Investigation of throat film coolant for advanced LOX/RP-1 thrust chambers

Volkmann, J.; Mcleod, James; Claflin, Scott

doi:10.2514/6.1991-1979

Cited by 4 publications

(1 citation statement)

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“…The effects determining film cooling efficiency and the influences on the combustion process itself for conditions typical for rocket combustors are still not sufficiently understood. While for film cooling in gas turbines comprehensive publications exist, beside some old NASA papers 1,2 only a few investigations on film cooling in rocket engines have been carried out recently [3][4][5] . These studies are mostly focusing on nozzle cooling at limited pressures or fundamental experiments only.…”

Section: A Backgroundmentioning

confidence: 99%

Assessment of Film Cooling Characteristics in a GOX/ Kerosene Rocket Combustion Chamber

Kirchberger

Schlieben

Haidn

2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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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.

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Section: A Backgroundmentioning

confidence: 99%