ORNL-1771 - Oak Ridge National Laboratory

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PERIOD ENDING SEPTEMBER 10, 1954
TASLE 3.1. PRINCIPAL FEATURES AND STATUS OF FORCED-C1FtCULAflON CORROSION LOOPS
__._......_..i__-...... ~
. ....._.._
......... ...~~~.-...-..I___ -I____.. ____ ._..--......
Loop Number
..-~ -.-.~~._~_____..-~..__I___-..-~---
1 2 3 4 5 6
Reynolds number at 1500'F 10,000 1 0,000 10,000 800 3000
Temperature differential, OF 100 2 00 300 200 2 00
Power input, kw 27.7 54.2 80,O 6.8 25.5
Heating section length, ft* 8.08 8.08 8.08 6 22.3
Cooling section length, ft* 15.64 15.64 15.64 1.6 6
Heat exchanger length, ft** 18.75 18.75 18.75 None Nons
Pressure drop, psi 35.12 36-54 47.5 0.06 0.57
Status Detail Detail Construction Detail Pre I i mi nary
design
complete
design
complete
and assembly
80% complete
design
90%
complete
design
complete;
detail design
20%
comp lete
. ..
~ ~
"OS-in.-OD, 0.020- in.-wal I tubing.
**loo-in.-OD, 0.049-in,-wall tubing used for outer tube of concentric-tube heat exchanger.
to 10% of the total heat transfer exists at the
heater section and at the heat exchanger.
Diosimi lor-Metal Loops
L. A. Mann
Aircraft Reactor Engineering Division
A loop for testing combinations of structural
metals in contact with high-velocity turbulent
liquid metals under high temperature differentials
is being developed, If combinations of materials
are found that ore satisfactory for use in liquid
metal systems, greater flexibility and ease of
construction may be attained. An optimized design,
patterned after that used for beryllium-lnconel-
sodium mass transfer tests (cf. Sec. 2, "Reflector-
Moderated Reactor"), has been developed and is
to be used first for testing combinations of lnconel
and type 316 stainless steel in sodium.
GAS- F U R N AC E HE A +-SOU RC E DE V EL 0 P M E N T
L. A. Mann
Aircraft Reactor Engineering Division
L. F. Roy"
University OF Mississippi
Several exploratory tests were made OQ cam-
mercial and QRNL-designed-and-fabricated burners
for use with the gas-furnace heat source described
previously. l 2 The heat release intensity desired
15,000
200
86.9
8.08
15.44
18.75
1 15.5
Construct ion
20% com-
plete
is on the order of 3000 Btu/ft3.sec, which is of the
same order as that attained in iet aircraft burners.
The maximum rate of heat release obtained in
the tests, 170 Btu/ft3, was obtained with the
burner designed by A. P. Fraas. The results of
these exploratory tests are presented in Table 3.2.
Although the rate of heat release contemplated in
the original design (about 3000 Btu/ft3.sec) was
not approached in these tests, it appears that
rates higher than 170 Btu/ft3.sec can be attained
by securing more rapid mixing of air and gas,
preheating the combustion-air, and providing a
positive pressure in the combustion chamber.
Additional tests are to be made.
STUDY OF THE CAVITATION PHENOMENON
W. G. Cobb A. G. Grindell
J. M. TrummeI
Aircraft Reactor Engineering Division
G. F. Wislicenus, Consultant
One of the problems associated with operating
liquid metal systems at elevated temperatures,
high flow rates, high pump speeds, and minimum
container weight is that of local boiling or cavi-
tation. Because there is little information available
'Summea ~csearch Participant.
"A. P. Fi-~iis, R. W. Bussard, R. E. McPherson, ANF'
Qutar. Frog:, Krp. jzine 10, 1954, ORNL-1729, p 23.
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