AD-755 408 ENGINEERING DATA ON NEW AEROSPACE Battello … · 2018. 11. 9. · AD-755 408 ENGINEERING DATA ON NEW AEROSPACE 0. L. Deel, et al Battello Columbus Laboratories V [ Prepared

AD-755 408

ENGINEERING DATA ON NEW AEROSPACE

0. L. Deel, et al

Battello Columbus Laboratories

V [ Prepared for:

Air Force Materials Laboratory

September 1"72

DISTRIBUTED BY:

Novaol Ticmnic Aormalm SeniU. S. DEPARTMEN1 OF COMiERCE5285 Port Royal Road, Spring ,:4d Va. 22151

milkI! • -

.. .• A F ML-1 R- 2-196,

ENGINEERING DATA ON

NIEW A•ROSPACE ST•UCTURAL MuATLRIALS

0.• .L. DEEL •rgH. Mi NOLIN

B ¢,tioe I 'e

Columbus Laboralaries

TECHNICAL REIPORT AFML-7I-72-196 :5

VOLUME Ne

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|. "v Tdlf TITLE

Engineering Data on New Aerospace Struci al Materials

S 4. 011lCRIFI;|VE "CYI TRS e f e4 ofr a"@ &h"lmA~ikr eFinal Summary Report, April 1971 to July fl72

S. . At)T94Ole-) (La' Ai,aet im , lla)

""eel, 0. L., and Mindlin, H.

IS. IPORT DATE T "0* 4 ProTs Nt. p.m••

September 1972 ,168

$0, CON4TRACT 00 GRANT NO. OR. @sION&T@R AE@Tim~bf~

F33615-71-C-1261 ( ML-TR-72-196IL ;kojecT Mo.] L" • ,•#€©vm. ,Vol. 11

7381 i

Sb. gr.JPOfTY ROM) (A n os owabo Ow SmW eod1Tian. No. 736106

d.d

I'- 10. A VA IL ASILIV/LrINIVATION NoTICES

Approved for public release; dirtribution u:ilimited I KIf. $'JPP,•,INTANY NOTES M. 1SPONiOeINu OLITARY ACTIVITY

Air Force Materials LaboratoryWright-Platterson Air Force Base, Ohio

The major objectives of thils rscearch progran were to evaluate newlydeveloped materials of interest to the Air Force for potential weapons systemusage, and thea to provide 'data sheot" type presentation of engineering datafor these materials. The eftort covered in this report has concentrated on15-5 P1I (H1025) forced bar. HP 9Ni-4Co-0.20C fored bar. PH 13-B Mo (H0l6ia)ro;-ged bar, 7049-T76 extrusions, Ti-6A1-2n.4Zr=-6Mo sheet, Inconel 702 sheet(Aged), &xnd Inconel 706 forged bar (creep-rupture heat trea, m'nt).

The properties investigated include tension, compression, shear, bend,impact, fracture toughness, fatigue, creep and stress rupture, and stress-corrosion at selected temperatures, I

./

DD -JN" 1473

Security Classificmbon

14 -

Security Classification.LINK A LINC( a LINK C

KEY VORD$ ROLEf 0 0 L WT ROLE VT

Mechanical Properties

Chemical Composition

Corrosion Repistance

Physical Properties

Stainless Steel

Alloy Steel

Aluminum Alloy

Nickel Base Alloy

Titanium Alloy

15-5 PH

PH 13-8 No

9Ni-4Co-O.20C

Ti-6-2-4-6

Inconel 702

Inconel 706

- I•

A

s csa

i-i

7!II

ENGINEERING DAtA ON NEWAEROSPACE STRUCTURAl MATERIALS J

!, " a.~~r,-,/• --L IL lZ LA ý.• .IIE

C * t. Dea l .a A'11 M UdLnL

Ai

Iiio Approved for public release; distribution unlimited.

Fr___

FOREWORD

This report was. prepared by Battelle's Columbus Liboratories, Columbus,Ohio, under Contract F33615-71-t-1261. This contrast was performed under ProjectNo. 7381, "Materials Applications", Task No. 738106, "Engineering and Design Data".The work was administered under the direction of the Air Force Materials Laboratory,Air Force Systems Command, Wright-Patterson Air Force Base, Ohto, by Mr. ClaytonHarmswortt tAFML/LAý , technical manager.

This final report covers work conducted from April, 1971, tc July, 1972.This report vwas submitted by the authors on August 4, 1972.

This technicai report has been reviewed and is approved.

A. OlovitchChief, Materials Engineering BranchMaterials Support DivisionAir Force Materials Laboratory

ii

- - ---- - .

TABLE OF CONTENTS

Page

INTRODUCTION ................. ............................... 1

MATERIALS INFORMATIA'N AND TEST RESULTS ..... ................... 3

15-5 PH Stainless Steel ................ .................... 3Material Description. ............ ................... 3Processing and Heat Treating ............ .............. 3Test Results .......... .......................... 5

liP 9Ni-4Co-O.20C Alloy Steel ....... ................. ... 21Material D2s-zrip'X LL . .. . . . . . . . . . .. . . .. . 21Processing and Heat Treating .... ............... ... 21Test Results ............ ....................... .... 21

PH 13-8 Mo Stainless Steel ..... .................. 41Material Description ..................... 41

Processing and Heat Treating ........ ............... 4CTest Results ................. ....................... 41

7049-T76 Aluminum Extrusions ..... ............... ..... 60

i Material Description ...... ....... ................... 60

Procebsing and Heat Treating ..... ............... .... 60Test ReLsults ............. ...................... .... 60

Ti-6AI-2Sn-4Zr-6F% Alloy .............. ................... 78¶ I LtilL . . . ... ...................... . ..

Processing and Heat Treating ..... ............... .... 78Test Results .......... ........................... 78

Inconel 702 Alloy ........................................ 96Material Descriptior ....... ................... ..... 96Processing and Heat Treating ..... ............... .... 96Test Results ............ ....................... .... 96

Inconel 706 Alloy ............................... . . 113Material Description ........ ................... .... 113Processing and Heat Treating ...... .............. .... 113Test Results........... ....... .................. ..................... 113

DISCUSSION OF PROGRAM RESULTS .......... ................... 132

CONCLUSIONS ......... ....... ..... ................................. .132

APPENDIX 1

9 EXPERhIENTAL PROCEDURE. ........... ....................... . ... 133

APPENDIX II

SPECIMEN DRAWINGS ..... ....... ........................ 143

APPENDIX III

DATA SHEETS ........................ ........................... 14/

Preceding page blank iv

1LI5T OF TABLES

Table I Tensile Test Results for 15-5 PH (HI025) Forged Bar . . . 6

IT Compression Test Results for 15-5 PH (111025) Forged Bar 7

III Shear Test Results for 15-5 PH (111025) Forged Bar .... 8

IV Impact Test Results for 15-5 PH (HI025) Forged Bar . , 9

V Fracture Toughness Test Results for 15-5 P11 (H1025)Forged bar (Longitudinal) .......... ................ 10

VI Axial Load Fatigue Test Results for Unnotched 15-5 PH(H1025) Forged Bar (Transverse) ..... .............. 11

VII Axial Load Fatigue Te3t Results for Notched Kt -9 3.0)15-5 PH (H1025) Forged Bar (Transverse) ............ ... 12

VIII Summary Data on Creep and Rupture Properties of 15-5 PH(H1025) Forged Bar (iransverse) ..... ............. ... 13

IX Tensile Test Results for HP 9Ni-4Co-0.20C Forged Bar . 24

X Compression Test Results for HP 9NiMdCo-0.20C Forged Bar. 26

Shear Test Results for zF 9Ni-4Co-u.2Ou Fur~ed o•r . . . 2.'.

XlI Impact Test Results for Hp 9N1-4Co-0.20C Forged Bar . . 29

\IXlf Ftacturc T.-x'ghness Test Results for HP 9Ni-4Co-0.20Clorbed Bar .. . .... . ........................ ............ C

"K IV Ax~al Load Fatigue Test Resmlts for Unnotched Kh9Ni-4Co-0.20C Forged Bar (Transverse) ... ......... . . 31

XV txal Load Fatigue Test Results for Notched (K . 3.0)HP 9Ni-4Co-0.20C Forged Bar (Transverse) ... ........ .. 32

XVI Summar Data or Creep and Rupture Properties of HP9Niuo-0,2OC Forged Bar (Transverse) .............. ... 33

XVII Tensile Test Results for PH 13-8 Mo (HlO00) Forged Bar . 44

XVIII Compression Test Fesults for PH 13-8 Mo (H1000)*Forged Bar . . . . . . . . . . . . . . . . . . . . . . . 45

XIX Shear Test Results for PH 13-8 Mo (H1000) Forged Bar . 47

XX Impact Test Results for PH 13-8 Mc (H1000) Forged Bar . . 48

S..v

'Rw , 4 .

LIST OF TABLES(Cout inued)

Page

Table XXI Fracture Toughne~is Test Rcsults for PH 13-8 Mo(111000) Forged Blar (Longitudinal) .... ............ .. 49

XXII Axial Load 1atigue Test Results for UnnotchcdPH 13-8 Mo (O11.000) Forgý,l Bar (Longitudinal) .... ...... 50

XXIII Axial Load Fatigue Test Results for Notched (Kc - 3.0)PH! 13-8 Mo (i1I000) Forged Bar (Longitudinal) ........ ... 51

XXIV Stnmary Data on Creep and Rupture Properties of PH 13-8Mo (111000) Forged Bar (Longitudinal) .... .......... ... 52

XXV Tensile Test Results for 7049.-T76 Extrusions ........ ... 63

XXVI Compression Test Results for 7049-T76 Extrusions .... 64

XXVII Shear Test Results for 7049-T76 Extrusions ......... ... 65

XXVIII Impact Test Results for 7049-T76 Extrusions atRoom Temperature .......... .................... ... 66

XXIX Fracture Toughness Test Results for 7049-T76 Extrusions(LongiIudinal) ............ ..................... ... 67

XXX Axisl-Load Fatigue Test Results for Unnotched7049-T76 Extrusions (Transverse) ..... ............ ... 68

XXXI Axial Load Fatigue Test Results for Notched (Kt - 3.0)7049-T76 Extrusions (Transverse) ..... ............ . .. 6?

V XXXII Sulmmary Data on Creep and Rupture Properties of 7049-T76Aluminum Extrusions (Trans--a-) ..... ............ .. 70

XXXIII Tensile Test Results fez Ti-6A1-2Sn-4Zr-6Mo Sheet .... 81

XXXIV Compression fast Results for Ti-EAI-2Sn-4Zr-6Mo Sheet . 83

"XXXV Shear Test Results for Ti-6Al-2Sn-4Zr-6Mo Sheet

at Room Temperature ................... 85

XXXVI Axial Load Fatigue Test Results for UnnotchedTi-6A1-2Sn-4Zr-6Mo Sheet (Transverse) 86

=X\VII Axial-Loac Fatigue TGZ Rebslts for Notched (K 3.0)Ti-6A1-2Sn-4Zr-twio Sheet (Transverse) .............. ... 87

TLXVIII Summary Data on Creep and Rupture Properties ofTi-6A1-2Sn-4Zr-6Mo Sheet (Trnasverse) .............. ... 88

vi

I

LIST OF TAI31S(Cent inued)

Table XXXIX Tensile Test Results for Inconel 702 Sheet (Aged) . . .. 99

XL Compression Test Results for Inconel 702 Sheet (Aged) 101

XLI Shear Test Results for Inconel 702 Sheet (Aged) ... ..... 102

XLII Axial Load Fatigue Test Results for UnnotchedInconel 702 Sheet (tged) (Transverse) .............. ... 103

XLIII Axial Load Fatigue Test Results for Notched (K - 3,0)Inconel 702 Sheet (Aged) (Transverse) . . ........ 104

XLIV Sumnary Data on Creep and Rupture Properties ofInconel 702 Sheet (Aged) (Transverse) ...... .......... 105

XLV Tensile Test Results for Inconel 706 Forged Bar(Stress-Rupture Heat Treatment) ..... ............. ... 116

XLVI Compression Test Results for Inconel 706 Forged Bar(Stress-Rupture Heat Treatment) .... ............. ... 117

XLVII Shear Test Results for Inconel 706 Forged Bar(Stress-Rupture Heat Treatment) ..... ............. ... 119

XLVIII Impact Test Results for Inconel 706 Forged Bar

XLIX Fracture Toughness Test Results for Inconel 706

Forged Bar (Stress-Rupture Heat Treatment) ......... ... 121

L Axial Load Fatigue Test Results for Unnotched Inconelr706 Forged Bar (Stress-Rupture Heatment) (Transverse) 122

LI Axial Load Fatigue Test Results for Notched (K - 3.0)C >

Inconel 706 Forged Bar (Stress-Rupture 1,eat Treatment)(Transverse) ............... ...................... ... 123

LII Summary Data on Creep and Rupture PLoperties for- Inconel 706 Forged Bar (Stress-Rupture Heat Treatment)(Transverse) ............... ...................... ... 124

LIST OF ILLUSTRATIONS

Figure 1 Specimen Layout for 15-5 PM (H1025) Forged Bar 4....4

2 Typical Tensile Stress-Strain Curves for 15-5 PH(H1025) Forged Bar (Longitudinal) ..... ............ ... 14

3 Typical Tensile Stress-Strain Curves for 15-5 PlU

S(HI025) Forged Bar (Transverse) ... ............. .. 15

• vii

Pt

_ _ _ _ _ _ _ _

LIST OF ILLUSTP&.TIONS(Con.:in.ed)

Figure 4 Typical Comptassive Stress-Strain and Tangent-ModulusCurves for 15-5 PH (HI025) Forged Bar (Longitudinal) . . . . 16

5 Typical Compressive Stress-Strain and Tangent-ModulusCurves for 15-5 PH (111025) Forged Bar (Transverse) ...... 17

6 Effect of Temperature on the Tensile Properties of

1.5-5 PH (HI025) Forged Bar ......... ................. .. 13

7 Effect of Temperature on the Compressive Properties of15-5 PH (HI025) Forged Bar ......... ................. .. 18

8 Axial Load Fatigue Behavior for Unnotehed 15-5 PH (HI025#Forged Bar ................. ......................... .. 19

9 Axial Load Fatigue Behavior for Notched (Kt = 3.0) 15-5 PH

(H1025) Forged Bar ...................................... 1.

10 Stcess-Rup~ure and Plaitic Deformation Curves for 15-5 PU

(HI025) Forged Bar (Transverse) ............ .............. 20

11 Specimen Layout for HP 9Ni-4Co-0.20C Forged Bar ........ .. 22

12 T'w.4r-sionnle Ctrnaoýtran4. Cur,-ves for Hp 0

Wi4..1

,2a.Si 9C

Forged Bar (Longitudinal). . .. ............... 34

13 Typical Tensile Stress-Strain Curves for HP 9Ni-4Co-0.20C

Forged Bar (Transverse) .......... .................. .. 35

14 Typical Compressive Stress-Strain and Tangent-ModulusSCurves for HP 9Wi-4Co-0.20C Forged Bar (Longitudinal) ... 36

15 Typical Compressive Stress-Strain and Tangent-Modulus

Curves for liP 9Ni-4Co-O.20C Forge i Bar (Transverse) . . 37

t 16 Effect of Temperature on the Tensile Properties of

HP 9Ni-4Co-0.20C Forged Bar .............. ................ 38

17 Effect of Temperature on the Compressive Properties of

liP 9Ni-4Co-0.20C Forged Bar .......... ................ 38

18 Axial Load Fatigue Results for Unnotched HP 9Ni-4Co-0.20CForged Bar ................. ......................... .. 39

19 Axial Load Fatigue Results for Notched (Kt - 3.0) HP9NL-4Co-0.20C Forged Bar ........... .................. .. 39

20 Stress-Rupture and Plastic Deformation Curves for

HP 9Ni-4Co-0.20C Forged Bar (Transverse) .......... 40 4

3~it

viii

a *-

LIST OF ILLUSTRATIONS __

(Continued)

Page

Figure 21 Specimen Layout for PH 13-8 Mo (1!1000) Fozged Bar .. ..... 42

22 Typical Tensile Stress-StraLn Curves for Pil 13-8 Mso(H1000) Forged bar (Longftudii3l) ............. ........ 53

23 Typicel Tensile Stress-Strain Curves for P1! 13-8 Ms(H1000) :'orgsd Bar (Long Transverse) .... ............ ... 54

24 Typical Compressive Stress-Strain and Tangent-ModulusCu rves for PH 1.3-8 Mo (111000) Forged Bar (Longitudin&1.) 55

25 Typical Compressive Stress-Strain and Tangent-Modulus Curvesfor PH 13-8 Mo (111000) Forged Bar (Long Transverse) .... 56

26 Effp•; of Temperature on the Tensile Properties ofPH 13-8 Mo (h1000) Forged Bar ..... ............... .... 57

27 Effect of Temperature on the Compressive Properties ofPH 13-8 Mj (111000) Forged Bar ...... ............... ... 57

28 Axial Load Fatigue Results for Untotched PH 13-8 Mo(HIG90) Forged Bar ...................... ........... 58

29 Axial Load Fitigue Pesults for Notched (Kt - 3.0)

a rn ±3-0 flu ¼HIUVU) ruzed Bt r .u.......... . 5Jr

30 Stress-Rupture and Creep Deformation Curves for PH113-B MoI (H1003) rorged Bar (Longitudinal.) .... ............. .... 59

31 Spczimen Layout for 7049-T76 Extrusions .... ......... ... 61

32 Typical Tensile Stress-Strain Curves for 7049-T76Extrusions (Longitudinal) .... .... ............. 71

33 Typical Tensila Stress-Strain Curves for i049-T76Extrusions (Transverseb) ........ .................. ... 72

34 lypical Compreerive Stress-Strain and Tangent-ModulusCurves for 7049-T76 Extrision (Longitudinal) ........ 73

35 Typical Compressive Stress-Strain and Tangent-Modulus

Curves for 7049-T76 Extrusion (Transv-rse) ............ ... 74

36 Effect of Temperature on the Tensile Properties ofof7049-T76 Extrusador ....... ..................... ... 75

37 Effect of temperature on the Compressive Propertiesof 7049-T76 Extruslon .. .. .. .. .. .. .. .. . .. 75

38 Axial Load Fatiguc Results for Unnetched 7049-T76 Extrusions 76

"ix

LIST OF ILLUSTRATIONS

(Continued)

Figures 39 Axial Load Fatigue Results for Notched(Kt - 3.0) 7049-T76 Extrusions .... ............ .. 76

40 Stress-Rupture and Plastic Deformation Curvesfor 7049 Extrusions ....... .................. ... 77

41 SpecLmen Layout for Ti-6Al-2Sn-4Zr-6Mo Sheet ..... .. 79

42 Typical Tensile Stress-Strain Curves forTi-.6A1-2SLL-4Zx-6Mo Sheet (Longitudinal) ............. •. 89

43 Typical Tensile S~rens-Strain Curves forTi-6AI-2Sn.J+Zr-6Mo Sheet (Transversa) ........... ... 90

44 Typical Compressive Stress-Strrin end Tangent-ModulusCurves for Ti-6AI-2SnJ+Zv-6Mo Sheet (Longitudinal) . 91

45 Typical Compressive Stress-Strain and Tangent-ModulusCurves for Ti-6A1-2Sn--4Zr-6Mo Sheet (Transverse) . . . 92

46 Effect of Temperature on the Tensile P,-opertiesof Ti-6A1-2Sn-4Zr-6Mo Sheet .... . ............. .. 93

47 Effect of Temperature on the Compressive Prop-erties of Ti-6A1-2Sn-4Zr-6Mo Sheet ... .......... .. 93

48 Axial Load Fatigue Results for UnnotchedTi-6A1-2Sn-4Zr-6Mo Sheet ...... ............... .. 94

49 Axial Load Fatigue Results for Notched (Kt w 3.0)Ti-6A1-2Sn-4Zr-6Mo Sheet ...... ............... .. 94

50 f•tress-Ru,,ptunre And Plastic Deformation Curves for

TI-6A1-2Sn-4Zr-6Mo Sheet (Transverse) ..... ......... 95

51 Specimen Layout for Inconel 702 Sheet ........... ... 97

52 Typical Tensile Stress-Strain Curves forInconel 702 Sheet (Aged) (longitudinal) ... ........ .. 106

53 Typical Tensile Stress-Strain Curves forInconel 702 Sheet (Aged) (Transverse) ............ ... 107

54 Typical Compressive Stress-Strain and Tangent-ModulusCurves for Inconel 702 Sheet (Aged) (Longitudinal). . . 108

55 Typical Compressive Stress-Strain and Tangent-ModulusCurves for Inconel 702 Sheet (Aged) (Transverse). . . . 109

K

LIST OF ILLUSTRATIONS(Continued)

Figure 56 Effect of Temperature on the Tensile Propertiesof Inconel 702 Sheet (Aged) ....... ................ 110

57 Effect of Temperature on the Compressive Propertiasof Inconel 702 Sheet (Aged) ....... ..... ................ 110

58 Axial Load Fatigue Results for Unnotched Inconel 702C ;heet (Aged) ...... ......... ........................ Ill

59 Axial Load Fatigue Results for Notcbed (Kt V 3.0)Inconel 702 Sheet (Aged) ...... .................. ....1

(0 Stress-Rupture and Plastic Deforaation Curves forInconel 702 Sheet (Aged) (Transverse) .... ........... ... 112

61 Specimeu Layout far Inconel 706 Forged Bar ............ ... 114

62 Typical Tensile Stress-Strain Curves for Inconel 706Forged Bar (Longitudinal) (Stress-Rupture Beat Ireatmeut) 125

63 Typical Tensile Stress-Strain Curves for Inconel 706Forued Bar (Transverse) (Stress-Rupture Heat Treatment) 126

64 Typical Compressive Stress-Strain and Tangent-Modulus Curvesfor Inconel 706 Forged Bar (Longitudinal) (Ctross-RuptureHeat Treatment) ..... ....... ....................... ... 127

65 Typical Compressive Stress-Strain vnd Tangent-Modulus

Curves for Inconel 706 Forged Bmr (Transverse) (Stress-Rupture Heat Treatment) ....... ... .................. ... 128

66 Effect of Temperature on the Tensile Properties ofInconel 706 Forged Bar (Stress-Rupture Heat Treatment) . . . 129

67 Effect of Temperature on the Compressive Properties of1nonl '1706 Forgedar us. tQiraap ,nrAi amiet- Tramn ~ -129

68 Axial Load Fatigue Results for Unnotched Inconel 706Forged Bar (Stress-Rupture Heat Treatment) ..... ......... 130

69 Axial Load Fatigue Results for Notched (Kt -- 3.0) Inconel706 Forged Bar (Stress-Rupture Heat Treatment) .... ....... 130

70 Stress-Rupture and Plastic Deformation Curves for Inconel706 Forged Bar (Stress-Rupture Heat Treatment) (Transverse). 131

71 Tensile Ultimate Strength as a Function of Temperature . . 133

72 Tensile Yield Strength as a Function of Temperature .... 134

xi

LIST OF ILLUSTRATIONS(Continued)

Figuire 73 Sheet and Thin-Plate Tensile Speutmen ..... ............. ... 144

74 Round Tensile 3pecitin ........... .................... .. 144

k 75 Sheet Compression Specimen ......... .................. .. 144

"76 Round Compression Specimen . . . . ......... ... .. 144

77 Sheet Creep- and Stress-Rupture Specimen .... ........... .. 144

78 Round Creep- and Stress-Rupture Specimen ... ............. 144I

79 Snnet Shear Test Specimen ........ ................... ... 145[ 80 Fin 3hear Specimen ................... ...................... 145

81 Uronotched Sheet Fatigue Specimen ....... ............... .. 145

82 Notched Sheet F~tl:r.ia Specimen ............... 145

83 Unnotched Rour, d Fatigue Specimen ....... ............... .. 145

84 Notched Round Fatigue Specimen ......... ................ .. 145

85 Sheet Fracture Toughness Specimn.n ...... ............... ... 146

86 Slow Bend Fracture Toughness Specimen ............. 146

87 Stress-Corrosion Specimen ........ ................... ... 146

88 Thermal-Expansfon Specimen ....................... 146

89 Sheet B.id Specimen .... ................... ............ 146

90 Notched Impact Specimen .......... ...................... . 146

xii

INTRODUCT ION

The selection of structural materials to most effectively satisfy newenvirormental requirements and increased design load requirements for advz.ncedAir Force weapons systems is of vital importance. A major difficulty that designengineers encounter, particularly for newly developcd materials, materials pro-cessing, and product forms, is a lack of sufficient engineering data informatio1 .to effectively evaluate the relative potential cf these developments for a par..."--ular application.

In recognition of this need, the Air Force has sponsored several progrsmz Iat Battelle's Columbus Latboratories to provide comparative engineering data fornewly developed materials. The materials included in these evaluation programswere carefully selected t,- insure that they were either available or could becomequickly available on request and that they would represent potentially attraccivealloy projections for weapcas system usage. The results of these programs haveIbeen published in four tech'iical reports, AFML-TR-67-418, AFML-TR-68-211, AFM.-

TR-70-252, and AFlL-TR-71-cr49.

This technical report is a result of the continuing effort to reliuve theabove situation and to stimulate interest in the ;;se of newly developed alloys, or I -

new processing techniqu.s for older alloys, for advanced structures.

The materials evaluated under this program are as follows:

(1) 15-5 PH (H11025) stainless qteel forged bar

(2) HiP 9N-4Co-0.20C steel forged bar ,,i -

(3) PH 13-8 Mo (HlOOO) stainless steel forged bar 8(4) 7049-T76 aluminum extrusion

(5) 6Ai-2Sn-4Zr-6Mo titanium sheet

(6) Inconel Alloy 702 sheet (Aged)

(7) Inconel Alloy 706 forged bar (Creep-rupture heat treatment).

The temper or heat-treat conditions selected for evaluation are described Iin each alloy section.

The program approach was, os on previous contracts, to search the publishedliterature and to contact metal producers and aerospace companies for any pertinent

data. If very little pertinent information was available, a complete material

evaluation was conducted. Upon completion of each material evaluation, a "datasheet" was issued to make the data immediately available to potentiel users rather

than defer publication to the eia of the contract term and the su-,ary technical

report. These data sheets are rcprnduced in Appendix II.

Nt..Nw ~ ~ - - .. t.I

- --- --- -.

Detailed information concerning the properties of interest, testtechniques, and specimen types are conta3,ned in Arpendic'!s I and Ii of thisreport.

2

MATERIALS INFCPkMATION AND TEST RESULTS

15-5 PH Stainless Steel

Material Description

15-5 PH is a precipitatior-hardening stainle3s steel that offers acombination of high strength and hardness, excellent corrosion resistat.ce, plusgood transverse toughness and good forgeability. It is produced by conuumablevacuum arc remelting and is virtually "ferrite free".

Fabrication practices for 15-5 PH are generally the same as thoseestablished for 17-4 PH. Most techniques are similar to those recommended forthe regular grades of stainless steel. Hardening heat treatments require

temperatures of only 900 F to 1150 F, depending on the properties desired.Because of the comparatively low hardening temperatures, scaling and distortion"difficulties are essentially eliminated.

15-5 PH is available in the form of iheet, strip, plate, bar, and wire.

Typical applications include forgings, Tump and valv parts for high pressuresystems, aircraft components, and hollow bar parts for hydraulic actuators andSi controls.

The chemical composttion of the forginag used for this evaluation isas follows:

Chemical CGroposition Percent

Carbon .037Manganere ,31 'Phosphorus 1018Sulfur .010Silicon .30

• Chro•mium_ 1.14

Nickel 4.58Copper 3.32Columbium .24Tantalum .01Iron Balance

The material tested wva obtained from Armco Heat 4W0370 in the form of

2-1/8 inch x 5-3/4 inch x 8 foot forged bar.

ProcessIng and Heat Treating

The specimen layout for 15-5 PH is shown in Figure 1. Specimens weremachined in the Ls-received Condition A followed by heat treatment for 4 hours at1025 F ta Condition 111025.

3

'Ij..4

Itc 4 l atst

I6~ OII

2 -j

cii

IIII 0I111•

LI' I 2 all

.r I I

SGI goIVi5*j l

Cd

I-

zvao

LOG.

G96 939

-II

Its all

fu u

109 j

Test Results

Tension. Results of tests in both the longitudinal and transversedirections at room temperature, 400 F, 700 F, and 900 F are given in Table I.Typical LUnsi!c stress-strain curves at temperature are shown in Figures 2 and3. Effect-of-temperature curves are shown in rigure 6.

Compression. Results :f tests in thc longitudinal and transversedirections are given in Table II for room temperature, 400 F, 700 F, and 900 F.Typical stress-strain and tanget•L-tiodulus curves at temperature are shown inFigures 4 and 5. Effect-of-temperature curves are shown in Figure 7.

Shear. Results of pin shear tests in the longitudinal and transversedtrectious at room temperature are given in Table III.

Impact. Results of room temperature Charpy tests in the longitudinaland transverse direction are given in Table IV.

Fracture Toughness. S'x slow-bend type tests were conducted at roomtemperature. Results are presented in Table V. Since the uize ratio, 2.5( /TYS)t,was greater thai. both the specimen thickness and width in all tests, the K ýalueis not a valid K;c value by exisring ASTM criteria.

Fatigue. Axial-load tests were conducted at room temperature, 400 F,and 700 F for both unnotched and notched transverse specimens. Test results aregiven In Tables VI ana VII end presented as S-N curves in Figures 8 and 9.

Creep and Strmss Rupture. Tests were performed at 700 F, 900 F, and1100 F. Results are presented in tabular form in Table VIII and as log-stressversus log-time curves in Figure 10.

Stress Corrosion. Specimens were tested as described in the experimentalprocedure section of this report. No failures or cracks occurred in the 1000-hourtest duration.

Thermal Expanmion. The coefficient of thermal expansion for this alloyis 6.7 x ].7e in/in/F for 70 F to 900 F.

Density. The density value is 0.283 lb/in3 .

TABLE 1. TENSILE TEST RESULTS FOR15-5 PH (H1025) FORGED BAR

0.2 Percent Elongation Reduction TensileSpecimen Ultimate Tensile Offset Yield in 2 Inches, in Area, Modulus,

Number Strength, ksi Strength, ksi percent percenL psi x 108

Longitudinal at Room TemperatureiL-I 164.0 163.0 15.0 62.4 30.51L-2 165.0 164.0 15.5 63.6 30.81L-3 164.0 163.0 15,5 62.2 30.6

Transverse at Roam TemperatureIT-I 164.0 162.0 12.5 50.0 28.7;IT-2 65.0 162.0 13.0 52.7 28.61T-3 163.0 161.0 13.5 50,9 29.2

Longitudinal at 400 F1L-4 147.0 141.0 12.5 50.0 27.31L-5 147.0 140.0 12.5 49.8 27.81L-6 147.0 140.0 11.5 43.8 28.1

Transverse at 400 F1T-4 147.0 -- 141.0 10.5 43.3 27.91T-5 146.0 i39.0 1U.5 42.0 27,2IT-6 147.0 141.0 11.5 43,7 29.5

Long:.tudinal at 700 FIL-7 137.0 128.00.0 43.5 26.5IL-8 136.0 127.0 10.0 46.4 27.0IL-9 139.0 130.0 11.0 46.2 27.4

Transvers at 700 F1T-7 136.0 126.0 9.0 38.6 24.0IT-8 136.0 128.0 9.0 37.8 25.2IT-9 136.0 127.0 9.5 39.2 26.2

Longitudinal at 900 FIL-10 120,0 112.0 15.0 60.8 21.91L-11 120.0 111.0 15.0 58.3 21.3]L-12 119.0 110.0 14.0 58.2 23.4

Transverse at 900 FIT-IO 118.0 108.0 14.0 51.0 23.7IT-I1 118.0 110.0 13.5 50.2 23,0IT-12 120.0 112.0 13.0 53.2 22.9

6

TABLE 11. COMPRESSION TEST RESULTS FOR

15-5 PH (H1025) FORGED BAR

0.2 Percent Compressive

Specimen Offset Yield Moduius,Number Strength, ksi psi x 106

Londitudinal at Rooin Temperature

2L-1 168.0 *29.82L-2 165.0 31.02L-3 173.0 29.9

Transverse at Room Temperature2T-1 165.0 29.82T-2 166.0 30.12T-3 165.0 30.9

Longitudinal at 400 F2L-4 14 5.U 29.12L-5 145.0 28.3

2L -6 144.0 -,o 9

Transverse at 400 F2T-4 f.45.0 28.22T-5 143.0 29.32T-6 144.0 29.2

Longitudin! at 700 F2L-7 133,0 27.9

2L-8 129.0 27.72L-9 128.0 27.4

Transverse at 700 Ft 2T-7 130.0 27.8

2T-8 130.0 28.6I 2T-9 130.0 27.8

Longitudinal at 900 F2L-10 113.0 24.62L-11 111.0 24 .4

2L-12 111.0 24.2

Transverse at 900 F

2T-10 111.0- 25.3

2T-II 111.0 23.92T-12 111.0 24.2

7

TABLE . SI•AR TEST RESULTS FOR15-5 PH (111025) FORGED BAR

Specimen Ultimate ShearNumber Strength, ksi

4- Longitudinal4L-2 106. 04L-2 106.04L-3 105o 0

S4L-4 105.0

Transverse4T -1 105.04T-2 104.04T-3 104.04T -4 106.0

8J_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _

I.!• m I II I . ... i II

TABLE IV. IMPACT TEST RESULTS FOR 15-5 PH(H1025) FORGED BAR

Spectwen Energy,Number ft/lbs

Longitudinal

10L-i 81.0lOL-2 81.0IOL-3 bo.01OL-4 78.0IOL-5 82.5

7O 10L-6 81.5

Transverse

1OT-1 37.01OT-2 38.51IOT-3 38.510T-4 43.0IOT-5 44.01OT-6 43.0

9

TABLE V. FRACTURE TOUGHNESS TEST RESULTS FOR 15-5 PH (H1025) FORGED BAR(LONGITUDINAL)

Specimen W, a, T, p, Span, fa KO(a)

Number inches inch inch pound inche3 ) (

IL J-501 .873 .749 11,800 6 3.5 181.49

4L.500 .886 749 12,600 6 3.6 200.6

2L 1.500 .883 .748 12,050 6 3.6 190.6

6L 1.501 .891 .749 12,450 6 3., 200.2

3L 1.500 .852 .748 11,900 6 3.3 174.5

5L 1.500 .882 .749 12,600 6 3.6 198.6

f-- ('..-,4A..9•n- ng s-,,ohnaq vahlestip. K. are invalid as K- values since a. T.

lOc

<2.5

10

1 10

TABLE VI. AXIAL LOAD FATIGUE TEST RESULTS FORU1NNOTCHED 15-5 PH (HI025) FORGED BAR

(TRA&NSVERSE)

Specimen Maximum Lite irme,Number Stress, ksi cycles

Rooma Te~mperature5-5 170 ld,720

5-3 165 42,2005-2 160 120,7005-4 155 111,2005-1 151) 4,156,2005-6 14 273,3005-7 140 7,934,5005-8 135 4,167,900 (a)5-9 130 1,':0

5-20 160- 14,9005-19 150 31,6005-18 140 47,0005-23 130 49,8005-22 130 113,5005-24 120 944,9005-25 120 10,208:100(a)

700 15-10 140 (b)5-14 135 37,7C05-13 1O0f an,'

5-L6 125 66,6005-11 120 59,4005-17 1i5 '0 ,4005-1" 110 1 0, 1 2 3 , 0 0 0fa)

(a) Did not fail.

(b) Failed in first cycle.

iii

TABLE VII. AXIAL LOAD FATIGUE TEST RESULTS FORNOTCHRED (Kt-3.0) 15-5 PH (H1025) FORGED BAR

(TRASVERSE)

Specimen Max imum Lifetime,Number Stress, kst cycles

Room Temperature5 -37 130 9,2605-32 120 14,6505-33 110 16,CIO5-34 90 45,1205-35 80 80,2505-36 70 128,9W05-37 60 191,1005-38 50 10,965,000

400 F

5 -49 90 39,1005-40 80 16, 2005-41 70 700.,0005.-52 65 1470,205-42 60 7121,2C05-53 60 16,121,300

70n F5-59 100 13,0005-57 90 16,5005-56 80 47,7005--55 70 44•, 4005-60 70 815,2005-53 65 2V547,900

5-54 60 5,548, '/W5-61 55 11,060,300

(a) Did not fail.

4

I

12

4i 0 '0%0 (4 ri41 IP08 Q 400C)0 vi 00OD P-4 100 r-0 C)0 -. 7000

~~..0~~~ 0- 0Q0- 00 0 0 0

C,

o 0

w4.0 un'10. V ) P4 I -ý~~4 f%4 *ý~-l 94cn

I-4 b4Q

0 I-4)atoacct

0:r % - I0 cngnt0 ýr 0 - rý

" 4)cl ; 8C C36 :; 0;:c::C

W44

CL, .- *-s-4 a.1 -4 .54 4.'n 0

C-8 r- Icps

to3

200 - 7

Longitudinal

175- RT

150- 400

125- 900

S100

75

50--

25-

0 0002 0.004 0006 0.008 QO010 0.012Strain, In./in. A-1149

FIGURE 2. TYPICAL TENSILR STRESS-STRAIN CURVES FOR15-5 PH (H1025) FORGED BAR (LONGITUDINAL,)

14

./M

200

Transverse

175-t RT

150 400

700 -

125-• 900

75-r

It-

25

oI ,!, ,o/i

0 C002 0004 0.006 Q008 0.010 0.012

Strain, In./in. A-1150

FIGURE 3, TYPICAL TENSILE STRESS-STRAIN CURVES FOR15-5 PH (H1025) FORGED BAR. (TRANSVERSE)

I I I I I I I I I I I5

2I00

175- TR

15.0O .04 0.0 F~O 40.0) F 0

FIGU7 4. = = 7--7C6)( FLNrDNL12GE5-MDUU

200 Transverse

175-R T

150-N0 0

;25 IJ

0 ~ ~ ~ ~ 0 F O I 2 5 3

TJAn ouu, 0 s -3

FIGUR 5.T-IA OPESW~SRSSSRI N)TN1N-OU

CUVSFR125H(12) OGDBR(RNVRE

01

0 0.02 .004 aOO 0.08 0010 .01Strain,------

.160/utme

140

10 T *us CL)

r 4' t~~~~~ TUS (T) _ _ _ _ _ _ _ _ _ _

0 TYS (L)

25 3

- 0. _ 30 *

oElongation C

S 200 400 60 8001000

j. tempeature0

Moeu (T)___ Ic .,"

5r-O E140 28 2

1000 ~ E(T) ____2

0 200 400 600 800 1000Temperciture, F -a

FIGURE 7. EFFECT OF TEMPERATURE ON THE T~PENSIEPROPERTIES OF 15-5 PH (H11025) FORGED BAR

IS18

- , 1 - - Urnotched

Transverse170, --- ..... ....- ! R=O.,

? ,I160.-

"• 150 --- ---- - -

140--0 -- R"E

1b0 .... .j . _-

o1 - RT £00110 A 400 F

0 700 FS103 105o'•6 o

Lifetime, 4yies /IFIGURE 8. AXIAL LOAD FATIGUE BEHAVIOR FOR UNNOTCHED 15-5 PH (H1025) FORGED BAR

160 II' 'IiiIII Notched7_4_ Transverse

I2----4o H-~ r~RzO.lI

1 00! (QOF- 4140 4

Lifeime cycles A-uSE

FIGURE 9. AXIAL LOAD FATIGUE BEHAVIOR FOR5 FRG. BRNOTCHED (Kt-m 3.0) 15-5 PH

19

•t 'n.Kt=a=

0

'-4

*-6 -

- E

1O< -

16L sai -

20

HP 9N-4Co-0.200 Alloy Steel

Matecial Description

HP 9Ni-4Co-0.20C steel was developed specifically to have high harden-

ability combined with good fracture toughness. It can be welded in the fully

4 heat-treated condition and achieve essentially 100 percent joint efficiency

without prehest or postheat treatment. The 0-20C grade is available as sheet,

strip, plate, bars, forginge, arid tubing.

The material used for this program was consumable electrode vacuum

melted and from Republic Steel Heat 3821003. It was obtained as a 2-1/4 inch

x 6-inch x 84 inch forged bar and had the following composition:

ChemicalCom,.)asltion Percent

Carbon 0.19

Manganese 0.36

FPhosphorus 0.008Sulfur .0- -Silicon 0.04Nickel 9.30Chromium 0.80Molybdentun 1.04Vanadium 0.08Cobalt 4.70

Iron Balance

Processing and Heat Treating

The specimen layout for this alloy is shown in Figure 11. Specimens

-# .. L .L achined4 .. , n - .-.. edA na•ne A nnnA4r-4nn heat f•rentAd anfol lows :

(I) normalize at 1650 F, 1 hour, air-cool,

(2) austenitize at 1500 FS, 1 hour, oil quench,

(3) single temper at 1025 F, 6 hours, air cool and[ then finish machined.

Test Results

Tension. Results of tension tests ir. the longitudinal and transversedirections at-room temperature, 500 F, "700 F, and 900 F are given in Table IX.

21

"KY- ý 7--nr"jj7-, -I-r

-j -jI "IJ -j -wd cm c~ N N

UP 4DO

_q

611 OW

121~0

211 143I

6±1 Z12O

lip; Z09 -

__ __ __ _ 0"

jZ4

fi tg 0o

le Bg 0

K '-4

____ 12 ON

fig In

-&- 039 -M

±19 9ý1 I

112 I S Ui OURV9 ftil *14

91

22

Stress-strain curves at temperature are presented in Figures 12 and 13. Effect-

of-temperature curves are shown in Figure 16.

Compression. Results of compression tests in the longitudinal andtransverse directions at room temperature, 500 F, 700 F, and 900 F are given inTable X. Compressive stress-strain and tangent modulus curves at temperatureare presented in Figures 14 and 15. Eff'ct-of-temperature curves are shown inFiguire 17.

Shear. Teat results for pin shear tests in both the longitudinal andtransverse directions at room temperature are given in Table XI.

Impact. Charpy test results at room temperature for longitudinal andtransverse specimens are gtven in Table XII.

Fracture Toughness. Results of six slow-bend type tests are given inTable XEII. The size ratio, 2.5 (Fo/TYS) 2 , was greater than both the specimenthickness and crack length in all t ats, therefore the • value in the table is

not a valid KI 1 value by existing ASTM criteria.

Fatigue. Axial-load fatigue tests were conducted at room temperature,500 F, and 700 F for transverse specimens, both unnotched and notched. Resultsate given in tabular form in Tables XIV and XV. S-N curves are presented inFigures 18 and 19.

Cree and Stress Rupture. Tests were performed at 500 F, 700 F, aad900 F for transverse specimens. Tabular test results are given in Table XVI.Log-stress versus log-time curves are presented in Figure 20.

Stress Corrosion. Specimens were tested as described in the experi-mental procedure section of this report. No failures or cracks occurred in the1000 hour test duration.

Thermal Expansion. The coefficient of thermal expansion for thissteel is 6.4 x in/in/F for 80 F to 900 F.

Density. The density of this alloy is 0.284 lb/ind.

t23

SITABLE IX. TENSILE TEST RESULTS FOR HP 9Ni-4Co-0.20C FORGED BAR

-i

Ultimate 0.2 PeircentTensile Offset Yield Elongation Reduction Tensile

93!p.?cimen Strength, Strength, in 2 inches, in Area, Modulus,No. ksi ksi percent percent 10 psi

SLongitudinal at Room Temperature

1.-i 198.0 181.0 17.5 67.1 28.01L-2 196.0 181.0 17.5 68.2 26.6IL-3 197.0 180.0 17.j 68.4 26.4

Transverse at Room Temperature

IT-I 197.0 180.0 14.5 55.0 27.9

IT.2 197.0 180.0 14.5 56.3 27.7

IT-3 197.0 180.0 15.0 57.1 -26.4

Longitudinal at 500 F

IL-4 178.0 165.0 16.0 66.7 25.4

IL-5 182.0 1.65.0 16.0 65.4 26.0iL-6 179,0 165.0 15.5 64.4 26.7

Transverse at 500 F

IT-1, 179.0 166.0 14.0 56.0 25.7

IT-5 179.0 166.0 14.0 55.1 25.8iL-b 179.0 166.0 14.0 55.8 26.2


IL-7 172.0 155.0 16.0 64.4 24.0

1L-.8 170.0 155.0 16.5 69.4 24.3IL-9 169.0 156,0 16.0 66.4 24.6

Transverse at 700 F

IT-7 169.0 151.0 14.5 58.4 24.91T-8 169.0 154.0 14.5 57.4 24.81T-9 IT.0 153.0 14.5 57.7 2':.4

24

TOBLE IX. .(Concluded)

Ultimate .0.2 PercentTensile Offset Yield Elongation. Fadu,2tion Tensile

Specimen Strength, Strength, in 2 ilaches, in Arua, Modulus,No. ksi ksi percent percent l0o psi


IL-10 148.0 130.0 18.0 69.6 22.2

IL-11 148.0 130.0 18.0 69.9 22.2

iL.-12 147.0 129.0 18.0 59.9 21.7

Transverse at 900 F

IT-1o 147.0 128.0 16.0 61.2 25.3

1T-11 i - "7. 0 i28.0 Uo U j 7 ._; &.a 4

IT-12 147.0 131.0 16.0 60.6 22.7

25

F:I

i. ' 25

I

TABLE X. COMPRESSION TEST RESULTS FOR1P 9Ni-4Co-O.23C FORGED BAR

0.2 PercentOffset Yield Compression

Specimen Strength, Modulus,No. ksi lo0 psi

Longitudinal at Room Temperature

2L-l 196.0 2-.62L-2 198.0 27.72L-3 196.0 28.0


2T-1 194.0 27.12T-2 195.0 28.6


2L-4 169.0 25.72L-5 173.0 26.521-6 173.0 26.9

Transverse at 500 F

2T-4 171.0 27.021-5 171.0 25.92T-6 172.0 25.7

longitudinal at 700 F

2L-7 162.0 24.82L-8 158.0 25.52L-9 157.0 25.0

Transverse at 700 F

2T-7 159.0 25.12T-8 156.0 24.92T-9 159.0 25.9

26

TABLE X . (Concluded)


Spezimen Strength, Modulus,%o. ksi 106 psi I


2L-1O 137.0 23.32L-11 135.0 24.82L-12 134.0 25.0

Transverse at 900 F

2T-0l 136.0 23.22T-i1 135e.0 I)/-, .,2Tr-I2 136.0 24.4

27

:I

TABLE XI. SHEAR TEST RESULTS FOR HP 9Ni-4Co-0.20CFORGED BAR

Specimen Ultimate ShearNo. Strength, ket

Longitudinal

""4.- 123.04L-2 124.04L-3 124.0

Transverse

4T-1 120.04T-2 124.04T-3 123.0

28

28

4s

TABLE XII. IMPACT TEST RESULTS FORHP 9Ni-4Co-0.20 C FORGED BAR

Specimen Energy,Number ft/lbs

Lon.i t.ud inal

IOL-1 73.0IOL-2 37.01OL-3 62.0lOL-4 63.0IOL-5 77.0

1 Transverse

IOT-l 50.0lOT-2 54.0lOT-3 52.0IOT-4 56.010T-5 54.0

29

U -•._l. _

1

TABLE XIII. FRACTURE TOUGHNESS TEST RESULTSFOR HP 9N_-4Co-0.20C FORGED BAR

Spec imen W, a, T, P, Span, f(-) K (a)Number inches inches inches lbs inches w

ransverse

3T 1.254 .648 o631 6,650 5 2.8 107.3

2T 1.255 ,640 .632 7,450 5 2.7 115.3

1T 1.255 .692 .631 8,200 5 3.1 146.3,-, Lnl itud inal

2L 1.514 .861 1755 12,650 6 3.4 186.1

3L 1.50' .8V0 .755 12,9800 6 3.5 193.4

IL 1.504 .735 .757 9,450 6 2.5 104.3

(a) Canldidate ýracture touZhreLi values, K are inv;alid as KI, values since a, T,

<2.'.

30

TABLE XIV. AXIAL LOAD FATIGUE TEST RESULTSFOR UNNOTCHED HP 9NI-4Co-0.20CFORGED BAR (TBANSV•PRSE)

Specimen Maximum Lifetime,Number Stress, ksi cycles

Room Temperature

5-1 120 26,900

5-2 i10 23,9005-3 100 34,0005-4 90 58,2005-5 80 69,9005-6 70 124,1005-7 60 5,024 9005-8 50 11,920,400(a)

500 F_I 5-7 10 A12,•000--I

5-19 135 23,6005-18 130 21,1005-20 125 17,4005-16 120 1 0 , 1 1 5 , 0 0 0 (a)

5-14 100 109 0005-15 100 12,916:000(a)

700 F5-26 180 30,000

5-25 160 746,4005-24 150 360,900,,5-22 140 25,600ku;5-23 140 2,052,400

5-21 130 2,702,0005-27 120 50 8005-28 120 10,277,000

(a) Did not fail,

(b) Failed at thermocouple.

31

TABLE XV. AXIAL LOAD FATIGUE TEST RESULTS FORNOTCHED (Kt=3.0) HP 9Ni-4Co-0.20CFORGED BAR (TRANSVERSE)

Specimen Maximum Lifetime,Number Stress, ksi Cycles

Room Temperature5-31 90 ,' 11,9005-37 85 17,9005-32 80 21,4005-35 75 13,3005-33 70 21,6005-36 65 50,9005-34 60 12,381,800(a)

500 F5-41 9r 7,8005-42 AS 116Ann5-43 80 27,3005-44 75 13,2005-45 70 25,2005-46 65 34,4005-47 60 31,3005-48 50 99,0005-59 40 60,6005-60 40 109,9005-61 30 1 0 , 8 5 0 , 9 0 0 (a)

700 F5-5 90 UU10,9005-52 80 14,4005-53 75 32,4005-54 70 1,699,3005-55 65 28,1005-56 65 85,2005-57 60 51,9005-58 50 1 2 , 9 8 6 ,0 0 0 (a)

(a) Did not fail.

32

/

:3 0.a Ln a I n c4 0

-A-

~ * I.* I It I s

In 0 0 r'. 04J~.~ .7W .4 0 It -. Cn ýa ~ C' 0 %0 (n.40 ('. ~ 0

toc S. 1: i P .4 q. Cý P0 r. ' -t 11- .0.4

L -'d in. c.c r r , LM5

o~~~o 00- i(n00 0,4t~ ~ -4 in 0% 0 n %0'

0 00r

00 -, -4 .h14 *-4. 1. 0 'w

.44J Io Q '1- I ~ . . L4n 4 ~ 8 0

0. -4 0 r-I - 0 0 :4Zf:* ~~ ~ , a I

R* -4 1 A Is ', ~E-44

14 91 &M

0 I,4

Ia0 0% -0%.I-

,4 0d -4 .4 _4 4

mt 'A 14 -4 0 ~I 0A 8% 1'. '.A4 A A A

0~- II33

20011Longitudinal 500

700

qi//

750

150-

25

41;

5o

0 0.002" 004 0.006 O.OO0 0010 0.012.

FIGURE 12. TYPICAL TENS"LE STRESS-STRAIN CURVES FORHP 9Nt-4Co-0.20C FORGED EA.R (LOWSITUDINAL)

34

200Transverse 500

17590

150

125

05

5O

00.002 Q.004 006 0.008 Q.010 0.0120 0.006r nir na

Strain, In./in. A-119?

FIGURE 13. TYPICAL TENSILE STRESS-STRAIN CURVES FOR

HP 9NJ-4Co-0o.20C FORGED BAR (TRANSVERSE)

35

200 RT Longitudinal IT

150-90 0175 %-

I7OO

100-

50-

25

0. OX2 0D04 Q006 0.008 0O 0.012

Strain, in./in.i .. . . I - Iu _ i0 5 10 15 20 25 30

Tangent Modulus, IdP psi A-1193

FIGURE 14. TYPICAL CC*IPRESSIV9 STRESS-STRAIN AND TANGENT-MODULUSCURVES FOR HP 9NL-4Co-0.20C FORGED BAR (LONGITUDINAL)

36

L. . . -

SRT Transverse RT

500175 •00

70000i

150-

100-

75-

501

0 Q002 Q004 0006 000S 0.010 O012

Strain, In./in.I . - I _ 1. 1 1I I I I0 5 10 15 20 25 310

"Tangent Modulus, & psi A-1199

FIGURE 15. TYPICAL C0O4PRESSIVE STRESS-STIRAIN AND TANGENT-MODULUSCURVES FOR HP 9N.-4Co-0.20C FORGED BAR (TRANSVERSE)

37

1601

4-

I 120 "ouu

MoModulus (

CC

10- 200 40 60 80

w 0 Temperature(TF

FIGURE 16. EFFECT OF TEMPERATURE ON TUE TENSILE PROP- 1ERTIES OF HP 9Ni..4Co-O.20C FORGED) BAR

*'200 10

"'160- 26 wj

T) 140- E Modulus (L) 24

120 220 2-00 400 60.0 800 1000

Temperature, F A- 1353

FIGURE 17. EFFECT OF TEMPERAIURE ON THL COMPRESSIVEPROPERTIES OF HP 9Ni.-4Co-O.20C FORGED BAR.

38

Unnotched• -- • !Trarisvarse

160 --- - -- -C R=0.!

I. - - --- - -.

500 F-

407 P7FF-

100---- '

i ~ ~0 RT ' " -

, 6 &- 500'i £3) 700 FI ."

4 40

I0 3 IOs I07

Lifetime, cycles

FIGURE 18. AXIAL LOAD FATIIGI•E RESULTS FOR UNNOTCHED HP 9NM-4Co-0.20C FORGED BAR

120 _ Notched- Tr-nsver

R=.Kt=5.

Rr"Iv)i60 60-- -. ... RO -

F • I I _,.

E 40S60----- - -"---500

5O r"OF2- 0 RT I

0 700.- .. _ F . ....... i.

Lifetime, cycles ."19

FI'URE 19. AXIAL LOW FATIGUE RESULTS ?OR NOTHED(Kt 3.0) %P 9M.-4Co-0.20C FORGED BAR

: •; 39.

CL C,

U--

8 00INIssai40 r0

PH 13-8 Mo Stainless Steel


V This alloy is a martensitic precipitation hardenable stainless steeldeveloped by the Armco Steel Corporation. It can be heat treated to highstrength levels and exhibits good ductility in the transverse direction. Thistransverse direction toughness is obtained by composition balance designed toprevent formation of delta ferrite in the structure, low carbon content to mini.-nmize grain boundary carbide precipitation, and double vacuum melting to reducealloy segregation. The rlloy reportedly has excellent resistance to stresscorrosion cracking in synthetic seawater and excellent resistance to corrosionin a 5 percent salt spray environment.

The material used in this evaluation was obtained as a 4-inch x 5-inch

x 5 foot forged bar from Armco Heat IW0241. The composition was as follows:

ChemicalComposition Percent

Carbon 0.035Manganese 0.01Phoephorus 0.002

I; Sulfur 0.003Silicon 0.02Chromium 12.62Nickel 8.24

V. Molybdenum 2.16Aluminum 1.02Iron Balance

Processing and Heat Treatingj

P,0The specimen layout for PH 13-8 Mo is shown in Figure 21. Specimens

were machined in the as-received condition A and then heat treated at 1000 F for.4 hours to Condition II 1000.

Test Results

Tension, Results • tests in the longitudinal and transverse directionsat room temperature, 500 F, 700 F, and 900 F are given in Table XVII. Tensile stress-strain curves at temperatu:e are shown in Figures 22 and 23. Effect-of-temperaturecurves arz presented in Figure 26.

SCompression. Test results are given in Table XVIII for longitudinsl and4 transverse specimeni at room temperature, 500 ., 700 F, and 900 F. Compressive

stress-strain and tangent modulus curves at temperature are presented in Figures24 and 25. Effect-of-temperature curve. are shown in Figure 27.

41

LoL

0

C-4

pm0

a slit 2

rShear. Results of pin shear tests at room temperature for longitudinal

and transverse specimens are shown in Table XIX.

Impact. Charpy test resuilts are shown in Table XX.

Fracture Toughness. Results of slow-bend type tests are shown inTable XXI. The size ratio, 2.5 (K /TYS) 2 , was greater than both the speciwenthickness and crack length in all eats, therefore, the JQ value shown in the.table is not a valid KIc value by existing ASTM criteria.

Fatigue. Axial load fatigue tests were conducted at room temperature,400 F, and 700 F for transverse specimens, bocii unnotched and notched. Testresults are given in Tables XXII and XXIII. SN curves are shown in Figures28 and 29.

Creep and Stress Rupture. Tests were preformed at 500 F, 700 F, and900 F for transverse dpecimens. Tabular test results are given in Table XXIV.Log-stress versus log-time curves are presented in Figure 30.

Stress Corrosion. Specimens were tested as described in the experi-mental procedure section of this report. No failures or cracks occurred iu the1000 hour test duration.

Thermal Expansion. The coefficient of thermal expansion for this alloyis 6.6 x 10-" in/in/F for 80 F to 900 F.

Density. The density of this material is 0.279 lb/in 3 .

I43

TABLE XVII, TENSILE TEST RESULTS FOR PH 13-8 1o(H1000) FORGED BAR

Ultimate 0.2 percent Elongation Reduction TensileSpecimen Tensile Offset Yield in 2 inches, in Area, Modulus,

Number Strength, ksl Strength, kai percent percent UP psi

Longitudinal at Room Tem ereture

IL-I 194.0 190.0 13.0 49.5 27.711-2 193.0 187.0 14.5 58.5 27.6IL-3 191.0 185.0 12.5 47.5 27.9

jfjL.atranaverse at Room Temperature

IT-1 192.0 187.0 13.0 51.0 27.3IT-2 188.0 179.0 14.5 55.5 28.31T-3 191.0 184.0 14.0 56.0 28.4


lL-4 170.0 165.0 12.5 58.0 27.iiL-5 169.0 164.0 13.0 5910 27.31L-6 168.0 165.0 12.0 53.0 26.5

Lona Transverse at SQO F

1T-4 168.0 162.0 11.0 49.5 25.2IT-5 166.0 163.0 12.5 56.0 25.51T-6 171.0 166.0 11.0 50.0 25.2


1L-7 158.0 148.0 14.0 59.5 24.7IL-8 150.0 153.0 11.0 45.0 24.9IL-9 157.0 153.0 13.0 55.0 25.8

I "n.. Trnnva~raa at Wil F

1T-7 159.0 148.0 12.0 51.0 26.2IT-8 156.0 150.0 12.5 50.0 24.71T-9 157.0 151.0 13.0 56.0 24.4


IL-1O 129.0 119.0 21.0 71.5 22.1IL-lI 129.0 119.0 21.5 69.0 20.7IL-12 X27.0 119.0 21.0 71.0 22.8

long Transverse'at 900 F

IT-10 125.0 116.0 22.5 72.0 20.4IT-i1 128.0 120.0 22.0 71.0 22.3IT-12 128.0 118.0 20.0 68.5 21.6

44

wr

TABLE XVII1. COMPRESSION TEST RESULTS

FOR PH 13-8 Mo (HIO00)

FORGED BAR


Specimen Strength, Modulus,

No. ksi 106 psi


2L-1 183.0 30.8

2L-2 193.0 30.6

2L-3 187.0 28.7

Long Transverse at Room Temperature

2T-1 199.0 29.9

2T-2 198.0 30.0 I2T.3 202.0 30.0


2L-4 160.0 25.9

2L-5 155.0 26.1

2L-6 160.0 26.6

Long Transverse at 500 F

2T-4 170.0 25.92T-5 170.0 25.82T-6 LV7 .5.4


2L-7 148.0 25.8

2L-8 157.0 25.82L-9 147.0 25.7


2T-7 160.0 23.6

2T-8 159.0 25.22T-9 157.0 24.5

45

TABLE XVIII, (Concluded)


Specimen Strength, Modulus,No. ksl I03 psi


2L-10 120.0 22.62L-11 115.0 23.22L-12 120.0 23.7


2T-10 122.0 23.12T-11 119.0 23.02T-12 123.0 23.0

d

L 46

TABLE XIX. SHEAR TEST RESULTS FOR PH 13.-8 Mo"(HI000) FORGED BAR

Specimen Ultimate ShearNumber Strength, ksi

4L-I 122.04L-2 122.0q4L-3 120.0

Long Transverse

4T-I .j.23.04T-2 123.04T-3 123.0

5.4

• 47

TABLE XX. IMPACT TEST RESULTS FOR BPH 13-8 Mo (H1000)rORGED BAR


Longitudinal

lOL-1 36.0

1OL-2 35.51OL-3 34.5IOL-4 33,510L-5 31.0IOL-6 33.5

Long Transverse PIOT-I 28.010T-2 28.0101-3 26.0lOT-4 28.01OT-5q 29.01OT-6 27.0

48

-- - -sr .. . . -= - ,

TABLE XXI. FRACTURE TOUGHNESS TEST RESULTS FOR Ph 13-8 Mo(H1000) FORGED BAR (LONGITUDINAL)

Specimen W, a, T, P, Span, f(aKNumber inches f ches inches lbs inches w

5L 1.500 .879 .742 10,750 6 3.5 i69.0

4L 1.501 .880 .741 10,500 6 3.6 166.0

3L 1.499 .868 .741 10,300 6 3.5 158.9

2L 71.500 .871 .741 9,800 6 3.5 151.9

IL 1.499 .870 .741 10,500 6 .3,5 162.8

(a) C~a-idiate 'fracture toughness values, MQ, are invalld ais %Ir values s' a T.

<2.5 I

49

TABLEXXII. AXIAL LOAD FATIGUE TEST RESULTS FORUNNOTCHED PH 13-8 Mo (K1000)FORGED BAR (LONGITUDINAL)


Room Temperature

5-1 215.0 14,4905-2 210.0 26,1205-3 205.0 35,1905-4 200.0 61,5705-5 195.0 65,4705-6 190.0 247,0505-7 180.0 333,3305-8 175.0 4,404,8005-9 170.0 785,9005-1.0 170.3 .....3J, U5-11 160.0 458,000..5-12 150.0 109010,000

400 F

5-15 •200.0 1005-14 190.0 17,4005-12 180.0 151,0005-11 170.0 42,9005-16 170.0 1,015,6005-18 165.0 1 0 , 3 2 9, 9 0 0-,.a5-17 1.60.0 10,407,300''

700 F

5-22 170.0 (b)5-26 165.0 2005-?4 160.0 33,9605-2L 155.0 28,9005-29 150.0 945,5005-23 150.0 1 0 , 0 9 0 , 7 0 0(a)

(a) Did not fail.

(b) Failed on loading.

50

I LI-TABLE XXIII. AXIAL LOAD FATIGUE TEST RESULTS FOR

NOTCHED (Kt - 3.0) PH 13-8 Mo (H1000)

FORGED BAR (LONGITUDINAL)

Specimen Maximum Lifetime,Number Stress, ksl cycles

Room Temperature

5-1 180.0 1,410

5-2 160,0 1,9005-3 140.0 3,8005-5 120.0 7,9105-6 100.0 32,8305-7 80.0 72,?005-8 60.0 210,0005-9 50.0 1 7 , 5 5 5 , 6 0 0 -a)

400 F

5-11 180.0 1,1005-12 170.0 1,7005-13 160.0 1,8005-14 140.0 1,3505-15 120.0 1,9005-16 100.0 8,1005-17 90.0 26,4005-18 80.0 60,50505-20 70.0 14,754:7005-19 60.0 10,192,200(a)

700 F

5-21 100.0 3,9005-23 90,0 18,3005-26 85.0 16,900p-2i 80.0 599,800

5-27 75.0 1,344,7005-24 70.0 5,358,700. (5-25 60.0 14 ,928 ,700

(a) Did not fail.

51

1

EI CQ C; 44 4

F-4 0 0.t -

0 z 0 4 s4 00 1 0

. ,4 4 * ') 0

04.w 809, 00T 0 C4(~ 00

0 (U14t8C'Jr- .W

,~~~.,±f To ' ~ a

I~q C k2 "1 11

~~~~G I 1~- 1 .4 0 ,- 3f 1N 0

0 -44 4.1(V4 '.4

-A ID

00 .0 Q t: C; C; 1 a

P. cC.I HI ý4 4n~ 1

,-4C m ' U -t

0 a n o~r.4 a4 a1 C. co ~-. a -4j

.K9 co

4,4 cfa. t -b-

M -as a

'e44

a.4 4. C, -. Ni lei'a '

I

200 Longiludinal RT h,

175 700F

150 -// 900 F

125

75

50[

0 Q.002 0004 'Q006 0.008 0.0K) 0.012

Strain, iri0n. A-1392

FIGURE 22. TYPICAL TENSILE STRESS-STRAIN CURVES H'0RPh 13.8 110 (111000) PO'EGED BAR(LONGITUDINAL)

53

S train' , I, oln -3

200_20Long Transverse R

500F

175-

125 -

IVI

750

50

0 0.002 0.004 0.00. 0.008 0.010 Q.012

FIGUJRE 23. TYPICAL TE4SILE STRESS-STPAIN CURVES FORPH 13-8 Mu (H1000) FORGED BAR

(LONG TRANSVERiSE)

54

IL - :. 7-- -- - --- ___

S200-•:•! RT ~ Longitudinal•'T•

S175- 500 F_

750

150

125-o0 F •-900 F

50-

25

0 0.002 0004 0.006 0.008 0.010 0.012

Strain, In./In.i I I I

0 5 10 15 20 25 30

Tangent Modulu.,, 10 psi A-1390

FIGURE 24. TYPI'CAL COMPRESSIVE STRESS-STRAIN AN•) TANGENT]-MODULUSCURVES FOR PH 13-8 Mo (H1000) FORCED BAR(LONGITUDINAL)

55

S~200

t Long Transverse RT

Ic, 175S700 F70F

150-

t ISOO125

I10

I I _____ . . ..J . . I

0 0.002 0.004 0.006 0008 0.0D 0.012

Strain, in./in.

0 5 10 15 20 25 30

Tangent Modulus, 10 psi A-089

FIGURE 25. TYPICAL COMPRESSIVE STRESS-STRAIN AND TANGENT-MODULUS

CURVES FOR PH 13-8 Mo (H1000) FORGED BAR(LONG IRANSVERSE)

56

c,#!

200

140--

0 A2 TUS LT)_____

0 TYS (LT)

25c 28-

Elongation) ____0____

10 22 9

ad 51 0 Etonauflon (LI 1 20

01 -- E l n0ti n00T

0 _ __ _ IL00 400 _ 800 Boo P;000

Temperature,F

OPH1.3-8 Mo (H11000) FORGED BAR

~ 20 0 Mouu3L) -2__

cr 1 0 MMoullus-T

1600 - 22

014 4060 200 0 0;

PRPRTE OFdlu (1 38Mo(100 FRE A

57

220 -- - ...-- I Unnotched+ 4 F-Longitudinal

200- -----80ooI- 0---0- F -- =--1

-4• 400 F D- - ;o= F

ý4 i 4u-. . .3 160 L .......--- n---dln-tL

Lifetime, cycles

FIGURE 28. AXIAL LOAD FATIGUE RESULTfS FOR UNN(YtCHED PH 13-83 Mo (H.1000) FORGED BAR

-i1I0........... I ...... . .1200k. . . ... ..

Notched

1130 Longitudinal

KKI'"4O0 1--... .120 .... 1---. --- 4 . . .

S.. .. . . -... . t

') RT-oa0'0F F "ci 700 F -

4 0.60310 4 I05 10 6 10 7

Lifetime, cycles .-1339

FIGURE 29. AXIAL LOAD FATiGuE RESULLS FOR OTICHLED (Kt ' 3.0) P11 13-8 Mo (H1000) FORGED BAR

58

S... '•- -" • '.F :• ;- • •'-'-•.- ... . - .. . .. " "--.. ..- '"- ..... **...... -. ....... . .. ... ... .... .. ....... ..

0

10

I.I

lx,- 9I i i

Ii~ LI. 410

EL

0

00 COO

59

7049-T76 Aluminum Extrusions

Material Description FAlloy 7049 was developed by Kaiser Aluminum and Chemical Corporation

to have a strength level in the range of 7075-T6 and 7079-T6 coupled with a highresistance to stress corrosion cracking. Initial development and production wasin the form of forgings arid hand forgings. Further development has been inplates and extrusions.

The material evaluated was a 4-inch x 4-inch extrusion supplied byKaiser with the following composition: J

ChemicalComposition Percent

Zinc 7.6Magnesium 2.5Copper 1.5Chromium 0.15Silicon 0.25 maxIron 0.35 maxTitanium 0.10 maxManganeac 0.20 maxAluminum Balance

Processing and Heat Treating

The specimen layout for 7049 is shown in Figure 31. Specimens weretested in the as-received -T76 temper.

Test Results

Tension. Test results for longitudinal and transverse specimens at roomtemperature, 250 F, 350 F, and 500 F are given in Table XXV. Room temperatureshort transverse tensile test results are also given in Table XXV. Stress-strain curves at temperature are presented in Figures 32 and 33. Effect-of-temperature curves are shown in Figure 36.

Compression. Test results for longitudinal and transverse specimensat room temperature, 250 F, 350 F, and 500 F are given in Table XXVI. Compressivest.ress-strain and tangent modulus curves at temperature are presented in Figures34 and 35 Fffect-of-cemperaruze curves are presented in Figure 37.

Shear. Pin shear test results for longitudinal and transverse speci-mens at room temperature are shown in Table XXVII.

60

-. 4 .- -.

Am

--

_. F'4

;.k 61

....... .. . . .. .

Ia__c. Charpy test results for longitudinal an(c transverse speci-mons at room temperature are shown in Table XXVII.

Fracture Toughness. Slow-bend type tests curve performed for sixlongitudinal specimens. Results are shown in Table XXIX. Since the size

ratio, 2.5 (KQ/TYS) 2 , was greaLer than both the specimen thickness and cracklength in all tests, the K values are not valid Kic values by existing ASTMcriteria.

Ftue. Axial-load fatigue tests were conducted on transverse speci-mens at room temperature, 250 F, and 350 F. Tabular test results are presentedin Tables XXX and XXXI. S-N curves are shown in Figures 38 and 39.

Creep and Stress-Rupture. Results for transverse tests at 250 F,350 F, and 500 F are shown in Table XXJII. Log-stress versus log-time curvesare presented in Figure 40.

Stress Corrosion. Tests were conducted as described in the experi-mental procedures section of this report. No failures or cracks occurred inthe 1000 hour test duration.

Thevana Ex..nljvi. of thc".-C exran•!e., for this allony

is 12.9 x Tld-3hinlin/F for 80 F to 212 F.

Density. The density for this material is 0.099 lb/in3 .

6

I

J 62

K

TABLE XXV. TENSILE TEST RESULTS FOR

7049-T76 EXTRUSIONS

Ultimate 0.2 PercentTensile Offset Yield Elongation Reduction Tensile

Specimen Strength, Strength, in 1 Inch, 1rn Area, Modulus,Number ksi ksi percent percent l06 psi


1L-I 81.1 72.2 13.0 35ý9 10.6IL-2 82.1 74.6 13.0 34.7 11.0IL-3 86.9 81.0 12.0 36.3 10.5


IT-1 76.2 67.2 11.5 23.3 9.51T-2 76.2 67.7 11.0 23.2 9.91T-3 76.2 67.4 11.0 23.3 10.2

Short Transverse at Room Temperature

1ST-I 76.2 68.0 12.0 22.6 10.41ST-2 76.4 67.8 12.0 22.6 10.31ST-3 76.2 67.4 11.0 22.6 10.6


IL-4 64.1 62.6 22.0 52.4 9.51L-5 64.4 63.3 22.0 52.6 9.0IL-6 64.6 63.8 22.5 54.2 9.5

Transverse at 250 F

If-4 58.4 56.0 15.5 34.1 9.3IT-5 58.4 56.4 18.0 34.5 9.4IT-6 59.9 56.8 17.0 34.7 9.3


1L-7 48.1 47.9 24.0 68.2 8.311,-8 48.9 48.7 26.0 70.4 8.3IL-9 48.2 47.8 29.0 74.3 8.0

Transverse at 350 F

IT-7 44.8 43.5 18.5 50.4 8.4IT-8 43.9 42.8 22.0 52.0 8.3IT-9 46.1 45.0 18.0 51.6 8.6


IL-10 17.0 16.8 40.0 93.0 8.0]L-IL 17.6 17.5 35.0 92.6 8.01L-12 18.8 18.6 39.0 93.3 6.9

Transverse at 500 F

IT-10 16,5 16.2 37.0 88.0 7.2IT-I1 16.6 16.2 29.0 87.2 7.4IT-12 16.2 15.9 31.0 86.8 7.4

63

7V77A:

TABLE XXVI. COMPRESSION TEST RESULTS FOR7049-T76 EXTRUSIONS

0.2 Percent CompressionSpecimen Offset Yield Modulus,

Number Strength, ksi lO' psi


2L-1 75.3 10.62L-2 81.4 11.0S-3 79.6 11.1

Transverse at: Room Temperature

2T-3 75.0 10.82T-2 73.0 9.92T-3 76.2 10.9


2L-4 66.4 9.52L-5 71.2 10.02L-6 71.7 10.1

Transverse at 250 F

2T-4 64.0 10.42T..5 62.6 9.92T-6 63.2 10.2

Longitudinal a- 350 F

2L-7 53.8 8.72L-8 53.8 9.12L-9 50.4 9.1

Transverse at 350 F

2T-7 48.8 8.92T-8 48.7 9.22T-9 49.0 9.1


2L-1O 18.6 6.62L-11 19.4 6.32L-12 19.0 6.5

Transverse at 500 F

2T-10 17.6 8.02T-11 17.8 7.42T-12 17.7 7.7

64

f -. . . . .-. -- 7

TABLE XXVII. SHEAR TEST RESULTS FOR7049-'176 EXTRUSIONS

Specimen UltLrmate SheerNumber Strength, ksi

Lon~i tudinal

4L-1 45.14L-2 45.64L-3 44.6•L-4 46.2

Transverse

1.1, 1 4.2_6, IIT~ ~~ --4T-2 44.94T-3 41.84T-4 41.8

I

i

"• ~65

TABLE XXVIII. IMPACT TEST RESULTS FOR 7049-T76EXTRUSIONS AT ROOM TEMPERATURE


LongitudinaltIO1L-I 6.5

1OL-2 5.01OL..3 6.5I OL-4 5.0IOL-5 7.01OL-6 4.5

Transverse

1OT-I 1.510- 2.0lOT-3 1.510T-4 2.0lOT-5 1.0lOT-6 1.5

66

I ..

'VY

wm

TAbLE XXiX. FRACTURL TOUGHNESS TEST RESULTS FOR 7049-T76 EXTRUSIONS (LONGITUDi.NAL)

nt- -me T. P. San. -) (. a

Number inches inches inches Ib3 inches w

61, 1.500 .830 .750 3,440 6 3.1 47.7

5L 1.500 .848 .7 3,870 6 3.2 55.3

IL 1.50" .866 .751 3.720 6 3.4 56.0

3L 1,501 .856 .750 3,850 6 3.3 55.9

2L ],502 .859 .750 3,650 6 3.4 54.0

4L .50IJ .854 .750 3,800 6 3.3 55.8

S (a't CandidatL ýracturc toughness values, \,, a-e invalid as Klc values sir.ct: a, T,

d\ys)

TABLE XXX, AXIAL-LOAD FATIGUE TEST PESULTS FOR UNNOTCHED7049-T76 EXTRUSIONS (TRANSVERSE)

Spec imen Maximum Lifetime,Number Stress, ksi cycles

Room Temper'Ature

5-4 65.0 9,3005-3 60.0 68,3405-2 55.0 86,0305-1 50.0 177,2205-5 45.0 7,075,4105-6 40.0 9,717,860

250 F

5-17 65.0 11,9505-19 62.5 26,2405-.5 60.0 29,5305-20 57.5 81,0505-16 55.0 289,21.05 -21 52.5 540,5605-18 50.0 1 0 , 1 9 9 , 4 3 0 (a)

5-7 60.0 19,790

5-10 55.0 54,7605-8 55.0 217,850S5-12 52.5 45,11G5-11 50.0 1,457,64J5-13 47.5 400,4205-9 45.0 6,006,9005-22 40.0 1 1 ,4 2 9 , 78 0 (a)

(a) Did not fail.

68

TABLE XXXIo AXIAL LOAD FATIGUE TEST REFULTh FORNOTCHED (Vt 3.0) 7049-176

EXTRUSIONS (TRANSVERSE)

Specimen Max Low Lifetime,Number Stress, ksi cyr-Ies

Room Temperaturc

5-19 40.0 6,8405-1 35.0 1.5,4105-2 30.0 19,0.05-3 25.0 31,2705-4 20,0 144,7505-5 17.5 3341,0505-i 15.0 558,5905-7 13.5 331,080 (5-8 10.0 15,146,300

250 F -I

5-16 35.0 7,6405-21 32.5 9,6905-17 30.0 20,0405-22 27.5 23,8105-23 25.0 i9,860 I5-18 25.0 934,0905-24 20.0 841 , 4005-25 10.0 843,1005-26 5.0 10,016,000(a)

350 r

5-9 35.o 9,3605-10 30.0 20,76055-.i 25 0 19,6205-12 20.0 84,6705-13 15.0 159,4105-14 10.0 652,300 (,5-15 5.0 10,062,800(8)

(a) Did not fail,

S•' ~69 .

'311

n) C-4 0 0 4$

0.

0 C

'4 it' Ol c;r rc

p- vi~i co I1 In .. r I V) '-ý 4 "1 I

-4 &-J'-lN I-. C1 cNa%

41 03 .4 0 Ch 0f t004rr4 Ln .4 0) . 4ý St 4 (

1-4. (J) r' ; z

~04 f) 00 A10 .' C. () N A$

.,4Icn~.~ A 6 c C'4 9- 14 c$

00 A) - 00l ýl 000 0

r-4 An41

HLe C) V) 0 ~-

LA C4.- .4- NOI

'IJI)O~ a, Ir '0 -inO 0

'4,4

00

(4 C

0 o D o o Cc'4 u'i tu'A> 9 q "L .4 '

rl ;11(n An ,IAn-C

1~Longitudinal nRi

70-

60

-~50- 5

S40-

30 -

20 500 F

10/

0 0.002 0.004 G00" 0.008 0.010 0.012

Strain, In./in. A-1344

FICURE 32. TYPICAL TENSILE STREiSS-STRAUIN C'URVFS FOR

7049-176 EXTRUST.ONS (LONGITUDWIA-L)

71

80raonsverse

RT70-

, /G0o- 250 F

50-350 F

20 .500 F

o / .. ------ - - -- --- -

0 0.002 0.004 OOm• 0.008 O.01O 0.012Strain, In./in.

FIGURE 33. TYPICAL TFNSILE STR•;SS-STiRAIN CURVES FOR7049.-T7- EXTRUS)ONS (TRANSVERSE)

7?

Longitudinal R

250 F1570--

60"

%,ý50 IF 3 -i 50 F

50- rk

•I L340

2050O F 50=I

0- 0,0 0-01 -.V6 008 Qi

Strain, In./in.

) 2 4 6 8 10 12

Tangent Modulus, 10 psi A-n3Z

F.FIGURE 34, 'TY1lICAL COMPRESSIVE STRESS -STRAIiN AND TANGFNT-MO4DULUSCURVES FOR 7049-Tt6 EXTRUSION (LONCITUDINA.)

73

70-

625 F

640

305

20 F5 I

30-

We0 t04oc 0.006 0.008 on00011

0 4 $ 10 12

74

. 80-- ....1 60

'• .... .. . . f(L ) -i! ,•TYS{,I (T__

4W c4 TLJS (L)•" ";• ,A TUS (T"

oi 20 0 TYS (L)

c TYS (T) i

0 6_ _ _ _

50 o Modulus () ! 14"___/_ / A Modulus (T)

40- -- Elongation (L) 124C ' -" • Elongation (T) 12!,R" 30 10. U;.i .,o • -_

"g 20 Elongatio

I00

I 00 200 300 400 500 !1Temperature, F

FICURE 36. EFFECT OF TEMPERATURE ON THE TENSILEPROPERTIES OF 7049-T76 EXTRUSION

In 1.= , IT)CYS

i • - •Modulus

i FIri.'ai: 37. EFFECT OF TEMPE1tATURE ON TH{E COMPRESSIVE

pROPERKTIES OF 7049-T76ETRSO75

Transverse

60

25 35 F30

250 FO

FIGURE 38. AXIAL LOAD FATIGUE RESULTS FOR UNNOTC!{ED 70'9-T76 EXTRUSIONS I

__ __Notched

Uf OR RTKeF

ILIFIGUR 39.AXIA LOADFATIUE RSUL 0 FR NOTHE (50 F .)74-76ETUI

E7

I I II

-a{l

--

ii

7 z,1

0U

LIMP

- -- 0

Ti-6Al-2Sn-4Zr-6M. Alloy


Initially, this alloy was developed by the Titanium Metals Corporationas an off-shoot of the Ti-6Al-2Sn-4Zr-2Mo high temperature alloy. Studies hadshown that increasingyond Tlyb1enumrconhigh temperathe 2 percent ievel resultedin an alloy having improved room and elevated temperature strength with goodcreL-p resistance. During early development, investigetix'ns were limited to the

* ev-'L-a.Lion of the alloy as a heavy section forging alloy. Promising high tempera-'_,ire properties achieved in heat-treated sections up to 3 inches suggested the

* alloy might also be useful as a sheet alloy since it should be air hardenable at-sheet gages.

The material used in this evaluation was 0.075 inch sheet obtainedfrom TMCA. It had the following composition:

Chemical 58

Composition PercentiAluminum 5.9E

Tin 1.99 -

Zirconium 3.94Molybdenum 5.86Iron 0.057Oxygen 0.10Nitrogen 0.004

Titanium Balance

Processing and Heat Treahing_

The specimen layout for this ailoy it 5bEJtIt .t- FigUt:e 4k. apeP , t.; rwere machined in the as-received condition and heat-treated as follows:

(1) 1600 F, 15 minuteq, air cooled,

(2) 1325 F, 15 minutes, air cooled,

(3) 1100 F, 2 hours, air cooled.

uti.s was suggested by TMCA and is called the "strengthened and heat-treated;toid{ tiohi.

Test Results

Tension. Results of tests in the longitudinal and transverse directions

at r-om temperature, 400 F, 700 F, and 1000 F are given in Table XXXIII. Stress-

78

RI Oil OI 61 OlLied -f J Z I4If

Via

Ilia

0

0

9!

" i VJIIoii i oil 1 I iIIS... .. I a•' I• "

Al Lz i

siti

" .__ .ii !•L . (-4•t . . .z ff.0"Og

I~~~1 st .1rS

019 P1 iig 92i 9gJi

GglIs Icr'l tip% S99g

a-- p,____1 0___ ,t z z i Losl 21 I 0s

____~~oz usOS __ _ __ _ _ ___ _ _ _

79

I ' ,,I'.-4

strain curves at temperature are presented in Figures 42 and 43. Effect-of-temperature curves are shown in Figure 46.

Compression. Test results for longitudinal and transverse specimensat room temperature, 400 F, 700 F, and. 1000 F are shown in Table XXXIV. Stress-str;ain and tangent modulus curves at temperature are presented in Figures 44and 45. Effect-of-temperature curves arc presented in Figure 47.

St ear. Test results for single-shear sheet-type specimens tested inbuth Lhe longitudinal and transverse directions at room temperature are givenin' Table XXXV.

Fracture Toughoess. Test specimens were the full sheet thickness (0.075-inch) x 18 inchx6 nch with an EDM flaw in the center. The 36 inch specimendimension was parallel to longitudinal grain direction of sheets. The average K

Cvalue obtained was 132 ksi /I. The net section yield stress at fracture wasless than the tensile yield strength of the material. Therefore, the Kc value Isconsidered valid.

Fatigue. Results of axial-load fatigue tests for transverse specimens, yboth unnotched and notched, at room temperature, 400 F, and 700 F are given inTables XXXVI and XXXVII. S-N curves are presented in Figures 48 and 49.

Creep and Stress-Rup'ure. Tests were conducted at 700 F, 900 F, and1100 F. Tabular results are given in Table XXXVIII. Log-stress versus log-time curves are presented in Figure 50,

Stress Corrosion. Testing was conducted as described in the experi-mental procedure section of this report. No failures or cracks occurred inthe 1000 hour test duration.

Thermal Expansion. The coefficient of thermal expansion for thisalloy is 5.5x 10 in/in/F for 80 F to 1000 F.

Densi&. The density of this alloy is 0.165 lb/inn.

!4

}4

SI

B'IA LE XXXIii. TEI:N LE TES1 RESULTS FOR 1Li-6AL-2Sn-4Zr-6y) SHEETA

Ultimate O.L Percent-T rsile Oifsc-t Yield Elo.geY -on To.r. nP le

Specimren Strength, Strength, in 2 inches, Modulus,SNo. ksi ki percent 10' psi

SL~~ongitudinal at Room '2Lmeratre

1 I.I 168.0 160 .V 16.0 17.5LIL-. 168.0 160.0 10.0 17.-

AiL-3 168.0 160.0 11.0 17,5

Transverse at Rocom Temperature

IT-I 169.0 163.0 10.0 17.2IT-2 170.0 163.0 11.0 17.2IT-3 169.0 163.0 14.0 17.2

SLngicudinal ac 400 F

1.L-4 149.0 129.0 14.5 16.4IL-5 148.0 127.0 15.0 16.2IL-6 148.0 127.0 15.0 16.4

Transverse a' 400 F

IT-4 150,0 130.0 14.0 15.4IT-5 150.0 131.0 14.5 15.7IT-6 150.0 131.0 14.0 15.9


IL-8 141.0 115.0 14.0 15.4IL.9 140.0 114.0 15.5 15.0

Traroverse at 700 F

If-7 141.0 117.0 15.0 14.71T-8 142.0 117.0 14,0 14.51T-9 143.0 l1,110 14.0 14.7

81

TABLE XXXIII. (Concluded)

Ultimate 0.2 Percent

Ten:• i C1e; Y£-ieid Liongation TensileS~ecilmen Strength, Strength, in 2 inches, Modulus,

No. ksi ksi percent 101 psi.


IL-10 107.0 98.2 29.0 13.11L-I1 104.0 96.0 41.0 12.6IL-12 105.0 97.8 39,0 12.6

Transverse at 1000 F

1T-10 Ij6.0 98.5 35.0 12.6iT-1l 108.0 99.5 33.0 12.8IT-12 106.0 98.8 36.0 13.0

I

82

IABLE XXXIV. COMFREiSI01 TEST R&SULTS TORTi-6A1-2Sn-4Zr .6Mo SIHET

0.2 P-rcentOffs,•t Yield Compro.-ssion

Specimen Strength, Modulus,No. ksi 105 psi


2L-1 167.0 19.12L-2 167.0 19.62L-3 168.0 19.4

Tren•verse at Room Temperature

2T-l 169.0 18.8

2T-3 172.0 18.9


2L-4 133.0 17.92L-5 133.0 17.92L-6 134.0 18.0

Trancverse at 400 F

T-4 136.0 17.5Z'-5 138.0 i7.82T-b 138.0 17.6

Loagitridinel at 700

2L-7 123.0 16.22L-8 124.0 16.42L-9 123.0 ;6.3

Transverse at 700 F

2i. 127.0 16.12T-8 127.0 16.121-9 126.0 16.1

83

TABLE XX IV. (Concluded)

G.2 PercentOffset Yield Compression

Specimen Strength, Modulus,No. ksi lOe psi

Lon itudinal at 10C' F

2L-10 ii1.0 13.82T,--11 1.13.0 14.1

U1-12 t09. C 13.7

Trarfverse at 1100 F

2T-10 112.0 13.421-11. 113.0 13.7

2T-12 113.0 13.7

A 8

84

NICW

TABLE XXXV 3HEAR TEST RESULTS FOR Ti-6AI-2Sn-4Zr-6Moi SHEET AT ROOM TEMPERATURE

iI

[Specimen Ultimate ShearSNo. Strength, ksi

i ~Longi tudinal

4L1 97.3

Ii4L2 96.4403 (a)4L4 96.8

Transverse

4T1 (a)4T2 98.24T3 98.14T4 98.0

(a) Did not faUl in shear.

85i

'H°-

TABLE .'.xXvi. AXIAL LOAD FATIGC7ý TEST RESULTS FOR

UNNOTCHED T1 - 6AI-2S -4Zr-6Mo SHEET

(TRAflSVERSL)

Sp.c inen iaxinum LIfetime,

Number Strcss, lcsi cycles

Room Temperature

5-7 120,0 102,620

5-1 115,0 43,920

5-5 112.5 1,864,2505-2 1.10. 59,270

5-4 107.5 6,079,8705-6 105.0 495,200

5-8 90.0 1 2 , 0 0 7 0 8 0 a)

400 F

5-19 125.0 28,60ýJ

5-20 122.5 17,1G• w

5-18 120.0 1,666,400 .5-22 117.5 68,700

5-21 115.0 5,420,3005-23 110.0 64,3005-24 100.0 573 Coo (a)

5-25 90.0 1 2 , 8 3 7 :2 )

700 F

5-9 120.0 9,30 '51 115.0 !4n An

5-11 110.0 14,70C

5-12 105.0 17,OCL

5-13 100.0 192,20C

5-17 100.0 10,796, 0 0 ca)

5-1; 90.0 11,0 3 2 ,000(a)

(a) Did not fail.

86

TABLE XXXVII. AXIAL-LOAD FATIGUE TEST RESULTS FOR NOTCHED(Kt = 3.0) 1i-6A1-2Sn-4Zr-6Mo

SHEET (TRANSVERSE)

Specimen Maximuw Lifetime,Number Stress, kai cycles

ROOM TEMPERATURE

5-1 100.0 1,1305-2 90.0 2,5105-3 70.0 1,510

5-4 50.0 6,3105-5 40.0 17,SOO5-7 35.0 272,700 .

5-6 30.0 10,157,600

400 F

5-7 60.0 15,C905-8 55.0 19,000

5-9 50.0 19,8405-10 45.0 27,7505-11 40.0 43,590/.0

5-12 35.0 10,119,850"•

700 F

5-13 60.0 7,400S-14 55.0 12,8005-15 50.0 18,1005-16 45.0 215,6005-17 40.0 188,6005-18 40.0 152,8005-19 35.0 84,3005-20 30.0 4,457,600"5-21 25.0 10,074,800(u)

(a) Did not fail.

J

87

4) 14

~~e IC7 Nn 0 C- ' r4

i

0 0C0 0 00 0

N 4 .. = e4 0 en)vSO an.. 0 0~ 0 0 a 0' ca

u4 e U \ Z1 co a, cnn N n Il c.i tA 0

'a r- N4D i-I IT m ~ .% 4 00l 4n 4lA C' 0

.2 16. N~ 0i- eN N 4cn

ca-4

CL x A cC - 0 C3 0% en C, A 3 C

0.-Lm en 4 4.0 0 'a nN N n n .'J In - 4 - 4 a, N a C ,

to 0s q -t4

c3 n c a, c4 1 S a, 4 C; 0m I

04 en r4

0

14 0 A~ 0040

71 in 4- U

A ACgoin 0A

41 a% N ) N N c4 B a44.

0 44 -- C;. C4N n C Co

Si A 4n~.

J,4a * 64 a C NC0 9 0

1. fec -'n a r4 in t

in cm g

C; £ r--a O 9 i

200Longitudinal

175

150 -

- ooo p125 - 0

100

75

50- 1I

0 0.002 0.004 0006 0.008 0.010 0.012:, ,Strain, In./in. A•-1394

rIGURE 42. TYPICAL TENSILE STRESS-STRAIN CURVES FORTi -bAl-2Sn-4Zr-6Mo SHEET (LONGITUDINAL)

89

200 --. ---

Transverse

175

RT

400 F

125 ---

700 F

1, f -1Q00 FSIOO

75 7

50-

25-

0 0.002 0.004 0.006 0.008 0010 0.012

Sirain, in./in A-139

FIGURE 43. TYPICAL TENSILE STRESS-STPAIN CURVES FORTi-6AI-2Sn-4Zr-6Mo SHEET (TRANSVERSE)

90

200

Longiiudinal

175-- R

15 --

50--

; ,/... I

0 0.002 0.004 0.006 0.008 0.010 0-012

Strain, In./in.

,•L _L1I I .J0 4 A 12 16 20 24

• rTangent Modulus, 0 psi A-1151

FIGURE 44. TYPICAL COMPRESSIVE STRESS-STRAIN AND TANGENT-MODULUS CURVES

FOR Ti-6A1-2Sr&-4Zr-6Mo SHEET (LONGITUDINAL)

91

.-. 14.' 4,4~* A. .- ~-

Transverseý

-RT RT

150- /.400 //40C

'707

25j7//i

0 0,0012 0,004 0.006 (2000 QUIO 0012Strcain, in./In.

02 416I 201 24

Tangent Moduiu5, Q06 PCi; S

FI'JLRL 45. TYPICAL GOW'4.LSSIVE S7~SSlAWAND TANGEg•KZODULUSCUThFS FOR -I-6Al~l2Sn-4Zr.-6Mn- SHEET (TANSTEPSE)

02

180II~

TUV,~o TYS -- j

OTUS ()-A2T~US (T)-

100 UTYS (L) I80L2TYS (T)

40 j Ju j(L)200Modulus (L) __

0 Elonvti~on (L)0) El~ongation(T 1620--

0 900 400 600 800 I~

Temperature, F

IFIGUid, 46. EFEFECi OF TF1'EMRATURE ON TRK TENSILE PROM1 RTXESOF Ti-6AI-2Sn-4Zr-6Mq SHEET

160 1 0

rModulus (L)j

0 Modulus (T)

-C 200 400 600 8000 10~Temperature, F A-IbS?

rwuhI11C 47. ThKP'rcc.[4 or rupuar oimcA)MPREssivE

rL~~u1'JoK- IkRI.ht ES of Ti -6A1 -2Sn-4Zr..6Mo SHEET

I9

O -- I ". . Unnotch.ed

774j 8 400 F Tr -ansv~rse

II

60- -

Lifetime, cycles

[i FIGURIW 48. AXIAL LOAD FATIGUE RESULTS FOR U!N1OTCHED Ti-6A1..2Sn-4Zr-6Mo SHEET

120F

00 - 0 Ko o-•-. 0

FIGUR 49 K*LLODFTGE EUT O NOT1I (K .0 K,-6A-Sn.0-M, 'E

• • 60 1 1•,• If ! .. :

E-

'R 94

* RT "-'20 -- a 400 F

* 700 F

Lifetime, cycles ^=s

FIGURE 49. AXIAL LOAD FATIGUE RESULTS FOR NOTCHED (Kt -3.0) Ti-6Al-2Sn-4Zr-6Wo S%1EET

94

---

1116 CL

In

IF I -

U-z

OLDL ~1

i.l 4IsJsfl

95A

Inconel 702 Alloy

Material flescription

InCXtLel alloy 702 contains high aluminum content for excellentresistance to oxidation at temperstures up to 2400 F. At elevated tempera-tures, the surface of a nickel-rich, ntckel-chrominu alloy becomes covered witha compact layer of uniformly thick oxide- the aluminum content of alloy 702improves thr protective action of the oxide. Alloy 702 has good mechanical strengthat high temperatures; age hardening improves the strength of the alloy up toabout 1500 F.

The material used in this evaluation was 0.050 inch sheet from HuntingtonAlloy Products Divtsto; Heat HT38C3DS. The comporition ,,as as follows:

ChemicalCEomposition Percent

Carbon 0.01Manganese 0.02Iron 0.32Sulfur 0.007Stlicon 0.11Copper 0.01Chromium 16.34Aluminim 3.12Titan:.am 0.54Nickel 79.50

Pxcessing and Heat Treatsna

The spec'rmen layout for Ynccrel 702 sheet is shown in Figure 51.

Spcimens U Lere MaCaiu .n r... . .......... & u %.LeV&L L 1cdCLw

14'0 r for 5 hours.

Test Results

Tension. Results of tebLe ax longitudinal and transverse spacimensat room temperature, 600 F, 1000 Y, and 1400 F are given in Table EXUIX. Tensilestress-strain curves at temperef.re are shown in Figures 52 and 53. Effect-of-temperature curves are presented in Figure 56.

Comyression. Compression test result" at room temperature, 600 F,1000 F, and 1400 F for longitudinal and transverse specimens are given in TableXL. Stress-strain and tangent modulus curves at temperature are presented inFigures 54 and 55, Effect-cf..temperature curves are presentted in Figure 57,

96

E40

Lot

C4 N I 0 1 f i l l 6. . .

S [5I'zi!" ____ '"F,

zaI ,i ' ____" __ tI-" i

va OUR--

" 4 .. " , 1 IJ -'

7 1_ I0;"

Its t~~agfisw

Olp 99 bts"S 1G49 fg M. Its

_______to_____ 0__________ ________________ 919 Io 6I

19 97

Shear. Test results for longitudinal and transverse specimens ut roomtemperature are given in Table XLY.

Fracture Toughness. Tests were conducted on specimenu of full sheetthitkness (0.050-inch) by 18 inches by 36 inches with EM' flaw in center,. Thenet section yield stress at fracture was greater thar, the tensile yield strengthof the materials; therefore, the K values are considered not valid.

Fatigue. Axial-load fatigue test results for unnotched and notchedtransverse specimens at room temperature, 600 F, and 1000 F are given in TablesXLII and XLIII. S-N curves are presented in Figures 58 and 59.

Creep and Stress-Rupture. Tests were conducted at 800 F, 1100 F, and1400 F for transverse specimens. Tabular results are given in Table XLIV. Log-&tress versus log-time curves are presented in Figure 60.

Stress Corrosion. Tests were conducted as described in the experimentalprocedure section ot Tfi-rrjport. Uo failures or cracks occurred in the 1000hour test duration.

alloy is 87 x F for 70 F to 1500 F.

Density. The density of this material is 0.305 lb/in3 .

t t 98

TABLE XX.IX. TENSILE TEST RESULTS FOR INCONEL 702 SHEET (AGED)

Ultimate 0.2 Percent

Tensile Offset Yield Elongation Tensile

Specimen Strength, Strength, in 2 inches, Modulus,

Nu. ksi ksi percent 10e psi

Longitudin at RoomTemerate

IL-I 152.0 ;4.6 34.5 34.8

IL-2 153.0 94,8 35.0 35.2

IL-3 153.0 94.8 35.0 33.5

Transverce at Room Temperature

IT-I 151.0 94.5 34.0 34.4

IT-2 1.51.0 94.5 34.5 33.8

IT-3 151.0 95.3 34.0 JZ.9


I.L-4 139.0 85.0 35.0 30.1

IL-5 139.0 86.0 38.5 29.5

1L-6 139.0 86.0 34.0 29.2

Transverse at 600 F

1T-4 137.0 86.3 36.0 31.6jq~~ ~ A37-0 30.0

IT-6 138.0 86.4 37.5 31.1

Longitudinal at 1000 _

IL-7 131.0 85.5 36.0 28.3

1L-8 131.0 84.1 36.0 30.6

IL-9 130.0 84.0 37.0 28.8

Transverse at i00U F

1T-7 129.0 85.7 34.5 28.3

IT-8 128.0 84.9 36.0 26.91T-9 128.0 85.2 36.0 27.8

99

I

TABLE XXKIXo (Concluded)

Ultimate 0.2 PercentTensile OfUset Yield Elongation Tensile

Specimen Strength, Strength, ir 2 , , Modulus,ND. ksi ksl perccr.t 10 10 psi


IL-10 66.3 63.8 8.5 19.7IL-il 66.8 64.5 9.5 20.0IL-12 65.4 62.4 10.0 21.0


IT-10 67.1 64.6 9.0 19.9

IT-I1 67.5 64.9 8.5 1.9.6IT-12 68.0 65.8 7.0 22.9 * I

' T,

TAnLE XL. COMPRESSION TEST RESULTS FORINCONEL 702 SHEET (AGED)

0.2 Percent CwmpressivfSpecimen Offset Yield Modulus,

Number Strength, kel psi x lcp

Lonitudinal at Room Temeratu•e•2L-1 99.0 34.22L-7 99.4 34,22L-• 99.8 34.8

24Trans.erse at Room TemneratureS2T..1 i01.0 34.5

2T-2 101.0 34.52[-3 101.0 35.0


2L-4 91,0 34.5

2L-5 91.3 34.4"2L-b 9U.85 3b.1

Transverse at 600 F2r-4 94.4 33.0

2T-5 93.6 34.82T-6 92.8 32.2

Longitudinal at 1000 F2L-7 90.7 31.32L-8 90.3 29.22L-9 89.6 30.0

Traniverse at 1000 F2T-7 90.9 31.32T-8 90.3 30.42T-9 91..9 30.1

LongLtudinal at 1400 F2L-l0 67.5 20.72L-11 68.1 22 02L-12 68.3 20.2

Transverse at 1400 F2T-10 7•0.4 20.22T-1I 7U.6 21.02T-12 70,5 20.9

101

IABLE XLI. SHEAR TEST RESULTS FOR INCONEL702 SHEET (AGED)

Specimen Ultimate ShearNumber Strength, kui

Lonxitudinal

4LI 117.0

4L2 115.0

4L3 117.,

4L4 116.0

Tranpverse

411 117.0

4T2 116.0

4T3 113.0

4T4 117,0

102

TABLE XLII. AXIAL LOAD FATIGUE TEST RESULTSFOR UNNOTCHED INCONEL 702 SHEET(AGED) (TRANSVERSE)


Room Temperature

5-4 75.0 98,3005-3 65.0 209,9005-2 55.0 591,7005-1 45.0 1,594,8005-8 40.0 7,086,4005-5 35.0 3,403,100..5-7 30.0 L0,138,000(a)5-6 25.0 10,130 ,o000

600 F

5-11 75.0 117,5005-12 65.0 184,4005-13 55.0 584,2005-14 45.0 4,809,000O5-16 40.0 10,226:700()5-15 35.0 12,376, 900

1000 Y

5-21 75.0 12,4005-22 65.0 245,3005-23 65.0 536,2005-26 60.0 5,428,8005-24 55.0 4,337,200. (a5-25 50.0 10,097,70 (a)5-27 45.0 10,331,300

(a) Did not fail.

103

TABLE XLMIT. AXIAL LOAD FATIGUE TEST RESULTS FORNOTCHED (K< - 3.0) INCONEL 702 SHEET

(AGED) (TRPNSVERSE)

Specimen Maximum Lifetime,Number Stress, ksl cycles

Room Temperature

5-4 65.0 31,9005-3 55.0 111,1005-2 45.0 336,2005-7 40.0 782,4005-8 40.0 1,651,0005-1 35.0 1,511,600 fl5-6 30.0 636,000 (a5-ý 25.0 1 0 , 5 3 7 , 5 0 0(a)

600 F

5-13 65.0 15,7005-11 55.0 75,300

5-15 50.0 821,2005-12 45.0 2ý0,4005-24 42.5 6,248,0005-25 40.0 3,672,800 (5-16 37.5 24,268,000Ca5-14 35.0 10,069,500(p.)

1000 F

5-21 65.0 12,9005-22 55.0 51,5005-27 50.0 719,2005-23 45.0 1,q74,8005-35 40.0 7,917,100 .5-34 35.0 10, 54 9 , 6 0 0(a)

(a) Did not fail. 4

104

I a ' 0 cn - m .-4 -4n

a 0n

.4 4

C4 .

0 v c A 0%e C V n

r. 0

0 'D40 'n~ 0.4 P-Sb

-4 -4

5- .4 -4 54 -4 0 ý4jf A 04 ený

%4S 14

-, a C;'.5 -

Ct Is V~ Is ' M~tO 1

1.;

120Longitudlno;

905-

75

1400 F

~e0

45-

0 0.002 Q004 Q006 QOO8 Q.010 0012Strin In.in

FIGTJRE 52. TYPICAL TENSILE STRESS.-STRAIN CURVES FORINCONEL 702 SHEET (AOEIb) (LONGITUDINAL)

106

Tronsverse

90- 600 F

VOF

140 F

~6 o

40

fb-

0 (A002, 0.%J)4 0.os 0008 CLOD 0.012Straon, [n./i. A-1410

HUUIAL, 53. IYPICAI. Th1J311E STRI3S-STRAIN CURVES FOR114CO~ULL 702 S1TJeST (AGED) (TRANSVERSE)

to0'

120

Longitudinal

"105RT

757

tiIt60

S~45•

0 Q,002 0.004 0.006 0.008 0.010 0012

Struln, in./in.

0 6 12 ld 24 30 36

Tanpent Modcluos106 PO , A-1153

FI(,IJRE 54. TYPICAL COMPRESSIVE STRESS-STRAIN AND TANGEUT-MODULUSCURVES FOR INCOIEL 702 SHEET (AGED) (LONGITUDINAL)I10

120-

Transverse

105-R

RTI

__________________________________________00__

1009

f 6l0* 0 TYIS Mi

S120.CI)S

CC10k _2 _'__

20 - 0 Elongation MC28)& Elongation (T Modulus . Eio tloi,..--

1-QModulus UC2L)2j ~ 0Modulus (T

0 200 400 600 B00 1Q00) 1200 1400

Te mperature, F

FIGURE 56. EFFECT OF TEKPVRATURE ON THE TENSILEPROPERTIES OF INCONEL 702 SHEET (AGED)

so LCY S(L) .--...... 28_0o CYS (T) cs

~ ~60 oModulus (L) 2c~i OL Modulus MT

40C20 200 400 600 B00 1000 1200 K400

Temperature, F -7

FIGURE 57. EFFECT OF TEMPERATURE ON THE COMPRESSIVEPROPERTIES OF INCONEL 702 SHEET (AGED)

11.0

I 9 0 - . .. jI Unnotched

SI • • •l .'rronsverse

80- R -0,

" 60--. . -_ - -

1 0-. , -- - - -- __-60

30 0 RT

20 104 600 F W

10 3 1O O 1i0• !0o IOai(P 9

Lifetime, cycle.

FIGURE 58. AXIAL LOAD FATIGUE RESULTS FOR UNNO'.CHED INCUNEL 702 SHEET (AGED)

80 -- -- ... TTTT --

80 Notched

70- - I __ - - TransverseS. . .. t R -O~i"6R -0

K03.600

4C - -- -- ---0 - -

40-0

0ORT03 0 -A 600F---

20 - . �. -1 1-

Lifetime, Cycle A-44M

FIGURE 59. AXIAL LOAD FATIGUE RESULTS FORP NOTC•ED (Kt w 3.0) INCONEL 702 SHEET (W.GED): Ill

_ 04

LA--

I - L-1-"4 -

0 G 0

1124

Inconel 706 Alloy

Material D(reition

Incanel alloy 706 is a precipitation-hardenable, nickel-iron-chromi,zi m&Li with characteristica similar to those of Inconel 718, exceptthat 71)6 hav improved machinability. It has high strength at temperaturesranging from cryogenic to 1300 F. It also has good resistance to oxidationand corro,.ion over a broad range of temperatures and environments,

Fabrication of the alloy is enhanced by its good formability aadweldability. Alloy 706 hau excellent resistance to postweld strain-age

crackiog.

T'he material used in this evaluation was obtained as a 6-inch-square forging from INCO,Hnat Irf5OC3HK. The composition was as follows:

£ Chemical

Composition Percent

Carbon 0.03Manganese 0.12Iron 36.37Sulfur 0.007Silicon 0.13Copper 0.02Chromium 16.32Aluminum 0.28Titanium 1.62Columbium plus

Tantalum 2.9GNickel 42.12

Py~jo t.sa d Heit Tr•a- ma

Thy! 6-Lich-square material was press forged to a 2 inch x 6 inchbar to make viecimen blank* eawier to obtain. The specimen layout ia showniD Figure 61. After machinrking, specimens were heat treated as follows foropt mum creep-rupture strength:

(1.) lr'tO F, 2 hours, air cool,

(¶) i!¶iO F, 3 hours, air cool,

(3) IM25 F, 8 hours, furnace cool to 1150 F, hold fo19.1 hours, air cool.

Test Results

Tenriiov, Results of longitudinal and treanverse tests at room tempera-ture, 800 V-1THO F, and 1200 F are given in Table XLV. 8tress-straiu curves at

S 3.13

IUI

11.23

[ - •OK

a i" a.'t

i's

114

F I

temperature are shown in Figures 62 and 63. Effect-of-temperature curves areshown in Figure 66.

tm Ctmpression. Results of longitudinalv and transverIe tests at rooatemperature, r0esi, o00 F, and R200 F are given in Table XLVI. ttress-strao nand tangent-modulus curves a.- temperature are shown in Figures 64 and 65.Effect-of-temperature curves are presented in Figure 67.

rhear. Pin shear test results for longitudinal and transversespecimens a: room temperature are given in Table kXLVII.

Impact. Charpy test results for room temperature longitudinaland tralsverse specibvns are given in Table XLVIII.

Fracture ToughnrLea. Results of slow bend tests at room temperatureare given in Table XLIX. Th,', size ratio, 2.5 (KQ/TYS)s, wps greater than boththe specimen thickneas and crack length in all tests, therefore the KQ value inthe table is not a valid KIC vilue by existing ASTM criteria.

FAtnoUS. Axial-load fatigue tests were perforaed on transverse speci-mens, both notc d and unnotched, at room temperature, 600 F, and 1000 F. Te.Lresults are given in Tablas L and LI. S-N curves are presented in Figures 68 and69.

Creep and Stress-Rupture. Tests were conducted at 809 F, 1000 F, and1200 F. Results are given -in bTe LII. Loi-atrnss versus log-ttae curves tr'4

presented in Figure 70.

Stress Corrosion. No failures or cracks occurred in thc 1000 hourtest duratiorLt as discrled in tEM oxpari-ntal pr.... cdre ection of this report.

Thermal Expansion. The coefficient of thermal expansion for Inconel706 is 9.8x0"0i7i-nf-lor 70 F to 1500 F.

ensity. The density of this material is 0.291 lb/in3 . 4

115

TAPLE XLV, TENSILE TF.,' PESULTS FOR

INGOEL 7lM FORGED LAA(STRISS-RUJrUMR IIEAK TELATMEdT)

Ultimate 0.2 percent Elongation Reduction Ttnmsile

Specimen Tensila Offoet Yield in 2 inches, in Area, Modulus,

Number Strength, kai Strength, Lei percent percent i08 psi

Lait•inlSLe

IL-1 177.0 138.9 22.0 32.5 30.9

e IL-2 178.0 139.0 22.5 33.5 28.9

.L..3 178.0 139.0 22.0 32.5 27.9

raneverumrht Room aTaiermitor4e

IT-I 176.3 146.0 21.5 30.0 29.7

XT-2 176.0 140. 0 22.0 31.5 28.6IT-3 176.0 140.0 22.5 31.5 51.6

SLonitudial. at 800 F

lL-4 157.0 120.0 22.0 37.0 24.3

1i.-5 155.0 120.0 21.0 39.0 23.9LJIU *.a~ 3~5 2&4-

""ransv.rse 1t 800 v

IT-4 138.0 121.0 21.0 36.5 24.8

1T-5 IY5.0 122.0 20.5 33.5 25.91 .-6 1!. .0 U.3.0 19.0 34.3• 23.3

Lorfttudtnal at 1000 F

IL-7 X52.0 119.0 20.0 38.0 22.1

IL-8 152.0 120.0 20.5 40.0 20.4

IL-9 151.0 119.0 22.5 40.5 21.2

TranmverSe at 1000

3T-7 152.0 120.0 19.0 33.5 22.0

1T-8 153.0 M21.0 19.5 35.5 21.2

1T-9 154.0 122.0 18.0 35.0 21.3

Longitudinal &L 1200 V

IL-10 139M0 117.0 25.0 39.5 21.4

IL-I 138.0 116.0 25.5 40.5 21.4

IL-12 138.0 115.0. 26.0 41.5 20.3

IT-10 139.0 11M.0 23.0 40.0 20.1

IT-1i 139.0 117 0 24.0 36.0 20.7

IT-12 139.0 118.0 21.5 37.5 20.9

116

"TABLE XLVI. COMPRESSION TEST RESUL.TS FORINCONEIL 706 FORGED BAR(STRESS-RUPTURE REAT TREATMENT)

0.2 Percent

Offset Yield CompressionSpecimen Strength, Modulus,

No. ksi 106 psi

Longitudinal. at Room Temperature

2L-1 149.0 31.82L-2 150.0 30.92L-3 150.0 30.6


2T-1 149.0 30,82T-2 149.0 31.12T-3 149.0 32.4


2L-4 127.0 23.92L-5 124.0 25.22L-6 129.0 23.7

Transverse at 800 F

2T-4 129.0 24.6

2T-6 128.0 23.9

Lm.i.,itudinal at 1.000 F

2L-7 123.0 23.221,-8 123.0 23.02L-9 124.0 22.8


2T-7 125.0 24.52T-8 125.0 23.42T-9 124.0 24.0

1i7

TABLE XLVIJ (Conrtuded)

0.2 PercentOffset Yield Co~np'e•*ion

Specimen Strength, iGVdulus,

No. ksi I,' psi

Longitudinal at 1200 "

2L-10 118.0 !3.32L-11 120.0 22.02L-12 122.0 22.1

Transverse at 1IM F

2T-11 120.0 ..2 I2T-i1 120.0 22° 22.

11

Ii

11.8

TABLE XLV I' SMEAR 12?YST RES'J.!:? FOR ).I,, tL 706 FOKGTb BAR

(CTRES-WfUSZ EA!C TREAT-KEN)

S pu, mel UltiuuiLC Shear

4L,-1 119.041 2 117.0I4 A-3 1,17.04 4-4 118,0

T- arpverse

4 T - -1 7 b

I AT-Ii U7.b 1

4P-3 117.0 I

Mimi

T~kDLE XLTVI)). ILIPAcrL TES',' RfQ5rULTS FOR 1INCONE-f 706 FORGED BAR(ZTl1.1ESS.-RIUPTURE- HEAT TREATMEMT)

S pvAt.-c mn Energy,Numba f ijlbc

IOL-i 29 5-

~CL 32.0

101,-3 33. I1O- 33.0

10~. .~32.0

Tr~ana-m.rse

10T-2 26.0.31

107-4 ~6*5i~a .-3 27.0.

I~~~ 'U ¶

It

I

[ 'ITABLE XLIX. FRACTURE TOUCHNESS TEST RESULTSFOR INCONEL 706 FORGED BAR(STRESS-RUPTURE HEATTh•ENT)

Nutl¢pr iftcholl inkhot inch a, lba inches f( 4)

Loniitudinal

IL 1.498 .737 .750 9,800 4.5 2.6 $3.3

2T 1.499 .754 .751 9,900 4.5 2.6 86.9

3it 1.500 .760 .750 10,250 4.5 2L7 91.1

1. 2.497 ,740 .750 10,150 4.5 2.6 88.3

2'j 1,490 .749 .747 9,85C, 4.5 2.6 84.3

37 1,49/ .735 .749 10,7"O 4.5 2.6 9L.3

(a) C•rt•cllatt Vro(. cvl;± toughinosB va&lu*o', , are invalid a& s c values since a,

122

TABLE L. AXIAL LOAD FATIGUE TEST RESULTS FORUNNOTCfED INCOU•EL ?06 FORGED BAR(STRESS-RUPTURE HEAT I4EATMENT)(TRANSVERSE)

Specimen MaximumTV L fe time,Number Stress, ksi cycles

Room Tem.perature

5-3 125.0 88,1005-4 115.0 150,3005-2 105.0 227,5005-1 95.0 364,4005-5 65.0 679,0005.6 -75.0 2,199,4005-7 "65.0 8,446,0005-8 60.0 10,025,200(a)

600 F

5-17 125.0 25-2205-18 ~ -11 0 A~ n5_19 105.0 82,100

5-10 95.0 139,9005-21 85.0 164,3005-22 75.0 422,3005-23 65.0 6,226,100=-24 55, " 1 0 , 7 9 2, 7 00 (a)

1000 F

5-9 125.0 14,Ot63-10 115.0 42,7005-11 105.0 31,3005-12 95.0 163.6005-13 85.0 165,3005-14 75.0 722 3005-15 65.0 2,232,3005-16 55.0 5,557,7005-25 45.0 12,239,200(..'

(e.) Did iot fail.

122

TABLE LI. AXI LOAD FATIGUE, TEST RESULTS FORNOTCHED (Kt - 3.0) INCOIIEL 706 FORGED )AR(STRESS-RUFTURE HEAT TRMATMENT)(TIANSVERSE)

Specimen Maximum Lifetime,Number Stress, ks cyycles

Room Temperature

5-1 105.0 9,9005-2 9j.0 14,1005.1 85.0 32,0005-4 75.0 29,0005-5 65.0 47,2005-6 55.0 88,300547 45.0 150,0005-8 35.0 445,9005-23 30.0 475,0003-9 25.C 4,770,490 (5-10 20.0 11,953,000'a)

600 F

5.1-1 75.0 25,3005-12 65.0 44,9005_01 55.0 74,0005-14 '.5.0 204,7005-25 40.0 255,1005-15 35.0 529,5005-26 30.0 10,O12,OOO(R)5-16 25.0 1 3 , 0 9 1 , 9 0 0 (a)

1000 F

5-17 75.0 12,2005-18 65.0 25,7005.19 55.0 46,9005-20 45.0 116,3005-2/. 40.0 1 7 , 5 5 5 , 7 0 0 (a)

:5.21 35.0 7,421,6005.-22 30.0 11,685, (a)

(e) Did not fail.

123

g.40 C-44 CJ

t1 S, CASr¶ 0 0

CC

0 4L.].

a 0ý0 CrJN %& RC O1 C4 ý4 cnIfo' 4'U

ýC. ý44 .- 0d 4'r

V5 to m -4%

a-; do .4' 4-- m~ -

1 4 . .4 %0 y4 0 0

is Q. ) w- C4m P.4 -0 cc

r-~ 44 0 (4.

04 4

Aii a. 040

It n

* 9*2.4 ,

OFt. 0 -S 00C .

"1 s F1 4 ,

4.InnA.: .., ' 4 8 .1

v--. 4 r44"q H v4 ri vC,-4

*44

on Vt (V,Vt 4 I'll on

160 Longitudinal Rr

140- 0

120-::ý 126F

100-

60-

40

20-

0 00 .04 D6 0.008 ('.01 0.012

FIGURE 62. TYPICAL ThtNSILE- STRESSATRAIN CURVES FORINGOONEL 706 PP0RGLID PAR (LON4G ITtDINAL)(SMkE8-1UIUklr H"IA TWMMI~TW)

125

Transverse RI

140- 0

100-

~80~

0 0.5102 0.004 000f6 0008 QIor 002

Stioln, IVn./in.56

P1.GURE 63. TYPICA.L TfrNSILL STUSES-SThAIN CURVES FOR~I~l'NU-L 706 FORCED B~AR (ThANSVEaB98)

(TEl-RUI-fUlE1kRE HEAX~ TI'A.TKENT)

1.26

RT Longitudltiol

140F

p00so-

60--

40--

0 0002 000 0006 0000 0.010 001?

o 5 10 Its 2.0 2530Tangent Modukis, *4 psi A-3

FIGURE 64, TYPICAL COMPRESSIVE STkESB-STRAIN AND TAYENrr4IO1DLUSCURVES FOR INCONEL 706 FORGED BAR (LOlNGLTUD1NAL)(STRESB-1UJMFTIJ HW~ TWHKEANET

127

ISO -

RT Transverse RI'

1200

100-

s8o-

4--

60

20

0 0-wt 0.004 0.006 (0000 OO O1

Tangent Modulu, 0) psiA-4

FIQURE 65. TYPICAL COt4PRLBSIVE 8¶llESS-BTRAIjN Allb TANGENT -H)DULIUSCURVES FOR INCONEL 706 FORGED bAIL (TRANSVZR$SE)(STRESS-RUlyTURE HEAT TR&AXIMEk)

128

180 -

616 --

_ S

0 Tus (L)0 TUS (T)_nTUS (L)

60 ,,TUS T) _

35 -,Z • - _o

Modulus30 ----- - -

Elongotk~n

20c Elonoation (L)

,. 5A Elongation ')- I %

2 I

0 I

101 Modulus (T)

0 200 400 600 800 tw00 1200

lemperoture, F

FiGURE 66. EFFECT OF TePRAIVRJE 01 THE TENBUY,PROPERTIESI OF INCONEL 706 FORGED UAR(STRESs-RIPTUuE RUIT r•uA1ElNT)

0 '-o Modulus (L) ,

0---" 22O 200 400 10 0 000 1200

S~~FIGURE' 67, EFFECT OF TEMPERAATURE ON "T1• COMPiESSIVE

PROPIERT1EE OF INCONEL 706 FOILGED MiP,(STRESS-IRUPTURE HA '/kIET

129

(L = = = = = = =

140- Transverse

0 Rl'

Lifetime, cycd"

AVLAT. T.QAD FATIGUJE RESULTS FOR U1NiOTCHED INCONEL 706 FORGED BlAR

NotChedTransverse

Kt,-3.0

130

-130

fci d 1i

L163LL0

DISCUSSION OF PROGRAM RESULTS

The tendency in an evaluation program of this type is to compare themiý.terials property information obtained with similar data on materials alreadyin use. Whether such a comparison should be the deciding factor for interestin a newer alloy is open to question. Many criteria, such as forming character-istics, weldahility, oxidation resistance, etc., can be of particular importanceso that strength properties may become secondary. However, since first compari-sons are almost always made on the basis of mechanical strength (tensile ultimateand tensile yield) the data generated on this program are compared to informationfor similar alloys in Figures 71 and 72.

CONCLUSIONS

The objective of this program was the generation of useful engineeringdata for newly developed materials. Duriag the contract term the following alloyswere evaluated:

(1) 15.5 PH (H1025) stainless steel forged bar

(2) HP 9Ni-4Co-0.20C steel forged bar

(3) PH 13-8 Mo (H1000) stainless steel forged bar

(4) 7049-T76 aluminum extrusion

(5) 6A1-2Sn-4Zr-6Mo titanium sheet

(6) Inconel Alloy 702 sheet (Aged)

Ii -ne A611eny 7f6 f£rSed bar (Creep-rupture heat treatment),

A data sheet was issued for each material, As a susnary, each of thedata sheets is reproduced in Appendix Ill.

132

. /4I

"INI

1331

1 E4

~ttIa

q~qr./ I10r

/~ I J __

134H

*1'IK?I

I1!. .4

dv

APPENDIX I

EXWRP4W3'AL PROCEDURE

V -- a--I II

U

I135

I

APPENDIX I

EXPERRI)INTAL PROOCFDUREP

Mechanicr l Properties

The various mechanical properties of interest for each of the atate-rials are as follows:

(1) Tension

(a) Tensile ultimate strength, TUS

(h) Tensile yield strength, TYS

(c) Elongation, e

(e) Modulus of elasticity, Bt+

(2) Compression

(a) Compressive yield ctrength, CYS

(b) Modulus of elasticity, R .

(3) Creep and stress-rupture

(a) Stress for 0.2 or 0.5 percent deformation In 100hours and 1000 hours

(b) Stress for rupture in 100 hours and 1000 hours.

(4) Shear

(a) Shear ultimate strength, SUS

(5) Axial fatigue*

(a) Unnotched, R - 0.1, lifetilue: 103 through 107

cycles

" "R" represents the algebraic ratio of the minimum stress to the maximum stressin one cycle; that is, R Smin/ Smax. '"IL' t' represents the Neuoer-Pet.rsontheor tical stress concinLrat on factor.

136

(b) Notched (K.- 3.0), R 0.1, lifetime: 103 throu.gh

107 cycles.

(6) Fracture toughness, K r

(7) Stress corrosion

(a) 80 percent TYS for 1000 hoursmaximum, 3-1/2 percentNaCI solution.

(8) Thermal expansion.

(9) Bend

(a) Minimum radius.

(10) Impact

(a) Charpy V-notch..

(11) Density.

pecimen, Identification

A simple system of numbers and letters was used for specimen identifi-cation. Coding consistel of a number indicating the type of test and also indi-cating a comparable area on the sheet, plate, or forging. For certain testtypes, the number was followed by a letter signifying specimen orientation (Lfor longitudi[Lal, T for transverse, ST for short transverse). The test typeswhere the letter did not appear were creep, fatigue, and bend since, in these

c3ses, only one specimen orientation was used. The next number in the codingspur.Lflia tbe lo--t--n _rcm wht¢h the &Deciwon blank was taken from the originalmaterial configuration. Coding was as follows:

AssignedNumber Test Type

1 Tension

2 Compression

3 Creep and stress-rupture

4 Shear

5 Fatigue

6 Fracture tcoughnras

137

AssignedNumber Test Type

7 Stress corrosion

8 Thermal expansion

9 Bend

10 impact

11 Density

As an example, a specimen numbered 2-T5 is a compression specimen, transverseorientation, cut from Location 5. Also, a specimen numbered 5-12 is a fatiguespecimen cut from Location 12.

Test Description

Tension

Procedures used for tension testing are those recommended in ASTHmethods E8-68 and E21-66T as well as in Federal Test Method standard No. 151a(method 211.1). Sir. specimens (three longitudinal and three transverse) weretested rt each temperature to determine ultimte tensile strength, 0.2 percentoffset yield ntrength, elongatior., and reduction in area. The modulus ofelasticity wr.. obtained from lotd-strain curves plotted by an autographicrecorder during each tesL.

All tensile tests were carried out in Baldwin Universal testingmachines. These machines are calibrated at frequent intervals in accordancewith ASTH wtbod £4-64 to a"sure loading accuracy wit.u... 0.2 perc-nt. Themachines are equipped with integral automatic strain pacers and autographicstrain recorders.

Specimens tested at elevated temperatures were heated in standardwire-wound resistance-type furnaces. Each furnace was equipped with a Foxborocontroller capable of maintaining the test temperature to within 5 F of the con-trol temperature over a 2-inch gage length. Chromel-Alumel thermocouplesattached to the specimen gage section were used to monitor temperatures. Eachspecimen was soaked at temperature at least 20 minutes before being tented.

An averaging-type linear differential transformer extenesoeter wesused to measure strain. For ellevated temperature testing, the extensometerwas equipped with extensions to bring the transformer unit out of the furnace.The extensometer conformed to A[ L E3-64T Clataification B1 having a sensitivityof 0.0001 ioch/inch. The strain rate in the elastic region was maintained at0.005 ipch/inch/minute. After yielding occurred, the head speed was increasedto 0.1 inch/inch/minute until fracture.

138

Compre sB3 ion

Procedures for conducting compression tests are outlined in A-STMMethod E9-67 along with temperature control provisions of E21-66T. All sLeetand thin plate tests were carried out in Baldwin Universal testing machinesusing a North American type compression fixture as shown in Reference 2.Specimen heating was accomplished by a forced-air furnace for temperatures upto 1000 F. Specimen temperature was maintained by means of a Wheelco pyrometer.Three Chromel-Alumel thermocouples attached to the fixture were used to monitortemperatures to within 3 F of the test temperature. For highe.: temperatures,wire-wound furnacc.s were used with controls as described in the tensile test isection.

The extensometer useJ for the compression tests was quite similar tothat used in the tensile testing. The axtension arms were fastened to the speci-men at small notches spanning a 2-inch &age length. The output from the micro-former was fed into a load-strain recorder to provide autographic load-straincurves. Diring testing the strain rate was adjusted to 0.005 inch/inch/minute.

For bar and forging "terial, cylindrical specimens similar to thosedescribed in ASTM E9-67 were used with appropriate temperature control and strainmeasurement as described above.

Six apecimens (three longitt, lnal and three transverse) were tested ateach temperature.

; 'hear

Single-sheoa sheet-type specimens were used for sheet anid thin-platematerial; for ber and forgings, a double-shear pin-type was used. Shear testingwas performed at room tomperature only. A minimum of six specimens (three loigi-tudinal and three transverse) were used to determine ultimate shear strength.

� Bend

The procedures for conducting bend teszs are described in Report HAB-192-M. The specimens were placed in a rigid three-point loading ft:cture andbending tups of various sizes were used to .determine the minimuu bend rclis

at r'jom temperature.

Creep and Stress Rupture

Standard dead-weight type creep testing frames were used for tht creeland stress-rupture tests. These machines are calibrated to operate tll. withinthe accuracy requiremente of ASTM method E139-66T.

139

K.

Specimens similar to those used fo. tension tests were used for thecreep and stress-rupture studies. A pl&tinum, strip "slide rule" extensometeris attached fcor twasuring creep strain and thrae Chromel-Alumel therm.accuplesare attached ro the gage section for temperature measurcments. Extensometermeasurements were mede visually through windows in the furnace by means of aMilar micrometer microccope in which the smallest division equals 0.00005

inch.

1The furnace was of conventional Chromel A wire-wound design with tapsalong the s.dL to allow for correcting small temperature differences. Furnacetemperature wat maintained to within + 2 F by Foxboro controllers in response tosignals frcta the centrally located thermocouple. The temperature of a specimenunder test woe stabilized for at least 1/2 hour prior to loading.

For each temperature condition creep and stress-rupture data were ob-tained to 100 and 1000 hours using as many specimens as necessary to obtainprecise information. The percent creep deformation obtained was deperdent onthe material under test. In most instances streas-time curves were defined for

r 0.2 and 0,5 percent elongation.

Stress Corrosion

corrosn, -,racking by alterate immersion in 3-1/2 percent sodi•mt chloride solu-tior,• at r:on temperature.

Specimens were prepared for testing by degreasing with acetone. Where

& turiace film remained from heat treating, it was abraded off one side and theadjacent 'rong edge of five of the specimens, and left intact ar the other two.

Etx-h specimen was placed in a four-point loading fixture and deflected

tG a stress coPrresponding to 80 pe:ceut of the tensie yield strength of thoýparticular wat..riol. The specimen was electrically insulated from the fixture

Sby me.s of glass o sapphire rode. Def'sction for a given maximAM fiber stresswas COculated by tht following expression:

y a deflection

a -a knaximm fiber stress

A - distance between outer load pointt

a - distance between outer and inner load points

d - specimen thickness

S- modulus of specimen material.

140

Each stresoed specimen was suwpended on an alternate immersion unit.This unit alternately immersed specimens3 in the 3,5 pe..zent sodium chloridesolution for ten minutes and held them above the solution to dry for 50 minutes.Tests were continued to the first sign of cracking or for 1000 hours, whicheveroccurred first.

Specimens were given frequent law-power microscopic examinations todetect cracks. At the first sign of cracking the specimen was removed. At theconclusion of the test, selected samples were sectioned and examined metal-lographically for any indicution of cracking. Representative samples in whichcracks were found were also given a metallographic examination t:o establish thetype and extent of the cracks.

Thermal Expansion

Linear-thermal-expansion measurements were performed in a recordingdilatometer with specimens protected by a vacuum of about 2 x 10- mm of mercury.In tbhs apparatus a sheet-type specimen is supported between two graphite struc-tures inside a tantalum-tube heater element. On heating, the differential move-ment of the two structures caused by aptcimen expansion results in the displace-ment of the core of a linear-variable differential transformer. The output ofthe transformer is recorded continuously as a function of specimen temperature.

Vic~ eazi~itj aaseimhl~y 4a c-nclc-.e" in a r~ chamber-

The furnace is controlled to heat at the desired rate, usually 5 F perminute. Errors associated with measurements in this apparatus are estimated notto exceed + 2 percent. This is based on calibration with materials of knownthermal-expansion characteristics.

Fatlu.

Fatigue tests were conducted using lTS ela,-trohydraulic-servocontrolledtesting machines. The frequency of cycling of these mathines ia variable tobeyond 2,000 cpm depending on specimen rigidity. These machines operate withclosed-loop deflection, strain or load control. Under load control used inthis program, cyclic loads were automatically matntaineC (regardless of therequired amnount of ram travel) by means of load-cell feedback signals. Thecalibration and alignment of each machine are checked periodically. In eachcase, the dynamic load-control accuracy is better than -.' 3 percent of the testload,

For elevated temperature studies, an induction heating coil controlledby a Lepel Induction Heater was used. A thermocouple placed on the center ofthe specimen controlled temperature to + 5 degrees.

After machining and heat treating (when required), the edges of allsheet and plate specimens were polished according to Battelle-Columbus' standardpractice prior to testing. The t.,itched specimens were held against a rotatingdrum covered with emery paper and polished using a kerosene lubricant. Succes-sively finer grits of emery paper were used, as required, to produce a surface

141

of about 10 RMDS. Unnotched round specimens were polished in the Battelle-Columbus

polishing apparatus, This machine utilizes a rotating belt sander drivenrectilinearly along the specimen test section while the specimen is being rotated.The belt speed and specimen speed are adjusted so that polishing ,•arks on tlaspecimen are in the longitudinal direction, The surface finish is about the sameas that on the flat specimens. The notched flat specimens were held in a fixtureand polished with a slurry of oil and alundum grit applied liberally to a rotat-ing wire. Notched round specimens are polished in the same manner, except thatthe specimen is rotated.

A shadowgraph optical comparator was used for measuring the test sectionsof all polished specimens and for inspection of the root radius in the case ofthe notched specimens.

The stress ratio for all specimens was R - 0.1. Stresses for notched(Kt - 3.0) and unnotched specimens were selected so that S-N curves were defined

between 1& arid 107 cycles using approximately 10 specimens for each set of fatigueconditions.

Two types of fracture toughness teats were used. For heavy sectionmaterials, the chevron-notched, slow bend test specimen of AS2M Hethod E-399-72was selected. r.-- t-. r seet.on sh,'• msaterials, center through-cracked ten-sion panels were used as test specimens. All specimens were precracked in ±a-tigue and subsequently fractured in a servocontrolled electrohydraullc testingsystem of appropriate load capacity.

The slow-bend type specIMens were precracked and tested under 3-pointloading. The pop-in load for materials susceptible to brittle fracture was deter-mined from the load-compliance curve. When pop-in was not detectable, L'1 9UL .V.U;were analyzed using the 5 percent secant offset method of the AST14 procedure.

The thin sheet center through-crack tension panels were initially saw-cut and then precracked in constant amplitude fatigue loading. In order to main-tain a flat fatigue crack and not plastically strain the uncracked section, themaximum rtresses were adjusted to keep the applied stress-intensity factor lessthan one-third or one-quarter of that anticipated at fracture. This usually in-volved stepping down the stresses am the cracking proceeded. The crack wasextended to approximately one-quarter of the panel width. Buckling guides wereattached and a clip-type compliance gage was mounted in the central notch. Thepanels were fractured in a rising load test at a stress rate in the range

.002 E < i < .005 E ksi/min

which corresponds nominally to the gross strain rate of standard tensile testing.

142

APPENDIX II

SPECIMEN DRAWINGS

143

A A' d' el mm....71:

FIGURE 73. SKEET AND THIV-PLATE TENSILE FIGURE 74 . ROUND TENSILE SPECIMENSPECIMEN

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Nowr I £Maf mW g 110 9WA W60t withinW OW~)2 of rwiti ODOM",

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FIGURE 75. SHEET C(OMPRESSION SPECIDEN

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144

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,.FIGURE 80 ?11, SHEAR SPECI,•N

FIGURE 79. SHEET SHEAR TEST SPECIMEN

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FIGURE 81. UNNOTCHED SHEET FATIGUE SPECIMEN SPECMN

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SPECIMEN FIGURE 84. NOTCHED ROUND FATIGUE

SPECIMEN

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-A-Soctio A-A

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I -FIGURE 86. SLOW BEND FRACTURE TOUGHNESSS PE C ME N

FIGURE 85 SHEET FRACTURE TOUGH-hESS SPECIMEN

2000.

FIGURE 87. . STRESS-CORROSION SPECIMEN FIGURE 88. THERMAL.-EXPANSIONSPECIM•N

FIGURE 89. SHEET BEND SPECIMEN FIGURE 90. NOTCHED D.PACT SPECIMEN

146

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AD-755 408 ENGINEERING DATA ON NEW AEROSPACE Battello … · 2018. 11. 9. · AD-755 408 ENGINEERING DATA ON NEW AEROSPACE 0. L. Deel, et al Battello Columbus Laboratories V [ Prepared