Final Report February 1977

Effect of High-PressureOxygen on theMechanical Propertiesof Alloys

(NASA-CR-150137) EFFECT OF HIGE-PEESS_RE

OKYGEN ON THE MECHANICAL PROPERTIES OF

ALLOYS Final Report (Martin Marietta Corp.)

35 p HC A03/MF A01 CSCL 11F

N77-18250

gnclas

G3/26 17180

REPRODUCEDBY

NATIONAL TECHNICALINFORMATION SERVICE

U.$.DEPAR/14E_IOFCOMMERCESPRINGFIELD,¥A, 221GJ

3_

https://ntrs.nasa.gov/search.jsp?R=19770011306 2018-06-02T07:10:07+00:00Z

MCR-77-103

Contract NAS8-31956

Final

Report February 1977

EFFECT OF HIGH-PRESSURE

OXYGEN ON THE MECHANICAL

PROPERTIES OF ALLOYS

Authors

Fred R. Schwartzberg

John A. Shepic

MARTIN MARIETTA CORPORATION

P.O. Box 179

Denver, Colorado 80201

FOILEWORD"

The work described in this report was performed by Martin MariettaCorporation under Contract NAS8-31956for the Marshall Space FlightCenter (MSFC)of the National Aeronautics and SpaceAdministration.Mr. W. B. MacPhersonacted as ProgramTechnical Monitor at MSFC;at Martin Marietta, Mr. F. R. Schwartzberg acted as Program Managerand Mr. John A. Shepic was Principal Investigator.

This report is submitted in accordance with the reports require-ments list, Item II-B: Final Report, of the Operations Directivefor Contract NAS8-31956and covers work performed during the periodof May17, 1976 through February 17, 1977.

ii

ABSTRACT

An exDerimental programwas performed to determine the effect of30-day high-pressure [69 MN/m2 (i0,000 psi)] oxygen exposure on theunnotched and notched tensile properties of stressed _80%of Oys)and unstressed specimensof wrought 316 stainless steel, Incoloy903, _nel K-500, and cast specimensof Inconel 718. As a con-trol, tests were also performed in atmospheric pressure air and69 _/m 2 (i0,000 psi) nitrogen.

Data showedthat oxygen did not alter the tensile properties ofany of the alloys studied.

iii

CONTENTS

I°

II.

III.

A.

B.

C.

D.

IV.

V°

INTRODUCTION ...................

MATERIAL AND PROCESSING ...............

EXPERI>_NTAL PROCEDURES ...............

Specimen Design ...................

Specimen Stressing ..................

High-Pressure Environmental System ..........

Test Procedure ....................

EXPERI}_NTAL RESULTS .................

CONCLUSIONS AND RECO}_ENDATIONS ...........

APPENDIX

MECHANICAL P_)PERTY TEST DATA ............

Figure

PageI-i

and

I-2

Ii-i

and

11-2

III-i

III-i

Ill-i

111-4

111-6

and

111-7

IV-I

thru

IV-5

V-I

A-I

thru

A-12

III-i

111-2

111-3

111-4

111-5

Specifications for Unnotched Tensile Specimen ....

Specifications for Notched Tensile Specimen .....

Disassembled Stressing Cylinder ...........

Stressing Cylinder Installed in Testing Machine

Schematic Diagram for High Pressure Oxygen

System ........................

Table

III-2

III-2

III-3

III-3

111-5

II-i

I1-2

Ill-]

IV-]

IV-2

IV-3

IV-4

Certification and Composition Data ..........

Thermal Processing Data ................

Loading Data for Stressing Cylinders .........

Data Summary for 316L Stainless Steel ........

Data Summary for Incoloy 903 .............

Data Summary for Monel K-500 .............

Data Summary for Inconel 718 .............

II-i

II-2

III-4

IV-2

IV-3

IV-4

IV-5

iv

I. INTRODUCTION

The objective of this program was to determine the effect of high

pressure oxygen exposure on the mechanical properties of four

materials used in the Space Shuttle main engine. These materials

are :

i) 316L stainless steel;

2) Incoloy 903;

3) Mone! K-500 ;

4) Inconel 718.

The effect of environment on the behavior of metals continues to

be a concern in the prediction of performance for service condi-

tions. Numerous materials considered to be immune from certain

environmental influences have been involved in premature and often

catastrophic failures. A typical example is the titanium-methanol

compatibility problem. Titanium was reputed to be the "wonder"

metal. Early claims that it had excellent corrosion resistance

qualities have now been tarnished by the hot salt corrosion fail-

ures and its low threshold in methanol. With each succeeding

failure, the technical community continues to reevaluate its

ability to predict materials compatibility based on factors such

as similitude, general description, engineering judgment, and the

like. A greater reliance is being placed on good, simulated ser-

vice testing.

During the past decade, much research has been conducted in the

area of "environmentally induced embrittlement." This descrip-

tor is used to differentiate from embrittlement that results from

the deleterious species inherent in the metal, such as hydrogen

in solid solution, that can result in delayed failure. A signif-

icant portion of the environmentally induced embrittlement data

obtained during recent years has dealt with the effect of hydrogen.

The increased uses of hydrogen at high pressures and temperatures

have resulted in the embrittlement in materials previously thought

to be immune from embrittlement. A significant amount of data is

currently available to characterize the effect of hydrogen on the

mechanical propert behavior of metals. Data for gaseous oxygen,

particularly at high pressures, are relatively scarce.

The effects of oxygen and nitrogen are anticipated to be somewhat

different than those described above for hydrogen. Because of

greater atomic size, nitrogen and oxygen effects are generally

manifested by a diffusion-controlled chemical reaction.

I-i

Tiffany, et al.* studied the effect of high pressure gaseous oxy-gen on the crack growth threshold of Inconel 718 and found no ef-fect at i000 psi. No attempts were madeto evaluate tensile be-havior or the effect of higher pressure. A similar program wasperformed by Bixler and Engstron# on D6 steel at 3000 psi gaseousoxygen pressure. No effect on threshold was observed.

An effect of high pressure oxygen on mechanical properties is morelikely to be manifested as a change in the crack growth threshold.However, preliminary investigation to determine the effect ontensile properties is a low cost, simple approach to assessingthe magnitude of a potential problem.

The specific tests performed in this work consisted of deter-mining the unnotched and notched tensile properties in air atatmospheric pressure and room temperatu_ of the four subjectalloys after stressed and unstressed exposure to the followingenvironments and conditions:

Environment Temperature Pressure

Air Ambient Atmospheric

Oxygen Ambient 69 MN/m 2 (i0,000 psi)

Nitrogen Ambient 69 MN/m 2 (I0,000 psi)

This report gives the findings of the test program.

*C. F. Tiffany, J. N. Masters, and W. D. Bixler: Investigation

of Crack Growth Threshold of In_onel 718 Exposed to High Pressure

Oxygen. NASA CR-I08485, August 1970.

+W. D. Bixler and W. L. Engstron: Crack Growth of D6 SteeZ i_z Air

and H_gh Pressure Oxugen. NASA CR-I14860, July 1971.

I-2

II. }_TERIAL AND PROCESSING

Alloys 316L, Incoloy 903, and Honel K-500 were procured as 1.27-

cm (!i in.) diameter wrought bar stock. The 316L was purchased

in the annealed condition and was reannealed by Martin Marietta.

The 903 and K-500 alloys were procured in the solution treated

condition and then precipitation hardened by F_rtin Harietta.

Tile Inconel 718 was evaluated in the cast form in order to simu-

late application in the Shuttle engine. Unnotched specimens were

procured as standard cast ICI 6.4-mm (;_ in.) diameter test ba_s.

The material for preparation of the notched specimens was obtained

as 1.27-cm (_2 in.) diameter by 15-em (6 in.) long cast rods. The

718 material was purchased from Teledyne Cast Products, E1 _bnte

Division, in the fully heat treated condition in accordance with

specification RBO 170-155.

Heat number identification, source, and chemical composition data

for the four alloys is given in Table II-I.

Data for thermal processing is given in Table 11-2.

a_>e II-i Certification and Composition Data

Heat Mill

Alloy Number Source Composition, Weight Percent

316L 4840

Incoloy 903

_1onel K-5OO

Inconel 718

HH24A80Y

MI4ASK

CV-37

Jones and

Laughlin

Huntingto_

Alloys

Huntington

Alloys

Certified

Alloy

17.28 Cr, 13.03 Ni, 2.07 Mo,

0.02 C, 1.29 Mn, 0.22 Si,

Balance Fe

41.62 Fe, 37.62 Ni, 15.29 Co,

2.8 Cb + Ta, 1.4 Ti, 0.03 C,

0.15 Fin, 0.07 Si

65.08 Ni, 29.29 Cu, 3.13 AZ,

0.48 Ti, 1.08 Fe, 0.16 C,

0.73 Mn, 0.03 Si

53.16 Ni, 18.77 Cr, 3.16 Mo,

5.4i Cb + Ta, 0.97 Ti, 0.70

AZ, 0.12 Co, 0.04 C, 0.07 F_,

0.2 Si, Balance Fe

II-i

Table fI-_ FT_er,_a_ Processing fJata

Alloy Thermal Process

316L

Incoloy 903

Monel K-500

Inconel 718

Anneal 1339K (1950°F), 30 min, Water

Quench

Solution Treat 1227K (1750°F), 1 hr,

Air Cool

Age 922K (1325°F), 8 hr, Furnace Cool

at 56K (100°F)/hr to 894K (II50"F),

Hold 8 hr, Air Cool

Solution Treat 1255K (1800°F), 30 min

Water Quench

Age 866K (II00°F) 16 hr, Furnace Cool

at 14K (25°F)/hr co 755K (900°F),

Air Cool

Homogenize 1408K (2075°F) i0 hr, Cool to

1311K (1900°F) and Solution Treat for

2 hr, Cool

Age at 1005K (1350°F), 8 hr, Furnace

Cool at 56K (100°F)/hr to 894K (II50°F),

Hold for 8 hr, Air Cool

11-2

III. EXPERImeNTAL PROCEDURES

This chapter describes the specimen design, specimen stressing

scheme, high-pressure environmental system, and test procedure

used in conduct of the work performed.

A. SPECImeN DESIGN

Unnotched and notched tensile specimens were designed in accor-

dance with ASTM Specification E8 requirements. The unnotched

specimen, shown in Figure llI-i contains a 6.4-mm (_ in.) gage

diameter and 2.54-cm (I in.) gage length. The notched specimen

utilizes a standard 60 deg vee-notch, 50_ notched area, to give

an elastic stress concentration factor \!IKtl of 8 (Figure III-2).

SPECIMEN STRESSING

A simple scheme for stressing specimens in high-pressure oxygen

and nitrogen was used. Triplicate specimens of the same alloy

and specimen type were joined by threaded couplers and loaded in-

to a simple stressing cylinder (Figure III-3) consisting of a

cylindrical body, end plates with a centering shoulder, and load-

ing nuts. Figure III-4 shows the stressing cylinder installed in

a testing machine.

One specimen of each set of three was strain gaged with a bonded

resistance gage. The specimen was loaded in a testing machine

to determine the strain level at the desired force. The cylinder

was then assembled and the train reloaded to the desired level.

The loading nuts were then tightened as the machine was permitted

to slowly unload. Tightening of the nuts was performed in a man-

ner that did not permit the strain to exceed the desired level

during machine unloading. After loading, the strain gage leads

were pulled off the specimen through the pressure equalizing hole

in the cylindrical body.

All specimens were stressed to a nominal 80% of the unnotched

yield strength of the respective alloy. Actual data, Table III-l,

show that the stress levels were in good agreement with the de-

sired values.

III-i

!i-20 UNF-3A

-_0._50 -+0.001

002@P.D. 0. I

Section A-A No Scale

Figure III-1 Specifications for Unnotched Tensile Specimen

Sym

_--1.25_ 0.62 _-- [

tl I!!* LA *

_ 60° _

• . Max

Section B-B

No Scale

0. 250@P.D. 0.0021\• B

/--0.353 _ 0.001

/ _) P.D.. 0.0021

Section A-A

Figure III-2 Specifications for Notched Tensile Specimen

111-2

q_

r_

@

@

(o

_0

_o

III-3

Table IIi-1 Loading Data for Stressing Cylinders

Alloy

316L

Incoloy 903

Monel K-500

Inconel 718

Specimen

Type

Unnotched

Notched

Unnotched

Notched

Unnotched

Notched

Unnotched

Notched

Stress Level (% _ )ys

for Indicated Environment

Oxygen

77.1

80.0

79.2

77.4

80.0

76.6

80.7

77.9

Nitrogen

81.2

80.0

80.4

73.9

78.2

78 .i

82.8

81.0

Specimens for evaluation in atmospheric pressure air were dead-

weight loaded as triplicate specimens joined by threaded couplers

in Satec creep racks. Eight.racks were used for the 30-day ex-

posure period.

C. HIGH-PRESSURE ENVIRONMENTAL SYSTEM

The high pressure oxygen system was designed for simplicity, safety,

and a high degree of cleanliness. Because of the safety hazards

associated with pumping oxygen to 69 MN/m 2 (i0,000 psi), we elected to

use a liquification-vaporization pressure intensification approach.

Basically, we charged a pressure vessel submerged in a liquid

nitrogen bath with gaseous oxygen. The oxygen liquified. We

then pressurized the liquid oxygen, drained the LN 2 bath and per-

mitted the LO 2 t9 vaporize and provide pressurization for the test

chamber. Figure III-5 is a schematic diagram of the system. All

of the high-pressure apparatus was contained in a high-pressure

test cell. As shown by the diagram, the valves between the LO 2

supply/pressurization system and the specimen vessel and oxygen

supply bottles are remotely operated. The pressure gage was ob-

served through a safety window.

III-4

_-GO

rI _'x_

II cn a)

L, _

ill.__ ,--__

Irl_I! .- _

,,, ._g._Ill

,__!ll •!l I ._.,III _

iI I m!lll !

-e_ !

-)

e-

)

°l

q_

%

_3

.4a

Figure III-5 111-5

The specimen and supply vessels were fabricated from 6.4 cm (2.5

in.) O.D. by 1.59 cm (5/8 in.) wall 304 stainless steel pipe. To

avoid nonmetallic seals and gaskets, the pressure vessels were

fabricated by welding stainless steel plugs in each end. One end

of each vessel contained a welded-in pressure tubing connector.

Each vessel was radiographically inspected to assure conformity

to AS_ Code _51 and pressure tested to 103 _/m 2 (15,000 psi).

The specimen vessel was then cut near the end to permit loading

of the specimens. After loading the vessel was welded shut and

the new weld joint radiographically inspected.

All system components, test specimens, and stressing cylinders

were GO2-cleaned before assembly.

For evaluation of the effects of nitrogen, the testing chamber

was loaded, sealed, and radiographed as described above. Pres-

surization was obtained by using a ii0 _H/m 2 (16,000 psi) pump.

D° TEST PROCEDURE

The procedure used for the 30 day 69 _H/m 2 (i0,000 psi) oxygen

exposure is summarized below:

i) Test specimens and stressing cylinder components were cleaned

and subsequently handled with white gloves;

2) Specimens for stressed testing were loaded into stressing

cylinders;

3) Cylinders were loaded to desired levels;

4) Cylinders were then recleaned, placed in poly bags and de-

livered to the Propulsion Engineering Laboratory;

5) Specimens and cylinders were placed in a test container, unit

was welded closed, radiographed and taken to high-pressure

test cell;

6) Following assembly of test chamber in cell and verification

of system integrity, test was initiated;

7) Pressure in the test chamber was monitored daily for the 30-

day test period;

8) Following the exposure period, the end of the chamber was cut

off, and specimens were removed and placed in poly bags ready

for testing.

III-6

A similar procedure was used for the nitrogen exposure.

The oxygen specimens were delivered to the Mechanical Property

Laboratory and tested within an 8-hour period following removal

from the test chamber. Cylinders were unloaded and unnotched

specimens gage marked for elongation measurements. All speci-

mens had been measured for cross sectional area prior to expo-

sure.

Unnotched specimens were evaluated _Jith a mechanical extensometer

to provide stress versus strain behavior into the plastic range.

Notched specimens were tested to failure giving only the failing

load.

The nitrogen specimens were placed in polT_ bags under a positive

pressure of nitrogen and the bags were heat sealed. These speci-

mens were tested within 2 hours after opening each bag.

III-7

IV. EXPERIMENTALRESULTS

All exposures were completed satisfactorily. No failures occurredduring the exposure periods.

Triplicate specimenswere exposed and evaluated for all test con-ditions.

Test results are summarizedby alloy in Tables IV-I through IV-4.These tables comparethe six mechanical properties determined forthe stressed and unstressed conditions of the three environments.No significant effect of environment was apparent for any of theproperties as a result of environment. The variation in proper-ties was deemednormal for the triplicate specimenexperimentused. Of particular significance is the good agreementbetweenconditions for the notch/unnotch strength ratio data. Notch be-havior is frequently a sensitive indicator of environmental ef-fects.

A detailed presentation of the unnotched data for each of the ex-posure conditions is given in appendix Tables A-I through A-6.Similarly, notch data are given in Tables A-7 through A-12.

IV-I

Table IV-I

OD _--0 _-_

.._._ ._-Z w_

<o

v

O

¢,4

oo

-.T_D

-.T

oo

--,.I"

<O

v

c-4co

4-J_9

CDoo

OD>_ r--M

OoO

c_

c_

cq

r_

'..o'_o

--T

o--,

c-4

'..o

o

v

".D

oO

cq

q_v

&

L_

'7

c

oD _--

0 ",_

•_w -.T

CD

0

_r_

• 0

°oov

4-I

< un

O9

C_

c_v

c_c-4

CO

',,.O oO

O

cq

O

',.O_D

_D

O

v

C_

ov

c-4

c_ r_ oo

O

oO

v

c_

o_

_0

o_

,_ ..Mv

=-O

0

0

0

4_1

0 IJO

M _

u'3

0

0CC

C

0 _-_Z _c

IV-2

!

Table IV-2

F

L_

P_

o

0

0c,.l

_A? tn

N .er0 ,---t

0

co

¢.1

% _ ¢¢3

'.D

cl o_ ¢',1

0

Z _

0cxl

0 ,'_

_ 0m t",l

•_ ".0

(D,--4

_-__-_ ._

•_ _ _

,--t

c-I

v

u'3

r_p_

v

¢Xlr--t

0()

-..T

¢xlv

,.-t

u'3

t_

,--t

cO

,.--t

O

v

Le3

u_r_,--t

p_Oc-4,--4

t3(3

,goo

v

oO

v

O _4,--.t

v

v,-tO

.r-4

¢_ -.-t

t_ u'3

O

¢'.1

tt_,--t

C ,---_ _ 0_ 0

•_ ._ ",'_ 0_._ _._' _ ._

ul _.<

O ,I-_ O

xD

,.-.4r¢3

,-4

,.D

,--4

t_3

t_

0

o_

o

IV-3

Table IV-3

_) ,.Db,O _,40

•r4 r-_

Z

p__0

C'J

O0

q_ 0_ Lq

cO

C u'_

0c4

•H ,-_Z

-.T

_b ,.D",,D

I qJ_ ,.0

0

m ,.D

m

E _c4

O

v

if3t_

,.4O

cO

kq

cO,--4

O

v

c',lr_ t'M t_

t_cO

cO

O

v

Otmr_ ¢M

¢xl

c-4

r_

oDO

O,.Mv

r_u_t_

,gO

P_

P

,--t

O,-.4v

p_ AO

t'-qoO,-4

g-o00

0cq

wh

0

_D0o_

C ,,"-, _ 0-_,1_ 0 _:

_ "_ 0

t.l-4 .._-OO _ O

•_ _-4

A

A

0

0

b B

eW_0 -_

IV-4

co

%

4_

c_

£

%

Table IV-4

4-1 _1

Z

0

_D

0 v

0

_ _-_

u_

@ -..?t_3 .,--I0

c'q-r_ C3Z

--.T

0Lr',

c; ,-_0 "---/b.8

N 00

"0 0",

,-.-I

.I.JtO _ oO

0

-,-I

_; _-__-_ ._

r_

co ,--tt_

C-.l

v

,.D -.:1-,---t c--I

¢M

O

O

u'3c-,I

,-.-4t"4_q

00

,-.4

,g¢xl

cqt".-cO

,g,--t

O

_D

v

O

,--4v

,.D,-4

c_

O

v

O

O

u'3c-I,--I

'.D O

,dv

_ c..l

•r_ Z

J0

4-)

0

0

C0

0 .I.n 0-,-I _-I

,--I 4Jc-_

O,-_Z

o_

Lr_

,--t

C'q".1"

,--I

C_

C_-.1"

,.-q

U_

,--4

0

-IJ

0 c_

C .C

O 0

0Z

IV-5

V. CONCLUSIONS AND RECO_IENDATIONS

The results of this investigation show that 69 _/m 2 (i0,000 psi)

oxygen exposure has no effect on the unnotched or notched tensile

properties of 316L, Ineoloy 903, Mone! K-500 and cast Inconel 718

alloys.

Although tensile properties are unaffected, it is difficult to

speculate behavior in terms of crack growth threshold. If the

application necessitates, a similar program using fracture mechan-

ics specimens to evaluate threshold behavior may be warranted.

V-i

APPENDIX

Mechanical PropertyTest Data

%

-:+-3

%

%.

%.--..3

%

%

++,%

_+_,

_b5:,

23_+_

_i _

r,+,I- A

J

Table A-

_LD

U

,-'4 Z

t_

0

0.H

_J

J0

.,-I

c_C2

0,-4

_-J

•_ _ _ _

0

<

0

c_

,.--t I

> > > >< < < <

°• . • ° _ " °

> t:> > ;>< < < <

• . o i-- • ° ° °

• ° ° o

¢%lO_lcq 0",+,I ¢'.Ic_r--I r'_ OOCOCO

,--l;.---4,--I +

< < < <

.... _ _ _

_t_ _ _ O_ -_ _ _ O__ _ _ _ _ _ _0_

rm 0 03

I

0 ¢1,--I ,-H ,"0 • O

0

A-1

Table A-2

-q

%

%

%

%

%

.4&

%

%

%

.37;:

I

0 _ ,--4

,.-4 .l-a c'.,

O_ Z

0

0

g0

.,.-i

0 ....

-r'4 IJ _ _'4 t"-.1C_I_mc;

m

_._ _c_•_ m _ N mom

o

b0

>

_ c_ Lt_ Oq• °

O_ O0 U'_,-_ ,-q ¢q Oq

__ _ _ _i _

• . ._ - . .vvv v vvv vv_

08 b_ b_ O_

r..- ,,.-.I 0-, ,c'-,.I ,,.-.-I ,,,-_ c,"_ r--. -.,1- ,--_ 0 c-,I oo

> > > >

> > h >

• ,_ '_ _ _ _o _ _ __ _ _ ,_ _ ,_

0"-,O009 O0 ....1" -.1" Lm Lt'h u_ r---,_1 ,.-I ,,,-,-I ,,..-I r-- r._ r.-. 09o0oo,,-I ,,-,,,,.I,-.I ,-4

_ _ ooo o _ _ _

_ _ _ _ _ _ _ o o _o

rm 0 oo0 0o'_ um

I

0

0 _ 0

0

A-2

Table A-3

%

%

c_

k_

%

%

%

%

la

%

r_

%

U

%

%

c_

I

%

L_

cO

_qDu,_ >,0

.r.t

_-I _1 cxl

O_--IZ

0

0.r-I

0

0_

O

4-1

it"

O

,--I"

><

c-4 ,-4 _,I _

> > >< < <

_ '..O _o ,--t co _'h

o_o,oo I'_ r--.

;> > :> >< < <, <

",.D oO C_ C_ "..D b-- O_ u"_ O ...1- t_ r'-. CO

_'_ --.._ C'-I f'_ ---.T Oq ._ --.1" -.T c"3 u'5

• °

< < < <

O O• ,

o,I _,1 o-I¢,'3 o"_ c"_

vvv

< <

• , -- --°

_ _ _O_

b..0 0.0> >< <

O', "-.1" O

O c'_ ;--_ cq ¢q

("q _'q. C'q

•,.O c-q

oo r_ oo

vvv

0.8_>

<

O

O_o

• °°

t8 b..8> >< <

-.1" Lm '.,.1"

_ _1 O_O _ _ _ _O_

_ _ _ L_ _ _ _ _ _ _ _ _ O O O

C'm

0 oo0 0

I;>, 'v' ,._0

I--4 _ I-4

A-3

,9..,

_3tO%

_d

%

%

_Q

%

¢9%

"i-3

%

%

I

Table A-4

"4 v

o

o

4_

o

4J

o_r!o

v

,._ u,4

b..00

°r'4

r/l

_ v

•_ _ _w E

o,---t

> > > >< < < <

oo -.,o,_o_::) oooo o'.,o-,

> > > >

_ , _ _ _ _

> > > >

> > > >< < < <

• ° ° °

><

£

< < <

_ _ _ _'_

,-1

cm

r-h o oo

o_ Lt% r,-,.I

o

o ¢J o

I--I _-4

A-4

Table A-5

%

cQ

7T

%

a_

%

_d

25E_

%

%45

%

4-',

%

2".,_%

%

. &

_-_

%

%

I

t*.4 > 00 _,-I

_ 4.ao4

t..,-i

0

0.,-.t

I;n:J _

0.,-4

0

1...1 _

•_ _c.

;23 _ _._

0,.--4,--4<

|__m

< < < <

• . • • ° ° ° ° . ° °

--.1-

> > ;- >

• , .,, .,, ,,

> > > >

• ,° _ --

> ;> [:> _>

,,, , ,,°', ,,. • ,,

_ _ _1 _ o_ _ _

c'q 0'_1 t'q e-,! 0 0 ,,-.I 0 ....0 L", L_ _ r--. "....o r_.

.-. q, .-.0 cO

'o_v

....J v

CJD b-.O O8 Ob> > _ :><_ < < <:;

• . . .

..oorm 0 cO0 0 _'_Oh u", v---

I

0

0 ¢_ 0

A-5

%

_44

%

%

%

/3

%

4_

%

%

%

%

%

%

%

%

I

Table A-6

t_ U._

c3 _

"_ (.3

0

0

0

O

v

H-_ _

0

• ._ • • • . .

>

cr-i

• ,°

>

Ir'--'c-4

o4CxlC'_l cq c_r--Ic'q 04 r._ o0cc,_o

O c.q '..D O'_ cO _ _ r--.,. O ,,--I

o_,--1v

_o

c'_ O ooO O ,-t

I_ ,-_

O

O 0_ Ord _ o

._9.o

A-6

Table A-7

Room Temperature Ambient Air Notch Tensile Properties

Alloy

316L

Inco loy 903

Monel K-500

Inconel 718

Notch Tensile

Strength,_/m L (ksi)

748 (108.6)

743 (107.8)

738 (107.1)

743 (107.8) Avg

1963 (284.9)

1931 (280.2)

1890 (274.3)

1928 (279.8) Avg

1273 (184.8)

1306 (189.6)

1257 (182.4)

1279 (185.6) Avg

1479 (214.7)

1477 (214.4)

1461 (212.2)

1472 (213.7) Avg

Notch/Unnotch

Strength Ratio

1.35

!.35

1.12

1.51

A-7

Table A-8

?00,'7 f_eT_._era t__.raia _bie;_t Air

.7otch Tensile Properties after Stressed Expos _re

Alloy

316L

Incoloy 903

_nel K-500

Inconel 718

Notch Tensile

Strength,

MN/m 2 (ksi)

741 (107.6)

739 (107.2)

762 (110.6)

748 (108.5)

1911 (277.4)

1798 (261.0)

1696 (246.1)

1802 (261.5)

1266 (183.7)

1350 (196.0)

1308 (189.9)

1431 (207.7)

1497 (217.3)

1421 (206.2)

1450 (210.4)

Avg

Avg

Avg

Avg

No tch /Unno tch

S treng th

Rat io

1.35

1.26

1.14

1.42

A-8

?able A-9

empe_ a_r_ 72otch _ _

pos_e in High Press.:re Oa_'yTen

ProperVies aften Unsvressed St'_-

Alloy

316L

Incoloy 903

Monel K-500

Inconel 718

Notch Tensile

Strength,

_/m 2 (ksi)

732 (i06.3)741 (107.6)

731 (106.1)

735 (106.7) Avg

1903 (276.3)

1961 (284.6)1874 (272.0)

1913 (277.6) Avg

1317 (191.2)

1268 (184.0)

1310 (190.2)

1299 (188.5]

1456 (211.3)

1481 (215.0)

1497 (217.2)

1478 (214.5) Avg

Notch/Unnotch

Strength

Ratio

1.33

1 . 34

1.13

1.43

A-9

-ai;_e A-iO

.o _u,_ :e,_o_&_ Properties

0_2 £ e,:

afret Stressed Expos;me

Alloy

316L

Incoloy 903

}bnel K-500

Inconel 718

Notch Tensile

Strength,

_/m 2 (ksi)

783 (110.8)

721 (104.7)

754 (109.4)

746 (108.3)

1768 (256.6)

1950 (283.1)

1917 (278.2)

1878 (272.6)

1255 (182.2

1273 (184.7)

1217 (176.6)

1248 (181.2)

1550 (225.0)

1524 (221.2)

1477 (214.4)

1517 (220.2)

Avg

Avg

Avg

Notch/Unnotch

Strength

Ratio

1.34

1.31

1.08

1.51

A-10

Ta_ie A-i7

Room _Te_erat_a_e f/otch Tensile Properties

pos_re in High Pressure fJitroQen

_aiVer Unsvressed Ex_-

Alloy

316L

Incoloy 903

Monel K-500

Inconel 718

Notch Tensile

Strength,

_flq/m2 (ksi)

721 (104.7)

730 (i06.0)

732 (106.3)

728 (105.7)

1952 (283.3)

1937 (281.1)

1913 (277.6)

1934 (280.7)

1299 (188.5)

1286 (186.7)

1311 (190.3)

1299 (188.5)

1405 (203.9)

1422 (206.4)

1430 (207.5)

Avg

Avg

Avg

1419 (205.9) Avg

Notch/Unnotch

Strength

Ratio

1.32

i. _5

1.14

1.39

A-II

r_ i ?_,,a_e A-12

ae_'_,_er_2 e ;Jot_h Tensile Properties alve ;_ Stresse,_ Ex-

posture in High Prass_a_e Witrogen

Alloy

316L

Incoloy 903

Monel K-500

Inconel 718

Notch Tensile

Strength,

_q/m 2 (ksi)

729 '

743

739

737

(105.8)(107.9)(107.2)

(107.0) Avg

1943

1913

1962

1939

(282.0)(277.6)(284.7)

(281.4) Avg

1264

1370

1362

1333

(183.4)

(198.9)

(197.7)

(193.4) Avg

1483

1563

1530

1525

(215.3)(226.9)

(222.0)

(221.4) Avg

Notch/Unnotch

StrengthRatio

1.36

] .36

] .16

i .49

A-12