Investigation of the cooling film distribution in liquid rocket engine
doi: 10.5028/jatm.2011.03022711

Luís Antonio Silva*
Instituto de Aeronáutica e Espaço
São José dos Campos/SP – Brasil
silvalas@iae.cta.br

*author for correspondence

Abstract:

This study presents the results of the investigation of a cooling method widely used in the combustion chambers, which is called cooling film, and it is applied to a liquid rocket engine that uses as propellants liquid oxygen and kerosene. Starting from an engine cooling, whose film is formed through the fuel spray guns positioned on the periphery of the injection system, the film was experimentally examined, it is formed by liquid that seeped through the inner wall of the combustion chamber. The parameter used for validation and refinement of the theoretical penetration of the film was cooling, as this parameter is of paramount importance to obtain an efficient thermal protection inside the combustion chamber. Cold tests confirmed a penetrating cold enough cooling of the film for the length of the combustion chamber of the studied engine.

Keywords:

Cooling film, Rocket engine, Liquid engine.

J. Aerosp.Technol. Manag., São José dos Campos, Vol.3, No.2, pp. 171-178, May-Aug., 2011
Received: 09/06/11
Accepted: 04/07/11