Investigation of Film Cooling in a High Pressure LOX/GH2 Subscale Combustion Chamber

High accuracy predictions of combustion side heat transfer and cooling are major design criteria for developing advanced rocket engine combustion chambers for future high performance rocket engines. Experimental investigations of film cooling processes under real engine like conditions with a newly developed subscale LOX/GH2 combustion chamber has been performed at DLR site Lampoldshausen, using gaseous hydrogen as a film coolant. In this paper, a short overview of therefore used measurement techniques and instrumentation are presented and, furthermore, first experimental film cooling results are discussed.