Single Channel Testing for Characterization of the Direct Gas Cooled Reactor and the SAFE‐100 Heat Exchanger

Abstract

Experiments have been designed to characterize the coolant gas flow in two space reactor concepts that are currently under investigation by NASA Marshall Space Flight Center and Los Alamos National Laboratory: the direct‐drive gas‐cooled reactor (DDG) and the SAFE‐100 heatpipe‐cooled reactor (HPR). For the DDG concept, initial tests have been completed to measure pressure drop versus flow rate for a prototypic core flow channel, with gas exiting to atmospheric pressure conditions. The experimental results of the completed DDG tests presented in this paper validate the predicted results to within a reasonable margin of error. These tests have resulted in a re‐design of the flow annulus to reduce the pressure drop. Subsequent tests will be conducted with the re‐designed flow channel and with the outlet pressure held at 150 psi (1 MPa). Design of a similar test for a nominal flow channel in the HPR heat exchanger (HPR‐HX) has been completed and hardware is currently being assembled for testing this channel at 150 psi. When completed, these test programs will provide the data necessary to validate calculated flow performance for these reactor concepts (pressure drop and film temperature rise). © 2004 American Institute of Physics