Assessment of film cooling characteristics in a GOX/ kerosene rocket combustion chamber

C. Kirchberger, G. Schlieben, O. J. Haidn

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

1 Scopus citations


The knowledge on the heat transfer is crucial for the design of reliable and efficient rockets engines. Due to the high heat loads and chemical attack of the combustion chamber walls, film cooling is often applied supplementary or even as a primary cooling technique. The dominating processes determining the film effectiveness under the conditions typical for rocket combustors are still not well understood. The Institute for Flight Propulsion (LFA) operates a rocket combustion test facility which allows investigations on heat transfer and film cooling at application-relevant combustion pressures and temperatures. This paper presents results from film cooling experiments performed with two different liquid film fluids in a water cooled GOX/ kerosene rocket combustion chamber.

Original languageEnglish
Title of host publication49th AIAA/ASME/SAE/ASEE Joint PropulsionConference
StatePublished - 2013
Event49th AIAA/ASME/SAE/ASEE Joint PropulsionConference - San Jose, CA, United States
Duration: 14 Jul 201317 Jul 2013

Publication series

Name49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference


Conference49th AIAA/ASME/SAE/ASEE Joint PropulsionConference
Country/TerritoryUnited States
CitySan Jose, CA


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