NASA TECHNICAL

MEMORANDUM

NASA TM X- 73956-6

IVDmcr\00

(NASi-TM-X-73956-6) LaBC DESIGN ANALYSISREPCHT FOE NATIONAL T5ANSONIC FACILITY FOR9% NICKEL TUNNEL SH3LL. VOLUME 6: FATIGUZANALYSIS (NASA) 46 p HC $4.00 CSCL 13M

G3/39

N76-335U8

Unclas05764

t/i

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LaRC DESIGN ANALYSIS REPORT

FOR

NATIONAL TRANS01IIC FACILITY

FOR

9% NICKEL TUNNEL SHELL

FATIGUE ANALYSIS

VOL. 6 .

3Y

JAMES W. RAKSEY, JR., JOHI' T. TAYLOR, JO:CARL E. GRAY, JR., AMJ.-E D. LEATHERS A:;, JA!

AND JOHNNY W. ALLRED

This informal documentation medium is used to provide accel crated orspecial release of technical information to selected users. The contentsmay not meet NASA formal editing and publication standards, may be re-vised, or may be incorporated in another publication.

National Aeronautics andSpace Administration

Langley Research CenterHampton. Virginia 23665

https://ntrs.nasa.gov/search.jsp?R=19760026460 2018-08-26T07:44:02+00:00Z

1. Report No. 2. Government Accession No.

TM X-73956-64. Title and subtitle LaRC Design Analysis Report for the NationalTransonic Facility for a 9% Nickel Tunnel Shell - FatigueAnalysis, Vol. 6

7. Author(s) j . w. Ramsey,Jr., J. T. Taylor, J. F. Wilson,C. E. Gray, Jr., A. D. Leatherman, J. R. Rooker,and J. W. Allred

9. Performing Organization Name and Address

National Aeronautics and Space AdministrationLangley Research CenterHampton, Virginia 23665

12. Sponsoring Agency Name and Address

National Aeronautics and Space AdministrationWashington, DC 20546

3. Recipient's Catalog No.

5. Report Date

September 19766. Performing Organization Code

8. Performing Organisation Report No.

10. Work Unit No.

11. Contract or Grant No.

13. Type of Report and Period CoTechnical Memorandum

veredX

14. Sponsoring Agency Code

15. Supplementary Notes

Formal Documentation of Design Analyses to Obtain Code Approval of FabricatedNational Transonic Facility

is. Abstract This report contains the results Of extensive computer (finite element, finitedifference and numerical integration), thermal, fatigue, and special analyses ofcritical portions of a large pressurized, cryogenic wind tunnel (National TransonicFacility). The computer models, loading and boundary conditions are described. Gra.phiccapability was used to display model geometry, section properties, and stress results.A stress criteria is presented for evaluation of the results of the analyses. Thermalanalyses were performed for major critical and typical areas. Fatigue analyses of theentire tunnel circuit is presented-

The major computer codes utilized are: SPAR - developed by Engineering InformationSystems, Inc. under NASA Contracts NAS8-30536 and NAS1-13977; SALORS - developed byLangley Research Center and described in NASA TN D-7179; and SRA - developed byStructures Research Associates under NASA Contract MAS!-10091; "A General TransientHeat-Transfer Computer Program for Thermally Thick Walls" developed by Langley ResearchCenter and described in NASA TM X-2058.

17. Key Words (Suggested by Author(s))

Pressure VesselWind TunnelFinite ElementNumerical IntegrationDesign

19. Security Oauif. (of this report)

Unclassified

18. Distribution Statement

UNCLASSIFIED - UNLIMITED

20. Security Classif. (of this page) 21. No. of Pages

Unclassified 4422. Price"

$3.75

•For sale by the National Technical Information Service, Springfield. Virginia 22151

NTF TUNNEL SHELL

NASA LARC

FATIGUE ANALYSIS

9% Ni

SEPTEMBER 1976

VOLUME 6

LaRC CALCULATIONS

FOR THE

NATIONAL TRANSONIC FACILITY

TUNNEL SHELL

DATE: SEPTEMBER, 1976

APPROVED:

ANALYSTS;

x* ***) r •DR7 JAMES W. RAMSEY, JR., HEADSTRUCTURAL ENGINEERING SECTION

J0HN T. TAYLOR 'HEAD SHELL ANALYST

J5HN F. WILSON, SHELL WORKPACKAGE & CONSTRUCTION MANAGER

w • *£- LrtANNE D. LEATHERMANSHELL PROGRAMMER

CARL E. GRAY, -io7 ^SHELL ANALYST

JAMES R. ROOKERSHELL/THERMAL ANALYST

a-.JOHNNY W/ALLREDSHELL/THERMAL ANALYST

This report is one volume of a Design Analysis Report prepared by LaRCon portions of the pressure shell for the National Transonic Facility. Thisreport is to be used in conjunction with reports prepared under NASAContract NASl-13535(c) by the Ralph M. Parsons Company (Job Number 5409-3dated September 1976) and Fluidyne Engineering Corporation (Job Number 1060dated September 1976). The volumes prepared by LaRC are listed below:

1. Finite Difference Analysis of Cone/Cylinder (9% Ni), Vol. 1,NASA TM X73956-1.

2. Finite Element Analysis of Corners #3 and #4 (9% Ni), Vol. 2,NASA TM X73956-2.

3. Finite Element Analysis of Plenum Region Including Side AccessReinforcement, Side Access Door and Angle of Attack Penetration(9% Ni), Vol. 3, NASA TM X73956-3.

4. Thermal Analysis (9% Ni), Vol. 4, NASA TM X73956-4.

5. Finite Element and Numerical Integration Analyses of theBulkhead Region (9% Ni), Vol. 5, NASA TM X73956-5.

6. Fatigue Analysis (9% Ni), Vol. 6, NASA TM X73956-6.

7. Special Studies (9% Ni), Vol. 7, NASA TM X73956-7.

NTF DESIGN CRITERIAFOR 9% NICKEL

GENERAL

THE DESIGN OF THE PRESSURE SHELL REFLECTED IN THIS REPORTSATISFIES THE DESIGN REQUIREMENTS OF THE ASME BOILER AND PRESSUREVESSEL CODE, SECTION VIII, DIVISION 1. SINCE DIVISION 1 DOES NOTCONTAIN RULES TO COVER ALL DETAILS OF DESIGN, ADDITIONAL ANALYSESWERE PERFORMED IN AREAS HAVING COMPLEX CONFIGURATIONS SUCH AS THECONE CYLINDER JUNCTIONS, THE GATE VALVE BULKHEADS, THE BULKHEAD-SHELL ATTACHMENTS, THE PLENUM ACCESS DOORS AND REINFORCEMENTAREAS, THE ELLIPTICAL CORNER SECTIONS, AND THE FIXED REGION (RINGS8) OF THE TUNNEL. THE DIVISION 1 DESIGN CALCULATIONS, THEADDITIONAL ANALYSES AND THE CRITERIA FOR EVALUATION OF THE RESULTSOF THE ADDITIONAL ANALYSES TO ENSURE COMPLIANCE WITH THE INTENT OFDIVISION 1 REQUIREMENTS ARE CONTAINED IN THE TEXT OF THIS REPORT.THE DESIGN ANALYSES AND ASSOCIATED CRITERIA CONSIDERED BOTH THEOPERATING AND HYDROSTATIC TEST CONDITIONS.

IN CONJUNCTION WITH THE DESIGN, A DETAILED FATIGUE ANALYSIS OF THEPRESSURE SHELL WAS ALSO PERFORMED UTILIZING THE METHODS OF THEASME CODE, SECTION VIII, DIVISION 2.

MATERIAL

THE PRESSURE SHELL MATERIAL SHALL BE ASME, SA-553-1 FOR PLATE ANDSA-522 FOR FORCINGS. THE MATERIAL PROPERTIES AT TEMPERATURESEQUAL TO OR BELOW 150°F ARE AS FOLLOWS:

(A) PLATE, 2.0 INCHES OR THINNER

YIELD = 85.0 KSIULTIMATE =100 KSI

(B) WELDS (AUTOMATIC AND SEMIAUTOMATIC)

YIELD = 52.5 KSIULTIMATE = 95.0 KSI

(C) WELDS (HAND)

YIELD =58.5 KSIULTIMATE = 95.0 KSI

OPERATING, DESIGN AND TEST CONDITIONS

, THE OPERATING, DESIGN AND TEST CONDITIONS FOR THE TUNNEL PRESSURE' SHELL AND ASSOCIATED SYSTEMS AND ELEMENTS ARE SUMMARIZED BELOW:

1. OPERATING MEDIUM

ANY MIXTURE OF AIR AND NITROGEN

2. DESIGN TEMPERATURE RANGE

MINUS 320 DEGREES FAHRENHEIT TO PLUS 150 DEGREESFAHRENHEIT, EXCEPT IN THE REGION OF -THE PLENUM BULKHEADSAND GATE VALVES INSIDE A 23-FOOT, 4-INCH DIAMETER, FORWHICH THE TEMPERATURE RANGE IS MINUS 320 DEGREESFAHRENHEIT TO PLUS 200 DEGREES FAHRENHEIT.

3. PRESSURE RANGE

B

TUNNELCONFIGURATION

CONDITION I - PLENUMISOLATION GATES OPENAND TUNNEL OPERATING:

TUNNEL CIRCUITEXCEPT PLENUM

PLENUM (PLENUM PRESS-URE IS LIMITED TO.4 TO 1 TIMES THEREMAINDER OF THETUNNEL CIRCUIT

BULKHEAD

CONDITION II - PLENUMISOLATION GATES OPENAND TUNNEL SHUTDOWN:

ENTIRE TUNNEL CIRCUIT

OPERATING DESIGNPRESSURE PRESSURESRANGE, PSIA PSID

8.3 to 130

3.3 to 130

8.3 to 130

A. 3 EXTERNALB. .119 INTERNA!

A. 15 EXTERNALB. 119 INTERNAL

56 (EXTERNAL TO PLENUM)

A. 8 EXTERNALB. 119 INTERNAL

BULKHEAD

C. CONDITION III - PLENUMISOLATION GATES ANDACCESS DOORS CLOSED:

TUNNEL CIRCUIT EXCEPTPLENUM

PLENUM (PLENUM OPER-ATING PRESSURE CANEXCEED THE PRESSUREIN THE REMAINDER OFTHE TUNNEL CIRCUIT BY2U PSI, BUT DOES NOTEXCEED THE 130 PSIAMAXIMUM OPERATINGPRESSURE)

BULKHEAD

8.3 to 130

0 to 130

A. 8 EXTERNALB. 119 INTERNAL

A.B.

B

15 EXTERNAL119 INTERNAL

25 (INTERNAL TOPLENUM)119 (EXTERNAL TOPLENUM) FOR MINUS320 DEGREESFAHRENHEIT TOPLUS 150 DEGREESFAHRENHEIT

»C. 110.5 (EXTERNAL TOPLENUM) FOR PLUS151 DEGREESFAHRENHEIT200 DEGREESFAHRENHEIT

TO PLUS

-OPERATING PROCEDURES LIMIT PRESSURES TO THAT SHOWN.

D. CONDITION IV - PLENUMISOLATION GATES CLOSEDAND ACCESS DOORS OPEN:

TUNNEL CIRCUIT EXCEPTPLENUM

PLENUM

BULKHEAD

8.3 to 130

14.7

A. 8 EXTERNALB. 119 INTERNAL

A. 119 (EXTERNAL TOPLENUM) FOR MINUS320 DEGREES FAHRENHEITTO PLUS 150 DEGREESFAHRENHEIT

*B. 110.5 (EXTERNAL TOPLENUM) FOR PLUS 151DEGREES FAHRENHEIT TO PLUS200 DEGREES FAHRENHEIT

OPERATING PROCEDURES LIMIT PRESSURES TO THAT SHOWN.

VI

4. HYDROSTATIC TEST DESIGN CONDITIONSi

THE PRESSURE SHELL WAS DESIGNED FOR HYDROSTATIC TEST INACCORDANCE WITH THE REQUIREMENTS OF THE ASME CODE, SECTIONVIII, DIVISION 1. THE TEST PRESSURES SHALL BE AS FOLLOWS.PRESSURE SHELL TEMPERATURE SHALL BE EQUAL TO OR BELOW100°F DURING HYDROSTATIC TESTS.

CONDITION (1) - MAXIMUM INTERNAL PRESSURE CONDITIONFOR THE ENTIRE TUNNEL CIRCUIT

PH, = 1.5 (119) + HYDROSTATIC HEAD=178.5 PSI + HYDROSTATIC HEAD

CONDITION (2) - MAXIMUM DIFFERENTIAL PRESSURE CONDITIONACROSS THE PLENUM BULKHEADS

PH~ = 1.5 (119) + HYDROSTATIC HEAD= 178.5 + HYDROSTATIC HEAD

PH2- = 1.5 (111.5) (ff-1 ) + HYDROSTATIC HEAD

= 178.5 + HYDROSTATIC HEAD

*TUNNEL OPERATION LIMITATIONS PRECLUDE PRESSUREDIFFERENTIALS ACROSS BULKHEADS III EXCESS OF110.5 PSI FOR BULKHEAD AIJD GATE TEMPERATURES i:,: EXCESSOF 150°F.

CONDITION (3) - MAXIMUM REVERSE DIFFERENTIAL PRESSURE COIJDITIO:;ACROSS THE PLENUM BULKHEADS

PH3 = 1.5 (25) = 37.5 PSI

THE PRESSURE SHELL EXCEPT FOR THE PLENUM SHALL BZ PRESSURIZED TO141 PSIG. THE PLENUM SHALL BE PRESSURIZED TO 178.5 P5IG.

PRESSURE SHELL STRESS EVALUATION CRITERIA

THIS CRITERIA ESTABLISHES THE BASIS FOR ANALYSIS'AND DESIGN OF THEPRESSURE SHELL SO IT WILL MEET OR EXCEED ALL OF THE REQUIREMENTSOF SECTION VIII, DIVISION 1 OF THE ASME BOILER AND PRESSURE VESSELCODE AND CAN BE STAMPED WITH A DIVISION 1 "U" STAMP.

SECTION VIII, DIVISION 1, DIRECT APPLICATION

A. THE MAXIMUM ALLOWABLE STRESS (S)

S = 23.7 KSI (-320°F TO +150°F)

S = 22.2 KSI (-320°F TO +200°F)

(B) PRIMARY BENDING PLUS PRIMARY MEMBRANE STRESSES

THE LOCAL MEMBRANE STRESSES ARE NOT GENERALLY .CONSIDERED IN SECTION VIII, DIVISION 1 DESIGNS.HOWEVER, FOR THE PURPOSE OF DESIGNING LOCALREINFORCEMENT AT BRACKETS, RINGS OR PENETRATIONS NOTCOVERED BY DESIGN BASED ON STRESS ANALYSIS, THELOCAL. SHELL MEMBRANE STRESS SHALL BE:

Pb + Pm^1'5 SE '

NOTE: E IS JOINT EFFICIENCY

IN REGIONS OF THE PRESSURE SHELL WHERE DIVISION 1 DOESNOT CONTAIN RULES TO COVER ALL DETAILS OF DESIGN (REF.U-2(g)), ADDITIONAL ANALYSES WERE PERFORMED UTILIZING THEGUIDELINES OF THE ASHE CODE, SECTION VIII, DIVISION 2,APPENDIX 4, "DESIGN BASED ON STRESS ANALYSIS.." THE BASICSTRESS CRITERIA FOR DIVISION 2 IS REPRESENTED IN FIGURE4-130.1 AND RESTATED BELOW INDICATING ANY MODIFICATIONSOR EXCESS REQUIREMENTS APPLIED TO IT TO REMAIN WITHIN THEINTENT OF DIVISION 1 AND TO OBTAIN A DIVISION 1 .STAMP .-

A. GENERAL PRINCIPAL MEMBRANE STRESS

MAXIMUM ALLOWABLE STRESS

S = 23.7 KSI (-320°F TO +150°F)

S = 22.2 KSI (-320°F TO +200°F)

MAXIMUM ALLOWABLE STRESS INTENSITY

S = 31.7 KSI (-320°F TO +200°F)m

B. PRIMARY GENERAL MEMBRANE STRESS INTENSITY

P < Sm m

AND IN ORDER TO COMPLY WITH DIVISION 1, THE MAXIMUMPRINCIPAL MEMBRANE STRESS MUST BE:

NOTE: THE * IS USED TO DENOTE THAT MAXIMUM PRINCIPALSTRESSES ARE TO BE COMPUTED FOR THE GIVEN LOADINGCONDITION. THE INTENT IS TO DETERMINE THE STRESSES WHICHREPRESENT THE HOOP STRESSES AND MERIDIONAL STRESSES WHICHARE THE STRESSES USED IN DIVISION 1 COMPUTATIONS.

viii

DESIGN LOADS, PRIMARY LOCAL MEMBRANE STRESSINTENSITY

PT < 1.5 SL — m

NOTE: LOCAL MEMBRANE STRESS INTENSITY IS DEFINED INACCORDANCE WITH DIVISION 2,APPENDIX 4-112(1). THE 'TOTAL MERIDIONALLENGTH IS CONSIDERED TO BE 1.0

D. DESIGN LOADS, PRIMARY LOCAL MEMBRANE PLUS PRIMARYBENDING STRESS INTENSITY

PL + Pb^1'5 Sm

E. OPERATING LOADS, PRIMARY PLUS SECONDARY STRESSINTENSITY

3 Sm

COMMENT

BECAUSE OF THE LOW YIELD STRENGTH EXPECTED AT THEWELDS AS COMPARED TO THE YIELD STRENGTH OF THEPLATE, STRESS INTENSITIES COMPUTED IN (A), (B), (C),(D), OR (E) SHALL NOT EXCEED THE YIELD STRENGTH OF_THE MATERIAL AT EITHER WELD -OR PLATE LOCATIONS. -

3. A FATIGUE ANALYSIS WAS CONDUCTED IN ACCORDANCE WITHSECTION VIII, DIVISION 2 WITHOUT MODIFICATION.

4. HYDROSTATIC TEST CONDITION DESIGN CONSIDERATIONS

A. PRESSURE SHELL

IN ACCORDANCE WITH DIVISION 1 OF THE ASME CODE,DESIGN ANALYSIS OF THE PRESSURE SHELL FOR THEHYDROSTATIC TEST CONDITION IS NOT REQUIRED.HOWEVER, IN ORDER TO PROVIDE A SATISFACTORYENGINEERING DESIGN FOR THE PRESSURE SHELL THEFOLLOWING CRITERIA WAS USED:

(a) THE MAXIMUM GENERAL MEMBRANE STRESSPERPENDICULAR TO A WELD LINE WASLIMITED TO THE LESSER OF:

P * < 0.8 WELD YIELD STRESSm —

OR

P * < 0.5 WELD ULTIMATE STRESSm — •

IX

(b) THE GENERAL PRINCIPAL MEMBRANE STRESS INPLATE (NOT AT A WELD) WAS LIMITED TO THEOF:

P * < 0.8 PLATE YIELD STRESSm —

P * < 0.5 PLATE ULTIMATE STRESSm —

(*) THE STRESSES SATISFYING THIS CRITERIBASED ON MAXIMUM MEMBRANE STRESSESRATHER THAN INTENSITY CRITERIA.

•i NTF 9% NiFATIGUE ANALYSIS

.... TABLE OF CONTENTS -—

PAGE

I APPROACH 11, BASIS 2

2, REFERENCES 3

II ASME CODE SECTION VIII 4

1, DIV, I VS DIV, II VS NTF 42, DESIGN (STRESS) CRITERIA 53, STRESS-STRAIN RELATIONDHIPS 6

f 4, 9% Ni STRESS-CYCLES (S-N) CURVES 7

III OPERATIONAL PROJECTIONS 8

1, PROFILE 82, PROCEDURES 173, PRESSURE CYCLIC PROJECTION (20 YEARS) 26

IV NTF PRESSURE SHELL 27

1, PLAN VIEW 272, THERF1AL PROTECTION 28

A, PAINTING VIEW 28

B, INSULATION VIEW 29

X*-

PAGE

V FATIGUE LIFE SUMMARY 30

A, TABULAR 30

B, PICTORIAL - - 31

VI NTF QUALITY CONTROL PROGRAM DURING FABRICATION - - 32

APPROACHNTF LIFE

r IPEAK

STRESS

LMATERIAL

1EXPECTEDOPERATION

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FATIGUE

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Taylor, J.T.; Lewis, P.E.; and Ramsey, J.W.,Jr.: A ../Procedure for Verifying the Structural Integrity of anExisting Pressurized Wind Tunnel. A3ME ^'arior.ai PressureVessel Conference, June 19 74; and ASME JE T ^ r .? .. ^

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-3-REFERENCES

1. ASME Boiler and Pressure Vessel Code. 197$ Edition.

2- Taylor, J .T.; Lewis, P .E . ; and Ramsey, J .W. , J r . : AProcedure for Verifying the Structural Integrity of an

' Existing Pressurized Wind Tunnel. ASME National PressureVessel Conference, June 19 74; and ASMZ JZMT, October 1974.

3. McConnick, Caleb W.: The NASTRA1I User's Manual. NASA SP-222(Ol),

June 1972.

U. Cohen, G. A.: User Document for Computer Programs for Ring-Stiffened

Shell of Revolution. NASA CR-2036, March 1973.

5. ASME Boiler and Pressure Vessel Code. Section VIII, Division 2,

19Tf Edition.

6. O'Donnel, W. J.; and Purdy, C.M.: The Fatigue Strength of Members

Cert mining Cracks. Journal of Engineerins -cr Industry, May 196U.

7 Ramsey, J .W.,Jr . : Stress Concentration Factors forCircular, Reinforced Penetrations in Pressurized CylindricalShells. Ph.D. Dissertation, University of Virginia, May 137:

$ NTF Operational Profile by Dr. W. S. Lassiter,dated 12/22/76

7 NTF Operational Procedures for H1n1n1z1nq MoistureCondensation by Dr. W. S. Lassiter, dated 1/16/76

/V Vibration Consnlttee Memo by Dr. J. W. Ramsey, Jr.,updated 1/13/76

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OPERATIONAL PROCEDURES

FOR

MINIMIZING MOISTURE IN THE WTF

BEPRODUCIBILrrY OF THEORIGINAL PAGE IS POOR

INDEX

CASE A - CONSTRUCTION PHASE

CASE B - INITIAL STARTUP AND COOLDOWN

CASE C - CRYOGENIC CONDITION""— - 5=«* AMBIENT CONDITION FORENTIRE TUNNEL ACCESS— 2»» CRYOGENIC CONDITION

1. Weekend, annual, and as required inspections.

2. Repair and maintenance as required.

3. Ambient test following a cryogenic test.

4. Cryogenic tests.

CASE D - CRYOGENIC CONDITI ON *=—*•— :s=- AMBIENT CONDITION FORTEST SECTION AND PLENUM ACCESS ONLY,- — *-.. >~ CRYOGENICCONDITION

1. Model modifications/changes during research testprograms.

2. Inspection, repair, and maintenance of testsection, plenum, and model support apparatusas required.

CASE E - CRYOGENIC CONDITION —•.-•:»•> MODEL ACCESS THROUGHMODEL ACCESS HOUSING — -- -^ CRYOGENIC CONDITION

1. Model adjustments during research test program.

2. Model inspection., repair, and maintenance asrequired .

CASE F - AMBIENT CONDITION FOR ENTIRE TUNNEL ACCESS— ---- --~AHBITTT TEP.T — ----- /u-'y>T"Hfr r.O:-!DTTTON FOR ENTIRKTUi'iiiEL ACCLUS

1. Ambient tests.

2. Model chanpo/modif ication/ad juGtinrnt duringresearch tent programs.

3. Inspection, repair, and rnai jvt cnnncc as required.

NOTE: (TBD) indicates that a number is to be determined.

NOTE: Many of thoso proi.-edur-es imply m^nu.-.:l opera ti CMIH birt inreality will bf> au toin,! L Ic control operations.

DESCRIPTION OF PROCEDURES

CASE A - CONSTRUCTION PHASE

During the construction and installation phases it is highlyimprobable that the tunnel shell interior and the insulationsystem can be completely protected from humid environments.It is recommended that once the shell is complete andinstallation of the insulation commences, all tunnel shellopenings to the outside environment be closed and work occurthrough only those accesses exposed to the environment insidethe building (such as the test section) which is conditionedby air conditioning and heating. It is recommended thatrelative humidity of this conditioned environment not exceedabout 50 percent. This will prevent the insulation, uponbeing installed, from experiencing the very high relativehumidities often occurring in the Tidewater area.

CASE B - INITIAL STARTUP AND COOLDOWN

1. Close and secure all tunnel accesses (includingexhaust valve).

2. Open vacuum system valve and evacuate tunnel to about.3 psia pressure.

3. Close vacuum system valve and backfill tunnel to aboutone atmosphere with dry heated air.

4. Repeat steps 2 and 3 until tunnel dewpoint is downto about 435 R. During this time maintain tunnelstream temperature above dewpoint temperature.

5. Open vacuum system valve and evacuate tunnel to about0.3 psia pressure.

6. Close vacuum system valve.

7. Start fan and operate at minimum speed.

8. Open LN« valve and inject Ll\' into tunnel at low massflow rate.

9. When pressure increases to about one atmosphere, openexhaust valve to maintain constant pressure in orderto purge system.

10. Never allow stream temperature to exceed 635 R.

11. Purge system by maintaining constant pressure for atleast (TBD) hours with a stream dewpointtemperature of below 420 R.

12. Maintain stream temperature above dewpoint of streamuntil dewpoint temperature decreases below 380 Rand stream oxygen level less than (TBD) percent byvolume.

1.°. Att ..In tc-sf con-Jit-i-'nn by controlling L!-' flow r.-;tn,fan speed and pressure.

x . CASE C - CRYOGENIC CONDITION &-* AMBIENT CONDITION FOR/ ENTIRE TUNNEL ACCESS «~>- CRYOGENIC CONDITION

I. CRYO TO AMBIENT

1. Close• LM2 inlet valve.

2. Operate fan such that stream is heated andmaintained at about (TBD) R for at least

(TBD) hours to warm tunnel interior.Maintain tunnel pressure at about oneatmosphere.

3. If at end of a week, shut off fan and allow tunnelto warm up over weekend without opening. Assurethat exhaust v^lve is closed.

U. If not at end of week, continue heating tunnelas in step 2 until liner and insulation cons: d'.'re-risufficiently warm for opening tunnel. 0

5. Shut off fan and close exhaust valve.

6. Open vacuu™ system valve? and evacuate 1unn:;:lto .%(*'D?-r psia with vacuum system.

7. Close vacu-.:" system valve and rcpre?~uri;cetunnel to about one atmosphere v.-jth dry :, hi'^t^air .

8. Repeat steps 5 and 7 until oxygen level in •;•.:••..is at least 20 percent by volume.

9. Open doors to tunnel and perform inspection,repair and nc;i.nten:ince as required. Duringthis tiino main tain oxygon level at 20 percentor above by volurs? and air tc-mperatur-e abovo500 R by jnaintaining a positive pressurein the tunnc-1 with dry, heated air.

10. During any time the fan is; not turning and trv..-tunnol coiitn'i n?, dry, heatrd air, maintain a

-2Z.-

II. AMBIENT TO CRYO

1. Close and secure all tunnel accesses.

2. Close dry air inlet valve.

3. Open valve to vacuum system and evacuate tunnelto aboutJ^S psia. Close vacuum system valve.

4. Start fan and operate at minimum speed.

5. Open LN9 inlet valve and inlet LN- at lowmass flow rate.

6. Open exhaust valve to maintain pressure at about15 psia.

7. Maintain stream temperature above dewpoint ofstream until dewpoint of stream Decreases belov:380 R and oxygen level decreases belov; (TBD)percent by v:olume.

8. Never allow strewn temperature to exceed 635 ~.

9. Attain test conditions by controlling LK.~ "in-flow rats, fan speed, and pressure.

-rPEODUCBILrrY OF THEPAGE IS POOR

CASE D - CRYOGENIC CONDITION - 8=- AMBIENT CONDITION FORTEST SECTION AND PLENUM ACCESS ONLY ="CRYOGENIC CONDITION

I. CRYO TO AMBIENT

1. Close LN inlet valve.

2. Close exhaust valve.

3. Shut off fan.

U. Close and secure gate valves.

5. Relieve plenum and test section of pressure toone atmosphere through plenum pressure controlvalve .

bj pero:-:yg:e:-.

6. Purge plenum and test section with _ (TED)second mass flow of dry, heated air untilcontent level reaches at least 20 percent by volumeand until metal surfaces to be contacted v.-arnsufficiently, depending on work to be performed.

- ) 7. Adjust dry air inlet mass flow rate as requiredin order to maintain a _ (TBD) psia positivepressure, an air temperature of above 500 R,and an oxygen level of at least 20 pei'-cent byvolume while working in the test secticr. ?.r.-~.plenum volume.

8. Perform work as required.

II. AMBIENT TO CRYO

1. Close and secure test section and plenum doors.

2. Close dry air exit and inlet valves.

3. Open gate valve bypass valve and pressurize plenumand test section with cold G!;,, from tunnel.

L

4. Open gate valves.

5. Start fan and slowly increase speed.

6. Attain test conditions by controlling LN«~flowrate, fan speed, and pressure.

CASE E - CRYOGENIC CONDITION -• - -»— MODEL ACCESS VIA MODELACCESS HOUSING - SB- CRYOGENIC CONDITION

I. CRYO TO MODEL ACCESS HOUSING INSERTION

1. Close LN? inlet valve.

2. Close exhaust valve.

3. Shut off fan.

4. Close and secure gate valves.

5. Relieve plenum and test section pressure to oneatmosphere through plenum pressure control valv-

6. Condition model access housing tubes with v/jir:;. .dry air.

7. Open plenum and test section doors.

8. Insert and seal model access housing tubes.

9. Circulate warm, dry air through housing such r:.oxygen- level is maintained . to at least I'l- perceby volume and temperature maintained abov-? 5'JJ: j

10. Perform model adjustment/inspection as r <.-•• -.I u :' r •.•_:.

II. MODEL ADJUSTMENT/ INS 1-ECTI 01; TO CRYO

1. Close doors tc housing such that dry ai:;environment in housing is maintained oncepersonnel are evacuated,

2. Retract housing tubes.

3. Close and secure test section and plenum doors.

U. Open gate valve bypass valve and pressuriseplenum and test section -with cold GK~ frontunnel. Z

5. Open gate valves.

6. Start fan and slowly increase speed.

7. Attain test conditions by controlling LN2 "flow rate, fan speed, and pressure.

— 2.5-

CASE F - AMBIENT CONDITION FOR ENTIRE TUNNEL ACCESS fs*~AMBIENT TEST --»— AMBIENT CONDITION FOR ENTIRETUNNEL ACCESS

I. AMBIENT CONDITION TO AMBIENT- TEST

1. Close and secure all tunnel accesses.

2. Close dry air inlet valve.

3. Start fan.

4. Attain test conditions by controlling fan speed,cooling coil water flow, and pressure.

5. Perform test.

II. AMBIENT TEST TO AMBIENT CONDITION

1. Shut off fan.

2. Open dry air inlet valve to maintain positivepressure of (TBD) psia in tunnel.

3. Before' entering tunnel, assure that oxygoncontent is at leaat 20 percent by volume andtenroerature above 500 R.

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