NASA Technical Memorandum

NASA TM - 8 6 5 9 5 1

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A PRELIMINARY MECHANICAL PROPERTY AND STRESS CORROSION EVALUATION OF

DIRECT AGED INCONEL718 BAR MATERIAL VIM-VAR WORK STRENGTHENED AND

By J . W. Montan0

Materials and Processes Laboratory Science and Engineering Directorate

April 1987

(bASA-TB-86535) d E R E I X W I b I I I Y B E C H A N I C A L N87-262 16 EgOPERTX AND SIEESS CCEEOSlCL E V A I U A T I O Y GP fTIM-VIIE HORK S a h E I G l H E N E C AbE LIOEC'f AGEC IhCONIEL 718 E A E W A ' I E R I I L ( I r A I A ) 28 p Unclas A t a i l : NlXS RC A03181 A 0 1 CSCL 113' 63/26 0085593

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NASA National Aeronautics and Space Administration

George C. Marshall Space Flight Center

MSFC - Form 3190 (Rev. May 1983)

https://ntrs.nasa.gov/search.jsp?R=19870016783 2020-04-25T21:44:11+00:00Z

TECHNICAL REPORT STANDARD TITLE PAGE I . REPORT NO. 2. GOVERNMNT ACCESSION NO. 3. RECIP IENT’S CATALOG KO.

NASATM - 86595 1. T I T L E AND SUBTITLE 5. REPORT DATE

April 1987 A Preliminary Mechanical Property and Stress Corrosion Evaluation of VIM-VAR Work Strengthened and Direct Aged Inconel 7 18 Bar Material

. 6. PERFORMING ORGANIZATION CODE

EH22 8 . PERFORMING ORGANIZATION REPDR r # 7. AUTHOR(S)

J . W. Montano 3 . PERFORMING ORGANIZATION NAME AND ADDRESS 10. WORK UNIT NO.

George C. Marshall Space Flight Center Marshall Space Flight Center, Alabama 358 I2

2. SPONSORING AGENCY NAME AND ADDRESS

National Aeronautics and Space Administration Washington, D.C. 20546

Technical Memorandum

1.3. SPONSORING AGENCY CODE

I 15. SUPPLEMENTARY NOTES

Prepared by Materials and Processes Laboratory, Science and Engineering Directorate.

IS. ABSTRACT

This report presents a preliminary mechanical property and stress corrosion evaluation of double melted [vacuum induction melted (VIM), and vacuum arc remelted (VAR)], solution treated, work strengthened and direct aged Inconel 718 alloy bar [5.50 in. (13.97 cm) diameter] processed by Wyman Gordon.

Two sets of tensile specimens, one direct single aged and the other direct double aged, were tested at ambient temperature in both the longitudinal and transverse directions. Longitudinal tensile and yield strengths in excess of 200 ksi (1378.96 MPa) and 168 ksi ( 1 158.33 MPa) respectively, were realized at ambient temperature, for the direct double aged specimens.

N o failures occurred in the single or double aged longitudinal and transverse tensile specimens stressed to 75 and 100 percent of their respective yield strengths and exposed to a salt fog environ- ment for 180 days. Tensile tests performed after the stress corrosion test indicated no mechanical property degradation.

17. KEY WORDS

Vacuum Induction Melted (VIM) Vacuum Arc Remelted (VAR) Work Strengthened and Direct Aged Stress Corrosion

19. SECURITY CLASSIF . (d thl* 20. SECURITY CLA

18. D ISTRIBUTION STATEMENT

Unclassified - Unlimited

il F. (of thlm page) 21. NO. OF PAGES 22. PRICE

I 27 I Unclassified I Unclassified

USFC - Form 3292 (*Y 1969)

ACKNOWLEDGMENT

Mr. Ken Kohlstrom, Wyman Gordon - Sr. Product Metallurgist - Mr. Peter Rice, Wytnan Gordon - Metallurgical Technician - Consultation and independent mechanical property evaluation.

TABLE OF CONTENTS

Page

SUMMARY ........................................................................................................

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

EQUIPMENT AND TEST SPECIMENS ....................................................................

MATERIAL PROCESSING ....................................................................................

STRESS CORROSION PROCEDURE .......................................................................

RESULTS AND DISCUSSION ...............................................................................

CONCLUSIONS ...................................................................................................

REFERENCES .....................................................................................................

iii

LIST OF TABLES

Title Page Table

1.

11.

111.

IV.

V.

VI.

VII .

Chemical Composition of 5.50 in. (13.97 cm) Diameter Double Melted (VIM-VAR) Direct Aged Bar Processed by Wyman Gordon.. ................................... 6

Mechanical Properties of Inconel 7 18 Alloy Work Strengthened and Direct Single and Double Aged Bar Processed by Wyman Gordon from Allvac Heat E563. [MSFC versus Wyman Gordon Data]. ..................................

Mechanical Properties of Inconel 7 18 Alloy Work Strengthened and Direct Single Aged Bar Processed by Wyman Gordon from Allvac Heat E563. Lorigitudinal Tensile Specimens ...............................................

7

8

Mechanical Properties of Inconel 7 I8 Alloy Work Strengthened and Direct Siriglr Aged Bar Processed by Wyman Gordon from Allvac Heat E563. Trarisverse Tensile Specimens ................................................. 9

Mechanical Properties of Inconel 7 18 Alloy Work Strengthened and Direct Double Aged Bar Processed by Wyman Gordon from Allvac Heat E563. Longitudinal Tensile Specimens ............................................... 10

Mechanical Properties of Inconel 7 I8 Allow Work Strengthened and Direct Double Aged Bar Processed by Wyman Gordon from Allvac Heat ES63. Transvcne Tensile Specimeris ................................................. 1 1

Summary of Tensile Tests Performed on Work Strengthened and Direct Aged Inconel 718 Alloy Bar. After 180 Days Exposure to a 5% NaCl Fog Environment ........................................................................... 12

LIST OF ILLUSTRATIONS

Figure Title Page

I . MSFC Tensile Test Specimen Configurations .................................................... 13

2. Views of Sectioned, Solution Treated, Work Strengthened and Direct Aged Inconel 7 18 Alloy.. ..............................................................................

Enlarged View of Figure 2(C) Showing Longitudinal Specimens Locations..

14

15 .................. 3.

4. Sectioned View of Solution Treated, Work Strengthened and Direct Aged Inconel 7 I8 Bar Used for Evaluation of Transverse Specimens of Wyman Gordon Processed Material .................................................................. 16

5 . Trans. Specimen Locations and Ident. No.’s in Section 1 of Figure 4 Wyman Gordon’s Sol. Treated, Work Strengthened and Direct Aged Inconel 7 18 Bar ........................................................................ ....... 17

6. Trans. Specimen Locations and Ident. No.’s in Section 2(A) of Figure 4 Wyman Gordon’s Sol. Treated, Work Strengthened and Direct Aged lnconel7 I8 Bar 18 .........................................................................................

7. Trans. Specimen Locations and Ident. No.’s in Section 2(B) of Figure 4 Wyman Gordon’s Sol. Treated, Work Strengthened and Direct Aged Inconel 7 18 Bar 19 .........................................................................................

8. Trans. Specimen Locations and Ident. No.’s in Section 3 of Figure 4 Wyman Gordon’s Sol. Treated, Work Strengthened and Direct Aged Inconel 7 18 Bar ................................................................................... . 20

9. Transverse Microstructure of Work Strengthened Inconel 7 I8 Bar ......................................................................... Processed by Wyman Gordon 21

V

TECHNICAL MEMORANDUM

A PRELIMINARY MECHANICAL PROPERTY AND STRESS CORROSION

DIRECT AGED INCONEL 718 BAR MATERIAL EVALUATION OF VIM-VAR WORK STRENGTHENED AND

SUMMARY

This report presents the mechanical properties and the stress corrosion resistance of double melted [vacuum induction melted (VIM) and vacuum arc remelted (VAR)] solution treated, work strengthened and direct aged lnconel 718 alloy bar [S.S0 in. (13.97 cm) diameter] processed by Wyman Gordon.

Tensile test data generated by the Marshall Space Flight Center's (MSFC) Materials and Processes (M&P) Laboratory and by Wyman Gordon are tabulated for comparison.

The moderately work strengthened lnconel 7 18 alloy showed excellent resistance to stress corrosion as evidenced by the mechanical properties of stressed specimens after 180 days exposure to a salt fog environment.

INTRODUCTION

Inconel 7 18 is a nickel base austenitic precipitation hardenable alloy which was developed by the International Nickel Company in the late 1950's. The alloy possesses high strength, excellent corrosion resistance and is used over the temperature range of -423°F (-2S2.8"C) to + 1300°F (704°C).

The alloy is currently being used in the solution treated and aged condition at Kennedy Space Center (KSC) for the solid rocket booster (SRB) holddown studs which are approximately 3.5 in. (8 .9 cm) diameter and 31.5 in. (80.0 cm) length. The lnconel 718 alloy is also used as the mating frangible nuts on the holddown studs.

At MSFC the alloy has found use as high strength fasteners, limited to relatively small diameters due to cold working and hot heading restrictions. Large diameter bar material use has also been restricted to the solution treated and aged condition due to the limitation of,cold work. The normal penalties associated with cold working are loss in reduction of area, loss in elongation, and increased grain size.

Our preliminary investigation indicates a breakthrough by Wyman Gordon in processing large diameter bars of Inconel 718 alloy. Their processing of 5.50 in. (13.97 cm) diameter bar has resu!ted in increased yield strengths, elongation, and reduction of area and a significant reduction in grain size.

The preliminary investigation of moderately work strengthened and direct single and double aged material, as reported in this paper, resulted in a second evaluation of Wyman Gordon’s work strengthened material with higher yield and ultimate strengths. The results of that investigation were published in NASA Technical Paper 2634 [ I ] . Based on that test data generated by Wyman and Gordon and MSFC, the solution treated, work strengthened and direct aged material is being used at KSC in the Biach Industries tensioner which applies the tension load to the SRB holddown studs. This application is reported in the January 1986 Metals Progress Report, “86 Technology Forecast for Superalloys.” Biach Industries has also supplied Vandenberg Air Force Base with tensioners for SRB holddown application.

EQUIPMENT AND TEST SPECIMENS

The tensile properties for Figure 1 (A) and (B) configuration specimens were determined by using a Tinius Olsen (DS-30) Servohydraulic Testing Machine. The locations for the tensile specimen are shown in Figures 2 through 8. The specimen blanks were sectioned from these locations by the MSFC M&P Laboratory.

MATERIAL PROCESSING

The chemical composition of the as received material used in the investigation is shown in Table 1. This material was purchased in the solution treated, work strengthened, and direct single aged condition from Wyman Gordon. The material supplier to Wyman Gordon press converted a vacuum induction melted (VIM) vacuum arc remelted (VAR) 20 in. (50.8 cm) diameter ingot to 12 in. (30.5 cm) diameter round billets.

Wyman Gordon converted the billets on a cogging press to 10 in. (25.4 cm) diameter round billets using a semi-fine grain conversion practice. The billets were then press formed on a cogging press in two operations to yield 6 in. ( 1 5.2 cm) rough round bars. The bars were then special processed to 5.50 in. ( 1 3.97 cm) diameters and single aged at 1325°F (7 18°C) for 10 hours - furnace cooled to 1150°F (621°C) - hold for a total single aging time of 20 hours (repeat for double aging). The processing and heat treatment are documented in the Wyman Gordon report, “Product Test Report No. 362” [2].

The bar ends received by MSFC were sectioned and identified as shown in Figures 2 through 8. Some of the tensile specimens from these locations were given a second aging treatment.

STRESS CORROSION TEST PROCEDURE

A 180 day salt fog exposure test was performed on tensile specimens manufactured to the Figure 1 configuration. The test specimens were stressed to 75 percent and 100 percent of the trans- verse 0.2 percent yield strength prior to exposure to the chloride environment.

The salt fog test followed the procedures of ASTM-B-117-64, “Standard Method of Salt Fog (FOG) Testing,” which specifies a 5 percent salt solution at a pH of 6.5 to 7.2 and a temperature of 95°F (35°C).

RESULTS AND DISCUSSION

1. Tensile Tests

a. Wyman Gordon Test Data

The Wyman Gordon mechanical property evaluation of the [5.50 in. (13.97 cm) diameter] bar is tabulated in Table 11. The tensile test specimen gage diameters were 0.252 in. (0.640 cm) and 0.178 in. (0.452 cm) for the longitudinal and transverse directions, respectively. Wyman Gordon used 12 longitudinal and 8 transverse specimens to evaluate the bar.

The ultimate tensile strength and the 0.2 percent yield strength in the longitudinal direction were slightly higher than those obtained for the transverse direction, regardless of single or double aging. The elongation and reduction of area were significantly different between the longitudinal and transverse directions. Table I1 represents the MSFC condensed tabulation of Wyman Gordon data, which they have thoroughly documented in a Wyman Gordon “Product Test Report No. 362” [2]. MSFC test data is also plotted in Table I1 for comparison purposes.

b. MSFC Test Data

The complete results of the tensile tests conducted at MSFC are tabulated in Tables I 1 through VI. Figures 2 through 8 show the specimen locations and orientations within the bar.

Figure 9 illustrates the transverse microstructure at 1 00x magnifications taken from four loca- tions identified in Figures 3 and 6. Microhardness readings (D.P.H. values converted to Rockwell C) are also shown in Figure 9. These hardness values were consistent for all four locations and averaged Rockwell C -45 + .

The material processing employed by Wyman Gordon using a semi-fine grain conversion practice, when converting the billets from 12 in. (30.5 crn) to 10 in. (25.4 cm) diameter, resulted in a grain size varying from approximately ASTM size 6 to 8 .

A fine grain conversion technique, used later in the production of higher strength large diameter Inconel 718 bar material, resulted in a grain size of ASTM 10 and smaller, as reported in References 1 and 2.

Tables 111 and IV show the mechanical property evaluation of single aged longitudinal and transverse tensile specimens. Although there was an insignificant difference between the longitudinal and transverse yield and ultimate tensile strengths, there was a noticable increase in elongation and reduction of area in the longitudinal direction.

3

Tables V and VI show the mechanical property evaluation of double aged longitudinal and transverse tensile specimens. Once again, there was a noticeable increase in elongation and reduction of area in the longitudinal direction. The double aging treatment indicated a slight increase in strcngth in both tcsting directions without any loss in ductility as compared to the single aged mech- anical properties. For this reason a double aging treatment was later chosen for the evaluation of higher work strengthened material evaluated and reported in Reference 1 .

2. Salt Fog - Stress Corrosion Tests

The stress corrosion test specimen configuration is shown in Figure l (A). Section 2 of Figure 4 was split into two equal thicknesses to facilitate the removal of sufficient transverse tensile specimens to evaluate the stress corrosion resistance of single aged (Section 2A) and double aged (Section 2B) material removed from almost identical locations. Table VI1 lists the mechanical proper- ties for both the single and double aged longitudinal and transverse tensile specimens prior to and after 180 days exposure to the salt fog environment.

There were no tensile failures or loss in mechanical properties after 180 days of stress and exposure. There was, however, an increase in the longitudinal and transverse ultimate tensile and yield strengths of the stressed specimens, a phenomenon attributed to additional work strengthening of the Inconel 718 alloy.

CONCLUSIONS

Based upon our preliminary investigation of moderately work strengthened and direct single and double aged Inconel 718 alloy material processed by Wyman Gordon described in this report, the following conclusions are drawn:

I . A significant increase in ultimate tensile and yield strength can be achieved in large diameter bars of Inconel 718 alloy by the Wyman Gordon work strengthening process without the sacrifice of grain size, elongation, or reduction of area.

2. The Inconel 718 alloy’s excellent resistance to stress corrosion cracking in a chloride environment was not impaired by the Wyman Gordon work strengthening process.

4

REFERENCES

1 . Montano, J . W.: A Mechanical Property and Stress Corrosion Evaluation of VIM-ESR-VAR Work Strengthened and Direct Double Aged lnconel 7 I8 Bar Material. NASA Technical Paper 2634, September 1986.

2. Wyman Gordon Product Test Report No. 362, dated January 28, 1985, Hand Forgings-Alloy lnco 7 18, NASA Space Shuttle, Prepared by Senior Product Metallurgist Ken Kohlstrom, assisted by Metallurgical Technician Peter Rice.

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2 . Gage Section Finish 16-32 RWS.

3. WO File Harks or Nicks P e n i t t e d wl th in Gage Section.

4. I(0 undercutting w i l l be permitted a t Tangency Point o f Gage Section and .125’ i .375”. Radii.

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Figure 1 . MSFC Tensile Test Specimen Configurations.

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Figure 5 . Transverse Specimen Locations and Identification Numbers in Section 1 of Figure 4 Wymun Gordon's Solution Treated. Work Strengthened and Direct Aged [nconel 7 18 Bar.

Figure 6. Tran\\w-se Specimen Locations and Identification Numbers in Section 2(A) of Figure 4 Wyman Gordon'\ Solution Treated, Work Strengthened and Direct Aged Inconel 7 18 Bar.

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Figlire 7 . Trun\ver\e bpecinien Loction\ uncl idenril’ication Nurnbers in Section 2(B) of Figure 4 Wyman Gordon’\ Solution Treated. Worh Strengthened and Direct Aged Inconel 7 18 Bar.

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Figure 8. Transverse Specimen Locations and Identification Numbers in Section 3 of Figure 4 Wyman Gordon’s Solution Treated, Work Strengthened and Direct Aged Inconel 7 18 Bar.

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APPROVAL

A PRELIMINARY MECHANICAL PROPERTY AND STRESS CORROSION

DIRECT AGED INCONEL 718 BAR MATERIAL EVALUATION OF VIM-VAR WORK STRENGTHENED AND

By Joseph W. Montan0

The information in this report has been reviewed for technical content. Review of any infor- mation concerning Department of Defense or nuclear energy activities or programs has been made by the MSFC Security Classification Officer. This report, in its entirety, has been determined to be unclassified.

R . J . SCHWTNGHAhdER Director Materials and Processes Laboratory

*US. G O V E R N M E N T P R I N T I N G OFFICE 1987-730-067f40127

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