UNCLASSIFIED

AD2 6 0 728

M/e

ARMED SERVICES TECHNICAL INFORMATION AGENCYARLLNrON HALL STATIONARLINGTON 12, VIRGINIA

w

UJNCLASSIFI[ED

TECHNICAL PROGRESS REPORTCONTRACT DA-36-034-ORD-3296 RD

ORDNANCE CORPS PROJECT NUMBER-.OMS 5010.1180 800.51.03

c PREPARED FOR

U. S. ARMY ORDNANCE DISTRICTPHILADELPHIA, PA.

UNDERTECHNICAL SUPERVISION - FRANKFORD ARSENAL

CONTROL NO. A5180I

DEVELOPMENT OF HIGH PERFORMANCEROCKET MOTOR CASE

QUARTERLY REPORT NUMBER 12

Period-April 1, 1961 to June 30, 1961

PRODUCT DEVELOPMENT DEPARTMENT

q] THE BUDD COMPANYPhiladelphia 32, Pennsylvania

I Ii

PHILADELPHIA 32. PA.

PRODUCT DEVELOPMENT

ulGIBUMwQUAMERLT PROGRESS REPORT NUM 12

Period: April 1, 1961 to June 30, 1961

Contraet, DA-36-034-ORD-3296ED

Ordnance Corps. Project Number:OMS-5010-1180800-51-03

I ~ROCKET ?!OTOR CASE DI1TROPNT¶

Control iumber A-5180

Prepared by:

Approved by:Sveo y

Manager-Product Developumet Dept.

!

TABLE OF CONTENTS

SINTRODUCTION

rIATERIALS EVALUATION - - - - - - - -

9 Discussion of Fracture Energy Testing- -Specimen Tdentification - - - - - -

Data on Ti-i3V-liCr-3A-- - -- - -- - --

* Data on AM 359 Steel -------

UNTIAXTAL WELD JOINT EVALUATION 63

Data on AM 355 - PH 15-7 No Uniaxial Headto Shell and Shell to Shell Joints 63

Electron Beam Welded Joints JLS -300 A-l.-- y- -

HELICAL WELDED CYLINDERS c,00

WORK CONTEMPLATED FOR NEXT PERIOD.- - - -

Tab>p l. Fracture Energy Tests-

Fatigue Crack Observratons - 10

Table 2. Specimen Identification Charr-

Tablp 5. Chemical Composition of SelrenHeats of Ti 13V-llCr-3A'and Arc 7,,elding Filler ;Jire-

T Fb I -o Tensile Properties, AnnealedTi !3VllCr-3Al- - - - - -

Table 5o Tensile Properties 9 Cold Rolledand Aged Ti 13V-llCr-3A1

Table 60 Tensile Properties, SolutiorAnnealed and Aged at 9001Ffor 48 Hours 9 Ti 13V-llCr-3A! -.

Table 7. Tensile Properties, SolutionAnnealed and Aged at 9001Ffor 72 Hours. Ti 13V-IlCr-3A1- - - 25

I

IPage

NumberTable 8. Fracture Energy Properties,

Ti 13V-llCr-3A1 SolutionAnnealed and Aged @9001F,72 Hours 31

Table 9. Fracture Energy Properties,Ti-13V-llCr-3A1 SolutionAnnealed and Aged @9001F,72 Hours 32

Table lO Fracture Energy Properties,Ti-13V-llCr-3A1 Cold Rolledand Aged @ 9001F 33

Table 11. Bend Properties 9 SolutionAnnealed, and SolutionAnnealed and Aged at 9001Ffor 72 Hours, Ti 13V-IICr-3A1-- - 35

Table 12o Bend Properties, Cold Rolledand Aged Ti i3V-llCr-3Al 36

Table 13, Tensile and Tensile ShearData of Resistance Spot Weldsin Ti 13V-ilCr-3A1 39

Table 14. Stress Corrosion Data,Resistance Spot Weldsin Ti 13V-llCr-3A1 49

Table 15o Stress-Corrosion Data,Resistance Spot Weldsin Ti l3V-lICr-3A1 50

Table 16. TIG Welding Schedule,Ti 13VllCr-3AI, Annealed- 53

Table 17. TIG Welding Schedule,Ti 13V-llCr-3A1, Cold Rolledand Aged 54

Table 18. Mechai-ical Properties,Arc Welded Specimens 9Ti 13V-IiCr-3AI- 56

Table 19. AM 359 Alloy -Chemical Composition 64

Table 20. Heat Treatment andMechanical Properties ofAM 359 Steel Strip 65ý

PageNumber

Table 21. AM 355-PH 15=7 MoWelded Joint Specimens 9Joint Efficiencies 7- - - - - 2973

Table 22. AM 355 PH 15-7 MoWelded Joint SpecimensCorrelation of Strainwith Resistance Weld Design- 74

Table 23° Comparison of MechanicalProperties - TIG Weldingand Electron Beam onJLS 300 AIloy-= - - - - 80

Table 24. Chemical CompositionJLS 500 Alloy- - - - - - - 8

Table 2--,, El.ectron Beam WeldingSchedule - JLS 300 Alloy 84

Table 2Eo Eiectr,'n Beam WeldingS)mmary T1-'-3V=iICr-3AIA --I oy - 88

Table 27, Condition and Prcpertiescf Ti~l V~i iCr-.3AlAlloy Prior to ETlectro,

Beam We l ding - - - 91,

Table 28. Welding ScheduleT. 13V-IlCr-3Ai ElectronBeam Welding 93

Table 29. Mechanical PrcpertiesElectroon Beam WeldingT.--3V--Cr=-3Ai- - - - 97

Figure I. Fractre Energy SpecimenDwgo E 2434-00- - 4

Figure 2. Drill and Ream FixtureType !BI Specimen- - - - - - - - 6

Figure 3. Electrode Discharge MachiningFixture - Center Notch FractureEnergy Testing 7

Figure 4. Fixture for Fatigue CrackInitiation - Center NotchFracture Energy Testing-= 8

PageNumber

Figure 5 Pri. Loadng FixtureCenter Notch FractureEnergy Testing 12

Figure 6. Tensile Properties -vsAging Time at 90CIF for

L 18Ti 13V-ilCr-3A> 18

Figure 70 Photomicrographs,Ti 13V-ilCr-3AI 9Solution Annealed- 25

Figure 8o PhotcmicrographsTi 13V- .ICr-3AKSolution Arneal ed- 26

Figure 9. Photomicrcgrapris,Th '3V--iCr-3A¾Cold Rolled 25,% - - -- - 27

Figure 10o Phctom-crcgraphs•

'•°d R_-iled and Aged 28

Figure lio Photomacrographa9Ti 15V,"LCr-3AICOid Rclled and Aged - - 29

Fig-ure 'o Resistarice Spt,-• WeldingSchedule and Data SheetTi 13V l!Cr-3AL- 38

Figure 13. Phctcmacrograph andHardness Travrers- ofResistance Sp.t Weld4nr An-nea:Led Ti 13VIILCr-3AI 41

Figure 14o PTotCmicrMCgTapt cf WeldNugget and Heat AffectedZorne Strmcture inResistanCe Spot Weld inAnnealed T: 13V-IlCr-3A! 42

Figure 15o REsistan~e Spot WeldingScheduie and Data SheetTi 13'5r-l'.Cr-3AI~- 4-3

Figure '1.o Ph:tcmacrograph rand HardnessTra-erse of Resiastance SpotWeld In CoId Rciled and AgedT-Ti 13v-• 2CrT-3A- 45

PageNumbe r

Figure 17- Photomicrograph ,ýf Weld.Region ir. Resistance Spc-tWelded Ti .V r=ACzlId Rc-.>Aýd. an~d Aged

Fig-ure 18. Photomacrc:graph andHardness Traverse ofTIG weld9 c±1rAnniealed TiL .l3v-KICr-.'3AAl - - 58

Fi~gc--re 19. P-1*t macr~r-graph ardHardiness Traverse -:'ITIG We1.-d, Cold. Roll'-'edand Aged Ti :-15V-1.Cr,-3A- 59 r

F ig,,;re ~0 Phctomicrographs ofWelded Region in, TTGWeld=.d Ti ;53v=-:C~r-,3A.L,S,)lu*--i,, Aanm,-ale-d= - = 6C

FiLgur e 0 Pnc'tcirlcrographs -:fW--ided Regions in TIGWelded TýL ,IV3'.!Cr-4A-,,Cold. R,, led and Aged =61

Figure cc Sre S-traian DiagiamsAM 359 AIL-y ý-= 66 ---

F-.giure 23. PhctomicrographAM 55ý9 Alloy -67 ----

Figure 2' ANM5 PH 5T N:Welded J7 Lr- SpecimeLLFTes-'irg A-rrangement 71

Figure 27> Pho~tcgrapt~s AN 35.5PH 11--- MN: Welded,Tofn- SpecimensAfter Fractu1-re -76,77978979

F 4-g -, z,,e 26 E ELeot-rý,c- Beam WeldingFix-ture- 83

Fig,..re- 27. Phc,+onmc.rrographqElectýron Beam Wel-d,JLS 300 Al oy= = 86

Figuare. 28. Photomi.crc graphShear CrackJL3, 7n,,-*, -~w= - - = 89

PageNumber

Figure 29. Radiograph IndicationsTi 13V-1lCr-3ALAlloy, 94

Figure 30. Tensile Test Specimen40' Weld LineDwgo 2434-0i-5- - - 95

Figure 31. Sketch- Type ofFracture on Ti-l3V=llCr-3A1Alloy Electron BeamWeldments - - - 98

Figure 32. Geometric Relationshipof Cylinder Diameter,Weld Helix Angle,Coil Width- 101

Figure 33. Effect :f Helix Angleon the Yield Strength:f a Cylinder i-- --02

Figure 34. Photograph of HelicalWelding Fixture andAyrangement - i0' Dia.Cylinder= 104

Figure 35, Photograph and Diagram cfExplosive Sizing"0"'V Dia. Cylinder -.. 05

APPENDIX A - Repori Dsr -l on -on -- - 107

APPENDIX B - AN 355-PH "-5--7 McWeld 5.oint SpecimenDrawings (Revised)and Fixture Drawings- - 115

APPENDIX C - Test Detail cn AN 355-*TPH 15-7 MO Weld

Jcint Specimens - - - 128

el

I PREFACEI This progress report is submitted in conformance

with the requirements of U.S. Army Ordnance Contract

I DA-36-034-ORD-3296 RD dated June 21, 1960, for thedevelopment of a high performance rocket motor case. The

I work to be performed by The Budd Company is to initiateand conduct a development program, the ultimate objective

of which will result in a high performance rocket motor

I case, capable of being fabricated with reasonable ease,which will utilize the maximum strength potential of

I available materials. This will be accomplished throughi proper selection of materials, design of joints, and

improvement of fabricating techniques.

Acknowledgment is made of the contribution to this

report of Messrs. J. L. Herring and W. J. Hauck of The

I Budd Co., Producz Development Dept.IIII.III

I INTRODUCTION

SThis is the twelfth progress report covering thework being conducted under Contract DA 36-034-ORD-3296RD

by The Budd Company. The report will include work

S I accomplished during the quarterly period April 1, 1961to June 309 1961 and will serve as the monthly report

I for June, 1961.Evaluation of material selected for possible appli-

I cation to rocket motor cases continued during thequarterly period. This work included evaluation of Ti-

13V-llCr-3A1 alloy and data is included in this report.

Data on fracture energy testing and retests of stress

corrosion specimens without edge seal protection is

I reported on JLS 300 alloy. Retesting of the initialI heats 20% and 25% Nickel Steels incorporating modified

heat treatments to improve mechanical properties was

accomplished during the quarter. Results of tensile

tests on AN 359 material is reported.

S I Testing of uniaxial weld joint specimens of AN 355-S•PH 15-7 No material, utilizing a combination of resistance

and fusion welding, was accomplished during the quarter

I . and results are included in this report. Work on uniaxialfusion welded butt joints employing tungsten inert arc

1I process and electron beam processes continued duringthe quarter.

During the period a method of free state fusion

butt welding cylindrical sections, having weld lines

preferentially oriented in a helical pattern, was develo-

I ped. A discussion of this work is included in thisreport.

MATERIALS EVALUATION

I Evaluation testing was completed on Ti-13V-llCr-3A1alloy, JLS 300, and initial heats of 20%-259% Nickel

I Steel. Transverse and longitudinal tensile tests onlywere made on the AM 359 to confirm data obtained from

results at Allegheny Ludlum. Evaluation is in process

I on the Ti-6Al-6V-2Sn alloy. Preliminary samples of aus-rolled low alloy steels have been received. These

samples were taken from 3 different heats. We plan to

make a preliminary evaluation of these samples to obtain

tensile and fracture energy data. This will involve

I approx. 12 specimens. Based on results of this data, aselection will be made of a heat for complete evaluation.

The Ti-8AI-10V alloy ordered for evaluation was

received late in June and will be evaluated. The modi-

I fied analysis of 20% and 25% Nickel steel have not beenreceived to date but is expected within the next few

days. Armco PH 12-8-6 alloy is also expected shortly.

Discussion of Fracture Energy Testing

High strength sheet metals behave in a brittle

I manner in the presence of small flaws. This behavioris related tc the type and geometry of the flaw, the

environmental temperature, the state of stress and the

I metallurgical condition of the material. Pressure2

-vessels made from these materials also behave in a brittleImanner in the presence of flaws. Quantitative data on

the effects of changes in the parameters of the brittle

behavior are required to provide design, fabrication and

I inspection criteria for manufacture of reliable vessels.The test used to measure the brittle behavior

I characteristics must be relatively simple, practical toproduce and economical to make. To meet these conditions,

the recommendations cf the ASTM Committee on Fracture

I Testing of High Strength Sheet Materials were followed.The center notch test specimen, in lieu of the edge

I notch specimen was selected on the basis of betterreproducibility and econcmy.

The dimensions and tolerances used for the specimen

I are illustrated in Drawing E 2434-0014 Figure 1. It willbe noted that the symmetry control and tolerances are

I related to the pin holes, and that the perpendicularityof the notch with relation to the tension stress line

is tightly held. These conditions were established to

I minimize bending stresses during test and to providereproducible test results.

I The processes for preparation of the test specimenswere developed to assure that only elastic deformation

I _ occurred during any operation, except for the fatiguecrack initiation. This minimized changes in the fracture

characteristics as a resut of prior plastic deformation,

Sas would occur during roll or press straightening. The

Ic

132- a

J4

ad~i

w zi000

IL. 0i 1-1Iz

oCh uzz

:2 LI

z I

Iia z

00 -0

CNN (0m.

o a)AP..

itIzhi Li0

0

I Iz!

0I

oNU OMDUhill ui*iTNVt SIA Oimu ollwz3RO ~ lt ~ lA~N -o3lOA~d~3ivl - , -

or0 NO 9 K W.AOY-..OI0 AIOS0 *v*~nL OLINWLL DMIO* m vuwnl NI ANOD01 INO03O~jNISi % XVVQSIM

Due -4

I,StestI- specimen preparation sequence is as follows:•

I I Square shear, oversize blank from sheet. Dyepenetrant inspect to assure that edge flaws will

1 clean up on subsequent processing.

I 2. Shape to outline dimensions required by Figure 19and deburr.

3. Clean

I4. Heat treat, where required.5. Drill pin holes using the jig shown in Figure 2,

I deburr and clean.6. Machine the center notch using the electric

I spark discharge process and the fixturing shownI in Figure 3.

7. Clean, debur and inspect the notch at 50x, using

I a Kodak Optical Ccmparator.8. Fatig-.e crack using high stress low cycle tensicn

I fatigue as shown in Figure 4,Measurements of test specimens indicate that dimen-

sional contrcl and symmetry were satisfactory. The notch

I1 radius varies from 0.001" to 0°005". This is adequatefor subsequent fatigue cracking. The angle of the notch

3 with respect to the center line established by the pinholes was held to less than 0 minutes from 900. The

length cf the no,-ch varies from 0.600" to 0.608'". and its

shift, left :ýr rzgnt from the tension centerline was less

than -005 inches total. The pin hole diameters are

within the O04" tolerance allowed. These controls

4'5

U t I

Il

I

. 4 -g

SI-/ 44

0ý

40 c

0CT

00

hwi

(AI

I •......'I

I ai"i

,II

II

Electrode and holder, Fracture Energy Specimen andHolding fixture for electrode discharge Spark

I j Machining of Center Notch.

I:II

I

I

Fixturing for Tension-Tension fatigue Crack initiationof Center Notch Fracture Energy Specimen. BrokenSpeaimen used to illustrate 900 angle between crackand fatigue stress.

FI-

SFIG. 4 8

provide adequate alignment for test.

I• The fatigue crack length is controlled by visualobservation. When the crack initially becomes visible

I the test machine is immediately shut down. The remaining

cycles occurring after shut-down cause the crack topropagate to the required length. The specimen is then

I placed under a low static tension and the surface lengthof the cracks measured. Table I is a summary of fatigue

load cycles vs. crack sizes for three different alloys.

It will be noted that the visible crack length determined

during the fatigue test, and the length of the same

crack determined from examination of the fractured

specimen show good correlation. The fatigue crack

I initiates at the center of the notch tips and it propa-g gates normal to the longitudinal center line of the

specimen. The amount of deviation from a 900 direction

is almost unmeasurable. This condition of crack initia-

tion has occurred for the Ti-13V-llCr-3Al, Ti-6A1-6V,

I 25 Nickel, AM 355, and JLS 300 alloys tested to date.* (of 44 specimens fatigue cracked, 42 were satisfactory).

Two specimens broke in half during the fatigue cracking

I operation.The fracture energy tests are made at room tempera-

I ture using a 60,000 pound hydraulic universal testing

machine. The ink staining technique recommended by the

ASTM Committee is used for measurement of slow crack

growth. The important aspects of the test are proper

LiI

11 4. )Ij0 C

04P *0 coý t.D 00 00 0 0 0 0 01

I t. 8 00 0 00W a0 Q N

Hl H zaCdO0 0 0C.)00 (\J4 0

004: 00 0. 0~ 0.-E-1 bc Hw 4) KNto 0o0 * N c

14-rr, 0 0 0 0 0 0 p)

Iq n0 0ý 0 0 4-'0 o d r \ I z 0)E c N K

0 0 0 0 0 0 0 Po$I 00 00 0)0 co~ 1 00

U 0Ca 00 AP0 wo00 0 a) Uw

4Zir-I0 0 00 0 0 L\ 0 KIN U

P4 0100 P- '-4

0 0 40o!1ý 0 0:MI-

pq0I c0 0 0 *P4~or 0 0'444-

>- 0 *0 0 0 0) 0 c04 0O4 ~ - OI~ Wi

I~~~- I IZ ~O r4OP ~Hm

Ir o - )-tii 0I -

~ 10

kI

alignment of the specimen, sufficient but not excess ink,

I iand controlled application of the tension load. Axialalignment is obtained through use of the pin grips shown

Iin Figure 5. The amount of ink required is determined bySI experience. The specimen is strained using approximately

a 0.010 inches per minute cross head speed, until frac-

ture occurs.

Calculation of the fracture energy properties is

done in accordance with the procedures published in the

i ASTM Bulletin, Jan., 1960 and discussed in detail inreport No. 9 under testing procedures.

i Fracture energy data is reported for the alloystested during the period under each alloy heading in the

I report.I Specimen Identification

A newly revised specimen identification chart is

shown in Table 2,

Data on Ti lV-llCr-3A1

I iIn past reports we have included a general discuss-I iion of most of the materials which are being evaluated

in this program. The all-beta titanium alloy has been

on the commercial market since mid-1958 and in the last

three years a large amount of data have been gathered

. • on the processing, testing, and fabricating of this alloy.Therefore, the discussion of the basic material will be

brief, with the assumption that most readers of these

Sireports will have had an opportunity to learn elsewhere

11LiIl

IFI

112

5PUCIME I DENTIFICATION

Specimen number consists of a four letter group and one digit.The sequence is as follows:

.3 Material Condition Specimen Direction Jo.in GroupType

Materials Code Code

SAn- 357 A seet Tensile AAM- 359 B Fracture EnergyCenter25% Ni 0 Notched20% Ni D Sheet Tensile,"As Welded" CTi-l3V-llCr-3Al B Sheet Tensile,Weld Dep.i lS- 300 r Removed D25% Ni Mod. G Tensile Shear,Resist20% Ni (Mod.) H Weld BArmoo 12-8-6 K Fracture Energy,CenterTi-6A1-6V-28n L Notched ITi-8A1-lOV M Bend Specimen, BaseAusrolled steel A-i N Metal GAusrolled steel A-3 0 Bend SpecimenWelded,Auerolled steel B-2 P Weld Dept. Removed H

Stress CorrosionResistConditions Weld x

Dimensional ChangeAnnealed A Specimen LSOCRT B Arc Welding Plates MCRT C Photomicrographic Mounts NSOT I Photomacrographic Mounts 0TiSingle Age, 48 Era. F Tensile Speo.Cleaning PTiSingle Age, 72 Era. G Sheet Tensile,>58 RC RCold Rolled & Aged, TensileResist Weld,

200,000 psi J Criss-Cross SCold Rolled & Aged, Electron Beam, 900 ButtI230,000 psi K Weld Tensile T

25% and 20% Ni,Stand.Heat Treat L DIRRCTION

I Cold Rolled and Aged NPH 12-8-6, Stand. Indicated as L (longitudinal)

Heat Treat P or T (transverse)20% Ni, Isothermal

Heat Treat R25% Ni, Double

Sub-Zero Cool SCold Rolled 25% TQuenched + Tempered UQuenched, Subzero

Cooled + Temper. W

TABLE 2

13

about the basic characteristics of the alloy.

I Discussion and data in this report will be based onSI the results of the processing, testing, and fabrication

1 experience gained at The Budd Company in this phase

SI of the current program.

The beta titanium alloy is known by various names

I depending on the producer. It carries such designationsI as VCA-beta, i3-1i-3, Ti--20 VCA and Ti-i3V-ilCr-3A1.

In this report the allcy will be referred to as Ti-13V-

llCr-3AI which is used by the producer of our test

material and which is a self descriptive title.

I Compositions of Materials TestedI Sheet stock, in -various gages from 0.030" to 0.080",

was purchased from Titanium Metals Corporation of America.

We received seven different heats of material for our

test program, This complicated the evaluation and

I required additional tensile tests to substantiate theproperties of each heat. Table 3 shows the seven heat

numbers and the chemical composition of each heat as

SI reported by the prcducer. Also shown is the analysis

of the filler wire used for arc welding.

I Physical Properties of Ti I3V-lICr-3A1Density - 0.175 lb./cuo inch

Coefo of Thermal Expansion - 5.9 X 10-6 in./in./OF

(Room Temp. to 1000 0 F)

Specific Heat - 0o13 BTU/lb./OF (to 200 0 F)

Poisson's Ratio - 0.3C4

14l

tWC' r~c) 0 C\I C~Ij C~j 4 H (Jo H H H H H H- -

C' 0 0 0 0 0 0

MN Lr r-4 LC\ 8 8 C 0 O

"NJ(\ CU C\U C\J NU iKC CUi CU CC)I 0 0 0 0 0 00 0

I c O C O CO a' 0 z a' aE-1?

P14

k.0 0c N 0 0 0 PC\

0 0 ~0O 0 0 0U~~H H H- H- - - -

HO

P . . r H N H- H H HIUI C 0 7\. C- 0 0" U n a

N H~ H- CU H rI0 0 0 0 0 0 0 0 01 0 0 00 0

0 0 00 000 0 oN

$44

-H

0o C -C LAl ulr 0 H bWa) LA\ UA UM, 00 HN w Ht.0 c 9

NN a'a' a'l rjrH c

15

Modulus of Elasticity (room temp.)

Solution Annealed - 14.7 X 106 psi.AI Aged - 16,0 X 106 psi.#; I

Thermal Conductivity

I4.0 BTU/hr./ft 2 /OF/ft. - @70F• ft2

8.2 BTU/hr./ft /OF/ft. - @ 800OF

Melting Practice

SI Each heat of beta titanium in this program has been

double melted using the consumable electrode process for

better control of the metallic and interstitial additions.

The potential contamination by oxygen, nitrogen and

I hydrogen is minimized by the use of a vacuum in both theprimary and secondary melting.

Heat Treatment

One distinct advantage of the Ti 13V-llCr-3A1 alloy

is the lack of a requirement for a high temperature quench.

SI Material may be purchased in the solution annealed or

* Isolution treated condition and may be strengthened with a

Ssimple aging treatment at a moderate temperature, usually

between 800OF and 9000F. Solution annealing by the

fabricator may be done at 14250F + 250 F for 10 to 30

1 minutes. Quenching from this temperature is not required.Air cooling has proven to be satisfactory to obtain

maximum strength after aging,

S I Above 8000F titanium has a strong tendency towardcontamination by air. Therefore, an inert atmosphere

P has been used for all treatments above this temperature.16

The length of time used for aging is usually

between 10 to 100 hours depending on the properties re-t quired. Figure 6 is a reproduction of a chart publishedI by Titanium Metals Corporation showing the tensile values

Ii that may be expected at various aging times at 9000F.On this same chart we have inserted the minimum and maxi-

I mum tensile and yield strengths determined by our own'testing group with specimens aged to 48 and 72 hours.

U Our results were uniformly scattered between these limits

and the average values fall somewhat below the published

curves.

I Aging at 900OF was done in a 12 inch diameter by12 inches high cylindrical retort using a constant 10

CFI flow of argon. The outside atmosphere was effectively

excluded by use of a sand seal located at the top of the

retort. Temperature was maintained within + lOF. A

very light oxide which formed during aging was removed

by a light sand blasting.

Tensile Properties

The tensile properties of annealed material are

shown in Table 4. Three of the four heats of annealed

stock were tested in this condition. The values are

reasonably consistent and are normal for solution

annealed Ti 13V-IiCr-3A1.

a Material was also received in the cold rolled only,

and cold rolled and aged sonditions. The cold rolled

only titanium was tested as received and after aging.

S17

Ti 13V I11CR 34 LSHEET STOCK

TENSILE PROPERTIES VS.AGING TIME

U3II_

I00

I1

IIY--- T41

FIG 6K 81/ I l

0 co

00

o 0 C\ 4 HC,, * 0 91CjN r I AU C

P4, 4F-E-4O 4

NN 0)P

-4 E-4 d WH H H HH4r

H ca

E- CH 0

I ACD HH V- HHr-

A E-4PE-PP

II

H 4> 4) Ao 0 o0 0~ o 0

00

19

II!The results of these tests are shown in Table 5. The

*~ aging at 900*F proved to be very effective in improving

the cold rolled only properties. The limited number of

N tests indicates little difference in tensile values and

Ihardness when aged at 16, 48 and 72 hours. The specimensaged at 16 hours exhibited better ductility. However,

this material was from a different heat.

Four heats of annealed stock were tested after

I | aging at 9000 F for 48 and 72 hours. The tensile valuesare shown in Tables 6 and 7. The minimum and maximum

strengths are also shown superimposed on the Properties

I vs. Aging Time diagram (Figuie 6). The figures obtainedare lower than the producer's chart indicates. However,

I a band of values would probably overlap the pointsI obtained in our tests. The 72 hour aging time, on an

average, improved the tensile strength and yield

I strength 4% and 6%, respectively.All of the 72 hour aged tensile specimens and six

I| of the 48 hcur aged tensile specimens were tested usingI "V" grips in the Universal testing machine. The specimens

used for testing (dwg. no. 2434-0002) failed in tension

.across the area of the pin holes. This failure occurreddespite careful preparation and polishing of the inner

surface of the hole and despite the fact that the net

* cross section of the specimen at the hole was 86% greaterthan the cross-section of the specimen in the gage

length.

20*

0 0 Wr-Uq- 0c r\Cj4 rI O

t,0 E-

*- 0 0 - r C r4 4 - jr- 0 -0- H) C\A C\ UNCj C~

a-I

PC\4.IrAm a

4-)

I~F C\O 4-1N CJ

0 10

0. E

LqA MN

NU 4 IdU A C* 4 0 m CI t ); I- Ot r- -~I0

cmd CI-J P4 a210 4 0 g400IýýC~

I-ri HitoW000-

0 a

I * 0 0Ic C-0

W 43 0

Hi ow r4.v - u H Cj r-E-) oc.p 0

4; b ~ 8 0'f 't- (J0 ON

-ri E-i

0 bo14)

00 4 -

0 O '

U0- 0

C.)Z$4 00 iE-4 P E4 P E4 P E1 P E

0q H H- Hy H HC - r rI4 4 0E- - EIE1I g'

P4 P4 4 P422

')I0I~ Hao

C,ý

I 0

0 CO 4D * *0u H ., 0 CY Cuj C rI 0 0N l

NN 0

I4 M

I ~ * -H.Q

P4Io

A1 E-4 P E4 E-4 A E-1o E-E4 P E-

0~ H b 1

H~rc -P0 Po

4) lo \ f

0co)

Photomicrographs

.1 The microstructures of material in various conditions* •are shown in Figures 7 through 118 The annealed material

-I shown in Figure 7 exhibits elongated grains in the

I longitudinal direction despite the recrystallization ofannealing. The very fine secondary phase which is only

I slightly visible in the annealed specimen EANL-1, FigureI 6 is considerably more pronounced in the aged condition,

as shown in Figure 8. Specimen EGNL-2 is a 2000X

I magnification of this structure. This secondary phaseis most likely accicular alpha Ti forming in the other-

I wise all beta grains.i The cold rolled only material in Figure 9 shows a

grain structure similar to the solution annealed material.

However, the sharply defined grains are elongated andstrain lines are present as the result of the cold

I deformation.Cold rolling and aging for 16 hours produced the

structures shown in Figure 10. The elongated beta

I grains showing strain markings are typical. Not resolvedin this photomicrograph is the accicular alpha phase

S I that would be expected in the same manner as experiencedwith annealed and aged only material.

Material aged to 48 hours at 900OF after cold

rolling as seen in Figure 11 shows the same general

grain structure. However, the secondary alpha phase

I appears to be more nodular in form and there is little2'4

7.7-

ILongitudinal 10OX Nag.Specimen EANL 1

ITransverse 10OX Nag..1Specimen SANT -1

Ti 13V-llCr-3A1 Ht. No, D31 0.060"1 Gage

~~ I Solution Annealed 2Etchant: 2%0 HF + 4.0% HNO + H0

IFIGURE 7 25

WI

I......ILongitudinal 10OX Nag.

Specimen EGNL -1

ItI~~Is-

Longitudinal 2000X Nag.Specimen EGIN13 2

Ti 13V-llCr-3A1 0.06011 Gage

u Ht. No. D31 Solution Annealed + Aged 900*F, M2rs.I Etohant: 2%6 HF + ENO3 + H 0

FIGtTRE 8

26

F'VLogtdnl 5XMg

SpcmnSN

3 2FIUR

-2

ILongitudinal Sein N 6250X Mag.

Specimen EN1NL 6

TiIVl~-Al0041GgItN.D6 odRled+Ae 00,1Hs

4 IEcat %H 06HO3+H2

FIUR 10AI ... 28

!"~ '15

4.1~

Longitudinal 250X Nag.

Specimen ENNIL 1

TrnvreI5XMgSpcie ENN 1

Ti. ~ ~ 13-lr3l .3"GgHt.~~~~ No 97 odRle +Ae 00.4Hs

~~29

evidence of the accicular structure at this magnification.

I There also appears to be some grain boundary precipitant.Fracture Energy

The fracture energy values of the Ti 13V-llCr-3A1

was measured in various heat treated, and cold rolled and

aged conditions. Our method of testing is discussed

SI elsewhere in this report. The specimen used is

the center notch type (dwg. no. 2434-0014) initially

cracked by a high stress, low cycle tensile fatigue

process. The testing procedure used has been outlined

in Quarterly Report No. 9.

I The fracture energy data obtained from the testingof specimens from various heats of Ti 13V-llCr-3A1

are shown in Tables 8, 9 and 10, Tables 8 and 9 show

the properties of material which had been solution

annealed and aged at 900OF for 72 hours. Table 10

presents data on material which had been cold rolled and

aged at 900*F for 16 and 48 hours.

I• Material taken from three different sheets of oneI heat (D31) and a single sheet of another heat (M9584)

exhibited relatively good KC1 values in the longitudinal

3 direction. These values on an average were 33 to 54%better than the transverse figures. The critical

I crack index values are, of course, more widely spreadbetween the longitudinal and transverse directions,

IThe other two heats of solution annealed and aged

3 material (nos. M9853 and M9583) developed relatively30

H C~ V-LNC 0 s Lr\ Lr\ w

80 0 0 0 0 0 0

elo -C1-~ 4 n N 0 L\LC\ 0 0

0 0 0H 00 8O0H0H

PC 0 0 1

100 Ao0 (1 )

E-1 iýH H A"1.) 0 0 0 0 -

PI OpcpoHEE-1

0 0

Ed4 to H co HH 000 ODOD O aurd -~C'j jCj 'ci c~ q A A \JCrJC r

P4-

U 0)

0N E-4'-4E

I~~ ~ CD Ed0.Ee .4-

0 08)HH

Hor - . . H -P 0 H4-

ii 31

0 0 0 0 0J0

0 0 E- ~LrNLr\ LIN LrN rO'\~P-q ~H 00-4 00 0 0 00

000 000

0' 0' 0 0 00 0 0' C-J0 0H4 r~-4 0N LN 00 W ~ -Nt 1, - 0)

4-)'04 8

H 0)

p~ N C) 0)

r- E4 E ** *

H00

P4 4'C~

E~E0

4-) a\4

H ~ Ci rc s i-I IEca E-a 00 00 00 NP4 ý j ~ ~ 4)J UNI -4 ) I '.04 -

wacuIj ri

0432

%D r-

4 C~jb ~

8 0

0 CMU 0 0

0 "

00

l 0 0

r H

E-4 ho

I P*'pi

~0 W E-pqO

I "-4~0

0

co 0

00 CO

H 4z 4 0k

33

low values in both rolling directions. The analysis of

I the material, as reported by the supplier does not offera reason for this difference.

The cold rolled and aged specimens developed

relatively good KC1 values in the longitudinal direction.

Transverse specimens will be tested at a later date.

I All the specimens tested had yield strength todensity ratios greater than one million. The KC1 values

and the critical crack index figures are generally

I superior to these values reported for high strength Qand T steels at the equivalent yield strength to density

I ratio.Bend Testing

The results of bending specimens in the annealed,

cold rolled and aged, and aged conditions are shown in

Tables 11 and 12. The annealed material required a 1T

SI to 2.3T bend radius when bent through 1350 in a closed

punch ard die. Cold rolling to 25% reduction increased

Sthe bend radius to 3T. Aging afier cold rolling markedly

increased the bend radius requirements. The 48 hour

aging produced M7T and greater bend radii values for

jI 0.030 inch gage material.The material aged at 900OF for 72 hours could not

I be accurately tested. The largest bend die in the set hasa 0°500 inch radius. Indications were that both the

0.060 inch and 0.080 inch thick sheet stock required

bend radii considerably greater than 8.3T and 6.3T,

3

N 0

r-I a 4.'C) E-4 F: E-4E-1 E-1 E-4 E-1EA E-4E-4 E4 E-4

* E-4 * . o . * .00 Co oc omco 0DI. a; 6 0IA & 9AA /\A ^\A/

io

ow.o

0 90 0 0 II 9E i.E. 0E~= .dC.5 0 00 0 0 )

4) V

A ~4-j E4

0 0 m

Ir PI * )0r P4 -HC~ 4-(\

E-4~ d

Ia E4-1jr~ '.0

P E-4 P- E-1 - E-4 co

0 FA P -E-1 P. E-4 P E-4 P- E-4 PE-4 P E-1

I I~D E-4E- 4~) H - H - - 0 0

bo ID 0

co 0 0 0 0 0

r H H

); ~C a N~COa\ ON *P " C

H H 04' 35

I~

o 4)

o \E0 C- LI.-

SA AA

i Q" °4E0 r- Pr 0o A

O -4 0 •

0 08 0)0 04

,-p 4 00. 4.'•4• "•-

I~ Cl)

43

I 44

H 0d00) E-1 r)-CoV. AA

r-4 P4

00

P4 P4 -~-

0 KIN 36

0 d 0 2

respectively, These values would most likely be in the

I neighborhood of the 17T radii required for the 0.030inch specimens.

Resistance Welding, Annealed Ti 13V-llCr-3AI

SI Specimens in the solution annealed condition were

resistance spot welded according to the schedule shown

I in Figure 12. The following specimens were included inn this study.

Tension Shear, Type E, Dwg. No. 2434 - 0004

m Cross Tension, Type S, Dwg. No. 2434- 0012

Photomacrographs and hardness traverse, Type 0

I Photomicrograph, Type NStress Corrosion, Type K, Dwg. No. 2434-0011

The type E and S specimens were made from 0.060"

SI sheet taken from heat 9853, Sheet 13. These types of

"tests were discussed in Report No. 10, The results of

this work are shown in Table 13.

The material was prepared for welding by pickling

I in 40% H2 S04 at room temperature, followed by thoroughSI rinsing in running water and air drying. A final

acetone wipe was used prior to welding to insure cleanliness

I• because of a drilling operation done after pickling.The Ti 13V-llCr-3Ai alloy in the annealed condition

is readily resistance weldable. The weld nuggets formed

prove to be sound and reproducible. The weld nugget

extends to the limits of the electrode contact diameter

and there is little or no heat affected zone detectable I

iT 37

MATERIALS RESEARCH LABORATORY

I Resistance Welding Data SheetDate -May 4 1961

Project 5017

Welding Machine Material and Gage

150 KVA Sciaky Single Phase 0.060" Ti-lIV-IICr-3A1 (Cnn E)f Deatr Prr ise Counting

e leodle C i Material Condition

5/8" Dia. RWMA, Group A. Class 3, Solution Anneal and Pickled2 1/2" Rad.

Welding Schedule

"I Electrode Force, lbs. Phase Shift,%- 48Net -i- - - -- - ---- 1500 Squeeze Time Cycles 10

I Forge ---------- None Hold Time Cycles 50Weld Cycles- 10 Weld Diam., Ins. - - - .234

Impulses -------- 1 HAZ Diam.. Ins.- - - - .234

Cooling Cycles None PenetrationYo- - 66

Transformer Setting- - 2__ s2 Electrode Indent,% - -

Remarks and Special Functions1

Spec. No. EAO-I

II

Fig. 12

38

4-'

aa*E-4 4-4

~E- 0 ) 0 0 000 0I 0 *riP M I a) a) 0 0 00 0~z 0 .r4 co'

I 4) E-40 C 'COOQ AC/ WICC~J

I EacoP ON HLA\ Q H L 0 oN V-.r4 do

ýA El E-4 0--1 %(N \jH-4 0 ~c PI\ C' jI M -p 4 UNLrN LAl I .LLA\ VI4)xI4 H- ~ l - '

4) (D 0 ) *c

Hi H' A1 A A* *4 A0 q

H 2 q) 0 l0o2 CO

00 &4'O co P4 IP H P4P PI P4Cal

$v4 Wo#1) lj 10 bc&0'I IC 0 C 4 4% o0

Hq 0 r - -rl0 3 4 Hi00r- H0Lr\E- oo,\ -P oW

0 0~C

co 0 4

39

at the surface. The electrode indentation is normal

for this gage material. Sheet separation is expected to

be greater than normal because of the relative ease with

which this alloy is forged during the welding cycle,

Note the "fin" which is extruded between the sheets at

the edge of the nugget, shown in the photomacrograph in

I Figure 15.A micro hardness survey across the nugget is also

shown in Figure 13. The hardness is relatively uniform

I 'Prom the base metal through the weld nugget. This istypical for solution treated beta titanium.

I The photomicrographs of the heat affected zone andweld nugget of the resistance spot weld structure are

shown as a composite in Figure 14. Specimen EAK-l shows

mostly weld nugget. The heat affected zone is shown by

Specimen EAN-2. The large grain, equiaxed in the HAZ

I and columnar in the nugget is typical. The heat affectedzone is narrow and blends into the base metal with no

I definite demarkation of the boundary. The grains areclean and free from grain boundary constituents.

Resistance Welding, Cold Rolled and Aged Ti 13V-llCr-3Al

3 Ti 13V-llCr-3A1 in the cold rolled and aged condi-tion was evaluated for resistance spot welding in a

I similar manner as the annealed material. The alloy in3 this condition was readily welded using the same welding

schedule as for the solution annealed stock. This

schedule and other pertinent data are shown in Figure 15,

40

MICRO HARDNESS TRAVE.RSEWELD CROSS SECTIONSKENTRON MICRO HARDNESS TESTER

DIAMOND PYRAMID PENETRATOR

I I

Iz

1 CV

I cri

a0

0 0

|SME. NO. lg-:l WELD TYPEResistance fo AG. ].o

.,MATERIAL ,'Ti 13V-llCz,-3Al GAGE .0"

WELD DIA. .. I. HAZ IINS S. 0-254

k. PENETRATION 0/ 66 ELECTRODE INDENTATION %/ 1-FIG. " 13 41

\iI HdI f U)4coI4 4

'A: CHCIrI 4~' ',~-

co -

~ d d

IQIo H

Ia I

'42

!forIo I MATERIALS RESEARCH LABORATORY

Resistance Welding Data Sheet

Date May 11, 1961

Project 5017

IWelding Machine Material and Gage150 KVA Single Phase AC with 0-060" Ti-13V-llCr-3Al (Code E)Dekatron Timing ControlElectrodes Material Condition

5/8" Dia. RWMA, Group A, Class 3; Cold Worked & Aged to 200 Kpsi Y.S.2 1/2" Rad. Heat D575, Sht. #1

Weldinm Schedule

I Electrode Force, lbs1 Phase Shift,% ..- -48Net -- --------- 1500 Squeeze Time Cycles 50Forge-- - - --- '- --Hold Time Cycles 50

Weld Cycles - -i-----10 Weld Diam., Ins. - - - 0.236

Impulses- - --i----1 HAZ Diam.. Ins.- - - - 0.280

i Cooling Cycles None Penetration,%- - 68Transformer Setting- - 2 Series Electrode Indent,% -7

'~I

i Remarks and Special Functions

IISpec. No. EJO 1-1

I Fig. 15

43

! I

'IThe weld diameters are the same for the two condi-

I tions. The heat affected zone is more distinct in the* icold worked material. A photomacrograph of the cross-

section of a typical nugget is shown in Figure 16. The

I hardness traverse in Figure 16 shows complete and essen-tially uniform annealing of the nugget material with a

n rapid transition to the base metal hardness in the heat

affected zone,

The electrode indentation is typical of titanium

n base alloys. The sheet separation is more pronounced

than with other materials, being approximately 16 of

I the sheet thickness.The results of the testing of the tensile-shear and

the cross-tension specimens are shown in Table 13. There

I is a slight increase in the tensile-shear values ascompared to the annealed specimens. However, a substan-

i tial decrease is realized in the cross tension strength.The cross tension specimens failed by fracturing in

S * bending across the area of the weld nugget. See Report

I No. 10 for a complete description of these tests andphotographs of specimens and test fixtures. As a result

Sof the low cross-tension values the ratio of tensile totensile-shear is lower than would be expected from a

U cold rolled austenitic stainless steel. However, this is

3 iusually the case with titanium base alloys.Photomicrographs of the base metal, heat affected

zone and weld nugget are shown in Figure 17. These

44

MICRO HARDNESS TPAVERSEWELD CROSS SECTION

KENTRON MICRO HARDNESS TESTERDIAMOND PYRAMID PENETRATOR

I • ,z

I I>

I 1•~~ill t

uI ii

> oy

I SP:•NO. Bao-l,.,., WELD TYPE Resistance, MA.•ETCHANT___________________________

SMATERIAL Ti I3V-IIlzr-3A1 GAGE 0.060; 1 ~CONDITION Cold Rolled. and. Aged. H~eato D)575. Sheet •1SWELD DIA. INS. 0.236 .... HAZ DIA. INS. 0.280J PENETRATION 0/0 68 ELECTRODE INDENTATION 0/ ......

' |F'IG. 16 , 45

'1'0-JAc

fA0

Cl.4

glik EQC \J

+O

Io 0

r4~46

photographs at 10OX show the extent of recrystallization

SI and grain growth within the heat affected zone. The

u elongated grain and cold worked structure is found near- the base metal (dark area) and heat affected zone boundary.

.1 A relatively fine background structure is seen withinthe equiaxed beta grains. This fine structure may be

I alpha titanium which is not clearly resolved at thismagnification. The weld nugget shows large columnar beta

grains and a lesser defined dendritic s*ructure. Again,

I the precipitate is distributed through the grains. Thelower left corner of Specimen EJN-2 shows equiaxed grains

I of the heat affected zone.Stress Corrosion, Resistance Spot Welds

The description of the test used to measure the

I susceptibility of resistance spot welds to stress corro-sion cracking may be found in Report No. 11.

I As with all materials in this program a limitedstress corrosion study has been made. We have exposed

the Ti 13V-1lCr-3A1 to two concentrations of magnesium

3 Ichloride (5% and 20%) in a boiling aqueous solution forperiods of time up to 126 hours.

Sl One heat of annealed stock and one heat in the coldrolled and aged condition were used for the test speci-

I •mens. Two resistance spot welds were made in eachspecimen using the welding schedule shown in Figure 12.

The edges of the specimen were sealed with a synthetic

rubber substance to prevent penetration of the solution

47

01

between the two pieces joined by the weld. The results

I of these tests are shown in Table 14.SI The annealed specimens withstood the corrosive medium

in both the 5% and 20% concentrations of MgC12 for the

maximum test time. The cold rolled and aged material

showed no cracking in the 5% MgC12 but did develop typical

I stress corrosion cracks at 8 1/2, 74, 103 and 126 hours forthe four specimens in the 20% concentration. This spread

of results is to be expected with a test of this type.

To evaluate the effect of preventing the solution

from penetrating between the specimen halves a run was

I made in 20% MgCI 2 with the specimens unsealed. Theresults of these tests, which were run 78 1/2 hours 9 are

shown in Table 15.

The tests made with unsealed specimens did not

indicate any increase in the severity of the exposure.

I Only one very small crack developed in the 78 1/2 hourS I cycle.o

TIG Welding, Ti 13V-IlCr-3A1 Alloy Sheet

Solution annealed and cold rolled Ti 13V-llCr-3Al

sheet was Tungsten Inert Gas welded using beta titanium

S I filler wire. Radiographic examination showed that allweldments contained scattered porosity of 0.008" to 0.020"

I• diameter along the fusion line. Tensile tests of speci-jI mens machined from areas with 0o012" diameter and smaller

porosity indicated the yield and tensile strengths of the

weldments were normal; that is, the same as solution

1 48S

H~Hr

0k 40 ,, a'OlH

0 0 0 0

* 0

CO ý %~~~~l DDDD ',0WW WWI D kD to O %-0 %D %D43 H H Hr-I-HI.-I CU C\j ~C\J (~j (U( NC\j0 0 r- -I ru -I Hr-4 rIr-4 r -4 H Ir-i H H r-4 u-I H

E-4 W0

P4P 4 4u)4 4P P 40 0 4 P4 P4 P 4 0

KPNC MNIC\ 0CN~0 0EI jiIIIII11 bu- 4.rD JCJC R ' ~

0 1 000 0 0000 0 0000 00oo000El II r-rI4 4u 4r4r4 H r4Hr4 r4 ; r4

CO C., a 0 0 0 0 0 0 0 0 0 a a 0 0 0 0 0

0Id U - CD 00 00 000C)00 00 001OD00 004

C9 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 rI4

u-4 4 4 : 1 H r-r4 r4 1u44 u-4;1; 1 14 1; r-4 w00

0 0 0) P4H-Ia * * * * * * * * .

0 ~00 N JC~j CjN c ('C~j Aj 9H H ri rI rI r-Ir-4 @0 )

I r - - - - - rIrIr 02~ ~ 4-

I) H

000K> 1 84) co- * *aS40 430

a 4\ ON u-4 ** HE4-) - H 0 0\ 43.0j 00 'i0 6 r

49

ooo

SH H

0

0 4.0

4.) :3 4)

0 0 0- r $-H0 0

oP,

-' 0

I oI -

0F4 A 0 0 00 0

0 44 0I 0? 0o ',.HO rf4 N cO~C rH

•l •0

P. I-04 0* o 00 00I- Hp.' bP4 r 4-40 0 0 0

H0 0 0 0 0 E-4

0 P.j

ca 0

0 E-4 0 rid

00

F,~~U E- 0 -1ctOr P40

a)0 -04-*

oo 4) AodoA 0~ U00 o-

H0

05

I5

fl

annealed stock. Welding schedules to obtain full pene-

tration and adequate weld metal reinforcement were readily

established and were reproducible.

3 Materials,The 0.060" thick beta titanium sheet was procured

I from the Titanium Metals Corporation in the annealedi Icondition and in the cold rolled and aged condition. The

0.030" annealed beta titanium filler- wire was procured

S I from ARMETCO, Wooster, Ohio. The chemical compositionsof the sheet and filler wire are shown in Table 3. The

I mechanical properties of the materials are listed inTables 4 through 7.

Preparation of Samples for Welding,

I Coupons for welding were cold sheared from the sheetstock and dye penetrant inspected to insure freedom from

I shear cracks. The edge to be welded was ground to a 63I microinch finish. The ground edge was dye penetrant

inspected for grinding cracks and shear cracks that may

I have been missed during the first inspection. No crackswere found. The coupons were cleaned by immersing for

one minute in a water solution of 40% by volume of con-

centrated H2SO4, followed by water rinsing and air

drying. Just prior to welding, the ground edge and an

j area back about one inch from the edge on both surfaces,was mechanically cleaned with 400 grit emery paper and

it thoroughly washed with acetone. The filler wire was

mechanically cleaned in a similar manner just prior to

I welding the coupons,51

Joint Design.

SI A single pass butt joint was used. The welding

edges were prepared such that a 0.001" feeler gage could

not be placed in the joint when the edges were butted

under slight pressure. The weld metal deposit was

m parallel to the longitudinal direction of the sheet

m (direction of rolling), and the weld metal reinforcement

aim was 40 to 50 percent total, equally distributed top

and bottom. The size of the finished weldment was

approximately 10" wide by 12" long. The general charac-

m teristics of the joint design, except for the amount of

reinforcement, are shown in Figure 1 of Progress Report

#10, April, 1961.

I WeldingThe tungsten inert gas welding equipment consisted

m of a Vickers 300 ampere rectified power source, an AIRCO

m NOD. C torch, and an AIRCO high frequency starter.

Auxillary equipment consisted of a copper root shield,

Sa 5/8" nozzle, copper chill bars and C-clampso Afollower shield was not used. This equipment, with a

I mceramic in lieu of a metal nozzle, is illustrated in*m pages 10 and 11 of Progress Report #10, April, 1961.

The welding schedules developed and used for production

of the test weldments are shown in Tables 16 and 17.

These schedules provided reproducible test weldments

hi Iwithout difficulty.

* t 52

LL

I TIG FUSION WELDING SCHEDULE FOR Ti, 13V, llCr, 3A1, 0.060"SOLUTION ANNEALED SHEET

Item Description

ElectrodeType 2% thoriated tungstenSize 3/32", tapered point.

SStickout 3/8",Torch

Type AIRCO Mod. C.I Attack angle 90o.* Lead angle Zero.

Root ShieldType Copper,Budd Co. dwg. E2434-0121, (see

prog, report #10, fig. 4).Groove size 0.040" deep by 1/4" wide.Gas ports 1/16" diameter, spaced 3/4" apart.

Nozzle

Chill Bars Copper, 3/4" X 3-1/4" with 450 bevelto a 1/8" land.

I ARC Voltage 12 volts at electrode tip.DSSP Amperage 190 to 195 amperes.

Shielding GasNozzle Argon, 25 cubic feet per hour

I Root Argon, 3 cubic feet per hourSFollower Follower shield was not used

Filler WireType 0.030 diameter, annealed beta titanium.Feed 18" per minute.

Welding Speed 7 1/2" per minute.

Preheat-Postheat None used.

*Power Source Vicker Is, 300 ampere, rectified

I Start, Me-h. AIRCO HF-.II °i TABLE 16

53

II

TIG FUSION WELDING SCHEDULE FOR Ti, 13V, llCr, 3AI 0.060"SHEET COLD ROLLED AND AGED TO 230 kpsi U. T. S.I

Item Description

ElectrodeType 2A% thoriated tungsten

I Size 3/32", tapered pointStickout 3/8"•

i Torch* e AIRCO Mod. C.

Attack angle 90oLead angle Zero

Root ShieldTy-pe Copper, Budd Co. dwg. E2434-0121,

(see prog. report #10).Groove size 0.040" deep by 3/16" wide.Gas ports 1/16" dia. spaced 3/4" apart.

I Chill Bars Copper, 3/4" X3-1/4" with 450bevel to a 1/8" land.

I NCzzle Metal, 5/8" diameter.ARC Voltage 12 volts at electrode tip.

I DSCP Amperage 180 to 190 amperes.Shielding Gas

Nozzle Argon, 30 cubic feet per hour.Root Argon, 3 cubic feet per hourFollower Follower shield was not used

I Filler Wire-=pe• 08030" diameter, annealed beta

titaniumFeed 18 inches per minute,

Welding Speed 7-7/2" per minute.

Preheat-Posthe at None

SPower Source Vicker's 300 amp. rectified.

i Start, Mech. AIRCO HF-1.

TABLE 17

S I 54

1IIRadiographic Examination of Weldments

I IWeldments were radiographed using a 200 KVMitchell source, a 00005" thick stainless steel penetra-

I meter, and the following technique.145 KV, 4.5 Ma., Kodak M Film

I 2 1/2 Min. Exposure, 36" FFD

5 Minutes Development Time

All welds contained scattered fusion line porosity vary-

I ing from 0.008" to 0.020" diameter. There was no evi-dence of cracks, craters, inclusions or serious under-

SI cutting.

Tensile and Bend Test Results.

Tensile and bend tests were machined from areas of

I the weldments containing porosity indications of 0.012"diameter and less. The procedures for preparation of

S I the test specimens, and the testing procedures aredescribed in Progress Report #9, March, 1961. The

mechanical properties of the weldments are listed in

Table .8. These properties are typical of fusion welded

beta titanium, The bending characteristics of the weld-

* ments are as follows,

Solution Annealed Weldments

I Controlled bending parallel to the weld axis to an3 angle of 135 degrees can be accomplished about a radius

of 2,4 times the base metal thickness. Free bending

K u through 180 degrees results in cracking along thefusion line.

55

.0

L, 0

0 CON 00 N3

C'JC~~~J(~Ji~~4 0C0~' 4ZJD4~O0

4 4 ~% rfrI - - . r1l 4) (H00 c 0 4 0 0

N C 0 01 I - -I0 f\Hl 4 Cj P44 4 4 4if K\~- 40 rC \ ( _ -_43F 4I

Cl) (L 0 to~DD~ FCI 0 . H

CO 4z~4 0 C PK30'd 4- 90

Ii(1 0 "A0 H 0000 11 Ll 00C-00 00ODCj MI cO 4 ~0c~ 4t 0. P

E-i t. C K\ .Lt\LrNiCN LrKLN K\r4"L\ K\ t. LI\ 0 fN 4 K% e-F-0

0c a) Lrd0

0i 0D- ED)

co ly *o w

co 0 co)

E-i&4 O 0H 4N 44 4r1 JC4 H('Jfr\ rI4 0C ~ I0t)-HNI'- M4E r-4 E4E- -4E- -4 E-i -IE-4E- A ~ 4E E 0- -i r

00 c

I-0- 4-)-')

04 0

.1'. 0P P- C\rd

* 56)e-%9 -- -

'ICold Rolled and Aged, as Welded

At a radius of 3.9 times the base metal thickness,

bending parallel to the weld axis through an angle of 135

I degrees results in cracking of the base metal. At a radiusof 2.9 times the thickness of the base metal cracking occurs

I in the weld metal.I The 135 degree bend test is described in Progress Report

#9, March, 1961.

Macrostructures and Hardness Gradients.

Typical macrostructures and hardness traverses of

weld bead cross sections for the solution annealed condi-

tion and the cold rolled and aged condition are shown in

Figures i8 and 19 respectively. The hardness gradient

of the weld metal and heat affected zone are essentially

the same for both conditions. That is, there is in-

sufficient difference to account for the difference in

S I the bend radius between weidments of solution annealedand cold rolled and aged sheet. Typical weld dimensions,

Iapplicable to both base metal conditions, are as follows:Weld width top - 0.200" to 0.208"

I Weld width oottom - 0.125" to 0.133"Weld thickness - 0.085" to 0.091"

Microstructure of Weldments

S I Typical microstructures of the weldments are shownin Figures 20 and 21. The microstructure of the as-

/ I welded solution annealed sheet is typical of fusionwelded beta titanium. The deposited weld metal is

i57

MICRO HARDNES TRAVERSEWELD CROSS SECTION[ KENTRON MICRO HARDNESS TESTER

DIANONO PYRAMID PENETRATOR

I0 8-j z gi

I1I-J zO

I- 0

C)

ISPEC. NO. 3CA0-2 WELD TYPE AMC (TIG) A. 2ETCI-ANT 2% HPF + 12 HN05 H20

M MTERIAL Ti 13V-1lCr%-3A1 GAGE0mI CONDITION Solution Annealed

Heat No. 9858, Sheet No. 13

WELD SIZE Top - 0.200". Bottom - 015

FIG - 18 58

MICRO HARDNESS TRAVERSE'I WELD CROSS SECTION

KENTRON MICRO HARDNESS TESTERDIAMOND PYRAMID PENETRATOR

>I\I1z 21_ 0

0 0I * i 0

I ~T00~

0p.o 9O2WL YE TGMG 2ITHN 0 % 1%20 2Ti 1V-llr-34

MAEIAL GAGCODTOInwle cl olgAslWtl eddWt

WEL SPSIZ.EJ WELD 0.208 in., BoAto 0,13ETI-ANFIG. +10 E 19O 59H

434

E-1

q4

06

ccF

8:1

~~' --01-

0.44

I- 4-K\t

,*~~ E-4. y,

~6

composed of large columnar grains containing twin and/or

strain indications. The relatively narrow heat affected

zone shows large equiaxed grains. The cold rolled and

1 aged as-welded structure (Fig. 21) is very similar to* Figure 20. The dark areas in the weld metal are believed

to be the result of the metallographic polishing procedure.

I ConclusionsThe Ti 13V-llCr-3Al sheet is readily weldable. The

I tensile properties of as welded solution annealed sheetare essentially the same as the base metal. The bend

ductility of these weldments is very good. The tensile

properties of weldments made from cold rolled and aged

sheet are essentially the same as those for the solution

I annealed condition. The bend ductility of these weldmentsis slightly inferior to that of weldments made in solution

annealed sheet. Complete penetration with controlled

I weld reinforcement was readily obtained. Slight varia-tions from the welding schedule did not lead to signifi-

cant changes in the characteristics of the weldmentso

Data on AM 359 Steel

I AM 359 alloy steel strip was heat treated and ten-3 sile tested. The ratio of ultimate tensile strength to

density varied from 0.80 to 0.82 million inch, This

3l ratio is too low for further consideration of the alloyin the current program, subject to the producer develop-

1i ing process techniques for increasing the strength level,

621!

-m

AM 359 is a precipitation hardening semiaustenitic

* Isteel produced by Allegheny Ludlum Steel Corporation.

H In the form of bar stock it is heat treatable to approxi-

SImately 250,000 psi ultimate tensile strength. In the

form of sheet and strip the tensile strength potential

appeared to be about 280,000 psi. At this tensile

strength level, the alloy would be suitable for use in

cold forming rocket motor end closures that could be heat

treated to a tensile strength-density ratio of approxima-

tely 0.98 X 106 inch. The chemical composition of the

I alloy are listed in Table 19. The annealed tensileproperties of .060" strip are listed in Table 20. It will

be noted that in the annealed condition the ratio of

yield strength to tensile strength is very low and that

the elongation is very high. This indicates that the

I alloy can readily be cold formed. Figure 23, is a photo-micrograph showing the annealed austenitic structure.

Samples of annealed .060 strip were heat treated

in accordance with the producers recommendations and

tensile tested. (The tensile test specimen and the

testing procedures employed are described in progress

reports #6, and #9 respectively). The heat treatment

S I practice and test results are listed in Table 20.3 ITypical stress-strain diagrams are shown in Figure 22.

A photomicrograph of the heat treated structure is shown

SI in Figure 23. The voids are areas where a precipitate,

probably carbide was removed during polishing of the

63

SI AM 359, ALLOY STEEL - CHEMICAL COMPOSITION

SI Percent by Weight

Specification Analysis ofElement Limits Mtl. Tested

I Carbon 0.17 to 0.21 0.20 to 0.21S I Manganese 0.50 to 1.10 0.66

Phosphorus 0.040 Max. 0.021

I Sulphur 0.030 Max. 0-017Silicon 0.50 Max. 0.39

Chromium 13.5 to 14.5 14o34

Nickel 6o5 to 75 7.13

Molybdenum 2.5 to 3.0 2.52

I Aluminum 0.80 to 1.35 1.00I

SI

I

I

• ITABLE 19

64

0

I~~ ~~ b b1oC' N4)0

o H

4)4) H HH H H J(J(\OC

Co 0 ~ 0 f -co 1

P40

00

IPP E-4 E-1 E-4 E-4E-4 E-4 E-4 E-

E-4P E-4E-4 E-f E- E-4 E-1 -H4)

E-4 4

0 P4

0 0 0 -H

E-4 -PkH 0) r) rd 0 d - D t

;4()0 00 1o!~ .5co 0O 0 0oH P 4 -

-HFI 0 HHH to(0l0-r14ONO)

65

r IIIIt_ Lr~1 STRESS VS. STRAIN

LUIA Il iA-39.6

MAI GGCODTOIEA RAE

TRN.TESL

IIqII

III

IIFIG. 22t

.. .... ..

IAnneal e l8600FAC 70F A.C.

-00Annea 18600F, A.C. l75O 0F, A.C.

Temper 9350F,A.C.

PhotomicrographsAm 359 Steel Strip .060"1 Thick 250X

Ferric Chloride Etch

I FIG. 23

D 67

specimen. The retained austenite (light areas) is very

F high, indicating there is a possibility of adjusting the

heat treatment to obtain higher strength levels.

Sl Conclusions.It is believed that heat treatment procedures can be

developed to obtain higher tensile strengths in AM 359

steel, to approach the ultimate strength to density ratio

of 1 X 106 inch desired for this program.

I UNIAXIAL WELD JOINT EVALUATIONData on AM 355 - PH 15-7 Mo Uniaxial Head to Shell and

I Shell to Shell JointsHydrostatic testing of resistance welded wrapped

chambers on previous programs, using AM 355 material for

shells and PH 15-7 Mo for closure, indicated the need for

a closer examination of the weld joint designs. Failure

in these tests occurred in the head to shell welded

joints. Analysis of these failures revealed that the

reinforcing doublers did not carry the membrane loads

I from the closure to the shell due to the inadequacy ofthe spot weld pattern in the doublers. A series of 9

I uniaxial welded joint specimens were designed and testedto obtain data to develop a more efficient joint design,

and verify the analysis reported in Appendix F. report

number 6. The results of these tests are reported herein.

The design variables for these joints were in two

SI major areas:

.� 1) The relative position and size of the spot

* resistance welds.

68I

'I

S2) The relative size and number of seam weldsSI immediately adjacent to the fusion weld.

Seam welds adjacent to the fusion welds were required

I to: (1) Seal interface areas and prevent contaminationi during fusion welding, (2) Increase annealed area to

provide additional strains to offset discontinuity strains

inherent in the particular design concept tested.

The material selected for the cylinder case simulation

I specimen was AN-355 in condition SCCRT. This alloy is astainless steel of the transformation - age hardenable

type. Condition SCCRT is obtained by solution annealing,

I exposure at -100°F, cold rolling and tempering. It has aguaranteed ultimate tensile strength of 2909000 psi for

thicknesses up to 0.080 inches.

The heat treatable steel for the end closure simula-

tion was PH 15-7 Mc, condition RH 1050. This alloy is a

I transformation - percipitation hardenable stainless steel.Condition RH 1050 is obtained by solution annealing,

I exposure at -100°F and aging at 1050 0 F. This heattreatment gives an ultimate tensile strength of 220,000

I psi.Certifications, tensile tests and chemical analysis

were obtained for all the materials, including the welding

3 wire, used in making the specimens. Spot resistance,seam resistance and fusion weld schedules were established

prior to assembly operations for maximum weld strength

values, This data was included in report Number 6.

ii 69

The specimens were tested on a 200,000 lb. Baldwin

Southwark testing machine. Special grip and adapters

were employed in head mountings and special extensomer

SI damps were used to permit measurement of strains over an

8" gage length. Fig. 24 is a schematic sketch showing

I the test arrangement.From the test data and examination of the joints

after failure several conclusions on the overall design

may be made. They ares

1) The doubler spot welds must be designed to take

I higher loads, by increasing the number of spoti welds and/or increasing the doubler length. In

every case the doubler spot welds sheared

I before joint failure. This confirms theconclusions reached from analysis of the results

of hydrostatic testing of large chambers.

2) The double row :;f seam welds through the

entire pile-up produced the highest overall

I strains because of the greater overall ductilityof the seam welds.

I 3) Joint designs shown on drawings E2434-0009 andi E2434-00l0 appeared to be the most desirable.

Table 21 shows a summary of actual versus calculated

I joint strengths and the failure sequence observed foreach joint. Table 22 is a correlation of actual strains

1 measured during the test with the number and pileup ofspot and seam welds in each joint design tested.

.11 70

171

1o 04 04e-0 r-4

$H 0H9 --H 04 HO 00 4

40 01 00~

Hi 4)P 0H "4 v -5A-

0~ W 0 -P0013 8 9 'CO' 00. r -' 0

C0 w~ r-~ 0~E4) 0 d 10 Id I FdI

;4 H- HUI HU*A HLI\Nr-H S 0 OH O- H H4 'P OH H

0 04 H3 S1.0H H+)r0 .CO 0 -4r

0 3 000 0120 0' 00r-P 4 ed ' 03 ' 0~ 0)o 0 f 0

'PH H 0 &0 00~~ .. 40

00 'd 10 q% P-P 'd 4 4-3 Id p44' co H wd 00 P rH 40.a- 0 g " q. 504) 4)0 004)4)0 0 0

0'P~ IN 0 k.cc capP4 cd p ~ COI 4 'd -P02 0'W

04 H o- .0 r-4 OH 8 0W

E-4 4 .pp El

0. (P.I -A $1C2.- 00 0H 0 0r u C ~X N Hý. NI H- - C

u-o H 0 0 0 0I- 0z*

UNN

f.- 4 4

0 0

.vH 0 Voe 0 .0. 0.l 0. K

X%. N~ N NM

0H 0 H r-4

.,-I 0 8

72

rqPVu4 0

0 0

-00 0 o

S 0 -S .0 A.

00 0o 4-'-ý0g' 4-1 0 0 0P

co r-4 M1 4H 4-)

00 0H re-4 0 0f04.' co -A4

H~ .

P 0o o rdo 30 4P.'l

0p 4) m rd 4 e . 0p 4)

4~-4 0 0 Ho ot 1004

$.14 0' i 0 4)H 0.0. 002 .e-0 P 0 CP$ 4- O4Dk43 0p djO 4) .

0)co P 000O0 4-) ~Ir- 0. -4 -4.r r4-: Hco ri ) ý4 0 4 04.' 0

0 ~ ~ ~ ~ ~ ~ -*4r 0H0r -. H COA4J0 DI0 8 0 0 Or3 b0.0,0 (D8..0C 0 H co0 00 0A

0 00 0r4

k x.2-8 0 V o -M f * 0 P40 94-140 4-30*44 0

bDA 00 F.

F.10 0 H4 -H00

-P 00.0 4

to 0 *o

40 0) 4-4 4) 1Z 8~ - 0 oo 0 P4000 4.4' 0 0 c

0 .r r- rdp*44 0) 0 N p4

~~r40 ~ H *rr4~' r(D- N. 4-) .

NP4)

r- Co 0 4 A

r4 020

p44

~co

ii 73

0 4- 0 00 0 0 00 0 0

0

co

4)j CP0 42

IH 0o am 4CO (1) 0 0 0 0 0 0 0 0 0

E-4 :30Id p. 0 UN\ 0 0 UN\ E- 0 0 0C) Hr N 0 mUýN 0 L.fl 0N wN UN tcý

P-1 H- Id ci o 0 0 0co~ Ho 9 A r4 0 0 0 41 a'N (IN CI 0 co H- H- H- H- --

El 4'

pq 0 ci C~-H 0r

S H (D 2 PL' 0~Cci) co C C

~HCOHG. MNi 0 C +4 4E- A D(0E%

0

I 0

4), 4) P' 4 4' ' 4 4 34:3 r- K\ KIN 4f 4f K\ wNt' rc CO

p Q$0 E-1

0 coA C,

H H ci)E-1 A~ :3 NM N CMj NCM I r H H -HH 4 --1 Hiq-i 0

:3 00 rdci)II

1 0 0 0' O4H CM4 --I 4 'E-00a 0 00 0 00 0 0 0 0

0 00 0 0 00 0 0

jIKI4

I

I •Appendix B includes revised specimen drawingsreflecting the addition of bearing plate reinforcements,

and drawings of the special test fixtures used in tensile

testing the specimens.

Appendix C reports in detail the sequence of failure

Iand load versus strain diagrams for each specimen type.

! |Figure 25 includes photographs of the AM 355-PH 15-

7 Mo specimens after fracture. Location of the fracture

with respect to weld patterns are illustrated.

Electron Beam Welded Joints - JLS 300 Steel

I JLS 300, .040 strip, cold rolled and tempered to340,000 psi yield strength, was electron beam welded.

Metallographic examination revealed the presence of

I shear cracks caused by overdrafting of the strip duringrolling. Subsequent work has been delayed because of

I this defective base metal condition. The results ofthe work completed to date are presented herein.

The mechanical properties of electron beam welded

I |specimens and comparable T.olG. specimens are shown inTable 23. Chemical composition of the .040 JLS 300

*• strip is shown in Table 24. Coupons were cold sheared

from the strip, then ground to remove edge cracks, dye

penetrant inspected and mechanically cleaned to remove

I a light oxide scale.The joint designs are shown in Appendix B, progress

report #9, March, 1961, drawings E2434-0116 and E2434-

0117. The important characteristics of the joint are

75

YE-

I Co4I UN

RibRaft

76

!

Sii A -355 SCCRT, PH 15-7 MO WELDED

TENSILE TEST SPECIMENSSHOWING FRACTURE LOCATIONS

ISPEC IMEV• B+80-aS-O013

i HEAD TO SHELL JOINTI

SPECIMEN B480-SK-0014

HEAD TO SHELL JOINT

I

j ~SPECIME3N B480-SK-0015I

HEAD TO SHELL JOINT

• FIGURE 25

I7

AM-355 SCCRT, PH 15-7 MO WELDEDTENSILE TEST SPECIMEN

SHOWING FRACTURE LOCATIONS

I SPECIMEN B480- SK-O010HEAD TO SHELL JOINT

I

ISPECIMEN B480-SK-O011

HEAD TO SHELL JOINT

- SPECIMEN B480-SK-0012HEAD TO SHELL JOINT

FIGURE 25

78

AM-355 SCCRT9 PH 15-7 NO WELDEDT.WNSILE TEST SPECIME•NS

!• SHOWING FRACTURE LOCATIONS

I SPECIMEN B480- SK-0007SHELL TO SHELL JOINT

I

I

SPECIMEN B480-SK-0008HEAD TO SHELL JOINT

SPECIMEN B48O-SK-0009HEAD TO SHELL JOINT

5 FIGURE 25 79

0i 0 H H o0 0A 0-H - 0~ 4' )

A 44 0 0 j ý K-O (I)r4 H ir-A - L

UN4-) 0)H

0 * 00q4-4

0 0

4-D 4-"

N ( '\ i N 0 0 ( 1

E-NN0-

COl c ,-I0I bo 0 0 0 OO0 Ord

00

0 0,d

0O 04-3 NN!C KN 0 4f-ý

HO 0 )CO 4.. 4- 0 0 -MI 4.; 4-.) 0H

0j4- 00r

0I 4-)

~o 0 40

0 4'-i

E-44

rd r-4 000P4 0 H -00

;4 1- 0 (1

a)0 0 0)

044-D 0 *r4000H 0~ F1r W dK

0 (a r-4 co-H Ci0) ) r-4 CO c

0 4- 43-00 H0 0 rd

to1 0 41)..

0 HE-i E-4 E--

80

am

CHEMICAL COMPOSITION JLS 300, 040" STRIPELECTRON BEAM WELDED

Element Percent by Weight

Carbon 0.115

I Manganese 1.27Phosphorus 0.020

I Sulphur 0.013Silicon 0069

Chromium 17.20

Nickel 5.12

Nitrogen 0 .08III

III

S I TABLE 24

V 81

- r1'

•I cleanliness, freedom from cracks and a fit up having

$ I less than 0.001" gap.The micro-cracks in the base metal apparently caused

excessive porosity and oxides in the weld metal. It was

determined that a multi-pass weld considerably reduced

I these unsatisfactory conditions. Two, 2 pass and one3 pass electron beam weldments have been made and are

currently being evaluated.

I The Bristol Machine & Tool Co. Inc., Forestville,Conn. welded all specimens, using Hamilton-Zeiss high

voltage electron beam welding equipment. Eight to ten

I bead on sheet tests were made to establish the weldingschedule. The specimens were then loaded in the fixture

I shown in Fig. 26 (see electron beam welding of betatitanium) and welded under a vacuum of 10-4 mm. of Hg.

I The welding schedule employed is listed in Table 25°I All weldments exhibited excessive porosity and

oxide inclusions when single pass welding was used. Two

I or three weld passes resulted in radiographic clearweldments.

I One single pass weldment was mechanically tested;I the weld metal being 900 to the direction of tensile

loading. The validity of the test results is open to

I question because of the presence of micro cracks in theheat affected zone. It will be noted, however, that the

I tensile yield strength of the weldment is 30% to 35%higher than similar weldments made by the tungsten inert

82

I,

rI

I 8

I

I' I ____.__V ,'I T •

I" ___________F .5"2"i

I•, FIGURE____________

I

ELECTRON BEAM WELDING SCHEDULEIg- JLS 3009 040 STRIP COLD ROLLED ANDU TEMPERED TO 340 KSI YIELD STR.

I Voltage - 110 K..V.Current - 1.8 Nil. amps.

Deflection - .050 (relative #, approx =(Parallel to Weld) to inches beam deflection)

Welding Speed -• 25 inches per minute

Beam Diameter - .006"

Focus of Beam - Surface of Specimen

I Filament - Tungsten Coil, 40 Nil. amp.current

I Vacuum - i04 mm of Hg.Number ef Passes - 1I

I

I

I

I TABLE 25

84

I arc process employing AM 355 filler wire. This is attri-buted to the fine weld metal grain size and the very

narrow heat affected zone,

Figure 27 is a photomicrograph across the weld zone.

The weld metal is fine grained. The fusion line and HAZ

consists of somewhat larger grains of austenite graduating

I into tempered martensite. There is also a small amountof ferrite (white areas) alcing the fusion line and through-

SI out the HAZ. A microcrack extending from the HAZ into

the base metal is 8hown in the right hand photomicrograph.

I Figure 28 is a photcmicrograph of the type of shearI cracking found in the base metal 0

Electron Beam Welding of TI-13V-llCr-3Al Alloy Sheet

The effects of the angle of inclination of the weld

deposit line to the applied tensile load, the prior

I metailurgical condition of the base meta-', and of theSI type of postweld treatment were measured for Ti, 13V,

1lCr, 3AI, electron beam weldments. Preliminary analysis

I of the data indicates that 0.060" sheet cold rolled andaged to 225 ksi tensile strength gives weldments having

•I the best combination cf strength and ductility when the

3 Iangle cf the weld deposit to the tensile load is about200 and postweld treatments are not employed. A more

3• thorough analysis of the data is in process and theresults will be included in a subsequent progress report.

The scope of the program is listed in Table 26.

S585

II4 D

I~c 04 .P43

1Q 0 04- 0

*'d C.-

4) cP4

P-I 0 *.-I$ 4 0

rd 0 0

0)l 0

00p

0 P4..l 0 q 4)H 4-H 0 0

o o M44 HH4)oE-0 Pq

ca H

PP H00 0 0 4-P

0i r-4 IC' H 404-) 4>0 0 .

~K 1 86

IfA

strip.

Ethn letoyiixlcAi

10O

FI.2

Materal ad Conitio

IKIc.~J C~)0 V

o) 0V'- Lr*% . N-.- TiN t-N r

Ar- e-fr-PC " C\d

0- 0H CH

Hp - 0 N-~~ E-In-&040COI r 1-

410 N 00

z HH '(DHaa)

0 4 0) r

EO40 (1 0 0) Od

o40 0 0 E-1 b- 0 E-1 H 0 00 w

0 r Z-- H J

ON 02' 0)

0~~4 UN 0430 )0+ 4) Z 4 Z14~ Z~ H 00H4 0O 4H H ) r r

0- -PE- c 9 c w4-

0 0 A4 o 0 a) (a0

0~~ 4. l, r4-q0c

b4 0

0 CO04~C CJ2H~ ObOH)

43 0 88

4)c

Three joint designs, three base material conditions, and

S* two postweld treatments were used. The joint designs of

200, 400 and 900 were selected on the basis of previous

research experience which indicated that for the lower

modulus material about 200 is the optimum angle and 900

I the least desirable angle for optimum joint strength and

I ductility, where the deposited weld metal strength islower than the base metal strength. A literature survey

Sl indicated that the tensile ductility, in the presenceof discontinuities, of cold rolled and aged sheet may be

I somewhat better than that of solution annealed and agedsheet; hence both conditions were included. The postweld

treatments were included to determine whether electron

beam weldments reacted in the same manner as TI.G.

fusion weldments. That is, single aging yields a

brittle structure and duplex aging yields a ductile

i structure, where the base metal has not been cold rolled.Sheet material 0.060" thick by 36" wide sheet

SI procured from the Titanium Metals Corporation was used.

Sheets were procured in the cold rolled and aged condi-

I tion and in the solution annealed condition. The solu-•I tion annealed and aged samples were prepared by The Budd

Company Research Laboratory. The samples for welding were

I cold sheared from the sheet and the edges dye penetrantinspected to determine the extent of shear cracks. None

I were found. The edges of the samples were ground to a63 microinch finish and reinspected to assure freedom

1 89D!

V

from cracks. The perpendicularity of the edge to the

upper and lower surfaces was within 15 minutes, and the

edge camber was negligible. The samples were then cleaned

I at room temperature in a water solution containing 40%by volume of concentrated H2SO. Prior to welding the

edges were cleaned with acetone to remove dirt and

SI grease that may have accumulated during transit and

storage. The metallurgical condition, and the mechanical

I properties of the samples are listed in Table 27.The joint designs are shown on drawings in Appendix

B, Progress Report #9, March, 1961, drawings E2434-0116

and E2434-0117. The important characteristics of the

joints are cleanliness, freedom from cracks, perpendicu-

I larity and straightness of the edge so that a 0.001"feeler gage could not be placed in the joint when two

I pieces are butted together under slight pressure. Thelength of the welded joint was limited by the amount of

jig movement available in the electron beam vacuum

I chamber.The Bristol Machine and Tool Co., Inc., Forestville,

.1 Conn., welded all specimens, using Hamilton-Zeiss high* Ivoltage electron beam welding equipment.

About 10 bead on sheet welds were made to establish

3 Ithe welding schedule for use in welding the samples fortest. On determination of a welding schedule, the

samples were loaded in the fixture shown in Figure 26

90

Iiz

~r4

0~

E-AIi i0

2-O r- &

0a4 ) ca 0 0 D Lr ' N

43 0-P0 C~ K

2ý -4 C1 44)/2 0-~litO ~ r

0 rx4

r-4 bo.- E

oo 00o0

00 H~ Caj

Fl a)0-

4 0A E -4 E- P E -

P44 ro-P 00*r4 r

Ird ~ 0 H-00 0 0S Hd04- e-ON~ ~ 0

0 0 $4 : C)

E- 0~

4)-a,'r

4191

I and welded. The welding schedules employed for the testIi weldments are listed in Table 28.

Radiographic Examination of Weldments

IThe weldnents were radiographed by the Magnaflux

Corporation, Hartford, Conn. using a Balto, 300 KVP, 5ma

machine a thin stainless steel penetrameter and the

following technique. 120 KV, 5ma, 36" FFD, Kodak AA film,

6 minutes development time. Examination of the radio-

J graphs indicated that some of the weldments were considera-bly more porous than anticipated. To date, the source

I. of the contamination has not been definitely established.However, it is believed that inadequate cleaning and/or

"interstitical gas content are the predominating factors.

Fig, 29 lists the radiograph indications found in the

weldmentso As a result of this condition, and of crack-

ing during preparation the number of specimens available

for test was reduced by 33%.

Tensile Testing of the Weldments

Coupons for tensile test were machined from the

weldments as shown in Appendix B, progress report #9,1"

1. March, 1961. Where possible, the coupons were removed

from radiographic clear areas. However, some of the

specimens contained porosity as large as 020" diameter,

which apparently had little or no effect on the resultant

tensile properties. The coupons were machined to the

form and dimensions shown in Figure 30, Dwg. E2434-0015

(Figure 2 shows a 400 angle weldment. All specimens

J 92

- 0

0O 0 LA\ UN 0 0 0 00 N C- N N N -1- 0 'H

*14- p4co

$4.

HH

0 -J 0 co H -0 H1 ~ \ ~ Cj Cj 0 ) 0zo: 0 r- pi r'Hp-Hq : 0

I- w\ CU U C0~P H0 4-'

00 co 0

H 0 0~~1) $.~p 4 44) Q 0p

Hr HO 0) 0 0) 0) H400 - $4 0 dOHd Id r dcI- 4)., 4) 4 4 p k- .

0 COiC r- co0 0aco 4) E 00piZ 4) (D 4) P4 4-3

E a 1 $&H 4) 4) +) +) +- +o )O 0I04-0 0 4 oc H 4aO044j p) 0I UN4 UN-

-H 93 54 91 co . C t o4)0 P

E- 0 0 0H )02 HCO*r 0 H -

4-1 4- 0 P4-c0 Lr\ c (1) P4 $

p4) 04) E 2'-4

0) ) HPep 90,H

L I -ri. - 4

VH CUl

93

'S'A

MOO J

WELIur 0 01~ H06 AZ,"mu

'Ii

I5A WELDO SLTS

.94

7- -

4J o0 4

u is tr 0N ae

7I

jI,had the same form and dimensions except for the angle of

* nthe weld deposit). Where postweld heat treatment was

required, the coupons were rough machincd, heat treatcd

I and then ground to finished size. Cracks were observedin specimens J7-1 and J7-3 after heat treatment, and

I they were discarded. The cracking apparently originatedI nduring the rough machining operation (blanking die shown

in progress report #9, March 1961). The grid noted in

i Figure 2 was applied to some of the specimens to allowtime-sequence pictures of the deformation occuring

n during test. The grid is a series of 0.1" X 0.l1

n squares ink stamped over the gage area of the specimen.

To provide sharp lines and good contrast, ink having the

following formula was used&

31 grams of rosin and 2.3 ounces of Dupont Victoria

Green Aniline dye in 100cc of methanol.

I iThe tensile test procedures described in progress report#9, March, 1961, were used, except for the specimens

I containing the grid. These specimens were tested in aTatnall Mod. UWR Universal Testing Machine employing

Shydrauiically lcaded V-grips. A 35MM Exacto V cameramanually operated was used to obtain time sequence shots

of the deformation patterns. The mechanical properties

S I are listed in Table 29. The types of fractures obtainedare shown in Figure 31.

K ~Metallographic work, and analysis of the deformationpatterns is in process, hence no conclusions will be made

4 * in this report.96

U- 0- 0 H I r-IHHHHHr- H r4HH.43 43 - -) 4 2 4, .'> 4 4-) 43-P

4) 4) 0 0 rd rd IdId N ~CM 'j r d-H 0)a q HHHH4 .- ' \ -.e H- r4r-I

I M*fl a\1 00000 1 0 00i

-PI- 0 WCs L\ % - 0K (0o 43$1 0

0) H~. IU - 0 oN Mf >

co 0 0I~- E4 0P 94 q-4E-1H000 0 0(\J 00

m ~ ~ $ 0ot00C~ ~ co 02

0COrI IDrf rEl fl 4 04, j 43-

0 r-4 CO( rA0O El d UN Lf o- rd uv d ON H

0 0 0 d co cP4 P4 0 p pO

4,W

Ho 4,f o~0 0)*rd * EO lrdE a

m1p Id '~bo 4 ) w Nr 0) 0 .-r4o,-4i &1H V ~ 0- 0 0 0 0) ,O 00m0 E-4E4H 0D)0 OH M ) OeN- fl""e- H"'0 H) e-'ý 000 ) 4-)e

P! r- -lP4-)4,CO -H -I4 . r-i4H - -t f-4 U-NXH OHI H -Ifr4 -P ~ CA-- H.J.E / rAo&

P4H

4, 4, 0

U EA 0 rd 0o4,bI H 4)~) 0 0 0 0

rd$0IdkU .4 %O~- bD r4,

O H 'r -IC r.rdH U)IP40 o W )0$-s CO PO CON.d AW-- ~ I4 a UN\ -400CO.0 N U2 dCM'dJ W.0 C\J

~4-1 WlUNL\ 3H UnH o - 0E400- P40~ o('JE-1: 0 'J E-1 3 0. 0 \ 0 0E-1

r- 00 -343- 0-H- H- 0 ~ ' 01 4 4*r4 fd P4 430 F rr40 04,4,4,~d 0 H4, rd. i-I CJ4HO 0 - )r-I '~~0 43 P H0 -P$N rrJ. Nr 0

O 0:30 0 0 0H D 00H-I4-') ICj P4 CJ oa0U ca o 00 00o'0 i oON FD 0 CM -,n IC'Jr

k$- N C\JHr4C\J0 nool

P4O CM r-i C\J HHCJC' H JN~ hl r- HO -4Cj Wi0 0 0 -5 -0 0 00

-- 10000000j fNLr L\ 0 kD% D -NC. 0 0H 1 -CMNC UNNU FO'D tO'ýD IrN Ft..-

97

5KE-TCHEZ OFr TYPICAL TEM'1LE

ME UUT Z 0-TL, 1:V I IC , 3 Al, WC 55E T.

:50LUTIOW~ AUW" LEC V%/!LI BA~,5e METAL FMAC-TUEp.,

OUCTILS FCACTUZEý IE-cKlOUG A&JO CGOOD FLOLJGATIOW.

I 25PECIL4M%-C-eI 5OLUTIOIJ AIUJUEALEDWELD, AGE .ZLU

I BEITTLE- PCA

F,It is anticipated that the metallographic studies

and interpretation of the mechanical test results will

he completoa in the next period. The investigation of

the effects of joint design and treatment on the proper-

ties of solution annealed and aged titanium sheet elec-tL tron beam weld will also be initiated in the next period.!!I

I

II

III

I"'

! 99

I HELICAL WELDED CYLINDERSIn report number 11 we discussed generally, designs

of cylindrical sections using strip materials in highii strength conditions. A helical fusion butt welded cylinderhaving the weld line preferentially oriented to reduce

the normal stress sustained across the weld line is being

S I considered.Geometric elements which control this design of

cylinder are: Material coil width, helix angle, and

cylinder diameter. Figure 32 shows the relationship of

these elements° A weld line helix angle of approximately

S | 180 to 250 appears to be optimum, based cn previous tests

U of small cylinders. This would apply where the weld

I strength is in the area of 60% to 80% of the yield

strength of the base metal, We expect to develop data

~ I on this using uniaxial tensile joint specimens and sub-scale cylinder tests.

Figure 33 shows a qualitative relationship between

helix angle and the ratio of membrane hoop stress to

yield strength of the base material. It can be seen

I that as the helix angle decreases there is a correspond-ing increase in this stress ratio. We are currently

obtaining actual data from uniaxial weld joint specimens

SI with welds oriented at 900 - 400 and 200 to the lineof load application. A yield criteria for various

I materials in different heat treat conditions will be-determined. From this data, actual values for each

100

SI THE BUDD COMPANYPOWARM Bill PRODUCT DEVELOPMENT PAi ICueOCuu my, PNSLNASUIA. PA.

SAYE mm,, . // ., .,S I a amps" Wo-

7~IAW IRJW NO.:

THE BUDD COMPANY-.--,YPRODUCT DEVELOPMENT PA.PgnigI.ANLMS. PA.

S I DATM__ PiOJWT NO.

EFFECT OF HELIX ANGLE ON THEYIELD STRENGTH OF A CYLINDER

rI .2II •O ---0

II .8

IMAX SHEAR STRESSI6 iYIELD CRITERIA

2:1 BIAXIAL FIELD

HI 4 oIHOOP STRESS• .4G p =PARENT METAL

l i YIELD STRENGTH

I °o , 3b7' e0' 70 9b0i IHELIX ANGLE

SFIGURE-33

Imaterial considered can be plotted and optimum helix anglescan be established. From tests of sub-scale 200 cylinders;

I we expect to obtain actual data to confirm the valicityI of the design and the cumulative effect bending stresses,

etc. on the performance of the cylinder.

A parallel program to the development of analytical

Sdata is being conducted on the method of welding helicalbutt welded cylinders. A fixture was rigged up using a

I stationary shoe, and roller drive to feed coil strip,under the welding head. This was done using 6" wide

I strip and a 10" diameter cylinder. The material welded

* was .020" thick Type 301 stainless steel. Figure 34

is a photograph showing the welding operation on a 36"

I long cylinder. A total of six cylinders have been weldedusing the rigged up fixture, which we feel amply

I demonstrates the feasibility of the method.We are currently designing a fixture capable of

welding 20" Dia. cylinders for the sub-scale program.

This fixture will have sufficient power in the drive,ii and accuracy to enable us to weld cylinders in variousalloys with reliab'le repeatability.

In addition to the welding development of 10"1

cylinders noted above, we are working on an explosive

sizing technique. Figare 35 shows a photograph and

schematic design of an experimental setup used to size

a 10" cylinder. The .020" thick cylinder was sized to

between 1% and 2% of its diameter explosively in a steel

103

I

I

il

!I

•• HELICAL WELDING FIXTURE AND

• •ARRANGEMENT- 1O" CYLINDER

S~ FIGURE 34

i10

4

I:04 YESO TILSIiw

IWATYE o

11~e-re&ZLUoI alPLAI

Icfm41 0& ~ wPkf'AA NI--A&M9I~~~AA. airO/V

10/A4N6MU