CONFIDENTIAL DEPARTMENT OF ENGINEERING RESJEARCH UNIVERSITY OF MICHIGAN ANN ARBOR STATUS OF VARIOUS INVESTTIGATION. IN:' PROGRESS FOR THE NATIONTAL ADVISORY.COMT TTEE. wOR AERONAUTICS AT T'-I UNIVERSITY';OF MICHIGAN Ap~rii 28, 1945 Approved by A. E. White Written by E. E. Reynolds J. W. Freeman Project Number M478-A April 28, 1945 CONFI DENT I AL

CONFIDENTIAL TABLE OF CONT iNTS Pare A. Evaluation of Properties of Alloys as Rotor Forgings............... *.. * * * * * 2 T. Sheet Al1oys at 1700~ and 1800~ F.............. 17 C. Rupture Tests:.t 1700) and- 1800~ F on M.I.T. Alloys ~.................................. 24 D. rLow Carbon N15,5 + Boron,......................... 27 F. Forged'ffodifications of 6059 and Low Carbon N1 ^ Allo yrs -at 13 0~ F..........................a.... * 30 F. Chromium Base Alloys at 1350~ F.................. 33 C. Effect of Heat Treatment and Processing on the Properties of Low Carbon N155............... 35 t. Investigations Completed......................... 38 I. Programs to be Completed........................ 39 CONFIDENTIAL

CONFIDENTIAL STATUS0 OF VARIOUS INVE'TIGAnIONS IN PROGRESS FOR THE NATIONAL ADVISORY COMMITTEE FOR AFRONAUTICS AT THE UNIVERSITY OF i4ICHIGAN April 28, 1945 Several related investi-ations are in progress at the Department of Engineering Research of the University of M4ichigan for the National Advisory Committee for Aeronautics under contract NAw 3781 covering a.eneral research program for the development of heat-resisting.alloys for aircraft power plants. In view of the lone tine recquired for the com:.pletion of the investigations a series o- "status" reports have been issued prior to meetings of thbe< Subcomnittee.. on HReat.-Res i. tien, Alloys, Committee on Polwer ~l.ants for Aircraft so that the members could be guided by partial results. The last'status" report was issued under date of Fb-:~, 194S. cSince thlat time two final reports have been issued. Report 17, "The Ruoture Test Characteristics of Six > 1re~ision Cast and Three Wrought Alloys at 1700~ and 1800~ F" April 3, 194.. IeQport 18, "A.eta.llurzical Investigation of a Large ),;7, Forged Disc of 234-A-5)Alloy" April 25, 19455.( <, The tstatus" reports are intended to be brief factual resentatior o.f oavrtiJ results. The data have not been checked asc in thle prpar tion o final reports. Likewise, further data from subsecuornt work ma, show that values and trends should be ^.r,~l1d. All statemenlts data and figures in this re-ort are tl^ re ore, tentntive and are sub Ject to chan e as more comp lete rPs uts beco-e avi l ab le. CONFIDENTIAL

CONFIDENTIAL 2. A. Evaluation of?ronerties of Alloy s Rotor _orings Samples of 19-9 DL, 234-A-5, Low Carbon N155, S590 and Timken Alloys are being subjected to room temperature tensile tests, tensile, rupture and creep tests at 1200~ and 1350~ F. The results obtained to date are summarized and compared in tables I, II and III. Descriptive information and rupture data for each disc are incluced as tables IV throuh XI and fi7ure 1 shows the stress-ruoture time curves. Briefly these data show the following trends: 1. Room Temperature Yield Strengths (See table I) 0.02-percent offset-yifeld strength of 70,000 psi or higher have been found only for the 1-40 forPing of Timken Alloy. The as-forged S590 disc and the' TC-1801 forging of Timken alloy had nearly as hith /ield strengths. At 1200~ and 1350~ F the as-forged S590 5isc h,.ad the best tensile oroperties.?.el!:tively little improvement in tensile oroperties resulted from increasingr the carbon and hot-cold. working 234-A-5 alloy discs. Tersile oroperties for cold-worked 19-9 DL and Low Carbon N155 discs are not yet available, althouch such processing would probably improve their oronerties in relation to the Timken alloy for ings. 2. Ru^pture Strengths at 1200~ F (See table II.) At 1200~ F the best runture strengths will be shown by the as-forged, disc NR66D of Low Carbon 7N15 alloy with the 2~590 disc about equally as good. T'e 1-40 for. ing of T imkn Alloy has quite -ood rupture strength, althouTh the T-1801 is considerhe.' R im o' for,.ing ha, been machined off. Specimnens are from metal midway between center and rim. CONFIDENTIAL

CONFIDENTIAL 3 The Low Carbon N155 discs, NR66E, made by Crucible Steel Company are considerably inferior to NP66D especially when aged for 24 hours at 1500~ F. The data thus ~far obtained do not show that high carbon content and hot-cold work appreciably improved the rupture strength of 234-A-5 alloy discs. The rupture strengths of 19-9 DL, Low Carbon N155 and S590 discs without hot-cold work compare favorably with those for the Timken Alloy discs. 3. Rupture Strengths at 1350~ F (See table II.) Solution-treated S590 discs have ti-e highest runture strengths and are considerably better than the as-forged disc. The as-forged disc NR66D of Low Carbon N155 alloy had nearly as food rupture properties, althou h the NTR66E discs were slightly weaker. 19-9 DL and 234-A-5 discs had considerably lower strenvtths. 4. Total Deformation Characteristics at 1200~ F (See table III.) The deformhtion characteristics vary for the various alloys and discs both with the stress and "the time at which comparisons are made. For instance the 1-40 forging of Timken Alloy will have much poorer creen characteristics than the TG-180 forging even thougih it had less total deformation up to 100 hours. This is caused by a much higher creep rate for the 1-40 specimens. Low Carbon N15' disc 1NR66E, solution treated and aged at 1350~ F, had much better properties than the other two NR66-E discs under 25,000 psi but was much inferior on the basis of 30,000 psi bh. en the yield strength had been exceeded. The Timken Alloy rotors apparently will have total deformtion characteristics similar to the as-forged 19-9 DL and 234-A-5 discs. A 1500~ F aging treatment increased deformation rates ~or Low C( rbon N1 5 NR6EF discs. The NP66D disc was considerably better than the NR66E discs. CONFIDENTIAL

CONFIDENTIAL 4 The as-forged S590 disc was similar to the Low Carbon N155 dic NR6.6D. The solution treated and aged S590 material disc was considerably weaker than the as-forged and probably the plain solution treated. Cold working 234-A-5 discs did not materially improve the total deformation strengths. COTTTriDTTT AL

CONFIDENTIAL T ABLE I TENSILE -PROPERTIES, OF LARGEi DISCS AT ROOM TEMPERATURE,1200 AND 1350~ p (Availble Daa for Radial Specimens aokr1%cnt;ji uf ial.~ 4 J- 4)sAvailable Dat <& m" 7~e.*^ ^ /..i, 1'1..::., K'"T ^ *' ~*?~w*~~~~~~^.Low U~&cw~~~~~t ^V ~~Carbon Alloy 2 99D 3 — 234-A- 234 A-5 N155- S590 S590, S590,/p7^. ~~~~~Low - HI gh High Disc N^/o (i) ~~~~~~~~Carb~onx Carbon Carbon NR66D No. 2 WO 1-^ NO l-I Size of disc diameter (in.),' 19 3/4 2'0.20 ~20 g1 1818 8 thickness (in,) 3 1/4 3 5/16 I31/2 3 1/2 3'1/4' 3 3/8 -3 3'Solution tre snt None None; 2100~F 2100~OF None Non* 23000~? 23QO~F'^r~~iV A.C. A, C t-o I.. W ____^c. _________, ~~~~~~~1400~?___F_ Hot-ftcold -workc As-. As- 10% 10%- after As- As- None None w^ Fo'rged Forged Out 0^O 24 hr at, Forged Forged ______________* __________.1400*F -Ageing treatment teTmperature(OF 1 1200 1200 1200 1200 1200 -40 None 10 time (hr) (^ 2 44 2 16 16:^ *'* ^ \ ^^ -3[ ' * Roo~~~~~~~~~~~~~~ ~ ~~ ~ ~ ~~~~ ~~~~~m~ ei e ature y /^ ** "i:Bftnell hardne-s~ 205 ~ 206 2,41 221 2-67 211.255* *Tensile., strengt "''','- /.; ^ (psi) (^m 103,~~~500 1 08,0 1550 117,500 1,500 13060-011,0 300 ^fOff set: yild'' *;.~<": a stres (ps ):"'.,:.'- * * <'O _0`02^ o4,0 37, 500 4500 46,500 5,0 69000 37*5005,0s ^~*::*:^1-Q-.1^;*-:-^*-*1^~-50-0 -52iya-D 50 -6,, 2QQ -68,0 0 9.Q0..53.O - -: 0.2^ roa^ 55,000 ~~~~~~57, 750 61000 66 50 72 50Q 10 0,0 (OQ --- **' roporti nal *".-,.; *.:*1. 1., - llT~~lt (pgl) WSO 26,500 22,500 ~~~22,500 30,9000 46000 37,500 22,500 — Elongatlon in0f 2 in. (^) ^*5 25.5 m~2 34-2 16,17 31.0 9*0 30<5 22.00 Reduction of ^ j &re9.^, ^0 ~~~2,4.6 37,2 16.3- 16.06 500 11.5 27.2 18.684 -arc; 5 5 r F -' O- I-* y' Tensile strengt. (psi 113< 57,875 52,000 58375 100 8,0 8787 82,0 Kre s (~Osj -^'^^.^-*i^1^"U 35,500 37.500.38,~500 38,000 47,0 62,504s0 0.2^^4w~& ~~~37,9900 40,000 41,000.41,00 4,0 7,000 44,00 Pjsonortional M ~O l~imlt (psi) ^^"^OL^OOO 16,250 1750 1,0 ^M 2250 20,000O'Il ngation in.A' 1. "" —, 11 - * 2 n, W. 4027.2 22621 165 12 Timken Timken iTG-180 I-40.1-2'62' -2^ - 8000 ll) 4+71500 jQ'- "y*^^^ */-7'a 23 ts 29*2 W-r 72^0 79, 0.00 51,000 61,000 56,500 6-3,500 15,000 37500' 30.16 Reducltion of 41ea 00^ 47.5 49.4 41019 35 336 21.3 17.7 ^ / ~~~~38,0 390059,7506,37 71,250 Of set y-ield' -(,.,-:*...:Storess (Si) 0.1^ 29,250 3^0032-0.37,.*500 48,0 41,00 ^^^^^^^^ ~ ~ ~ 2 3110 3,00 4000 5,0 41,000 ^ ^^^^^^^ 15,000 15,000 20,~~~~40000 1750 2,000 ^in,(^); 45.0~~3 49<0 24 31 11 Reutionaof i a3E~a~(^> 69.3 56. 24.8 45. 13.0 41.3 26,1 -See AICR 5C10 (reoort 1),.,..,^ ~ \' / j' ^*g~imhad -beenamnfitr off. Specimens taken. idway bewe enter and rila*i ^^S'*Alleghony Ludlum data*''* —3 l Icepoviect c\kTGo.A e-. Pt, t' CONFIDEWTIAL Z,-.'s 4-A- "'

Table IV Description of Low Carbon N155 Alloy Discs Chemical Composition Disc Feeat Number C Mn Si Cr Ni Co Mo W Cb Na. __.15 1.74.37 21.66 19.40 19.02 2.76 1.90 79.14 NR66E 1X2232.07 1.68.60 20.80 20.60 20.07 2.94 2.67 1.05.125 f.anufacturing Procedure 0) [ Disc NR66D was produced by the Universal-Cyclops Steel Corporation as a 20-inch diameti 3-5/16 inch thick forging finished at 1630~F, and stress relieved at 1200~F. for two Three discs were produced from Heat 1X2232 by the Crucible Steel Company. A 15-inch s< inrot was made from a one-ton induction furnace heat. A 9-inch square billet was coggC on a 7-ton hammer from the billet at 2100/2150~F. Three reheatings were required in ti operation. The billet was ground, pickled, chipped and cut into slugs weighing 225 poui slugs were reheated to 2100/2150~F. and upset to discs 14-3/4-inches in diameter X 4-3d thick on a 2800 pound hammer, the finishing temperatures being approximately 1500~F. Five representative conditions were rroduced by cutting the discs in half and subjectii them to the following treatments: As Forged: One-half of disc No. 1. As Forged + Aged at 1500~F: One half of disc No. I was heated to 1500~F. for 24 houI Solution Treated + Aged at 1500~F: Disc No. 2 was heated to 2200~F.. and quenched in One half was reheated to 1500~F. for 24 hours. Solution Treated + Aged at 1350~F: The other half of disc No. 2 was reheated to 1350 Solution Treated, "Hot-Cold" for 24 hours. Worked + Aced at 1500~F: Dioc No. 3 was left about 1/8-inch oversize in the setting operating, reheated to 2250~F. and water c After reheating to 1500~F. for 3 hours it was redu approximately 1/8 inch in thickness (approx. 3%, re the finishing temperature being about 200~F. The treatment was holding at 1500~F. for 24 hours. er hours. quare ed iAs ads. The /8-inches ag rs. water. )~F., upjuenched. iced 7duction), > final 0

Table V Description of 234-A-5 Alloy Discs Chemical Composition Disc Heat No. -... 1X2218 #5,#6 1X2280 o Processing Procedures o C Mn.25 4.14.42 4.47 Si Cr Ni Mo w Cb.25.41 18.32 5.76 1.46 18.06 5.20 1.30 1.51.95 1.20.28 I- j The disc from Heat 1X2218 was forged to a 20-inch diameter x 3-5/16-inches thick disc. The finishing temperature was 1400~F. and the finished disc was stress relieved at 1200~F. for 4 hours. Discs'!5 and #6 from Heat 1X2280 were made from a 15-inch square ingot. The ingot was hammer cogged on a 7-ton hammer to a 9-inch square billet. 290-lb. slugs from the billet were heated to 2150~F. and upset and rounded to a 20-inch diameter X 3-7/8-inch thick discsin one heat on a 7-ton hammer. The finishing temperatures were 1650~F. Disc #5 was air cooled from 2050/2100~F., heated to 1420~F. and "hot-cold" worked on a 7-ton hammer to 3-1/2-inches thick. The estimated finishing temperature was 1250~F. and the disc was stress relieved at 1200~F. for 4 hours. Disc #6 was heated to 2050/2100~F. and air cooled to 1400~F. and held 24 hours, air cooled. After reheating to 1420~F. it was "hot-cold" worked on a 7-ton hammer to 3-1/2-inches thick. The estimated finishing temperature was 1250~F. and the disc was stress relieved at 1200~F. for 4 hours. -v a

c~~- IA-) T=F........... S590 Alloy Discs Chemical Composition C Si Mn Cr Ni _ _.. - w Mo Cb Co P S, C, At 1 1I1 1 9.76 19.05 4.08 4.03 3.35 20.20.015.018 - *4H,). v* C' L qJ4. 1L C) S Manufacturing Procedure t.t tI ~-r 0 0 3 rrj I-tj (-4 acu h3 Po t> These discs were produced by the Allegheny-Ludlum Steel Corporation. 12-inch ingots were forged from 2250~F. to 9-inch square billets, air cooled and ground. The nine inch billets were upset forged from 2250~F. to rough 4-inch thick discs. Disc #1 - Reforged to 18-inch diameter 3-inch thick from 2250~F. #1l-A Solution treated at 2300~F. for 3-1/4 hours and water quenched #l-B Some of Disc 1'l was aged 16 hours at 1400~F. at Univ. of Mich. Disc #2 - Reforged from 2250~F. to 3-3/4-inch thick, cooled, then reforged in one heat to 18-inch diameter 3-3/8-inch thick (10%) from 2000~F. The disc was then aged for 16 hours at 1400~F. 0 *

D_-SCniP I9B,.TIMKEN ALLOY DISCS o Chrmicaal Composition Disc RHeat No,. C _Mn P S S i -Mi Cr o 1-40 F-4315 0.10 1.24 0.022 0.022 0.72 25.75 16.56 5..0 0.12 e I1-40 fl-4315 0.10 1.24 0.,022 0.022 0.72 25.75 16.56 5.80 0.12;r TGCT-180 1-4174 0.11 1.49 0.023 0.023 0.64 26.25 15.67 6.25 0.111 ^'oces-sin? Procedure Both dtscs were forged by M..idvale and are in the. s s-forged condition. The discs were machined to size at the Everett Plant of General.E:lectric. The 1-40 disc was. rejected for service and cult up for testing because of a slirht internal burst, as shown by x-rays, in the very center of the disc. The TG-180 disc was rejected for service after.x-ray examination because of a defective center. The section being tested was`Ncut so as to avoid Tmost of the defective center. This /sec. ion represents., ayproxi^te:r.(2 c'-ie and res ultI, rom mach ninf_/orff6 /'/h es /from -a 8 inch wheel. It does I.~reresent Va.ull section f nromn cnter tr, rim. 6,: Q/,,..-.,,z %.a (74 A. f. v ^ M t^ ^< C-) 0 0 M t4 H H H

CONFI DE. Nt P ILtL TABY-Jl' V1III RUPTUREl T5.:ST. CHARATRITICS OF LOW CARBON N].55 )ISCS8 (Radial specinimer' from center of discs at the rim) NR66D 860 -.1 "':; ~, 61. % 1 L~ R.' R v-,: - -. 62 "t'R 66 l <s:::t'iR66 w.. N R6 6 E.'..... 1'I6t....4 ti ~:~!, (- 6 ( I)}y*:l;.:,,? 6(:,E...:]. S~ze o-)f Discs Te sst ] I tu re J]!:lorngtlt ^ ^.. ^.,.,......_..,....,.^..^. ^. _.,.... ^ ^._...C[.!3t,~3~).[., t. = |l~tt nc^lles* f3li l jTemprerature J Strter.s.s T.inil.e, jin 1 int lw~~~~~~~~~~~~~~~~~~~~Tl bla.., > a'Ia~ 21 14 3/14 14 3/4 1.4 3/4'14 3/4, A14 3/4: 21] 1.4 3/4..1.4. 3/4 3 1/4 4/ 3/8 4 3/8 4 3/ 4 3/a As Forged + 2 hr at 1200~ F 3/8 4 As Forged As Forged +- 24 lir at 1.500" F 2200~ F W.Q. + 24 hr at 150()~ 2200~ F W.+Q - 24 hr at ].350~ 2250 ~ F W.Q. -, 3' hot-co e ld work at.1200~ F +-: 2/4 hr at 1500~ F As Forged +* 2 h-r at 1;00~- F A.s Forged 2200~ F W*Q. 4 24 tr at 1350~I 1200 1200 1200 1200 1200 1200 1350 1350 1350 77,000'72,000 55,000 50,000 45,000 40,000 55,000 47,500 45,o000 40,000 50, 000 45,000 40,000 37,500 50, 000 45,000 40,000 50,000 40,.000 35,000 48,000 45,000 40,000 52,000 A52pOOO 45,000 35,000 30,000 25,000 2 5,000 2 3,000 20,000 21, 500() 30,000 27, 500 25,000 23,000 1.07 2. 35 94. 204. 502 1461. 10.o 40. 178. 613 51.5 J14^3 o 237 o 504. 26.5 80. 205 11o 182. 1536. 61. 139. 228. 1.05 3~.186. I 432. 738 5 1.734.s 1.336. 3:1 /4 4 3/8 4 3/8 i 9 26 12 10'1 1.2 7 10 8 15 35 36 31 19 15 15 20,on Reduc tLion o 16.0 21.8 10.9 9.7 8.5 16.7 1';,'. 8A 18.9 17 8 43.7 4io8 24.5 21.7 20.0 22 3 24.5 1702 15.6 18.9 23 o9 27.7 *f?, 0' 7 231 0 7 24.5 33:.0 16. 7* 33.) ].]..- 5.159. 91 6.2 6.0 2 6 a olff 3o. 8 3(0. *9 45.6 30.8 -I i4- *:JE 1.4.4 iol.lrs 13 10 12 23 20 7 29 12 23 9 10 7 5 5 f 60. 239. 624 96,..60 392 In pr (w 35 34 25 I 24 9 30 i ogMress48 336,.:2..t-.... -,:.I-. _. I.O... -............................. N) CONFIX"t';E.NYTIAL.,

TABLE IX RUPTURE- TlST CULARACTTPIrnICS OF 234-A-5 ALLOY DISCS AT 1200~F. (Fadial Specimens from Center of Disc at Rim)'St c~~~~ize of Disc l " —-~Rupture E1 -memtion _wizfnches) ofIDsC Stress Time in 2 in. Disc mDTaeter Thickness... eat Treatment. (gsl) hr) h(percent_ Low Carbon- 20 3 5/16 As Forged + 4 hr at 1200~ F - 48,000 1.09 28 45,000 5.0 31 35,000 127. 32, I 302,500 196.5 19 30,000 974. 18!; t 28,500 1596. 13; I wih 1 20 I 3 1/2 1 2100~ F, A.C. + hot-cold 40,000 41 34 Carbon I worked approximately 10% 35,000 252 20 -5. from 14200 to 12500 F + 32,000 495 13 I!1 4 hr at 1200~ F,iqh, 20 3 1/2! Air cooled to 1400~ F from 1 43,0001 83 17 Carbon, 2100~ F and held 24 hr + 41~,000 90.5 24 r/6! J aprroximately 10/ hot-cold 40,000 534. 15 j $ ~ work from 1400~ to 1250~ F 38,000 180 18 _____ i _ _+ 4 hr at 1200~ F i 34,000 In progress 24 hr ~ 1See report number 18. P'Redction of area (oercent) 41.8 46.5 4*.3 33.0 51.5 35.6 30.8 25.6 46.5 30.8 29.8 6-28-45,,,, H wj

RUPTURE TEST CGARACT IGT_ OF S590 DISCS (~....-............. Ctadinrl- Pi ~-ll'.......'rfrf:P~ Dt RlLr~) e1 -ec; - - - x -.- - L I., -r- - - ---- - ---- --! l Si zeF ~ D | ITest Rupture Elongat Temperature Stress Time in 1 in D|sc D |"ameter. ickness,Heat Treatment.(~ F_) (psi) (hr) (erce ~' # W 1 3 | As Forged + 16 hr at 14+00~F 1200 55,000 69.5 21 y l 6 <->^ R |i c 50,000 150. 17!!1 c,1 45,000 372.5 9 Y-A -1-8- -" |3 3/4 hr at 2300~ F, W.Q. 1200 55,000 59 4 I i4EHY ces50,000 74 6 I1'tI54r,45,00049 3 | 11:B I ~.8r- ~ — & i. | 3 3/4 hr at 2300~ F, W.Q. 1200.50,000 153 I fJ? I R t |+ 16 hr at 1400~ F / 45,000 640 8 Y2 | 5 ^ 3 |~ As Forged + 16 hr at 1400~F 1350 30,000 60 12 fa- IO| clew f 1 25,000 180 8 4Y |20,000 676 6'1 A - y. c eR 3 3/4 hr at 2300~ F, W.Q. 1350 33,000 86 10 IqY T30,000252;a 11 I r 27 000|In progrcoo 40 |^qy I er. I 1 0-a...<..... |1/1B | 2-1 Y |.I ~ C3 3/4 hr at 2300~ F, W.Q. 1350 35,000 45.5 13 I, ^ <' |+ 16 hr at 1400~ F 30,000 ____ ______ _ ^ C_7 ion Reductic..9. of area nt) (percent 20.6 21.2 14.4 8.5'16.7 10.9 14.4 11.5 4.4 15.6 15.0:Ohr'.o 3 9. -10 — /1oLT A.; - 4'., Qt.I. //'/r I

CONFIDENTIAL 15 RUPTURE TEST MIMKEN ALLOY DISCS *w_ Stress Time in 1 in. of area Disc I @ at | (psi) (hr) (percent) (percent) 1TG-180 d 45,000 60 29 34 40,000o 155 26 27.2 I sr ^ 1 gS 135,000 424 22 26.7 I-40 A~ + * + 45,000 88 18 29.8 2Y ceL t 40,000 382 12 16.7'f. cf A ~ 37,500.7-4-2 9 | i$y crew: 35,000 n pogecs h _______r __..__._____ e..,_/16_6/7,Z lSnecimens taken midway between rim and center of disc. Cf 2R }. AAet" &t"'' 1LA-C aJ. A1 ft AJI CON'FIDENTIAL

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CONFIDFNTIAL 17 kb. "eet A!llos a't 17)0~ and 1?00~ F An evaluation of the rupture pronerties at 1700~ and 1S00~ F of several of the better high temperature alloys in sheet form is being carried out to obtain data for the evaluation of these alloys for use as liners in combustion chambers..u~+tr"A tests are in progress on eight alloys: Inconel,.F-1 (S5Cr-?OIiM-ei), V'itallium, S836, 309 (25 2N Co-Cr-2Ni, 10 (25Cr-20Ni), and 330 (15Cr-351i). As seen fronmtable XII and,Iriure 2, VitaIllium has t f ide rhanze of rupture strengths obta-ired for th-e alloys tested. Seven other alloys have been submitted and tests are to be conducted on five of these: N15, J837, J738, JY39, and J840. Chemical anCtlyses of all the alloys sucbitted are given in table XIII. All of the materials for which processing information have been received were in the hot rolled and annealed condition. (See tabie XIV.) The runture specirmens being tested are 22" byl-1/4" by 0.031" to 0.O40" in size with a 1n wide 2-3/4" long reduced gage section. The rupture test results obtained to date are given in t'ble tX and nlotted as stress-rupture time curves in figure 2. The rupture strengths were lower ttian was anticipated on th'e b'sis of the strenrths of similar alloys tested as round >ars. A stu dy of the- effect of heat treiatuent on the propertIes of Vitalliuin or Ifnconel Caloys is to be started as soon as th:e material is received. CONFIDENTIAL

CONFIDENTIAL 18 TABLE XII RUPTURE STRENGTHS OF SHEET ALLOYS AT 1700~ AND 1800~ F Stress (psi) for rupture at indicated' time oeriods Temperature 1700Q F' 1800 F Alloy (100 hr (1000 hr) (100 hr) (1000 hr) iVitallium 8000 3250 43800 | 2700 iCo-Cr-Ni 5400 3150 13200 (1) AF-18 A4800 3100 1 13600 (1) Q4 3 310 as25t l 3900 2300 I 816 13900 12000 4l 2300 309 i-) 3150 o l850 12000 1 1 Inconel 31500 100 12200 l350 330(15 Si 1 (1).. Data incomplete, CONFIDENTIAL

TABLE XIII CHEMICAL ANALYSCES OF SHEET ALLOYS H tr4 tl-l Alloy |Submitted by C Mn Si Cr Ni Co Mo W Cb B N2 Inconel General Electric 0.13 1 0.5 13 75 ---- --- AF-l1 n n.13 2. 25 20 —---. ---- - ---- ViAt-lliun. n.20 27 2.5 3al. 55 — S16 " n.35 18 20 45 4 3 309 n.12 25 12 —- - - Co-Cr-Ni Low 30 15 55 _. 310 Crucible.14 1.63 1.09 25.501 21.33 —- ---- 329.08.98.60 23.30 3.17 ----- 1.07 --- - 330 n.18 1.37.62 115.77 33.27. —-- -- -.- -- -- 446-N2.22.48.39 24.80 0.27 ---- -.1 N155.12 1.83.75 21.80 19.93 20.20 3.00 2.36 1.14 -.1 N155 Union Carbide.14 1.48.58 21.24 19.53 20.22 3.10 1.95 1.01 --.1 and Carbon J837.13 1.69.50 20.27 4.40'2082 4.35 4.56 --.34J838.11 146.51 20.30 14.90 21.14 4.35 4.43 ---.37J839 n.12 1.43.49 21.70 4.40 20.04 4.48 4.40 ---- 56.1; J840 n n.13 1.38.58 21.29 15.28 20.98 4.33 4.33 ----.45.1] _, 3 24 L7

CONFIDENTIAL 20 TABLE XIV PROCESSING INFORMATION FOR SHEET ALLOYS Alloy S Subtted by General Electri: AF-18 Alloy. S816 Alloy. Made by Alleqheny-Ludlum Steel Corporation. Hot rolled to 0.045" gage, furnace temperature 2100~F, annealed 2100-2150~F for six or eiPht minutes, air cooled, sand blasted and spot ground. Cold rolled to 0.033", annealed 2100-2150~F for six to eight minutes, air cooled, sand blasted and scrubbed, cold rolled one pass and buckled. Made by Allegheny-Ludlum Steel Corporation. Hot rolled to 0.035" gage, furnace temperature 2200-2250~F, returned to furnace and held five minutes at temperature, and air cooled. Sand blasted, scrubbed, two passes on cold rolls and buckled. Co-Cr-ti Alloy. Made by Haynes-Stellite Company, Rolling finished at 2100-2125~F. Annealed at 21752200~F Just long enough for the material to reach furnace temperature, air cooled. The manufacturing data for Inconel, 309, and Vitallium has not yet been submitted. Alloys Submitted by the Crucible Steel Compan'y: H eat Alloy Fumber 310 9R826 Induction melting. 9 X 9" 800-lb. ingot and 13 X 13" 1790-lb. ingot. Hot rolled to 0.031" (cross roll). Annealed 2050~F, air cooled, and pickled. 329 9R1187 Induction melting. 9 X 9" 770-lb. ingot and 13 X 13" 1770-1b. ingot, 14 X 4i" 400lb. bloom. Hot rolled to 0.031" (cross roll). Annealed 1850-1950~F, air cooled, and sand blasted. CONFIDENTIAL

CONITDIDENTI AL 21 TkBL, XIV P9OCESSING TINFORATION FOR SHEET ALLOYS (CONTINUED) {Teat Alloy Nuirer 330 R1 445 Induction mnltinp. 9 X 9" 780-lb. ingot and 13 " 13" 17(60-l ingot, 10 X 4" 30-l. bloome. ot role d to 0.3 1" (cross roll). Annealed 19503F, air cooled, and pickled. 446-412 P1077 N155 9R3 5 Induction mrelting. 10 X 18" 2520-lb ingot, 14 X 3" 273-lb bloom. Hot rolled to 0.031" (cross roll). Annealed 1600~F, water quenched, and sand blasted. Induction melting. 9 X 9" 840-lb ingot, 14 X 41" 300-lb bloom. Hot rolled to 0.031" (cross roll), annealed 1950"F, air cooled, and pickled. Alloys Submitted bjy Union Carbide annd Carbon Cornorration: Samrles 22" X 1l" 7 0.040" were fabricated from 30 lb. induction heats by forginq and rolling. The ingots were hot-forged, from 2100~F to a einishing tempera.ture near 1500~F, to sheet bars approximately 2" wide by 1" thick. These bars v':ere rolled, from 2000)F to a 7inishing temperature near 1400%F, to strips from which the 22" long samples were cut. After rolling the samoles were annealed in the range 2300-2100~F and air cooled. CONFIDENTI AI

CONFIDENTIAL TABLE XV PIRUPTURE TEST RESULTS AT 1700~ AND 1800~ F FOR SHEET ALLOYS i Reduction Temperature Stress -. Rut.re Time Elongation.of area Alloy (~ F) (psi) (hours) (%,'in 2 in.) (percent) Tnconel Inconel AF-18 1 1700 1800 1700! 1800: I'1700 t 12 000 o 4,000A 3,o0002,000 1,800',2'S - -''. 1,50C) 5,000: 4,0oo0.3 3.0uO.......:. A, 4 q L 0.20 45.5 118 177.5,_248. 31.5 18.5 27 19 35 18 21, 14 34 17.....KA_.Z_. ]&d&' _I.(J, --. - ~Y —__ _CIJPl~qLT~-~_J*~~ 1~4 ~ ~ - ~1 - - - - 1 0 -m p1 W~ 152.5 6,05 87^ L, m l 25 44 - a ib, rt -—. j,. r I6. _.c-.^^^jLL3L`ZI W —a a - 7;1 *-.. s"li~Vr F~~`i Or 3,500 3,000.-'.I TO "' I i i i I Vitallium Vr ta lIium S816' S816 309 309 Co-Cr,-Ni Co-Cr-Nil 310,,. W,.,,. ji o1o, 8,000 6,000 4,00 0.1'A I 11 *F - _ 1t_ -a- 5Z - - - - — W F - Jill,Ij;_ R _ _ E~~zw —e_'.W.A- t).'IO - 0- - - I 0 231 s ~~&~S -& -: fdi -. -. __ X - r~ rt - t-'11 - -, -A —.; -.. - r -. -11 _?3. -- 1 A,t`;,-45 $'! $',, ai**^'^~~~~~ wa<!^,-s,'w^^^t. — 4,I.-,tk.4':;-? - ~. 1.f - - v ~- Ir I 7t:. -,r. -,; r,,,.__,,,_,'Fit I - X,-<.@L,, 5,: -,< -,, A... 1 107 5907 f?9 -— ir,.-;R? -?,n t n-,; w - -'r: as- -s::...;;..:: -`'.=-: - 1." ~,.. 1 1:1800 "'. 1700....,._....;l. i.~O17QO. y.% r / O' 0Q. 0.:,ooo.'4,000.'3, 0-0; *;-.-2.... -; -:.... 6:5:75 472 /+7'.15.:23 Is" 19 11 13:.,~ ~,~~-:I l v - l.- i -s -. + _.. t -l-. —. - 1!I <.,:-'i 1- vi _.'.,:'.< -.,,._, 4....-,~r ~ 11~ If -:t> > 6 f- nl 3P 3800 1 —-. I 113 "'" 25-6. 5 t.%A, ll "~;. ~` 18-.- z> - -~i' ~, -,'Uru ~ ~;e~r* t,,, ~r% f I -:i: -i. ~- wz-)-~ lj 19. b A- J...t. 1 7..1,- - c --., c....,...... Z;;..;- d 14 u'k iA -.2"',: *.;.:-' S',. j^^ - ~ I:: 800 1700 1800 ci iCCIM-r1ZL i ~1 r'-Sj. ^t,.-^'t'i-^ -4 - s>;tS-^f.t,-i-w-i>f->.;_.r -,-Aa At 2,000 -": r,5...000:,000 2,500.1I 1 - 1700 1800 1700 -: 2,D02 1,500 5,000 4, 000 - <:: 3,00 3,000 I.. ~109 277* $s gl,. a r; W-;. $k < m.- \.w.. n:V, V_ _,YS.. _._.__:N rol@.so, lSts-e:,., __.,,,_ _ _,, 2't.5SrSef.wi6N f "' iS, -w s_ ftt ~ __^ s-K-. LA* S I r Cr -. Atm ~r....... ie: -r;zr~s-~w~s=Zvidos~byur-%r....................... v; 7 27 4 -: 21. 7 - It l!'I 52 333.5 132.5 285.5 285. —; — — ~.- _-~.17 46.5 s b Cs _ _ _ — _. w ~.-.:~..__~_..:.'..f~llll1Z 7 A 23 ^5 "^ 1. 1~i V;i.-"-;a.F=.;~cr2,,,, y? 2 1.T 3 4 2 (JF.... - li —,, 35-^: 27 11 17 I - 1'.;;'.3 5. 5.:"1..-...........''C 330' — I~~ ~~~~~~~~~.~.1 20 15:.. 10.......... -- r) 1700 4, UUu 2, 700: 2,000: I nrMoI' 1 n.A., 3I e i3, -5 2. I _.^~L~.~3~z;;r;~Cn- -9.1 At ^ ---- - -— A A * a & _ _Y"'""~:)u -—, L 8 - ^ ^^A^ _.\ America,,, ~ ~ ~ ~ ~ ~ ~ ~ a pb~ ~ CONFIDENTIAL'O'k- -'. -ff, mu.~~~~~~~~~~~~~~"' eT t,- In I... AS -St~a~"; B4 B

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U~T — I I A~P~Z~Q-rt~iTl~~ II 1..-li~ i;1;L 1 1 r -i ~ I,'-Ii "-~-~~t I 1 1 r,,,,.~f.. ., -i,,fltri j ir I;~ 5, f 5-( ~~^;-~~,-~r.c3;L uL1-L... 71' VI I T:T — -I I- -T -L , L.- -— t- J-d, q r37, -. i —:~-~: *J x 4 [. 4 -. n *- 4. 2 3 ~~~ ~~~~~4 5 6 78 to(0 3 4 5 6 7 8 9 tO TIME FOR RUPTURE, HOURS:-t:i t; ii:1 i,!1.1':I ti r f :? ~; Ii *; 4:;4 —^:4;Tt`E"-'F0 RUPTUR,'HOURS r-^'irr~-'~ a ]:^^ "ilp^tii_ fi"7nilttilll!1; 5 ~ 6 / 8~ 9- 10~ *2 3, 789-02 4 6 CO _______________ TIM FO RUPURE HOURS.i~~I, i I t 0 I.' -t - I - 4 p_ —* —-~ —---- FIGURE 2- STRESS-RUPTURE TIME CURVES AT 17000 AND 1800~ F _________________________________V ITALLIUM - 309Z Co-( FOR SHEET ALLOYS INCONEL, AF-18, S816:i-Ni. 310,AND 330. ___

CONFIDENTIAL 24 C. Rupture Tests at 17000 and 1800~ F on,.I.T. Alloys Rupture tests at short time periods were run since the last.proress report was issued. All of the data obtained to date are sum~rarized in table XVI and compared graphically in figure 3 with X40, the highest strength alloy previously tested at these tenmeratures(l)'. Alloy 97NT-2 gave very erratic results but on an nverage vwas somewhat stronger than alloy X-40. At 100 hours 7T-2 was equal to X-40 but at longer time periods was weaker. Samples of both alloys we-re submitted to Mr. Franks for chemical analyses. (1) Taken from report 17. CONFIDENTIAL

CONFIDENTIAL 25 TABLE XVI 1700~ AND 1800~ F RUPTURE PROPERTIES FOR TWO PRECISION CAST ALLOYS SUBMITTED BY M.I.T. Chemical Analyses (approximate, except carbon). ~ ~. Alloy C Cr Ni Co Mo w Ta 97NT-2 113VT2-2 128VT2-2 0.97 1.13 1.28 21 30 21 3 2.2 2 2 23 -- 67 6 Manufacture and Heat Treatment Both alloys were melted in a small arc furnace and cast by the Austenal procedure in molds preheated to 1850~ F at the Massachusetts Institute of Technology. The specimens were 0.250inch it diameter with 1-inch gage section. 113VT2-2 and 128VT2-2 were tested in the as cast condition. 97NT-2 specimens were heat treated at 2260~ F for 1/2-hour and water quenched. Runture Test Data at 1700~ and 1800~ F Temp. Stress Rupture Time Elongation Reduction Alloy F. L b./Sq.In. Hours in 1 In, of Area.% 97NT-2 1700 27,000 1.37 22 18.3 19,000 88.0 7 11.5 17,000 134.5 5 8.5 15,000 412.0 2 3.9 1800 21,000 1.38 20 34.0 15,000 48.5 8 12.1 14,000 61.0 3 7.1 13,000 490.0 3 4.7 11,000 329.5 4 10.9 113VT2-2 1700 24,000 6.0 20 18.0 17,000 108.0 1420.5 15,000 173.0 19 25.7 14,000 252.0 12 20.2 13,000 651.0 9 12.8 128VT2-2 1800 20,000 1.33 22 29.0 12,500 66.5 16 33.0 11,000 102.0 20 37.0 9,000 300.0 20 30.9 CONFIDENTIAL

~IlVllN]~GidNOD. *J, o009 1 GNV oOOL II lV' 0 7X A..0~l7 ZJ- AeZI` CINV En t z-iNL6 SAO~T~IV Ndoj s3AdJnD iii yndn', L 9 9 tr c T.I 6 8 L 9 9 t ~ 1 6 8 L 9 1 6 8 L 9 e CGNV j-SS3d~LS.3AllVH3VdNAO0 *c.3^ine Id C- t e z L 6 8 i1 9 9 t, c z I TI 6 8i 77 I.I. *I!::: I. L - T'V fight. i7l i -",L J; -4 I I m i. I:.. I - - I. — -... I I:....1 I I i. 4 4' 7 i. 11 — 4 i; ET, L *t'J*:^ l^,u:^;;^ I.'.: " *'-. ^:':.:l'^.;::-']': T:' -^;. *:.*'; _ |.. j.;^ -; |.*7F' 77, r-7.7 6 rArv-.-r - 7.- -'''' - v l.,-l I- - - I. -I.. I. - -,..I.7 I LI -, I I-, -- -1 " -,-. - -- +:.:.. --... t-.:. I,. - I. " TTm - I I tF ; ., I.. . . - ) I.. I. I! --- - I, -. -, — " J. I:..- -. " -,'i. . -. - --: - - I;. - -... I A.... I.. - I I I I I I 1. I... ^::~j:{' 4::-: *|::~,:: - J- ^f~~~~i s~~i!:^-'7 _mN'::I ^:^!!^ 0 i -4 4- -;.. -, _ -.: *-t ^-1.4 f i] I r l i *,,:; 4." -! "I I.z t—.7.:-, i I -I m-.!Ii Ii - i" "-?^J;^^;^^a;:-..^-H^~~~~~~~~~~~~~~~~~~~~~.47 I, li 3 T-r —7 T I T1. 4.1 —. — t. - - - I i. + -.-p ^.;.rt:.^U^:;;:^_I_ M r 7 —— ^ ^ l^:.: ";'. i::[:' r._:t-.;' * - ": ^ "-:': t,' {. " - - -'-. - -.'9 -L *8 *.6 11.;.; —.;, *' * i, I: I..I.;1.t -+-, -''' i:. -- I' l l, II —,I I: I I o! i.. I r., —., - 7-:7- I I 1, I. -- " r. I I.. -t.I I I " -;.;: I I I-i — - --- I.1!,i f i 1 i 1 -71 - - i -- —. -I I I,.,. - -; -, - i..- __I; Li. , I I t I I I: I I; I I I I -. I i:, t., i i f 1 1 1!..,, 4; I, i I I I " " 4,. f.Daniel 4l 4l li-4 I.... - \,:;,,;;; l,;W/Y\ t -'-t I-h- - 2t e -;-::- - 4 I I I.". o.'i.,. 1 t - i i-1.- -I. to:: - - 1: 1-:.-t - - -- ---- -. - = 1 i I I - t-,. i: f, -...-. I- - 1 - - i- - " I - -I-, I! I T; i F-I I _:. 7 - I -I.. I " II I-,, - I i -: I. I - 11-1 -,:,! 14. —,11., , I.1 i! " I I L4 t —4 TI j^^tfrt^"^"'^^-"""^^Itii'^^^i;^^^~~~~~~~~~~~~~~~~~~~~~~~~~-1 4z 7'Z4 -;t J-ibl T7,1 -7-T -7 ~;-'__:\:;.:^'i ^ ^ i:^^:.-"[':::'i^:L'.-: _;: _ __:_[:i'Tv._*it:' ^'i'^ 1'*^.L ^ ^^7:' _7 ~"~~^ ~ "^ ": ~'^r """"'T'~"'~*~ ""':^ r"*~"T ^7 7;: -.. —:.f?'-: r-v v^^ ^. ^ ^^lf]-^r-tn~~~~g^-^ ^^j —7;?-^^|~ 4 a^^^t~~fe~~t~il^^^^^7t. -1 I.1 I L: L 4 4 -77j. 1 -7 T 07 7,T I,..:^:_j-^juM.-^ ^~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~..... - Tt -"- ^;-f: - - — r.-^ - "-^ ~ - ~ -)^ -^ -j~~~~j E -q -~1 - [ ~ ^ "~: ~'^p l" " "t " ": ^ "^ Q O Q'C -777.T:.,.. -.- -- - I, - 4 1 I.- -11,- -. i - -. -1.1. j ..:.- 1- - I.- - , V., -t-, t -:-', U." -, — 1.:: -, -1 " r. I I.-,",..--.. -.:tt.'. - - -... I. "I, —- --- -- - I - -- - - j I I I -,, - o I:'.. 1- —,- - I i7. 4 -,'17 f - I: -.., -4 -,., - 1. I - - I..... I..I 1....., I I.... -. --, - L.' -: : t'''- "' - -- t-''7, - -- -: - -, -.1 -.f'' -. J, -1'".''"! -, I.- - ",',.. 1. f - - I 11 - I I.. . I,. I - I - I I I..,. I-,.. -; I I..: i-'' - i, :-, -, " — -- -7i. —. - 4'', ",_1 -, - - — t -'- - 7 1. I 6 8 i 9 S > g 2 I ~~~~~~1 6 8!::*: ~ ~ ~ 7 ^n ^,-" =:^ -r'T.7 I I ~ I 6 8 L' 9 L 6r ~ 1 8 9, f "IVI IN3'GUNO 00 T —--- --- I 6 e 1 6 v,

CONFIDENTIAL 27 D. Low Carbon N155 + Boron Three heats of Low Carbon N155 + Boron alloy have been rurture tested at 1200~ F, One heat, J597, had about the'iMhest runture strenpth yet found for any alloy. The other two heats were inferior to standard Low Carbon N155 alloy. (See table XVII and figure 4.) Rupture tests at 1350~ F on the high strength heat J597 gave 100- and l000-hour strengths of 40,000 and 30,000 psi which are exceptionally high. A satisfactory explanation of the difference in strength of the heats is not yet available. The excess constituents are more aggTomerated in heat J573 than in J597. Samoles of J593 were submitted to Mr, Franks for check chemical analysis. CONFIDENTIAL

CONFIDENT IAL I Table J Boron Modified Low Carbon N155 Alloy 28. Chemical Analyses Heat No. Cr Ni Co Mo W Si Mn B C N -u J573 21.00 20.04 20.88 3*08 2.17 0.45 1.65 0.37"0.20 0.14 J597 21.5 5 19 195 31 2.0 0.38 0.12 0.12 N175 — Analysis not submitted X Chec k COLaA- XAv-O -4C 0,589/0 TManufacture and Source Heat J573A iA as-forged condition. Machined 0.160" diameter specimensasubmitted by the Union Carbide and Carbon Research Laboratories, Inc. Heat J597^as-forged 0 mO d nd exerimental heat. Two 5-inch by 7/8-inch square bar, mitted b __ i-. C. -..O - for Project NRC-8...B the Union Carbide and Carbon Research Laboratories, Inc. Heat N175;:as-hot rolled m " ic -Pe-!!tetilgt-rla^- flnt-om iai'~ Xab=Qjcgg~ thammer cog ge Af om 2050~F. to 1750'F. toq2 ine square billet.% i illet olled from 2Q80~ F. to 1800~F.. S/8 inch s e One 8-inch by /8-inch square bar submltted Uniersal Cyclops Steel Corporation. X ^ A F ZfB/ ^7 t3<X t <Jr & < < l r *; 8 8 * ^ {19s l t s..........,r Q. rsn -,., ^ ^ _.,'r k Stress Rupture Time Lb,/SQ.In. Hours Specimen J573 J597 N17.5 Elongation Reduction % in 1 In. of Area. 60,000 55,000 50,000 44,000 65,000 60,000 55,000 60,000 5O,000 45,000 40.5 75.5 174.0 810.5 45.0 129.0 540.0 8.5 114.0 406.5 33 37 27 31 22 24 20 21 37.5 47 39.8 46.5 36.0 56.4 44.7 48.3 53.6 23.3 50.5 62.5 1350~F. Stress-Runture;Psult' J597 40,000 97.5 35,000 285.0 32,000 517.0 33 28 21 55.3 59.3 56.9 CONFIDENTIAL

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CONFIDENTIAL ^ Forked Modificatirons of (059 and Low-Carb n Ni Alloys act 13 0~ F These two wrought alloys were submitted by Mr. H. C. Cross of National Research Council Project 8 for testing at 1350~ F under the ACA program, The chemical analyses, alonp: with the analyses of normal heats of 6059 and Low Carbon N155, heat treatment, and 1350~ F rupture test results are riven in table *H-.: X — InComDlete rupture test resits, firure A indicate th —it these t/wo allo tiave irailar runture strengths. However, in the casel of the LSojCarb n N155 modification, the rupture strength aTpe~ars to' ae owc than t~hat tor normal Law Carboni condition / 1s;aan h,-e N155. No 1inforrmati.on is a l\'ialee for riormal 6059 in the wrought condition At 13500 F. It is, however, mch weaker than cast 6059. cond~~~~ "v'"',c's~t,96,... COr FIDI NTIAL

CONFIDENTIAL 31 TABLE XVIII 1350~ F STRESS-RUPTURE PROPERTIES OF IODIFICATIONS OF 6059 AND N155 ALLOYS Chemical Analyses: Alloy C Cr Ni Co tW _ _ _ _~ Mo Cb TNRt2 (Tod. 6059) 0.17 1Standard Cast 6059 0.46 24.5 32 32 2 26.17 35 35 - 3 1 6.4 - rT. n4 (rad. N155) 1Low Carbon N155 (Heat No. T1994) 0.14 21 0.10 20 25 25 1 2 20 20 4 1 3 1 Processing Procedure These two alloys were made from 100 nound basic induction furnace heats by the Union Carbide and Cprbon Company. Forcing was from 2100~ to 1400~ F from 3 inch square ingots to 1 inch square bars. Heat Treatment Both of the alloys were solution treated at 2200~F for 1 hour rnd water auenched followed by ageing 50 hours at 1350~ F. 1350~ F Runture Test Results Alloy Stress (psi) Rupture Time (hours) Elongation ( in 1 ln.) Reduc tion of Area (nercent ) IrT,2 (Mod. 6059),t. 4 ("o d. T! 5 5) 35,000 30,000 28,000 25,000 33,000 30,000 27,000 25,000 44.5 229.0 291.5 In progress 10 9 2hours, hours, 10.5 10.9,^. 12.5 4-'e-45 ^ 106.0 26 26.5 c% 196.5,33 39.0 338.0o I 30 34.2, Ift-Tmrori~ ~rp31V 4aQ ~ 3,4^ 45 " -1';ee T ACA ACR No. 4C22. 2nroke in gage mark. CO'F IDENTIAL

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CONFIDEINTIAL 33 F C hro^ium iln se.All ovs:.)t 1.)~ The National Research Council Project 8 has been investigAtinfr the nronerties at 1600~ F of cast chromium base alloys developed in connection with the Climax Molybdenum ComPany. Some of these alloys have shown excellent properties. At the last Subcoimnittee meeting it was decided that the properties of some of the best of these alloys be investigated at 1350~ F under the sponsorship of the NACA, A 60Cr-30Fe-10Mo alloy, specimen 608, fractured after 38 hours at 1350~ P under 50,000 psi. This life is about the same as that of 422-19 alloy, under this same stress. Alloy 422-19 shov.wed the highest rApture strength of any alloy previously tested at 1350~ F. (See NACA ACR 4C22.) A 60Cr-25Fe-157fo alloy has far better rupture strength. Orn sample, specimen 612-2, fractured after 484 hours under ~0,000 psi. This, particular alloy has phenominally hi!;h runture strength at 13.0~ F, since this compares with about 40 hours as the pest previous rupture time at this stress. Another specimen, 522, carried 45,000 psi for 450 hours before it was overheated through a controller failure. This time, however, was far in excess of the best previous rupture time of 175 hours for 422-19 alloy at 45,000 psi. CONFTDEJNTIAL

CONFIDENTIAL 34 TABLE XIX 1350~ F RUPTURE TEST RESULTS ON CHO-ROMIUMf BASE ALLOYS Rupture Elonga- ReducSrecimen Cherical Analyses__ Stress Time tion,5 tion of Number C Si Cr e Mo (psi) (hurs) in 1 in. Area, 608 0.03 0.14 61.96 29.14 8.73 50,000 38 40 35 612-2 0.01 0.13 58.86 25.11 15.89 50,000 484 9 9 522 0.05 60 25 15 45,000 Overheated after 450 hr. _________ __ ___ ____ ________________J__. Specimens prepared by melting and centrifugally casting under vacuum, then.grinding to a 0.1 lO-inch diameter gage section. J~~~~~~, -; CONFIDENTIAL

CONFIDENTIAL 35..... efct of ea aet Tr=trn. find. -`cv'esjing onf th e Prooerties ofr Low Carbon:.95':'. Lo vCarbon N155 alloy has been prepar,,a as bar ctock ir thirteen d r ffer t conditions as nrelim.inary vork in the study of the effect of rrocessing variables on the 1200~ F rupture nrooert!es of this alloy,. The chemical analysis and _manu,:facturi.rn nprocedure for the ori.inal hot rolled bar stock re r> iven in table XY. A large range in room temperature tensile properties wvas found for the -alloy in the thirteen different conditions. (See tablo XXI.) The most nronounced effect resulted from vari ation in amounts of hot-cold work. Reductions by rolling 10 percent.t 1200~ F produced yield strength in excess of 90,000 nsi, rith the as-forged bar stock responding the best. A reduction of 20 percent raised the yield strength to 120,000 psi. A reduction of 5 nercent Crave a yield strength of 67,000 psi. These vnl.ues show that the alloy is very responsive to hot-cold work, and tha.t reductions of about 15 percent would produce a yield strenrth in excess of 100,000 psi. AF soon as equipment is availab lermnure tests will e st:.'rted at 1200~ F. CO "TNFID'4TIAL

CONFIDENTIAL 36 TABLE XX HOT ROLLED LOW CARBON N155 BAR STOCK Chemical Analysis C Cr Ni C Mo s Wfl Si N2 S P 0.12 21.33 18.88 38.60 3.21 1.97 1.10 1.64 0.39003 0.026 Ta.nu. f ac ture The melt (TLot 30276) was prepared by the Union Carbide and C:rbide Research Laboratories, a 8" X 7" ingot weighing approximately (6100 pounds being produced. Hot working was done at Universal Cyclops Steel Corporation. This ingot was ha:mer cogged without difficulty to 2" square billets with?0500~F as maximum temperature and 17500F. as minimum. The 2" square billets were hot rolled to 7/8" square in one heat from 2075~F. to a finishing temperature of 1725~F. CONFIDENTIAL

CONFIETIAL TA BLti^ XXI ROOM TEMPERATURE TENSILE PROPERTIES OF L CAR ChBON N155 ALLOY (LOT 30 R feat Treatment J Hot-Cold Work j ield Solution, iolutionl Method Ageing!iAge ing, % Bftnell Ten sile Proportion —._. TemD. Time -of Temp* Time Temp. Redur' - ard- Strength al Limit 0,02f (OF.) R(ours) Cooling (~F.y |(EI8) (~F.) tion |nesf | si | -(ps) OfSet ot rolled ____ -2 | --- | -- 233 12 500 57,500 72,500 ____, — ____ ____ ---- t --- | 1200 10 (10.0) 312 V146 750' 70>0000 98,5001 ____ | ----; —?- | —, —| ---.^| 1200 20 323: 162, 500| 112 500 134,0001 WO50 1 2 W.Q. - --—: --- 208 11,500 27,500 QQ~ t 2050 1 2: 2 "W.Q. -- -- 1200 5 5 2 49 12,500 42,500 -67,000 I I. I I 1,; I.' 1 ( 4 v' 1 I:' - I I- " I 2050 2'W -- -- - 1200 10 301 138i750 52,500 + 90,000 (10.5) 2050 1 2 W.Q.| ---- l --- 1.1200 j 20: 01 34~ 154,500 85,000 121,0003 2050 I I II(2032) - 2050 2 W.Q.1 1400 24 -^ —. --- - 220 1 11,500 1 1,500 1:38,000 2050 2.Q. 1400 24 12001 10 1287 134000 65,000 90,000 I I I" 1.':. (10.6) -..':1 154p - 1 21 27900 1 W.Q. ------ - ~ ~~ --- --- - 205 115,750: 25,f000 1 42,000 2200 1 W.Q. -- -- 1200 10 0289 0136,50 75,00 90,000 (10.6) 2200 0 1 W.Q,1 14p001 24 t ~~ —-| ~ —-~ -. 221. 11 250} 25,1700 48000 22050 1 W.Q 1400 24 1200 10 288 136i,250 70,00 98,5003 ____________________ ____ __ ____ ~ ~~(I0^6)__ _ __ \ 1"^;___~ 37 1276) WITH IDICAT-D TREATMENTS I Streslses,(fgi -.. X. RFeductita 0~1% O 2 Elongation of area Of sfswty Offset-( in 2 in pe r,e.n t 76, 500 I 8.0 530 40.5 55.7.18,000 121,000 25.5 - 470.45-000 148,500 19.0 40.7 56,000 - 58,500 44.0 62.4 81,000; 84,000 35 5 54.7.07,500 |112 P 000 28.O 49. 2 L34p 000:3 8,000 23.5 49.5 53,000 58,500 36.0 41.6 lO-5, 000 109,000 23.5 37.9 53,000 { 57,000 46.5 64.3 L02 500 107,000 31*5 55.7 61,000 i (5,000 32,0 39.8.07,5 111,000 22.5 3,4. 7 CONFIDENTIAL

CONFIDENTIAL IT I i ti'at?'io Co-'""lo -d A renport is beinr, prepared on Low Carbon N155 disc in conjunction v ith'Mr. H. C. Cross for project NRC-8. The Iwork on the following three programas has been eor) leted and reports are being prerpared: a. S816 andn S590 bar stock at 1350~ F b. Vacuum M!el.ted Alloy c. Cerar.ic Conted 16-25-6 Alloy All of the data on these programs was included in the FThrury F, 1l94 nprogress report. CONFIDENTIAL

CONFIDENTTIAL 39 Additional work is to be done on the following progravns,.'lthoi h no data have been obtained since the last progress report as I. s que ad: a. 19-9 DL turbosupercharger discs at 1200~ and 1350o F. b. Typical 19-m9 DL bar' stock. c. Effect of processing and heat treatment on 19-9 DL. 234-A-5, Timken Alloy and Age-fIardena'b~ Inconel Alloys. CONFITDENTIAL