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A dual-cooled hydrogen-oxygen rocket engine heat transfer analysisThe potential benefits of simultaneously using hydrogen and oxygen as rocket engine coolants are described. A plug-and-spool rocket engine was examined at heat fluxes ranging from 9290 to 163,500 kW/sq m, using a combined 3D conduction/advection analysis. Both counterflow and parallel flow cooling arrangements were analyzed. The results indicate that a significant amount of heat transfer to the oxygen occurs, reducing both the hot-side wall temperature of the rocket engine and also reducing the exit temperature of the hydrogen coolant. The total heat transferred to the oxygen was found to be largely independent of the oxygen coolant flow direction. The reduction in combustion chamber wall temperatures at throttled conditions is especially desirable since the analysis indicates that double temperature maxima, one at the throat and another in the combustion chamber, occur with a traditional hydrogen-only cooled engine. A dual-cooled engine eliminates any concern for overheating in the combustion chamber.
Document ID
19910059533
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kacynski, Kenneth J.
(NASA Lewis Research Center Cleveland, OH, United States)
Kazaroff, John M.
(NASA Lewis Research Center Cleveland, OH, United States)
Jankovsky, Robert S.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 15, 2013
Publication Date
June 1, 1991
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 91-2211
Accession Number
91A44156
Distribution Limits
Public
Copyright
Other

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