. Develop mechanisms based Fatigue Life Diagrams to clarify:
• Effects of multiaxial loading• Conditions governing long fatigue life ( > 107 cycles)Step 2. Develop mechanics models guided by Step 1 to
quantitatively predict:• Effects of shear on tension-tension, tension-
compression and compression-compression fatigue• Effects of normal stresses on torsional fatigueStep 3. Develop failure criteria for long term fatigue life
under multiaxial loading.
Conclusion
• Grand plan for mechanisms based approach is in place
• Effects of combined transverse and shear stresses investigated
• Modeling efforts are ongoing, soon to be reported
• Phenomenological approaches not recommended