Circumferential Behavior of Tangential Film Cooling and Injector Wall Compatibility in a High Pressure LOX/GH2 Subscale Combustion Chamber

Kurzfassung

Within the present investigations of high pressure combustion at DLR Lampoldshausen, circumferential film cooling effectiveness in combination with injector wall compatibility have been studied in a LOX/GH2 fired subscale combustion chamber using gaseous hydrogen as a film coolant, injected in tangential direction in close proximity of the injector head. With the aim of future first stage high performance rocket combustion chambers, the combustion pressure levels have been varied up to 11.5 MPa with real engine like conditions. Experimental investigations have shown remarkable circumferential variations of thermal head load due to injector design and film effectiveness which remain existent far downstream from the film injection point and injector face plate, and which are more pronounced at higher chamber pressure levels.