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Heat Transfer in Rocket Engine Combustion Chambers and Regeneratively CooledNozzles

机译：火箭发动机燃烧室和再生冷却喷嘴的传热

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A conjugate heat transfer computational fluid dynamics (CFD) model to describeregenerative cooling in the main combustion chamber and nozzle and in the injector faceplate region for a launch vehicle class liquid rocket engine was developed. An injector model for sprays which treats the fluid as a variable density, single-phase media was formulated, incorporated into a version of the FDNS code, and used to simulate the injector flow typical of that in the Space Shuttle Main Engine (SSME). Various chamber related heat transfer analyses were made to verify the predictive capability of the conjugate heat transfer analysis provided by the FDNS code. The density based version of the FDNS code with the real fluid property models developed was successful in predicting the streamtube combustion of individual injector elements.

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