advanced refractory alloy corrosion loop

ADVANCED REFRACTORY ALLOY CORROSION LOOP PROGRAM

Quarterly Progress Report We. 5 Fer Quarterly Eadirg Jdy 15, 1966

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NATIONAL AERONAUTICS A N D SPACE A D M f N l S T R A f i O N E C O N T R A C T N A S 3-6474

1 - SPACE POWER AND PROPULSION SECTION

MISSILE AND SPACE DIVIS1ON

G E N E R A L f LECTR I C CINCINNATI, OHlO 45215

https://ntrs.nasa.gov/search.jsp?R=19660026398 2020-03-16T20:35:33+00:00Z

ADVANCED REFRACTORY ALUlY CORROSION LOOP PROGRAM

QUARTERLY PROGRESS REPORT 5

C o v e r i n g the Period A p r i l 15, 1966 t o J u l y 15, 1966

E d i t e d by

R. W. H a r r i s o n

Project Meta l lu rg i s t

A p p r o v e d by

E. E. H o f f m a n

Manager, C o r r o s i o n Technology

Prepared f o r

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

L e w i s Research C e n t e r

U n d e r C o n t r a c t NAS 3-6474

July 29, 1966

Technical M a n a g e m e n t NASA - L e w i s R e s e a r c h C e n t e r Space P o w e r S y s t e m s D i v i s i o n

R. L. D a v i e s

SPACE POWER AND PROPULSION SECTION MISSILE AND SPACE DIVISION

GENERAL ELECTRIC COMPANY CINCINNATI, OHIO 45215

I I . It I c E 5 I I I t E t I E E c t I

FOFLEWORD

The work described herein i s sponsored by t h e National Aeronautics and

Space Administration under Contract NAS 3-6474. For t h i s program, M r . R. L.

Davies i s the NASA Project Manager.

The program i s being administered f o r t he General Electric Company by

Dr. J. W. Semmel, Jr., and E. E. Hoffman, i s ac t ing a s t h e Program Manager.

J. Holowach, t he Pro jec t Engineer, is responsible f o r t he loop design,

f a c i l i t i e s , procurement and test operations. R. %'. Harrison, t he Project

Metal lurgis t , i s responsible f o r the mater ia l s procurement, u t i l i z a t i o n and

evaluat ion aspects of t h e program. Personnel making major contr ibut ions t o

the program during t h e cur ren t reporting period include:

Alka l i Metal Pur i f ica t ion and Handling - D r . R. B. Hand, L. E. Dotson, H. Bradley, and J. R. Reeves.

Welding and Joining - W . R. Young.

Refractory Alloy Procurement - R. G. Frank and L. B. Engel.

TABL;E OF CONTENTS

SECTION

I

I1

I11

IV

PAGE . . . . . . . . . . . . . . . . . . . . . . . INTRODUCTION.. 1

,7 PROGRAMSTATUS. . 3

3

9

9

14

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

A . MATERIALS PROCUREMENT - . . * - - * * 1. T - 1 1 1 A l l o y - Fansteel Metallurgical C o r p o r a t i o n . . .

2 . Mo-TZC A l l o y - C l i m a x M o l y b d e n u m Company

3 . Cb-132M A l l o y - U n i v e r s a l C y c l o p s S t e e l C o r p o r a t i o n . . . . . . . . .

. . . . . . . . . B. ALKALI METAL F’URIFICATION AND HANDLING.

. . . . . . . . . . . . . . . . . . . . C . QUALITY ASSURANCE 18

. . . . . . . . . . . . . . . . . . . . . . . F U T U R E P L A N S . . 19

. . . . . . . . . . . . . . . . . . . . . . . . . REFERENCES. 20

. . . . . . . . . . . . . . . . . . . . . . DISTRIBUTION L I S T 22

t 1 f I 1 c 2

ILLUSTRATIONS

FIGURE

1 Transverse Microstructure of T-111 Alloy Extruded Base Tube. . 4



4 Transverse Microstructure of T-111 Alloy Extruded Base Tube After Annealing a t 3000'F for One Hour i n Vacuum . . . . . . . 7

TABLES

TABLE PAGE

I Microhardness and Grain Size of Unannealed and Annealed T-111 Alloy Heat Number 111-D-1670 Extruded Base Tube. . . . . 8

I1 Extrusion Parameters f o r t h e 6.72-Inch Diameter Machined T-111 Alloy Ingot (111-D-1765) . . . . . . . . . . . . . . . . . . . 10

I11 Chemical Analyses of Mo-TZC Alloy (Heat No. TZC-4431) Produced by Climax Molybdenum Company . . . . . . . . . . . . . . . . . 11

I V Mechanical Proper t ies of Mo-TZC Alloy (Heat No. TZC-441) Produced by Climax Molybdenum Company. . . . . . . . . . . . . 12

V Extrusion Parameters f o r t h e 5.36-Inch Diameter Machined Cb-132M Alloy Ingot. . . . . . . . . . . . . . . . . . . . . . 13

V I Extrusion Parameters f o r t h e 3.75-Inch D i a m e t e r Machined Cb-132AI A l l o y B i l l e t s . . . . . . . . . . . . . . . . . . . . . 15

V I I Extrusion Parameters f o r t h e 2.0-Inch D i a m e t e r Machined Cb-132M A l l o y B i l l e t . . . . . . . . . . . . . . . . . . . . . . . . . 16

V I 1 1 Spectrographic Analysis of L i t h i u m Af ter Hot Trapping f o r 126 Hours a t1500"F. . . . . . . . . . . . . . . . . . . . . . . . 17

PAGE

-iv-

ADVANCED REFRACTORY ALLOY CORROSION LOOP PWRAlld

I. INTRODUCTION

i I I I I I t I I I 1 I I

This report covers t h e period from April 15, 1966 to July 15, 1966, of

a program t o f ab r i ca t e , operate f o r 10,000 hours, and evaluate a potassium

corrosion test loop constructed of T-111 (Ta-8W-2Hf) a l loy . Materials f o r

evaluation i n the turb ine simulator include Mo-TZC and Cb-132M. The loop

design w i l l be s imi l a r to the Prototype Loop; a two-phase, forced convection,

potassium corrosion test loop which has been developed under Contract NAS

3-2547. Lithium w i l l be heated by d i r e c t res i s tance i n a primary loop.

Heat r e j ec t ion f o r condensation i n the secondary !ocp w i l l be accomplished

by rad ia t ion i n a high vacuum environment t o the water cooled chamber. The

compatibi l i ty of the selected mater ia ls w i l l be evaluated a t conditions

representa t ive of space electric power sys t em operating conditions, namely:

a . Boiling temperature, 2050°F

b. Superheat temperature, 2150°F

c. Condensing temperature, 1400°F

d . Subcooling temperature, lOOOOF

e. Mass flow r a t e , 40 l b / h r

f . Boiler exit vapor velocity, 50 f t / s e c

g.

h. Average heat f l u x i n boi le r (0-250 inches), 23,000 BTU/hr f t

Average heat f l u x i n plug (0-18 inches) , 240,000 EiTU/hr f t 2 2

-1-

11. SUMMARY

During the f i f t h quar te r of t h e program, work proceeded on the topics

abstracted below:

Signif icant e f f o r t w a s made i n the past quarter i n monitoring t h e f ab r i -

ca t ion of the advanced re f rac tory a l l o y s . Poor yie lds i n the fabr ica t ion of

the T-111 a l loy have necessi ta ted t h e melting of an addi t iona l ingot. The

processing of t h i s ingot i s being expedited t o minimize t h e delay t o the

program. A l l T-111 a l loy material is now expected t o be on hand by September

15, 1966.

A l l the drawings f o r the Alkali Metal Pur i f ica t ion and Handling System

fo r Corrosion Loop I (T-111) have been issued.

The sodium t r ans fe r system, used with the Prototype Corrosion Loop, i s

being modified f o r use i n handling l i thium f o r Corrosion Loop I.

of the l i thium s t i l l i s i n progress.

Fabrication

-2-

.

111. PROGRAM STATUS

A. MATERIALS PROCUREMENT

1. T-111 Alloy - Fansteel Metallurgical Corpor-tio !

The processing of T-111 a l loy tubing f o r Corrosion Loop I (T-111) i s pro-

ceeding a t Wolverine Tube Division of Calumet-Herla. On May 4, 1966, the

three remaining 2.93-inch OD x 9-inch long T-111 a l loy tube hollows were extruded

i n t o base tubes each measuring approximately four-feet long.

I n t o t a l e ight T-111 a l loy base tubes have been processed. Subsequently,

the base tubes w e r e cleaned, the I D honed, t he OD polished, recleaned and

inspected.

ing the annealing temperature t o be used on the base tubes p r i o r t o tube re-

ducing.

2600°, 2700°, 2800°, 2900°, and 3000°F i n vacuum.

by metallographic and microhardness techniques.

As can be seen i n Figures 1 through 4, r e c r y s t a l l i z a t i o n has occurred i n

A br ie f study was performed a t General E lec t r i c t o a id i n se lec t -

Samples from the base tubes were annealed f o r one hour a t 2500°, The samples were examined

a l l of t he annealed specimens.

presented i n Table I.

des i rab le combination of hardness and gra in s i ze . Subsequently, the e ight

base tubes w e r e wrapped i n tantalum f o i l and annealed f o r one hour a t 2700°F

a t a pressure of less than 1 x t o r r by Wolverine Tube.

The microhardness and gra in s i z e data is

A one hour a t 2700°F anneal w a s se lec ted t o obtain a

On July 12 , s i x of these base tubes were successful ly given a 50 percent

reduction by Wolverine Tube t o an intermediate tube s ize .

On May 9-11, 1966, the conditioned 4.25-inch diameter b i l l e t s from the

four th T-111 ingots (No. 111-D-1102) were ro l l ed t o 3.5-. 3.25-, 2.75-, and

2.25-inch diameters a t 1700°F in air a t Braeburn Alloy Steel.

Electron beam melting of a f i f t h ingot , which w a s necessary when a

poor y i e ld w a s obtained from the fourth ingot, w a s completed a t Fansteel

on May 9 , 1966.

inch diameter e lectrode s tock on May 16, 1966, at Anderson-Schumaker, Chicago,

The f i f t h EB melted Ta-8W a l l o y ingot w a s forged i n t o 4.0-

-3-

I E 8 1

.

a) As Extruded

b) Annealed, 2500°F - 1 hour c2004-1

Figure 1. Transverse Microstructure of T-111 Alloy Extruded Base Tube.

Etchant: 30gmNH4F-20mlH20-50mlHN03 Mag. : l O O X

a> B830114 b) B830211

-4 -

a ) Annealed, 2600°F - 1 hour

b) Annealed, 2700°F - 1 hour c2004-2

F i g u r e 2. Transverse M i c r o s t r u c t u r e of T-111 Al loy Extruded Base Tube.

Etchant : 30~~-qF-2rSmlH20-50~lHN03 Mag. : l O O X

a ) B830311 b ) B830411

-5-

I 1 8 I 1 I I

8 1 D

n

I I 1 I 1 I 1

a) Annealed, 2800°F - 1 hour

b) Annealed, 2900°F - 1 hour

F i g u r e 3. Transverse M i c r o s t r u c t u r e of T-111 Alloy Extruded Base Tube.

Etchant : 30gmNH~F-20mlH20-50mlHN03 Mag. : l O O X

a) B830511 b ) B830611

-6-

F i g u r e 4 . Transverse M i c r o s t r u c t u r e of T-111 Alloy Extruded Base Tube After Annealing a t 3000°F f o r One Hour i n Vacuum.

Etchant : 30gnSH4F-20mlH20-50mlHN03 Mag. : l O O X

4:B8 30 7 1 1)

-7 -

.

TABLE I . MICROHARDNESS AND GRAIN SIZE OF UNANNEALED AND A"EA18D(a) T-111 ALLOY HEAT NUMBER 111-D-1670 EXTRUDED BASE TUBE

Annealing Temperature

O F

A s Extruded

(b) M i crohardnes s DPH

314

2500 217 7.5

2600 212 7.5

2700 2 1 0 7.5

2800 216 7.0

2900 214 6.5

3000 217 6.0

(a ) Specimens annealed for one hour a t pressures less than

(b) Average of fou r impressions a t mid-wall l oca t ion ; 450-

1 x 10-5 t o r r .

gram load.

(c) In te rcept (or Heyn) procedure used.

(d l No value, specimen heavily cold worked.

-8-

Illinois, and subsequently arc melted to the T-111 composition on May 25,

1966, at Fansteel. The resulting 7.5-inch diameter arc melted ingot was

machined to 6.72 inches, sectioned into two equal lengths, and shipped to

Canton Drop Forging Company for extrusion. The two billets were canned in

a molybdenlun lined Type 304 stainless steel seanless pipe by heliarc welding

and extruded on June 14, 1966. The extrusion parameters are presented in

Table 11. After extrusion, the cans were removed and the two billets were

conditioned to 4-inch diameter and subsequently rolled to approximately 3-

inch diameter on July 1, 1966. The rolling was performed at 800°F in air

at Braeburn Alloy Steel.

It is presently expected that all of the T-111 alloy material required

for loop construction will be on hand by September 15, 1966.

2. Mu-TZC Alloy - Climax Molybdenum Company The 2-inch diameter rod was shipped on April 18, 1966. The remaining

2.125-inch diameter rod was rolled at 2400°F to 1.3-inch diameter on April

21, 1966, by Climax. The rod was subsequently machined to 1-inch diameter

and shipped on May 4, 1966. The chemical analyses of the ingot and stress-

relieved rod, as supplied by Climax, are shown in Table 111. The mechanical

properties, also supplied by Climax, are presented in Table IV.

3. Cb-132M Alloy - Universal Cyclops Steel Corporation The remelted 5.375-inch diameter Cb-132M alloy ingot was canned in

molybdenum and was extruded to 3.75-inch diameter at DuPont on April 25,

1966. The extrusion parameters are presented in Table V. The extruded

bar was conditioned to 3.375-inch diameter and sectioned into two lengths.

One billet length was stress-relieved at 2300°F for one hour in vacuum,

machined, recanned in molybdenum, and extruded at 2400°F to approximately

2.25-inch diameter. This billet currently is being tested and inspected,

and will be used to produce 2.0-inch diameter rod. The second billet length,

which will be used to produce 1.0-inch diameter rod, was given a recrystalli-

zation anneal at 3200°F for one hour in vacuum, machined, recanned in

molybdenum, and extruded at 2900°F to approximately 2.25-inch diameter. The

1 1 I I

. .

TABLE 11. EXTRUSION PARAMETERS FOR THE 6.72-INCH DIAMETER MACHINED T-111 A W Y INGOT (111-D-1765)*

~~ ~~ ~~

Machined Ingot Size - 6.72-inch d i a m e t e r

Can Size - 7-1/4-inch OD x 1/4-inch th i ck wall Type 304 SS seamless pipe with a molybdenum f o i l l i n e r , a 2-inch th i ck Type 304 SS nose block and a l/2-inch thick Type 304 SS back-up block contained within the can.

Leader Block/Follow-up Block - 7-1/16-inch diameter x 6-inch long mild s t e e l

Container S ize - 7.51-inch I D

D i e Size/Design - 4.5-inch ID/conical

D i e Coating - None

Extrusion Ratio - 2.7/1

Lubricant - Hot d i e grease s i m i l a r t o Fiske 604

Furnace Temperature/Soak T i m e i n Salt Bath - 2200°F/2 hours

Extrusion Pressure (Hydraulic) - 1,800 psi peak 1,500 ps i runout

M a x i m u m Allowable Pressure - 3,850 ps i

Cooling Procedure - A i r cooled

Extrusion Direction of Ingot - Top of ingot was extruded through d i e f i r s t with hot top removed.

~

* Extruded a t Canton Drop Forging Company, Canton, Ohio, on June 14, 1966.

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~~

.

TABLE 1J.I. CHEMICAL ANALYSES OF Mo-TZC A W Y (HEAT NO. TZC-4431) PRODUCED BY CLIMAX MOLYBDENUM COMPANY

Material Sample Location

Ingot Top - center Top - mid-radius Top - edge Bottom - center

2-inch diameter Cross sec t ion rod

1-inch diameter Cross sec t ion rod

0.13 1.21 0.18 0.13 1.20 0.14 0.13 1.21 0.21 0.13 1.19 0.15

0.13 4 (1 2

0.13 4 <1 <1

~~

(a) Combustion analysis .

(b) X-ray fluorescence analysis .

(‘1 Vacuum fusion analysis .

-11-

' 8 II 1 1 8 1 8 I I 8 8 8 8 1 1 I 1 8

".4 m m w w

w o c u m

cum m w 0 0 0 0 . .

m c u lno m m . .

m m m c u d m . .

O d m m 0 0 r (d

. .

w o w w d d d d

. .

k m Q I c,d e,=

d I P a 2 : $2 E:-. d & I c e d P

k O h w o

-12-

c, e, m 'H ec 0 se (0

0

0 * a 7 E: d k \ d 2 -d \ d 0 c: d

Lo 0 0

0

ec 0 e, c, cd k

E: d

E * al me, r : k d 7 m * 3 0

cd P k

d o

e,E: + d CUE! a \ G

m

2 % E *

!!? s: G d d c, k O e , m a 0 0 . k O a r: e,@ d G m c:a e,E: B a

d +

n P W

P e, d d a a cd m c a cd 0 d

a k 0 w al P Fr 0 0 dl @a c, Ld k I

0

+ +I d d G cd k 0 w P d e, G e, k : m r: d 0 e, a m e, k I c, a 3 k I m m e, k * m

n 0 v

TABLE V. EXTRUSION PARAMETERS FOR THE 5.36-INCH DIMTER MACHINED Cb-132M ALLOY INGOT(1)

Machined Ingot Size - 5.36-inch diameter x 10.16 inch long

Can Size - 5.95-inch diameter molybdenum

Follow-up Block - Two one-inch thick carbon discs heated to 2000°F followed by one carbon disc at room temperature.

Container Size - 6-inch ID

Die Size/Design - 3.75-inch ID/conical

z*2 Die Coating - Extrusion Ratio - 2.56/1

Lubricant - Glass

Ingot Temperature(b) - 3120OF

Extrusion Pressure - 76,000 psi peak on stem

Extrusion Press Size - 2,750 tons

Cooling Procedure - Air

~ ~~ ~~ ~- ~~ - -

(a) Extruded at DuPont on April 25, 1966.

(b) Heated by induction in argon.

-13-

extrusion parameters f o r both b i l l e t s are presented i n Table V I .

two extrusions were performed by N u c l e a r Metals,, West Concord, Massachusetts,

on June 3, 1966. The second b i l l e t length w a s then s t ress - re l ieved a t 2300°F

f o r one hour i n vacuum, machined, recanned i n molybdenum, and extruded by

Nuclear Metals on July 15, 1966, a t 2400'F through a 1.75-inch diameter die.

The extrusion parameters are presented i n Table VII.

progress.

The l a t t e r

Decanning i s now i n

B. ALI(ALI METAL PURIFICATION AND HANDLING

The bakeout oven f o r t he high-vacuum s y s t e m on the l i th ium dol ly w a s

received, insulated, and w i r e d f o r use. A l l t he drawings f o r the Alkali

Metal Pur i f i ca t ion and Handling System f o r Corrosion Loop I (T-111) have

been issued.

The sodium and potassium t ransfer sys t em used f o r t h e Prototype Corro-

s ion Loop(') w a s inspected t o determine the extent of the modification re-

quired t o prepare i t f o r use i n loading and sampling the l i thium and potas-

sium f o r Corrosion Loop I (T-111). The only required modification of t h e

potassium system w i l l be the i n s t a l l a t i o n of a l eve l probe w e l l i n t h e

charge pot. Modifications of the sodium t r ans fe r system t o handle l i thium

w i l l be more extensive. A l l components which were i n contact with sodium

w i l l be scrupulously cleaned o r replaced w i t h new components p r io r t o re-

assembly, with the exception of the disposal tank. The disposal tank is merely

a container f o r co l l ec t ing used a l k a l i metal for subsequent disposal . Sodium

from the Prototype Loop T e s t w i l l be drained from t h i s tank p r i o r t o re-use.

The ana lys i s of the metall ic impurit ies i n t h e 29-pound batch of hot

trapped l i thium w a s received and i s shown i n Table V I I I . This material w a s

also analyzed f o r oxygen by General Atomic, San Diego, Cal i forn ia , using

the f a s t neutron ac t iva t ion technique. The r e s u l t s w e r e 106 + 16 and 123

+ 13 ppm oxygen. The ni t rogen concentration, reported previously(2), w a s -

- (10 ppm.

Fabricat ion of t h e l i thium still i s i n progress. The l i thium s t i l l

receiver s h e l l has been ro l l ed and welded. Necessary s t a i n l e s s steel

components f o r the s t i l l pot and condenser a r e being machined. The Cb-1Zr

-14-

I . II 11 I 8 I I

TABLE V I . EXTRUSION PAR4METERS FOR TtlE 3.75-INCH DIAMETER m m ~ m cb-132~ ALLOY BILLETS(^)

~~~ ~

Machined Billets Sizes - B i l l e t No. l(b) - 3.75-inch diameter x 12-inch long

Billet No, 2(c) - 3.75-inch diameter x 10-inch long

Can S ize - 3.95-inch diameter molybdenum

Leader Block - Mild steel heated to 1500°F

Container Size - 4.05-inch I D

D i e Size/Design - 2.625-inch ID/conical

zro2 D i e Coating -

Extrusion Ratio - 2.4/1

Lubricant - Glass

B i l l e t Temperature(d) - B i l l e t No. 1 - 2400°F B i l l e t No. 2 - 2900°F

Extrusion Pressure - B i l l e t No. 1 - 750-690 tons runout

B i l l e t No. 2 - 510-370 tons runout


Cooling Procedure - A i r

(a) Extruded a t Nuclear Metals, W e s t Concord, Mass., on June 3, 1966.

B i l l e t No. 1 w i l l be used t o make the 2-inch diameter bar.

(c) B i l l e t No. 2 w i l l be used t o make the 1-inch diameter bar.

(dl Heated by induction i n argon.

-15-

~1 I 1 ‘ I 8 ‘1 ‘ I 8 8

I t 8 8 I ‘I

8 1

‘ I

m

TABLE VI1 . EXTRUSION PARAMETERS FOR THE 2 .O-INCH DIAMETER MGCHINED Cb-132M ALLOY BILLET(a)

Machined Billet Size - 2.0-inch diameter x 12-inch long

Can Size - 3.95-inch diameter molybdenum

Leader Block - None

Follow-up Block - Mild steel heated to 900°F

Container Size - 4.05-inch ID

Die Size/Design - 1.75 ID/conical

Die Coating - Extrusion Ratio - 3.0/1

Lubricant - Glass

Billet Temperature(b) - 2400’F

Extrusion Pressure - 700 tons


Cooling Procedure - Air

z*z

(a) Extruded at Nuclear Metals, West Concord, Mass., on

(b) Induction heated in argon.

July 15, 1966.

-16-

i

TABLE VIII. SPECTROGRAPHIC ANALYSIS OF LITHIUM AFTER HOT TRAPPING FOR 126 HOURS AT 1500'F

E l e m e n t

Ag A1 B B e Ca Cb co C r cu F e K M g Mn Mo Na N i Pb S i Sn T i v Z r

C o n c e n t r a t i o n , ppm ( i n L i t h i u m )

<5

<50 c 5

<25 <5 <5

< 50 <5 <5 <5

< 25 < 25 <5 < 25

5

5

28 5

80 28

28

< 25

-17-

tubing for the l e v e l probe was received and accepted.

thermocouple w e l l has not been received; however, i ts del ivery should not

delay fabrication of the s t i l l .

Cb-1Zr tubing for the

C. QUALITY ASSURANCE

A l l of the necessary spec i f icat ions have been prepared and submitted

to the NASA Program Manager for review.

dcsigz drmings have bee3 a p p m r e d by the XASA Program mnager.

A l l of the Corrosion Loop I (T- l l l )

-18-

IV. FUTUREPLANS

A,. Monitoring the fabrication of refractory a l loy materials for Corrosion

Loop I (T-111) w i l l continue with special emphasis placed on meeting

the new schedule.

B. Fabrication of the c r i t i c a l loop components w i l l be i n i t i a t e d upon

receipt of the refractory alloy m i l l products.

C. Fabrication of the Lithium Metal Purification and Handling System

for Corrosion Loop I (T-111) w i l l continue.

-19-

I I * I 8 ‘I I 8 8

I 1 8 I I I I I I II 8 1

REFERENCES

Potassium Corrosion T e s t Loop Development, Quarterly Progress Report No. 7 for Period Ending April 15, 1965, XASA Contract NAS 3-2547, NASA-CR- 54735, p 55.

(2) Advanced Refractory Alloy Corrosion Loop Program, Quarterly Progress Report No. 4 $or Period Ending Apr i l 15, 1966, XASA Contract iG.5 3-6474.

-20-

I .

8 1 I I

Quarterly Progress

Report No. 1 (NASA-CR-54477)




PUBLISHED REPORTS

October 15, 1965

January 15, 1966

April 15, 1966

-2 1-

For Quarter Ending

July 15, 1965

I 1 - 1 8

DISTRIBUTION LIST QUABlXRLY AM, FINAL -8 EEwBLT8

contract -4474

NASA Washington, D.C. 20546 Attention: Amin &ith (BNI)

NASA Washington, D.C. a0546 Attention: James J. Lynch

NASA Washington, D. C. 20546 Attention: George C. Deutsch (RR)

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NASA Lewis Research Center 21000 Brookpark Road Cleveland, Ohio 44135 Attention: Dr. Bernard Lubarsky (m), 118 500-201

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ASRPP-10

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Flight VehiclePower Branch Air Force Aero-Propulafon Lab Wright-Patters= Air Force -8, Ohio Attention: George E. Thompson,

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SNAP SO/SRIR Roject Office

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Attention: Librarian ' Washington, D.C. 20225

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American Machine and Foundry Company Alexandria Division 1025 North Royal Street Alexandria, Virginia Attention: Librarian

Aerojet-General Corporation P.O. Box 296 Azusa, California 91702 At tention: Librarian

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Avco Research and Advanced Development Department 201 Lowell Street Wilmingt on , bkssachuse tt s 01800 Attention: Librarian

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Battelle 505 King

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Columbus, Ohio 43201 Attention: Dr. E. M. SinnrOne

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I I T Research I n s t i t u t e 10 W e s t 35th S t r ee t Chicago, I l l i n o i s 60616 Attention: Librar ian

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Martin Marietta Corporation Metals Technology Laboratory Wheeling, I l l i n o i s

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Union Carbide Nuclear Company P.O. Box x Oak Ridge, Tennessee 37831 Attent ion: X-10 Laboratory,

Records Department (2)

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Mr, W. H. Podolny United Ai rc ra f t Corporation Pratt & Whitney Division 400 W. Main S t r e e t Hartford, Connecticut 06108

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Union Carbide Corporation Parma Research Center P.O. Box 6115 Cleveland, Ohio 44101 Attention: Technical Information Services

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Westinghouse Electric Corporation Astronuclear Laboratory P.O. Box 10864 Pittsburgh, Pennsylvania 15236 Attention: Librarian

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Wyman-Gordon Company North Grafton, Massachusetts Attention: Librarian

Grumman Aircraft Bethpage, New York Attention: Librarian

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Allison-General Motors Energy Conversion Division IndfanapoPis , Indiana Attention: Librarian

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North American Aviation, Inc. Atomics In te rna t iona l Division P.O. Box 309 Canoga Park, Cal i fornia 91304 Attention: Director, Liquid Metals Information Center

Douglas Aircraf t Company, Incorporated Missile and Space Systems Divis ion 3000 Ocean Pa rk Boulevard Santa Monica, Cal i fornia Attent ion: Librar ian

Climax Molybdenum Company of Michigan 1600 Huron Parkway Ann Arbor, Michigan 48105 A t t e n t ion: Librar ian

Climax Molybdenum Company of Michigan 1600 Huron Parkway Ann Arbor, Michigan 48105 Attent ion: Dr. M. Semchyshen

Fansteel Metallurgical Corporation North Chicago, I l l i n o i s A t t en t ion : Librar ian

National Research Corporation 405 Indus t r i a l Place Newton, Massachusetts Attention: Librar ian

Varian Associates Vacuum Products Division 611 Hansen Way Palo Alto, Cal i fornia Attent ion : Librar ian

Ultek Corporation 920 Commercial S t r ee t Palo A l t o , Cal i fornia Attention: Librar ian

TRW Inc. TRW Systems Group One Space Park Redondo Beach, Cal i fornia 90278 Attn:' D r . H. P. SSlverman

Sandia Corporation Aerospace Nuclear Safety D$vision Sandfa Base Albuquerque, New Mexico 87115 Attn: Mr. A. J . Clark (3)

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advanced refractory alloy corrosion loop

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