Experimentally and Numerically Investigated Film Cooling in a Subscale Rocket Combustion Chamber

Kurzfassung

Film cooling is a widely-used cooling technique to reduce the hot gas side wall temperatures in turbines and combustors of airbreathing engines as well as in rocket thrust chambers. Prepared in the framework of the German National Technology Programme on Cryogenic Rocket Engines (TEKAN II), the paper presents the comparison of experimental film cooling data and heat flux results with numerical simulations. The experiments have been performed at the European Research and Technology Test Facility P8 at DLR Lampoldshausen, whereas the simulations have been carried out at Astrium GmbH, Munich, applying the spray combustion code Rocflam-II. Experimental data and numerical simulations show good agreement within the investigated range of chamber pressures and film cooling mass flow rates.