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http://dx.doi.org/10.6108/KSPE.2012.16.5.037

Transient Thermal Analysis on Wall Temperature Change of Rocket Engine Combustion Chamber Considering Film-Cooling  

Ha, Seong-Up (한국항공우주연구원 미래로켓연구팀)
Lee, Seon-Mi (한국항공우주연구원 미래로켓연구팀)
Moon, Il-Yoon (한국항공우주연구원 미래로켓연구팀)
Lee, Soo-Yong (한국항공우주연구원 미래로켓연구팀)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.16, no.5, 2012 , pp. 37-46 More about this Journal
Abstract
The calculation model for heat transfer analysis of rocket engine combustion chamber considering film-cooling has been established. Convective, radiative heat transfers and film-cooling effect in combustion chamber were evaluated using empirical equations especially for rocket engine combustors, and for heat transfer outward from chamber wall general convective and radiative equations were applied. Structural grid has been generated inside chamber wall for FVM calculations, and transient thermal analyses were carried out by time-marching techniques. LOx/kerosene rocket engine with chamber pressure of 50 bar has been analysed, and it is shown that, in that case, the film-cooling less than 4% remarkably contributes to reduce wall temperature, but the effect of the effect of film-cooling more than about 4% is not significantly increased.
Keywords
Rocket Engine; Heat Transfer; Convection; Radiation; Film Cooling; Transient;
Citations & Related Records
Times Cited By KSCI : 4  (Citation Analysis)
연도 인용수 순위
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