Assessment of Analytical Models for Film Cooling in a Hydrocarbon/ GOX Rocket Combustion Chamber

The understanding of the mechanisms of heat transfer and advanced cooling techniques is a key for mastering the designing of reliable and efficient rocket combustion chambers. However, the effects determining film cooling efficiency as well as influences on the combustion process itself under typical conditions for rocket engines are still insufficiently understood. Therefore, the Institute for Flight Propulsion (LFA) of the Technische Universitat Munchen operates a rocket combustor test facility which allows testing at application-relevant conditions. The experimental work is complemented by numerical investigations, where in day-to-day operations also analytical and semi-empirical correlations are used. This paper presents an assessment of different analytical and semiempirical film cooling models known from open literature and their application to kerosene film cooling in a GOX/ kerosene combustion chamber. Nomenclature

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