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ANP QUARTERLY PROGRESS REPORT - N -. 14 13 12 11 IO $ 9 0 10 ‘ 0 8 - W m 4 7 W (L 0 z 6 I- I (.!I f 5 s 4 3 2 1 UNCLASSIFIED ORNL-LR-DWG 4426 0 0 20 40 60 80 100 I20 140 160 180 200 ELAPSED TIME (hr) Fig. 7.1. Oxidation of Plated Hastelloy B in Air at 1500OF. backing up of the tube-to-header joints with Coast Welding Metals No. 52 brazing alloy. The fabrication of the three test assemblies P. Patriarca R. E. Clausing K. W. Reber G. M. Slaughter made to date has been routine, and no unusual Metallurgy Division behavior or difficulties have been encountered. Although it is expected that the characteristic aging of Hastelloy B and the subsequent loss in room-temperature ductility will affect the longevity of these test specimens, the first assembly has J. M. Cisar Aircraft R eactor Engineering Division R. L. Heestand Pratt & Whitney Aircraft withstood, without failure, as determined by a Preparations are under way for experiments to helium leak test, 100 accrued hours of life with evaluate the properties of Hastelloy B weld metal one air quench and one water quench directed at as affected by thermal history. A comparative the fin surfaces. Other test assemblies are being basis for the tests has been prepared through fabricated with type 310 stainless-steel-clad experiments in which the effect of aging time at copper in order to determine, in conjunction with 15OOOF on the room-temperature ductility of wrought the evaluation of Hastelloy B, the dimensional stability and oxidation resistance of this material Hastelloy- B was determined. For these tests, guided bend specimens, x y2 x 1% in., were under thermal shock. cut from 3/,6-in.-thick wrought Hastelloy B plate . . . - 4
- N E \ cn s 14 12 io z a e F $6 w 3 4 2 0 0 20 ELAPSED TIME (hr) PERIOD ENDING DECEMBER 70, 7954 Fig. 7.2. Oxidation of Nickel-Molybdenum Base Alloys in Air at 15OOOF. UNCLASSIFIED ORNL-LR-DWG 4427 which had been solution annealed at 215OOF and a period of exposure of less than 50 hr. If the quenched. One set of specimens was then aged material is given a stabilizing heat trtzatment, ctility is prolonged and 200 hr. The estigation indicate zing heat tteatment r treatments at 195OOF mperature and 15OOOF bend tests, and the will be compared with those for wrought 105
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ORNL DOCUMENT REFERENCE LIBRARY, Y-
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.. II 1. G. M. Adamson 2. R. G. Aff
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iv R ports pr ri ORNL-528 ORNL-629
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t s
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4 . CRITICAL EXPERIMENTS ..........
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Removal of Xe13' from Molten Fluori
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ANP QUARTERLY PROGRESS REPORT main
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ANP QUARTERLY PROGRESS REPORT 26OOC
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ANP QUARTERLY PROGRESS REPORT syste
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incident on crew shield sides and r
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1. CIRCULATING-FUEL AIRCRAFT REACTO
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clean reactor at a low power for a
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for more than 0.6 Mw in the sodium,
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I .o 08 0.6 . E - ‘z I - 0.4 0.2
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i PERIOD ENDING DECEMBER 70,7954 Fi
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Analytical studies, layout work, an
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XENON- REMOVAL SYSTEM 4 BLEED CIRCU
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c. . f 0 L .. would mean that most
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‘s = = (tot a I f i s s ion s/sec
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L . PERIOD ENDING DECEMBER 70, 7954
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PERIOD ENDING DECEMBER 70, 7954
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PERIOD ENDING DECEMBER 70, 7954 Fig
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A" d OIL IN-l OIL IN-2 NUCLEAR I N
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7 . " e- It should be noted that th
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the floor up to 3 ft below the bolt
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" i' Design work is under way on an
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The pump has unusual ability to rem
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into operation with a Reynolds numb
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. . . . .- . Fig. 3.5. Heat Exchang
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TABLE 3.1. GAS-FIRED FURNACE OPERAT
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n while connected to a small tank o
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15. TOWER SHIELDING FACILITY C. E.
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ANP QUARTERLY PROGRESS REPORT - .-
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ANP QUARTERLY PROGRESS REPORT 162 -
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