Experimental Investigation of heat transfer Processes in sub- and supersonic part of the film cooled high pressure LOX/H2 combustion chamber

Optimization of heat transfer management is a key issue in designing a combustion chamber. Film cooling is one of the most effective cooling methods used in combustion chambers of liquid propellant rocket engines. The reliable construction und dimensioning of this cooling method requires detailed knowledge of the all processes which govern the heat transfer under real rocket engine operating conditions. This paper presents the test specimen and the measurement technique that has been developed und successfully used by the Institute of Space Propulsion for investigations of the influence of injector-wall interactions on heat transfer in a subscale combustion chamber as well the measurement results. The presented investigations have been performed at the European Research and Technology Test Facility P8 for cryogenic subscale rocket engines.