FOURTH PROGRESS REPORT TO MATERIALS LABORATORY, 'WRIGHT AIR DEVELOPMENT CENTER DEPARTMENT OF THE AIR FORCE ON FOUR LOW-ALLOY STEELS FOR ROTOR DISKS OF GAS TURBINES IN JET ENGINES By A. Zonder J. W. Freeman PROJECT NUMBER:. M903 AIR FORCE CONTRACT NUMBER: AF33 (038> -13h96 EXPENDITURE ORDER NUMBER: 6o5-227 SR-7 December 31, 1951

FOURTH PROGRESS REPORT ON FOUR LOW-ALLOY STEELS FOR ROTOR DISKS OF GAS TURBINES IN JET ENGINES SUMMARY This report is the Fourth Progress Report on an investigation being carried out for the Materials Laboratory, Wright Air Development Center, Department of the Air Force, under Air Force Contract Number: AF33(038)-13496 (Expenditure Order Number: 605-227 SR-7). A study of the high-temperature properties of four low-alloy steels, 4340, 17-22A(S), H-40, and C-422, in the form of forged J-33 jet engine disks is being carried outo A concurrent investigation of the high-temperature properties of the products of isothermal transformation is being made utilizing bar stocko The results of the structural studies are to be correlated with the results to be obtained from the diskso The study of the properties of the products of isothermal transformation as outlined in the First Progress Report is virtually completeo The results obtained indicate that the normalized and tempered structures of 17-22A(S), H-ho, and C-422 possess superior high-temperature properties at 1100~F as compared to any of the other structures developed to date0 (The criterion used for comparison was the stress to cause 1-percent total deformation in 1000 hourso) For 340O, the upper-bainitic structure proved to be superior to the normalized and tempered structure both at 1000~F and 1100~F.

2 The time-temperature-transformation curve for C-h22 steel has been outlined. All three H-hO disks (normalized, oil quenched, and interruptedquenched) and the normalized 17-22A(S) disk have been split and the center slabs cut out. These slabs have been magnafluxed and macroetched and found to be sound. Also, a hardness survey has been made on each slabo The C-h22 disks were re-heat treated by the Crucible Steel Company of America to eliminate the problem of hard spots encountered in the disks as originally heat treated. Room temperature tensile tests have been made on specimens cut from the center slabs of the oil-quenched and interrupted-quenched 4340 disks, each of the 17-22A(S) disks, and the oil-quenched H-hO disk, as outlined in the Third Progress Report. The initial sorting survey at 1100~F to establish the rim properties of each heat treated disk has been startedo Because of the results obtained to date, a modified testing program for the disks has been suggested and is shown in the Procedure and Proposed Testing Conditions below. INTRODUCTION This report covers the progress made between 1 October 1951 and 31 December 1951 on an investigation of the high-temperature properties of four ferritic alloys, 4h30, 17-22A(S), H-O40, and C-h22, in the form of forged rotor disks for gas turbines in jet engineso The objectives of this investigation are to determine the effect of heat treatment upon the high temperature properties of each of these four steels and to obtain design data for the heat treated disk showing the best properties.

3 As a further clarification of the effect of heat treatment upon the high-temperature properties of these steels, a concurrent study of the creep-rupture properties of the products of isothermal transformation is being carried out, utilizing bar stocko PROCEDURE AND PROPOSED TESTING CONDITIONS The high-temperature testing program for the disks as originally outlined was as follows: (a) Establish stress-rupture time and stress-time for 1-percent total deformation curves out to 1000 hours at 1100~F for every disk. (b) On the basis of results of (a), select the best disk of each alloy and: (1) Establish at each of three temperatures out to 1000 hours curves of stress-rupture time, start of third stage creep, and time for total deformations of 1, O, 0 02, and 0.1 percent, using specimens taken radially at the rim. (2) Survey by limited tests the variation in high-temperature properties of specimens taken tangentially at the rim and at the center of the disks. (3) Establish tensile properties at each elevated temperature. Because interest in ferritic disk materials seems to be mainly focused at 11000F for regular jet engine service and because of results obtained to date in this investigation, it is suggested that the testing program be modified as follows: (a) For 4340 steel, survey all three disks at 950~F, the highest temperature for which long time properties appear to remain high enough to be of interest. At 1100~F and 1200~F, establish

4 stress-rupture curves out to 100 hours for the heat-treated disk showing the best properties at 950~F. (b) For 17-22A(S), H-40, and C-h22, limit the design curves to 1100~F, the temperature of major interest at the moment. Using the heattreated disk of each alloy showing the best properties at 1100~F, establish curves of stress versus time for fracture and stress versus time for a total deformation of 1 percent out to 1000 hours at 1000~F, and a stress-rupture curve out to 100 hours at 12000F. RESULTS The results obtained to date are presented separately for each steel under (1) disk investigation and (2) investigation of the properties of the products of isothermal transformation. Disk Investigation 4340 STEEL The room temperature tensile properties at the centers of the oilquenched and interrupted-quenched disks have been determined and are presented in Table I. The interrupted-quenched specimens, which were about 20 Brinell points harder than the oil-quenched specimens, showed higher tensile strength and lower ductility as compared to the oil-quenched specimenso For specimens 2W-2Z taken directly from the center of the disks, the interrupted-quenched disk had an average tensile strength of 137,h00 psi as compared to 124,000 psi for the oil-quenched disk, and showed an average elongation of 12 percent as compared to 17 percent for the oil-quenched disko The 0s2 percent offset yield strengths averaged 96,000 psi for the oil-quenched specimens and 105,000 psi for the interrupted-quenched specimens.

The rupture properties for rim material of both disks are determined out to 200 hours at 1100~F and are shown in Table IV o The stresses to cause rupture in 100 hours were 18, 500 psi for the interrupted-quenched disk and 15,000 psi for the oil-quenched disko 17-22A(S) STEEL The center slab of the normalized and tempered disk was cut out, magnafluxed and macroetched, and found to be soundo A Brinell hardness survey was taken and is shown in figure 1o The slab had a Brinell hardness range of 235 to 330. The principal ranges were 235 to 270 at the center and 300 to 330 around the edgeso The low hardnesses at the center of the disk seem to indicate incomplete hardening upon normalizing. The room temperature tensile properties for all three disks are summarized in Table IIIo Results from specimens 2W-2Z, taken directly from the center of each disk, show that the interrupted-quenched disk was slightly harder than the oil-quenched disk and had slightly higher tensile properties and tended to have much lower ductility. The normalized disk, which was much softer at the center than either of the other two disks, had much lower tensile properties than either the oil-quenched or interrupted-quenched disks and slightly better ductility The survey of the high-temperature properties of the three 17-22A(S) disks is now in progress and the results obtained to date are shown in Table V and in figures 2-4o The rupture strengths and 1-percent total deformation strengths at 1100~F are as follows: 100 Hour 1000 Hour Stress to Cause 1% Total Disk Rupture Strength Rupture Strength Deformation in 1000 hours Number (psi) ( psi) (psi) 1 (No) 35,000 14,500 13,500 3 (OoQo) 39,9500 18,500 l8,250 4 (IoQo) 400OOO 21,500 20,500

6 H-4O STEEL The center slabs have been cut from all three H-hO disks. All the slabs have been magnafluxed and macroetched and found to be sound. Brinell hardness surveys have been taken on all three slabs and are shown in figures 5-7. All three disks are harder than the specified hardness range of 280-320 Brinell and the oil-quenched disk showed one very hard area of 365-390 Brinello The variation in hardness tended to be erratic rather than localized at specific locations in the diskso The Brinell hardness ranges for the disks were as follows: (1) Normalized + tempered, 315-380 (2) Oil quenched + tempered, 315-390 (3) Interrupted quenched + tempered, 327-393 The room temperature tensile properties of the oil-quenched disk are shown in Table IIo The average hardness for the test specimens was 357 Brinell, the average tensile strength 177,000 psi, and the 0.2-percent offset yield strength 162,000 psi. The elongation at the rim averaged 10 percent and at the center 4h5 percent. The survey of the high-temperature properties of the three H-hO disks is now in progress and the results obtained to date are shown in Table VIo These data indicate that all three disks are brittle, showing low elongation at fracture in the rupture tests. C-2 2 STEEL The C-422 disks were re-heat treated by the Crucible Steel Company of America to eliminate the problem of hard spots encountered in the disks as originally heat treated. The original heat treatments and those carried out by the Crucible Company are as follows:

7 (a) Original Heat Treatment Disk #1. No 1900~F + tempered at 12000F. Disk #3o As forged. Disk #h4 O.Q, from 1900~F + tempered at 1200~F. (b) Crucible Company Heat Treatment Disk #1. Full annealed at 1600~F for 6 hours and furnace cooled. No 19000F + double temper at 1200~F for 2 plus 2 hours. Disk #3. Full annealed at 1600~F for 6 hours and furnace cooledo Disk #4. Full annealed at 1600~F for 6 hours and furnace cooledo O.Q. from 1900~F + double temper at 1200 F for 2 + 2 hours. The survey of the high-temperature properties of the normalized and tempered C-422 disk is now in progress and the results obtained to date are shown in Table VIIo Investigation of the Properties of the Products of Isothermal Transformation 43ho STEEL All creep testing of isothermal structures as outlined in the First Progress Report has been completedo Creep data obtained in addition to that shown in Table I of the Third Progress Report is shown in Table VIII. Using the stress to cause 1-percent total deformation in 1000 hours as a basis for comparison, the normalized and tempered structure was superior at both 1000~F and 1100~F to all structures developed except the upper bainitic structure. The stress to cause 1-percent total deformation in 1000 hours at 1000~F was 13,300 psi for the normalized and tempered structure, and 17,300 psi for the upper bainitic structure

8 17-22A(S) STEEL All creep testing of isothermal structures as outlined in the First Progress Report has been completed at 1100~F except for one test now in progress on the upper bainitic structure. Creep data obtained in addition to that shown in Table II of the Third Progress Report is shown in Table VIIIT The results obtained to date from creep-rupture tests at 1100~F are as follows: Stress to Cause 1% Total Deformation in 1000 Hours Structure BHN (psi) Norm. + To 10 Hrso at 1200~F 291/317 19,000 OoQo + T. 1 Hro at 1300~F 302/306 15,000 Austo 1750~F + 1~ Hrso at 1350~F 309/313 16,000 Aust. 1750~F + 10 Hrs. at 1150~F + T. 12 Hrs. at 1200~F 291/313 less than 15,000 Aust. 1750~F + 2 Hrso at 900~F + T. 16 Hrs. at 1200~F 317/327 approximately 16,000 Austo 1750~F + 5 Min. at 700~F + To 12 Hrs. 302/303 15500 Using the stress to cause 1-percent total deformation in 1000 hours as a basis of comparison, it can be seen from the above data that the normalized and tempered structure is superior to any of the other structures developed. H-40 STEEL The isothermal transformation data for the H-4O steel has been re-examined and corrected and the time-temperature curve has been redrawn and is shown in figure 8. This diagram shows that the only isothermal structure which can be developed is a bainitic structure between 700~F and 800~Fo All creep testing at 1100~F has been completed except for one test now in progress on the bainitic structure. Creep data obtained in addition to that shown in Table III of the Third Progress Report is shown in Table VIII.

9 The results obtained to date are as follows: Stress to Cause 1% Total Deformation in 1000 Hours Structure BHN (psi) Normo + To 18 HrSo at 1200~F 312/320 27-800 OoQ. + T. 12 Hrso at 1200~F 321/323 23,300 Austo 1950~F + 10 Hrso at 750~F + To 1 Hro at 1300~F (Bainite) 308/312 approximately 23,000 C-422 STEEL The time-temperature-transformation curve has been outlined and is shown in figure 9o The only signs of austenite transformation appear above 1100~Fo Holding above 1100~F out to time periods of 24 hours results first in the appearance of a dark etching material in the grain boundaries, similar to that which was obtained with the H-40 steel. Holding for the longer time periods also produced throughout the matrix what appeared to be carbide particleso Creep testing of the normalized and tempered and oil-quenched and tempered structures at 1100~F has been completedo The results obtained are as follows: Stress to Cause 1% Total Deformation in 1000 Hours Structure BHN (psi) Norm. + To 24 Hrso at 1200~F 299/306 28,700 OoQo + To 4 Hrso at 1200~F 307 30,000 Creep data obtained in addition to that shown in Table III of the Third Progress Report is shown in Table VIII. FUTURE WORK Early in the next period, the initial survey tests on the disks will be completed. The data should then be analyzed and a choice made of the disks

10 to be used for design datao In this connection, attention is directed to the extreme brittleness of all three H-h0 disks in the rupture test with the probable conclusion that all three are unsuitable for use at 1100~Fo Likewise the initial surveys of isothermally-treated specimens is nearing completion, requiring analysis of the data and decision as to future work. In view of the tests on disks it appears that the isothermal transformation survey ought to be extended to include rupture tests as well as total deformation characteristics. A correlative study of the microstructures of the disks and isothermally transformed structures of bar stock should be carried out.

TABLE I ROOM TEMPERATURE TENSILE PROPERTIES AT THE CENTER OF THE 14340 DISKS Disk #3 - Heat Treatment: First treatment - Second treatment - Yield Strergths (psi) 0.1% 0.2% O.Q. from 1750~F + 8 Hrs. at 1200~F O.Q. from 1550oF + tempered at 1050~F Specimen Number 1W 1X lx 2W 2X 2Y 2Z 1W IX 2W 2X 2Y 2Z Specimen Location (a) SRR CRR SRC CRC CRC SRC Disk #4 SRR CRR SRC CRC CRC SRC Tensile Offset Strength (psi) 0.02% 136,500 112,500 129,000 106,900 125, 00 96,700 123,800 91,700 122,800 89,800 123,800 92, 500 - Heat Treatment: 141,200 90,600 140,9200 87,000 137,900 79,000 137,800 86,300 137,800 91,200 Pi 115,800 116,000 109,200 110,700 98,700 99,200 94,700 95,200 94,100 94,600 95,800 96,200 Interrupted-quenched 104,700 109,200 101,200 106,300 97,400 103,700 99,500 105,300 102,300 106,600 roportional Limit (psi) 73,000 78,000 79,000 82,000 74,500 74,500 from 1750~F 64,500 63,000 47,000 65,000 68,000 60,500 Elongation Reduction in 2 in. of Area (%) (%) 18.5 62.2 17.0 58.3 15.5 39,2 17.0 44.6 18.0 48.6 18.5 4707 + 2 Hrs. at 1200~F 17.0 49.5 17.0 48o8 11o0 23.4 12.0 29.8 14.0 26.1 12.0 31.7 Brinell Hardness 280 273 260 255 255 260 288 289 290 292 286 287 136, 200 85,700 98,600 103,300 --- — I -I - - (a) SRR CRR SRC CRC Surface plane radial specimen near rim of disk Center plane radial specimen near rim of disk Surface plane radial specimen at center of disk Center plane radial specimen at center of disk

TABLE II ROOM TEMPERATURE PROPERTIES AT THE CENTER OF THE OIL-QUENCHED H-hO DISK Disk #3 - Heat Treatment: Specimen Number 1W IX 2W 2X 2Y 2Z Specimen *Location (a) SRR CRR SRC CRC CRC SRC Tensile Strength (psi) 182,000 183,500 175,200 172,500 177,000 178,800 Offset 0.02% 139,200 137,000 131,000 124,000 125,500 127,800 First treatment - OoQ. from 1950~F + 8 Hrs. at 1200~F Second treatment - Retempered at 1200~F Yield Strengths Proportional Elongation Reduction (psi) Limit in 2 in. of Area 0.1% 0.2% (psi) (%) (%) 160,700 166,000 113,000 9.5 23.5 158,500 164,200 108,000 10.0 23.7 155,700 163,800 10l4,000 2.0 2.8 150,200 159,700 95,000 2.0 2.8 150,800 159,400 96,000 5.0 7.8 150,400 159,800 99,000 8.5 16.0 Brinell Hardness 36h 36h 362 365 3h6 3h1 (a) SRR CRR SRC CRC Surface plane radial specimen near rim of disk Center plane radial specimen near rim of disk Surface plane radial specimen at center of disk Center plane radial specimen at center of disk

TABLE III ROOM TERATURE TENSILE PRPERTIES AT THE CENTER OF THE 17-?2A(S) DIS Disk #1 - Heat Treatmient: N. 1750~F + 2 Ers. at 1200~F Specimen Specimen NmLber Loeain _ I Ad 1X 2ff 2X 2Y 2Z 1W 1X 2w 2X,2Y 2Z lX 2W' 2X 2? 2Z 'SRR CRR 81C:CRC CRC tsDc St. CRRM m. - CRG Disk #4 SRR CRR SWG CRC CRC SWG Tensile Offset Yield Str Strength b )(psi (p i) 0.02% 0~1X i42,800 96,00 1095,o 4 137, 200 98,200 107,000 117,000 71,8t)0 79,400 116,000 73,14O0 78, 500 117,000 73,600 77,200 119,000 7,000 79,600 Disk #3 -Heat Treatment: 15,900 123,000 132,200 145,000 123,h100 130,500 144,800 121,800 126,UOO 1i5,000 120,600 126,200 rengths 0.2% 114,70C 111,300 81 WO 79,80C 79,20C 81,70C 0 Q. fro 133s80C 132, 800 128,30C 128,20 128,0O 129,00C Proportiona Limit (psi) ) 76,500 ) 89,010 ) 47,00(? ) 66,000 ) 62,500 ) 61,000 ml 1750~F + ) 93,00 ) 94,000 ) 109,500? 1031,000 ) 99,500 h 106X300.l Elongation RE in 2 in. c - (% _ 15.0 14.5 9.0 15.5 20.5 19.0 8 Hrs. at 1200~F 18.0 16.5 11.0 12.0 17.5 15.0 '50 ~F + 2 Hrs. at 16.0 16.5 5.0 8.0 15.0 15.5 eduction of Area 50.3 1U7.1 13.4 38.5 48.9 48.0 56.L 50.9 23.8 29.2 46.6 h0.7 1200 ~ 51.1 k9.8 6,4 9.3 U1.0 4U.9 Brinell Hardness 314 282 242 238 238 241 326 313 313 311 295 294 332 321 320 317 318 312 I i15,ooo 1i5,8oo 119,000 12551w 121,000 126, 7OO - Heat Treatment: Interrupted-quenched from 17,158,,80 155,500... 14I8, W 149,000 149,800 137,4QO 125,600 121,000 124,300 119,300 124,200 142,1>O 135,300 131,212 130,0i 128 ~,20 131,200 143,700 137,800 1342,0 132,800 131,600 133,200 126,s00 93,000 98,000 104Q.90 101,000 108,000 (a) SRR Surface plane radial specimen,nr rim of disk CRR Center plane radial specimen near rim of disk S: &Sfatce plane radial specimen at center of disk RC Center plane radial specimen at oenter of disk

TABLE IV RUPTURE DATA FOR 4340 DISKS AT 1100 OF Disk #3 - Heat Treatment: First treatment -0.Q. from l750'F + 8 Hrs.. at 12000F Second treatment - O.Q. from 1550'F + tempered at 10500F Specimen Specimen Number Location _ _ _ _ _ _ _ _ ( a ) Stress Rupture Time (psi) (Hours) 25.,000 17 Elongation (%) 'Reducti~on of Area (%) 39.1 hw Time to Reach 1-Percent Total Deformation (Hours) 20(c) 2.6(c) 20 SRR hx )4Y CRR CRR 20,9000 31 13,-000 212 23 Ob 57 0 (b) 34.4 41.0 Disk #4 - Heat Treatment:' Interrupted-quenched at 12000F from 1750'F + 2 Hrs. hw CRR SRR CRR 30,000o 17 25,000 29 8.1 4h7(d) 11.2 84 16,~000 199 700 (a) SRR Surface plane radial.specimen at rim CRR Central plane radial specimen at rim (b) Elongation 'in 2 'Inches (c) Extrapolated value (d) Approximate elongation

TABLE V RUPTURE DATA FOR 17-22A(S) DISKS AT 1100 0F 'Disk #1 - Heat Treatment: N. lWO0'F + 2 Hrs. at 1200'F Specimen Number 14w 14x 14z 6w Dis 14Z )4X 14w 14Y 6w 6x Disk 14x 14w 14Z iSpecimen Locati or (a) SRR CRR CRR SRR SRR;k #3 - Hea SRR CRR SRR CRR SRR CRR #14 - Heat CRR SRR CRR SRR SRR iStress Rui T (psi) (H( 50,000 140,9000 30,000 20,000 it Treatment: 1475500 142, 500 38, 500 32, 500 2. 000 20,500 Treatment: 145,ooo 37,5~00 32,500 26,000 ~pture Iime [ours) 26 36 60 l75 5l9 0.Q. Time to Reach Elongation Reduction 1-Percent Total (% of Area Deformation (b) (%) (Hours) 12.3 7.0 6 573,9 13 567.0 214(c) 1.7 0.8 1314 2.6 2.8 1406 from 1750OF + 8 Hrs. at 12000F 51 2.6 91435 86(d) 3.0 219 3.0 1489 2.6 792 2.1 Interrupted-quenched at 12000"F 69 2.3 l5l 14.0 1479 309 5.1 8.2 3.5 1.6 3.2 2.14 from 1750'F + 29 147 145 156 1402 7714 2 Hrs. 14.0 1.6 2.0 1.6 36 79. 186 337 9614 6w (a) (b) (c) (d) 20,500 1233 3.0 3.6 SRR Surf ace plane radial CRR Central plane radial Approximate elongation Extrapolated value Broke 'in gage mark specimen at rim specimen at rim

TABLE VI RUPTURE DATA FOR H-4o DISKS AT 1100 OF Disk #1 - Heat Treatment: First treatment - N. 19500F + 2 Hrs. at 12000F Second treatment - Retempered at 12000F Specimen Specimen Number Location ________ (a) LN Lx SRR CRR CRR Stress Rupture Time (psi) (Hours) 55,o00 28(b) 555000 4865(c) 45.,000 164L(b) Eo n gat ion (% (f ) Reduction of Area (% Time to Reach 1-Percent Total Deformation (Hours) 1.2 103 40O(d) D isk #3 - Heat Treatment: First treatment - O.Q. from 19500F + 5 Second treatment - Ret empered at 1200 0F Hrs. at 1200'F 6w Lw Lz SRR CRR SRR SRR 60,9000 35. - 0,000 136 L5~ooo 298 39,000 (e) 2.2 1.8 1.8 2.8 309 3.9 Disk #L - Lx Heat Treatment:, First treatment - Interrupted-quenched Second treatment - Retempered at 12000F from 1950'F 28 CRR 60,9000 34(b) Lw SRR CRR 50,000 108 L5,00o 2L3 (b) 39,000 (e) 2.6 8.1 73 228 Lz SRR (a) SRR Surface plane ORR Central plane (b) Broke 'in threads (c) Broke in shoulder' (d) Extrapolated value (e) Test in progress (f) Approximate elongat radial specimen at rim radial specimen at rim

TABLE VII RUPTURE DATA FOR C-422 DISKS AT 11000F Disk #1 - Heat Treatment: First treatment - N. 1900'F + 2 Hrs. at 1200'F Second treatment - Full anneal 6 Hrs. at l600'F and furnace cooled. N. 1900'F + double temper at 12000F for two plus two hours. Specimen Specimen Number Location _ _ _ _ _ _ _ _ (a ) Stress Rupture.Time (Psi) (Hours) Elongation in 2 inches (M 26.0 Reduction of.Area (% Time to Reach 1-Percent Total Deformation (Hours) hw SRR 55000 1.7 69.5 hx CRR 45,000 14.7 35,000 318 23.0 l1.0 73.0 36.3 0,9 26 CRR )4z SRR 32,000 (b) (a).(b) SRR CRR Test Surface plane Central plane in progress radial specimen at rim radial specimen at rim

TABLE VIII CfgSIP PROPERTIES OF 440.;17-22A(S), 4-40, AND C-422 STEELS Steel Heat Treatmmentf BHm tst Tiemp.* __ (01!) Stres's Titbe in Progress (ps t-Hbur's) 4,2950',1007, M i nimum Creep Rate (%/1000 Hrs.) 3.9 Percent Total Deformation at Indicated Time Periods 300.Hrs. 1.37 500 Hrs. 1000 Hrs. Time in Hours forSpcfe T.'o t al1' Da,,f orsation-Is 0.1% 0.2); 0.5^- 1.0^, 9 21 90 217 4340 Aust. 1750~F + 111 Hrs. at 1050~F - 2875 1100 +(Lower Pearlite).I.2 M r~ n.AlSt. 1750~F + 28 Hrs. at 850~F - (Upper Bainite) Aust. 1750~F + 1-1 Hrs. at 650~F + T#. 1i Hrs. at 1100~F (Lower Bainits 270 1000 13,000 84^ 8 525 1000 l5,500 1005^ 294 1000 15,000O 1052(a 5.4 0.42 0.53 2.o04 0.59 2.0 0.o41 0.5 0.88 0.52 4.2 0. 51 0.64 2.04 0.44 0.75 0.94 2 6 46 141 1 18 470 1595(c). 2 532 500 1104 ( 17-22A(S) Aust. 1750~F + 1l Hrs. at 1350or It n 509 51^ 5115 1100 lik00 1100 Aust. 1750~F + 10 Hrs. at 11500^ + T. 12 Hrs. at 1200~1F 9,o 000 I145,000 19,^0 0 15,~000 aea1 l?106~1) (bO'1 1 17 15.9 336 0.74 14 108 622 1465 (C) 1.78 (d) 10 79 194?t ft t~ 291 1100 (b) 652" (b)W 1.55 5.69 24 54 107 218 477 Aust. 1750~F + 2 Hrs. at 900~F + T4 16 Hrs, eat 1200~?i 327 1100 19.000 1.45 0.7 1.1 (d) 8 177 n_ Aust., 1750 T. 12 Hrs. Ia.l aw, 1.5,0500 too m t-^ (. 0.41 t 5 65 + 5 Min. at 7000^ + at 1200~F 1101 M,000 0. I45 0355 0.45 0.7 22 67 621 1698 (a) H-40 0.0. + T. 12 Hrs. at 12000F Aust. 1950~F + 10 Hrs. at 7500F + To 1 Hr. at 1500,OF (Bainite) 3235 1100 84,000 508 1100 28,000 512 1.00 25000 10 (a) 1004^ 0.85 0.5 0.66 1.14 (d) 23 500 862 1*37 0.73 1.05 2,16 (d) 1 131 470 n w) I. I 0.43 0.62 (d) 57 595 C-422 Norm. 1900~F + T* 24 Hrs. at 12000F 306 1100 1100 - 50.0.00 (a) 501^0 I M 0.88 0.49 0.67 0.82 0.75 1.34 1.01 (d) (d) 5 112. 690 0.&. + T. 4 Hrs. at i2SOOF 5 07 1 1335 970 (a) (b) (0) (d) Completed test Test fractured at this time Extrapolate'd value Test reached this deformation on1 loding

l (I) ( (D (D * *0 (D (D 0 * * * * ( 0 (D () (D (D 0 0 (D -— ( I I I D 0D 0* 0 0 0 0 *0 * 0 * ~ o ooooo o o o~~o ~0)0 DD 000000 0 0 0 0 00000 o o o o o o o o o o * * * ( o 0o ~~0o o o oooooooooooCD 0 ^^^ o = 23 - 270 Brinell Hardness * = 271 - 300 " o = 301 - 330 " i, Heat Treatment: Normalized at 1750Fo + tempered 2 Hrs. at 1200~Fo Figure 1o Brinell Hardness Survey on Center Section (1,2,3) of Disk #1 of 17-22 A(S) Steel M

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I 0 0 * 0 00 00 0 00 00 00 0 0 00 0 ,.. * 0 0 0 * 0 0 0 0 0 0 0 * ( 0 * * 0 0 * 0 * 0 * * ) 0 0 0 * 0 00 0 0 0* ** 0 (D 0 e* 0 0 0 0 0 ~(D ~ ~ ~() oo 0 0 ~ * * * (D Q 0 0 * * * * ~ * ~ * 0 ~ * * * * * * oi 00 0 d 0 0 0 0 0~ (0 W 0 0 0 0 at 0 = 315-340 Brinell Hardness 0 = 341-365 it ft a) = 366-380 n Heat Treatment: First treatment - N. 1950~F + temper 2 Hrs. at 1200~F Second treatment - Retempered at 1200~F Figure 5. Brinell Hardness Survey on Center Section (1-2-3) of Disk #1 of H-hO Steel.

* 000 00000( $ 0 i0 0 0 0* * 0 0 o0 * 0 * * *() ( ) 0 0 0 0 0 0 0 0 0 0 0 0 0 0 00 0 0 0 0 0 0 o t 0 0 0 0 * * 0 * 0 00 o 0@ * 0(D0o000 (I) )0 0 0 0 00 00 0 0 0 0 0 (D0 0 0 * 0 0 0 0 00 0 0 0 0 0 *0 0 0 0 oo o * 000 0 0 0 0 o * () * * * o = 315 - 340 Brinell Hardness * = 31 - 365 " n = 366 - 390 " Heat Treatment: First treatment - OoQo from 1950~Fo + 8 Hrso at 1200~Fo Second treatment - Retempered at 1200'F. Figure 6c Brinell Hardness Suvey on Center Section (1,2,3) of Disk #3 of H-4O Steel.

0 0 0 0 0 * @ O O O 'O c i G C O O O O *,) * ') 0O O (]) * * * 0 0 (0 0 0 0 0* (D 0 0 0 0 0 0 3 0 o o O O @ O O 0 00000000000000 00000 0 0 0 0 0 0 0 0 0 0 0 0~~ 0 0~000 o 0 0 0 _ 0 0 0 0 0 0 0 ~*000000000 0 = 327-350 Brinell Hardness * = 351-375 0 = 376-393 tt It tt Heat Treatment: First treatment - Water quench from 1950~F until black, then withdrawn until glow returned. This was repeated until the glow did not return upon withdrawal. Transferred to furnace at 700~F for 8 hrs. + temper 2 hrs. at 1200~F. Second treatment - Retempered at 1200~F. Figure 7. Brinell Hardness Survey on Center Section (1-2-3) of Disk #4 of H-4h Steel.

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UNIVERSITY OF MICHIGAN 3 9015 03526 9987