TWELFTH PROGRESS REPORT TO MATERIALS LAB ORAT OR Y WRIGHT AIR DEVELOPMENT CENTER ON FOUR LOW-ALLOY STEELS FOR ROTOR DISKS OF GAS TURBINES IN JET ENGINES by K. P. MacKay A. I. Rush J. W. Freeman Project 1903 Air Force Contract No. AF 33(038)-13496 Supplemental Agreement No. S9(54-1203) Expenditure Order No. R-619-llSR-12 June 30, 1954

SUMMAR Y This report presents the progress made in an investigation of the high temperature properties of low-alloy steels for use in jet engines. The period covered by the report was from April 1, 1954 to June 30, 1954. Nearly complete data are presented for survey tests to evaluate the influence of microstructure as controlled by continuous cooling transformation on the high temperature properties of SAE 4340, "17-22A"S, and H-40 steels at temperatures ranging from 700~ to 1200'Fo The structures studied are those obtained by continuous cooling transformation during the air cooling of 1-inch and simulated 3- and 6-inch diameter bars. Normalizing of 1-inch diameter bars resulted in mixed martensitic-bainitic structures, whereas the slower cooling cycles resulted in predominately bainitic structures for all three steels. It was observed that the microstructures of the simulated 3- and 6-inch bars of "17-22A."S and H-40 steel were considerably coarser than those of the 1-inch bar, but that little or no change was noted for the SAE 4340 steel as a function of heating or cooling rate. In all instances the hardness levels were adjusted by tempering to approximately 300 Brinell. The incomplete test data tend to show that little variation in creep-rupture properties is obtained for the subject steels as a result of normalizing in section sizes ranging from 1-inch to 6-inch diameter bars. The variations resulting from differences in continuous cooling transformation conditions indicate that the slower cooling cycles, selected to simulate the air cooling of 3- and 6-inch:diameter bars, tend to give strength properties equal to or slightly higher than those of a 1-inch diameter normalized bar. However, detailed consideration of such variations has been withheld pending the completion of the testing program.

2 INTR ODU C TI ON This report covers the work done during the period between April 1, 1954 and June 30, 1954 on an investigation of the metallurgical factors involved in the use of heat-treatable, low alloy steels at elevated temperatures in jet engines. Contract Number: AF 33(038)13496 (Expenditure Order Number: 605-227. SR-7) and Supplemental Agreement Number: S9(54-1203) (Expenditure Order Number: R 619-11 SR-lz) authorize the work. The investigation first evaluated the high temperature properties of four low alloy steels in the form of rotor wheels for gas turbines of jet engines. This work has been published as WADC Technical Report 53-277, Part 1. A concurrent investigation was conducted to determine the relationships between types of microstructure, as controlled by heat treatment, and the properties of the alloys. The properties of such steels at elevated temperatures vary with the types of structure formed by heat treatment. Therefore, the influence of microstructure on high temperature properties was evaluated by survey tests for the temperature range of 700 to 1200'F for structures obtained by isothermal transformations in the pearlitic and bainitic regions as well as those produced by oil-quenching and normalizing of 1-inch rounds. Three pearlitic and three bainitic structures were studied for the 4340 and "17-22A"S steels, but because of the narrow temperature range in which complete transformation could be obtained in reasonable time periods, only one pearlitic and one bainite structure were studied for the H-40 steel. A technical report entitled "A Survey of the Relations Between Micxostructure and Elevated Temperature Properties of Four LowAlloyed Steels at 700' to 1200 F" covering the results of this portion of the

3 investigation is in preparation and will be published as WA.DC Technical Report 7 53-277, Part 2. A third phase of the investigation concerned the properties of structures obtained by continuous cooling transformation at cooling rates approximating those existing during air cooling of sections sizes similar to rotor wheels. The present report presents the results of that portion of the work. The properties of structures produced by cooling rates simulating those existing in the center of 3- and 6-inch diameter rounds have been survey tested in the temperature range of 700' to 1200'F for the SAE 4340, "17.22A"S, and H-40 steels. It was believed that these cooling rates together with those previously studied, the oil-quenched and normalized 1-inch round bars, cover adequately the range of structures of major interest; that is, from martensite to bainite formed by relatively slow cooling rate. The initial surveys are nearly complete for this report. Future work will involve the completion of the study of the properties of structures obtained by continuous cooling transformation, and the extension to include the effect of variations in austenitizing temperature on high temperature properties. The ultimate objective is to establish the metallurgical principles of heat treatment for producing as nearly optimum properties as possible in such alloys for use at elevated temperatures. Test Materials The chemical compositions of the alloys being studied was reported by the manufacturers to be as follows: Steel Heat C Mn Si Cr Ni Mo V W 4340 19053 0.40 0. 70 0. 30 0. 78 1.75 0. 26 "17-22A."S 10420 0. 29 0. 61 0. 67 1. 30 0. 18 0.47 0. 26 H-40 K-2509 0. 29 0.48 0. 26 3. 05 0. 49 0.49 0. 85 0. 55

4 Procedure The transformation products obtained by continuous cooling are a function of the cooling rate through the transformation temperature range. Inasmuch as the cooling rates involved in the heat-treatment of parts of large section size are considerably faster than can be obtained easily by controlled furnace cooling, the desired cooling rates may best be obtained by varying the section size being cooled. Since only 3/4- and 1-inch diameter bars were available, the desired cooling cycles were obtained by the retarded cooling of the 3/4- and 1-inch round bars in a cylinder made from a low heat duty fireclay insulating brick. The general procedure was as follows: 1. To establish the cooling cycles for 3- and 6-inch diameter bars, the cooling cycles for 1-inch bars of "17-22A"S steel and 1- and 3-inch diameter bars of plain carbon steel were obtained during air cooling by means of a thermocouple inserted axially to the center of the bar. Cooling curves were not obtained for 6-inch rounds because of the handling difficulties and the capacity of the laboratory furnaces. 2. From the cooling curves obtained for the 1- and 3-inch rounds, the heat transfer coefficient (h) to the surrounding medium, air in this case, was calculated for the conditions existing in the laboratory, (1) From the h value obtained, the cooling curve for a 6-inch round was calculated. 3. Cooling curves were obtained at the center and surface of 1-inch rounds of 4340 and "17-22A"S materials and at the same locations for 3/4-inch rounds of H-40 during cooling in insulating firebrick cylinders estimated to produce cooling cycles similar to the 3- and 6-inch round bars. (1) T. F. Russell, "Some Mathematical Considerations on the Heating and Cooling of Steel, " First Report of the Alloy Steels Research Committee by a Joint Committee of the Iron and Steel Institute, 1936, page 149.

Through trial and error, the thickness of the firebrick cylinder was adjusted to produce cooling cycles equivalent to the experimentally determined cycle for the 3-inch round and the calculated cycle for the 6-inch round. The actual cooling curves obtained for "17-22A"S during cooling from 1750'F are illustrated in Figure 1, and Figure 2 shows similar curves for H-40 steel cooled from 1950'F. The cooling curves obtained for the 4340 steel, air cooled from 17500F, were nearly the same as those shown for '"17-22A"S, and, therefore, are not illustrated. Figure 3 compares the cooling cycles from 1750F with those from 1950'F on a semilogarithmic graph. It was found that since the principal factor controlling the cooling cycle appeared to be the rate of heat transfer across the metal to firebrick interface, the cooling rate at the surface of the enclosed bar was essentially the same as that at the center. This conclusion was confirmed by the uniform microstructure observed throughout the cross-section of the heat-treated bars. 4. After the necessary thickness of firebrick to produce the desired cooling cycle had been determined, a number of specimens were heat-treated by the following procedure: a. Barstock of 3/4- or 1-inch diameter was enclosed in the firebrick cylinder with a thermocouple attached to the surface of the bar at the midpoint. b. The assembly was inserted in a furnace at the desired temperature and held until the thermocouple indicated that the specimen had been at temperature for 1 hour. c. The assembly was removed from the furnace and the test bars allowed to cool to room temperature in the insulating firebrick. d. Throughout the previous work, all test bars have been tempered to a hardness range of 280 to 320 Brinell when the

6 as-transformed hardness was at a sufficiently high level. In the present phase of the investigation, the same hardness range was employed. Insofar as possible the tempering times and temperatures were the same as or similar to those previously used for the normalized 1-inch bars. However, since the as-normalized hardness of the 4340 steel was only slightly above 300 Brinell and even slight tempering resulted in hardnesses below 300 Brinell, this steel was tested in the as-normalized condition. Table I shows the as-normalized and normalized and tempered hardnesses for all three steels as well as indicating the microstructure obtained and the tempering procedure employed. 5. The general basis for the evaluation of the properties of the structures was the same as previously established for the isothermally transformed structures, which was as follows: a. Evaluate the properties of the structures for the range of temperatures over which creep and stress-rupture performance would be of most interest. The temperature range was set at 700' to 1100~F for 4340 and at 700~ to 1200'F for "17-22A"S and H-40 steels. b. Evaluate the structure on the basis of the property which is the controlling factor at the temperature of interest. Thus at 700' and 900~F, the criteria of comparison were creep rates and total deformation data. At these temperatures, the stresses causing rupture in reasonable times would be well above the yield strength, and thus service stresses would be limited to those below which rupture would occur. Attempts were made to find a single stress which would evaluate the structures on the basis of time required to obtain one percent total deformation. However, because of the low strength of the 4340 steel at 900'F, approximate 1000-hour rupture data were also obtained.

c. At 1000~F, testing was limited to the 4340 steel, but at 1100lF, all three steels —4340, "17-22A"S, and H-40 —were tested. Both creep and rupture properties were considered of interest at these temperatures. Consequently, one test was employed to evaluate the short-time rupture strength, and another to obtain the time for one-percent total deformation. d. At 1200~F, testing was limited the H-40 and "17-22A"S steels. At this temperature, the property of most interest was considered to be the 100-hour rupture strength, although some 1000-hour data were obtained to permit better correlation between structural variations and testing temperature. Results The structures obtained by the various cooling cycles are outlined in Table I together with the as-normalized and normalized and tempered hardnesses. These structures are illustrated in the as-normalized condition in Figures 4, 5, and 6. It should be noted that although, in most cases, the slower cooling cycles resulted in large percentages of bainite no attempt has been made in Table I to identify the bainites as "upper," " middle, or "lower" bainite as was previously done for the isothermally transformed structures. Inasmuch as the transformation occurred over a range of temperatures during cooling, the resulting structure is an intimate mixture of bainites which does not permit analysis. However, because of the slower cooling cycles and consequent longer time in the bainite transformation region, it might be expected that the structures of the 3- and 6-inch diameter bars would be composed of a larger percentage of the "upper" and "middle" bainites than the 1-inch bar. On the other hand, the cooling curves of Figures 1 and 2 indicate little change in temperature of transformation with

8 rate of cooling. The temperature of major transformation as evidenced by the retardation of the cooling cycle appears to be essentially independent of the cooling cycle within the range investigated. In the case of the simulated 6-inch round of "17-22A"S the cooling cycle was sufficiently slow to permit some ferrite precipitation. However, the same cooling cycle for 4340 was fast enough to retain considerable martensite. It was observed that the cooling cycles equivalent to 3- and 6-inch bars resulted in considerably larger grain sizes than the faster cooling rates for the "17-22A"S and H-40 steels. In particular, the H-40 steel showed a progressive increase in grain size with decreasing heating and cooling rates. The 3- and 6-inch bars of the "17-22A"S steel were quite similar but revealed a considerably coarser structure than the 1-inch bar. On the other hand, the 4340 steel showed little change in grain size although the bainitic structure appeared slightly coarser in slower cooled bars, Although the "17-22A"S and 4340 steels exhibited approximately the same as-normalized hardnesses of about 315 to 330 Brinell as shown in Table I, it was possible to temper the former at 1200'F for 6 hours with little or no change in hardness whereas the latter could not be tempered without excessive loss in hardness. The tempering treatment of 1-hour at 1100'F previously employed for the normalized 1-inch rounds resulted in a Brinell hardness of about 250 for the 3- and 6-inch rounds, Consequently, the 4340 steel was not tempered. Survey of Relationships between Section Size and Streng. th for- 4340,; "1'7-ZZA"'S, and H-40 steels The test data obtained during the period covered by this report are summarized in Tables II, III, and IV for SAE 4340, "17-22A"S, and H-40 steels, respectively. For convenience of comparison, the data previously reported for 1-inch diameter normalized bars are included.

9 Although the data are not yet complete, the following trends may be noted: 1. Properties of 4340 Steel: The variation in properties resulting from the range in cooling cycles appears to be relatively small. The 1-inch and simulated 6-inch rounds appear to have remarkably similar properties at all testing temperatures. The simulated 3-inch diameter bars gave very slightly lower values which are hardly significant. 2. Properties of "17-22A"S Steel: In general, the simulated 3- and 6-inch rounds tended to exhibit slightly higher strength properties than the 1-inch normalized round. The exception to this statement occurred at 700'F when the simulated 3-inch diameter bar exhibited lower creep strength than the 1-inch bar. The test at 700'F for the 6-inch cooling cycle has not been completed. 3. Properties of H-40 Steel: The tests at 700' and 900'F are not yet complete but those at 1100 and 1200'F indicate only slight variation in response with testing temperature. At 1100'F, relatively short time tests indicate a slight superiority for the 3/4-inch bar and the simulated 3-inch diameter bar, both in rupture strength and minimum creep rate. However, the simulated 6-inch diameter bars resulted in considerably better ductility in the rupture test. At 1200'F the simulated 3- and 6-inch diameter bars gave similar rupture times that were somewhat longer than that of the 3/4-inch bar. In both cases, however, the differences are so small that more testing would be required to establish significant validity. Discus sion The survey tests to evaluate the high temperature properties of structures formed during continuous cooling at various rates are nearing completion. While it is hazardous to draw conclusions from incomplete data, certain observations may be made. 1. In general, the trend of the data to date show that no

10 significant differences in creep-rupture properties exist for normalizing of stock ranging from 1 -inch to 6-inch rounds for the three steels studied. 2. With the exception of the 434.0 material, the slower heating and cooling cycles resulted in coarser microstructures than previously observed in the barstock material. 3. Detailed discussion of any differences in properties as a result of variations in cooling cycles and resulting structures is being withheld pending the completion of the testing program for this phase of the investigation. Future Work Future work shall consist of the continuation of the investigation to determine the effect of austenitizing temperature on the elevated temperature properties of 4340, "17-22A"S, and H-40 steels. In addition, the tests required to complete the investigation of properties of structures obtained by continuous cooling transformation will be conducted.

TABLE I Microstructure and Hardness Values for 4340, "17-22A"S, and H-40 Steels Transformed during Continuous Cooling at Cooling Rates Equivalent to 1-, 3-, and 6-Inch Diameter Bars Steel Size of Normalizing Microstructure Obtained B H N Tempering B H N Round (in.) Temp ('F) Temp(-~F) Time(hrs) 4340 1 1750 35% martensite + 65% 362/385 1100 1 290/311 bainite 3 1750 25% martensite + 75% 327/331 none 327/331 bainite 6 1750 20% martensite + 80% 315/329 none 315/329 bainite "17-22A"'S 1 1750 15% martensite + 85% 355 1200 10 291/317 coarse bainites 3 1750 100% bainite 320/330 1200 6 290/313 6 1750 98% bainite + 2% ferrite 320/330 1200 6 291/322 H-40 3/4 1950 20% martensite + 80% 435 1200 18 3 10/320 bainites 3 1950 100% bainite 400 1200 4 304/313 6 1950 100% bainite 390 1200 4 297/322

TABLE II Rupture, Total Deformation, and Creep Data at 700~, 9000, 1000~, and 1100~F for SAE 4340 Steel Normalized to Obtain Cooling Cycles Equivalent to Those at the Center of 1-, 3-, and 6-Inch Diameter Bars Temp Size of Stress Rupture Elong. Reduction Deforma- Time to Reach Specified Minimum Round BHN Time (% in of Area tion on Total Deformation (hrs) Creep Rate (~F) (in.) (psi) (hours) 2 in. ) (%) Loadingo) 0.1% 0.2(7o 0.5% I.0% (%/hr) 700 1 300 90,000 1294(d) -- -- 0. 467 a a 1 1000. 00016 3 327 90,000 1342(d) -- -- 0.463 a a " 3 668 0.00021 6 315 90,000 1342(d) -- -- 0. 450 a a -5 1000 0.00021 900 1 300 55,000 842 12.0 22. 3 0. 26 a a 8 64 0.00414 1 300 40,000 1919(d).- -- O 164 a 5 1160 >3000(b) 0.00015 3 331 40,000 1464(d) -- -- 0. 185 a '2 82 1800(b) 0.00024 6 315 40,000 1483(d) -- -- 0. 175 a n~4 430 >2000(b) 0.00015 1000 1 290 31,000 371 5.5 7.4 0. 126 a ~5 50 145 0.00505 1 300 20,000 1392 5.0 4. 0 0. 09,1 20 228 650 0. 00114 1 301 12,000 1000(d) -- -- 0. 05 12 114 802 2150(b) 0.00037 3 331 31,000 259 12.5 15.7 0. 148 a,-1 16 39 0.0114 3 327 20,000 1310.5 8.5 6.6 0. 101 a 5 110 387 0.0017 6 315 31,000 362. 1 11.0 11.1 0. 157 a, -,1 19 94 0. 0065 6 315 20,000 1488 6.0 6.6 0.092 ^'1 12 145 534 0.0012 1100 1 293 18,000 69.6 7.0 11.7 0. 116 a -- -- _ 1 311 4,000 1056(d) -- -- 0.017 18 96 484 1400(b) 0.00052 3 328 18, 000 78. 6 17.5 22. 5 0. 107 a <1 2.5 -- _ 6 321 18,000 77.2 18.0 21.8 0. 112 a <1 3 - -- (a) Specimen reached this deformation on loading. (b) Extrapolated value. (c) 0. 250-inch diameter specimen - elongation is percent in 1. 0 inch. (d) Test discontinued at given time.

TAB LE III Rupture, Total Deformation, and Creep Data at 700~, 900~, 1100~, and 1200~F for "17-22A"S Steel Normalized to Obtain Cooling Cycles Equivalent to Those at the Center of 1-, 3-, and 6-Inch Diameter Bars Temp Size of Stress Rupture Elong. Reduction Deforma- Time to Reach Specified Minimum Round BHN Time (% in of Area tion on Total Deformation (hrs) Creep Rate (~F) (in.) (psi) (hours) 2 in. ) (%) Loading(o) 0. 1%o 0 2% 0.5% 1. 0% (%/hr) 700 1 302 115, 000 132 21.0(c) 61.9 0.66 a a a 1 0.0220 1 307 102,000 1194(d) -- -- 0.465 a a -1 >2000(b) 0.00007 3 291 102, 000 1793(d) -- -- 0.62 a a a 150 0.00016 900 1 303 70,000 1482(d) -- -- 0.335 a a 24 1400 0.00030 3 302 70,000 1223(d) -- -- 0.288 a a 235 >2000(b) 0.00013 6 297 70,000 1152(d) -- -- 0. 285 a a 525 >2000(b) 0.00008 1100 1 309 41,000 111.5 2.5 3. 1 0.212 a a 26 -- 0.00614 1 311 20,000 773 2.0 -- 0. 090, 1 46 375 656 0.00086 1 317 17,000 1035(d) -- -- 0. 079 14 177 857 1500(b) 0.00045 1 291 14,000 1150(d) -- -- 0.065 50 230 1200 -- 0.00030 1 302 10,000 1060(d) -- -- 0.040 32 140 1700(b) -- 0.00016 3 291 41,000 109.4 2. 1 (e 0. 206 a a 34 -- 0. 00523 3 295 19,000 1319.9 2.0 (e) 0. 090 15 193 1045 --. 00026 6 293 41,000 114.9 2.0 3.5 0. 221 a a 29 -- 0.00420 6 291 19,000 1308. 6 1.2 2. 0 0. 091 5 183 994 -- 0.00028 1200 1 304 14,000 167. 1 4.0 5.0 0. 066 5 22 65 "140 0.0064 1 313 7,500 918 10.0 14.9 0. 046 6 46 176 333 0.0023 3 290 14,000 158.2 2.0 2.8 0. 072 5 22 91,,130 0.0040 6 295 14,000 152. 1 1.5 (e) 0. 070 5 22 93 ^,127 0.0041 (a) Specimen reached indicated deformation on loading. (b) Extrapolated value. (c) 0. 250-inch diameter specimen - elongation given in percent in 1. 0 inch. (d) Test discontinued at given time. (e) Broken in shoulder radius.

TABLE IV Rupture, Total Deformation, and Creep Data at 700~, 9000, 1100', and 1200~F for H-40 Steel Normalized to Obtain Cooling Cycles Equivalent to Those at the Center of 3/4, 3-, and 6-Inch Diameter Bars Temp Size of Stress Rupture Elong. Reduction Deforma- Time to Reach Specified Minimum Round BHN Time (% in of Area tion on Total Deformation (hrs) Creep Rate (0F) (in. ) _ _(psi) (hours) 2 in. ) (%) Loading%) 0. 1% 0 0. 2..o O 5. o 1.0% (-%/hr) 700 3/4 310 90,000 1292(d) -- -- 0.416 a a 13 1700(b) 0.00017 900 3/4 320 65,000 1052 18.0(c) 36.0 0. 301 a a 10 85 0.00328 1100 3/4 315 43,000 48.4 (f) -- 0. 226 a a 27 -- 0.0058 3/4 310 40,000 193 5.0 13.6 0.231 a a 20 89 0.0074 3/4 312 34,000 272 (e) -- 0. 165 a 6 162 -- 0.00148 3/4 320 31,000 720 (e) -- 0. 120 a 7 274 677 0.00105 3/4 316 27,500 1130(d) -- -- 0.146 a 36 430 1054 0.00064 3 304 40,000 213. 1 4.0 9.5 0. 230 a a 15 107 0.0047 6 297 40,000 149. 1 10.5 31.0 0. 230 a a 9 44 0.0134 1200 3/4 315 25,000 100 17.0 45.0 0. 142 a, _,1 9 38 -- 3 304 25,000 188 10.4 11.7 0. 170 a,1 24 71 0.0118 6 297 25,000 204.9 11. 1 7. 1 0. 172 a -1 29 82 0.0085 (a) Specimen reached specified deformation on loading. (b) Extrapolated value. (c) 0. 250-inch diameter specimen - elongation given is percent in 1. 0 inch. (d) Test discontinued at given time. (e) Specimen fractured in shoulder radius. (f) Specimen fractured in threaded end.

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X100ID X10OOD r' ~ ~ ~ ~ ~ r....... ~' ~;C~ r 1-1 41? Vs~~~~~ (a) Normalized as 1 -inch diameter bar. 4W?.':... '.:4t 45,.; kwrll 0r ir~ ~ ~~~~~~~~~~~~~~~~~,:': ",~~~~':~~~ ~"~'-,:~~ '_ (b) Normalized with cooling cycle similar to that at center of 3 -inch diameter bar. -art; 4 ",V4^4 (c) Normalized with cooling cycle similar to that at center of 6-inch (c) that at* cete of1I-~ 6g-inch diameter bar. Figure 4. - Microstructure of 4340 Steel Normalized at 17500? with Various Coolinz Cycles.

X OOD XIOOOD F~~' ~~~~ttr~~~f V $vt4A *4"'~~~~~~~ - 44. ~~~~~~~~~~~~~~~ 4 Ij~~ (a) Normalized as 1-inch diameter bar. A W4t ~ ~.. Kt......, W~~~~~~~~~~~~~~~~~~~~~~. "'''- F'" ~a <Vt I 4 Ali diameter bar. 4- "'p~~~~~~~~~~~~~~~~~~~~~~~~~~~ ~"~~~~~~~~~~~~~~~~~~~~~:'~ - ~~~~~~~~~~~~~~~~.1 'N'~~~~~~~-*N':4 6:y~~~t~rtt tN;A-A! 4., r- # (c) Normalized wit~h cooling cyrcle similar to that at center of 6-inch diameter oar, Figure 5. - Microstructure of '17-ZZA"S Steel Normalized at 1750~F with Various Cooling Cycles.

XI 0I01 XI 0 0 0:it::~:;:::~~~~~~~~~~~ ~ ~ ~ ~~~~.:.........:'::.':::.~.....'~:..... dae i' 4 2: o [i't.4;C *' 9*~~~; + di aai. e te r r o [1iild.~~~~~~~~~~~~~~u ~ ('i) NoP irol i. /g C ich ti ia 0 5 WtA~'tj1~ %"7 S ) 6. k lb A 42'es (14 No-)r nua I' AndcI wit coin ic h cm jiniar.t i itcctro 4c da'ite IN I I '44~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ O.~~~~~~~ ()N~o~rma~ri.(lized.... with coolilng Cycle sir illar to that at center of 364 ich diameter rmund(. i~guc6. Mcr~tuAneofli~ Sel o+ralzd t wtYVr ions Cat flag (iyc ec: +~~~~~~~~~~~~V