Assessment of Film Cooling Characteristics in a GOX/ Kerosene Rocket Combustion Chamber

The knowledge on the heat transfer is crucial for the design of reliable and efficient rockets engines. Due to the high heat loads and chemical attack of the combustion chamber walls, film cooling is often applied supplementary or even as a primary cooling technique. The dominating processes determining the film effectiveness under the conditions typical for rocket combustors are still not well understood. The Institute for Flight Propulsion (LFA) operates a rocket combustion test facility which allows investigations on heat transfer and film cooling at application-relevant combustion pressures and temperatures. This paper presents results from film cooling experiments performed with two different liquid film fluids in a water cooled GOX/ kerosene rocket combustion chamber.