Investigation of Film Cooling Efficiency in a High Pressure Subscale LOX/H2 Combustion Chamber

Kurzfassung

Film cooling performance in a LOX/H2 subscale combustion chamber was investigated. This paper presents both a new test specimen and measurement technique, developed and successfully tested by the Institute of Space Propulsion, as well as experimental results. The new measurement method provides detailed information about the cooling film efficiency and thermal load distribution on the hot inner surfaces at real rocket engine conditions and pressures up to 11.5 MPa. The presented investigations have been performed at the European Research and Technology Test Facility.