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SUMMARY AND The Aircraft Heactor Experiment isec. 1) is now well into the transition period between design and reality. The design is essentially complete, almost all the components areonorder, end a substantial number of these have been received and installed in the ARE rjuilding. The significant modifications during the past, quarter include cornplet,ion af the off-gas system design (incorporating holdup tanks rather than charcoal adsorbers) and the inclusion of a reactor hy-pass (so that the fluid circuits may be checked out independently of the reactor). Coincident with the completion of the reactor design, the Aircraft Reactor Experiment Hazards Summary Itspor t, ORNL-1407, was submitted to the AEC for approval. It is anticipated that even though the experiment may be completely assembled by the summer of 1953, a significant and indeterminant period will be required for shake-down operation before the reactor becomes critical. Val v e s , p ump s , i ns t rumen t a t i o n I and other components of both the fluoride fuel (NaF-ZrF4-UF, , 50- 46- 4 mole 7%) and reflector coolant (NaK) circuits are being developed for the Aircraft Reactor Experiment (sec. 2). In most, instances, these components have been tested on smaller than full- scale prototypes of the actual ARE components. Tests are now under way, however, on the full-scale pumps, valves, and some instrumentation designed for the reactor experiment. At this time, centrifugal pumps with both gas seals and frozen seals have operated satisfactorily for extended periods at temperatures between 1280 and 1500°F. A combination packed and frozen seal has been specified far the ARE pump. Although a bellows type of seal has been specified for the ARE, a considerable program has been undertaken on high-temperature, self- lubr ic at in8 seal s. INTRODUCTION The rotameter type of flowmeter and the modified Moore Nullmatic pressure transmitter havebothoperated satisfactorily at high temperatures (-140OOF). Neither of these instru- ments is affected by the ZrF, vapor above the fuel. Vapor traps of the type that will be required in the gas system above the fuel surge tanks have been satisfact,orily developed. The heat transfer coefficient of an aircraft type of sodium- to- air radiator, in which the radiator fins were sectioned every 2 in. i n the direction of air flow, was increased 20% over that of the same radiator with plain flat fins. The general design studies Isec. 3) were confined to performance analysis of a Sapphire turbojet: engine in which the engine radiator performance was extrapolated from a sodium-to-air radiator section tested at ORNL. Performance data for both the radiator and engine are presented. Arrange- ments have been completed with the Wright Air Development Center for their participation in the development of high-temperature liquid-to-air aircraft radiators. The several reactor physics studies (sec. 4) include those of oscillations in a circulating fuel reactor, a technique for reactor calculations, and the temperat ure-dependence of a cross section exhibiting a resonance. The damping influence of fuel circula- tion has been demonstrated even when the earlier assumptions are replaced by more realistic conditions. With regard to reactor calculations, it is shown that the slowing down of neutrons in parallel slabs of materials with different properties can be described in some instances by a set of images of the original neutron source. Critical assemblies of both the Aircraft Reactor Experiment and a ref 1 ec to r -mode rated re actor have been tested (sec. 5 ) . Critical mass,
ANP PROJECT QUARTERLY PROGRESS REPORT control rod effectiveness, flux and resulted in rather large self-shielding fission distribution, and self- effects. Measurements on the ARE shielding factors have been determined critical assembly continued. Cali- for this initial reflector-moderated bration curves for the AnE control assembly. As was expected, this as- rods were obtained, and the effects sembly gave rather peaked flux dis- of various core components on reac- tribution curves, and the lumped fuel tivity were compared, 6
Page 2 and 3: __~ ~ ~~~ . ......... ~ ..... - ...
Page 4 and 5: 98- 108. 109. 110- 117. 118. 119-12
Page 6: Reports previously issued in this s
Page 9 and 10: e e e PAGE Moore Nullmatic pressure
Page 11 and 12: .. CrF. .Na. CrFd .Li. CrF6 .......
Page 13 and 14: PAGE Melting point of 60% Pd-40% Ni
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Page 34 and 35: design of the first combination sea
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Page 44 and 45: MASS VELOCITY ( Ib/hr .ft2) - PEXIO
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Page 56 and 57: In the theory of power oscillations
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z 11 t- o a LT LL 1 .O 0.8 5 0.6 -
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300 250 >- I- 2 & 150 ct W LL 50 0
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T BLE 5. RADIAL PmITxm- (in. 1 REAC
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ANP PROJECT QUARTERLY PROGRESS REPO
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64 ANP PROJECT QUAMTEREY PROGRESS R
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AN€' PROJECT QUARTERLY PROGRESS R
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68 ANP PROJECT QUARTERLY PROGRESS R
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- *0° 1 BO 440 120 , '0° i 80 , I
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84 1 E 0 d a 1 Y d .4 rl h u C d d
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the last quarterly report,(') has b
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Design of the tower configuration a
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d 1 I 2 . k IJJ 10 c -- ___li i____
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person received about four times th
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ANP PROJECT QUARTERLY PROGRESS REPQ
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ANP PROJECT QUAIRTEHLY PROGRESS REP
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AIYP PROJECT QUARTERLY PKQGRESS REP
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ANP PROJECT QUAHTERLY PROGRESS REPO
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ANP PR0,jlECT QUARTERLY PROGRESS RE
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ANP PROJECT QUAR'FEHLY PROGRESS REP
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ANP PROJECT QIJARTERX,Y PRQCRESS RE
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ANP PROJECT QUARTEHLY PROGRESS REPO
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ANF PROJECT QUARTERLY PROGRESS REPO
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ANP PRQ JECT QUARTERLY PROGRESS RQE
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134 = e . , n N N N - Y) o m -J .m
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constituent was found in this loop.
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(mil SId: 3 6 10 15 20 25 30 Extern
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ANP PROJECT QUARTERLY PRQGIXSS HEPO
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ANP PROJECT QUARTERLY PRQGRESS REPO
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ANP lJHO JECT QUARTERLY PHOGRESS RE
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AhP PROJECT QUARTERLY PHOGRESS REPO
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ANP PROJECT QUARTElilLY PROGRESS RE
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BRAZING ALLOY Nic robr az 60% Mn-40
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ANP PRQJECT QUARTERLY PROGRESS REPO
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ANP PROJECT QUARTERLY PIJQGRESS REP
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ANP PRQJECT QUAMTERLY PWOd;l"aESS R
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on air radiations and simulated fla
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184 Fie. 13.6. Pyrex Thermal Convec
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ANP PROJECT QU.4RTEtlLY I'ROGRESS R
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SUMMARY AND INTRODUCTION The list o
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CF-52-11-85 ORNL- 1 43 3 OWL- 137 2
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H. Seal and Pump Development PERIOD
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12. 13. 14. 15. 16. 1.7. 18. 19. Pr
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i 3. U0,-NaOH Slurry Loop 4. Operat
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7. Fuel Spherical Particle Producti
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