Film Cooling of Accelerated Flow in a Subscale Combustion Chamber

Experimental investigations have been carried out to examine film cooling effectiveness of an accelerated hot gas In a subscale rocket combustion chamber. In support or future first-stage high-performance rocket combustion chambers, a Vulcain-2-like test case has been examined with combustion pressure levels tip to 12 MPa. The effectiveness of an almost tangentially injected film of hydrogen with an initial temperature of approximate to 280 K has been determined. Axial distributions of temperature were measured Inside the copper liner as well as on the chamber surface in the convergent and divergent parts of the nozzle segment. An existing film cooling model has been modified for application fit it combined convective and film-cooled combustion chamber with an accelerated hot gas. The new model predicts film cooling effectiveness at different combustion-chamber pressures Had film blowing rates at sub-, trans-, and supersonic conditions.