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Numerical Prediction of Spray Combustion and Film Cooling in a Liquid Rocket Engine  

박태선 (한국항공우주연구원 로켓엔진연구그룹)
류철성 (한국항공우주연구원 로켓엔진연구그룹)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.6, no.2, 2002 , pp. 9-17 More about this Journal
Abstract
For turbulent spray combustion flows a coupled numerical procedure was developed, This method was discretized by using generalized curvilinear coordinates to handle complex geometries. The preconditioning and eigenvalue rescaling techniques were employed to provide efficient convergences over a wide range of subsonic Mach numbers. The accuracy was validated by simulating the laminar cavity flow. The film cooling effect of a liquid rocket engine (KSR-III) were investigated by a spray combustion analysis. The film cooling showed a negative effect on the combustion efficiency. In the combustion chamber wall, the film cooling effect was revealed to be promoted by the production of fuel rich zone.
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