Theoretical Study on Film Cooling Process for Rocket Combustor

Abstract

The definition of film cooling is combined with regenerative cooling which is an efficient way to ensure the long term, safe and secure functioning of liquid rocket engines with higher heat flux densities. The liquid rocket engines need an effective wall cooling systems to reduce high heat fluxes from the hot combustion gases to the engine wall in the thrust chamber. Using liquid fuel propellant to sheet cool the interior chamber liners is one method of achieving this goal. For use in a combined convective and film-cooled combustion chamber with an accelerated hot gas, an existing film cooling model has been adapted.