Investigation of Kerosene Supercritical Film Cooling Techniquesfor High Pressure Thrust Chamber
The kerosene supercritical film cooling techniques for the thrust chamber of LOX/kerosene staged combustion cycle engine was investigated with the aim of understanding the effect of the physical property and film local injection structure. The numerical simulation was conducted using the same equations to describe the process of the flow and heat transfer between the core and film stream, in which the hot gas and the kerosene film treated as the same fluid only with their own different physical property. The local flow near the outlet of film cooling slot has been simulated for adiabatic wall temperature to compare the design parameters of the protruding structure (aft lip) by the Code Fluent 6.0 with κ-ε two-equation turbulence model. The results indicate that the step and angle of film ring injection have greatly influence on the local flow of the cooling rings by comparison with circumfluence area of the 6 typical local small step structures and the local temperature and concentration distributions. The adherence of the film to the wall and optimum local structure is of benefit to the heat protection of high pressure chamber.
Supercritical Fluid Film Cooling Heat Transfer Numerical Simulation Thrust Chamber
Chen Jianhua Lu Gang Zhang Guitian Zhou Lixin Sun Hongming
School of Aerospace, North Western Polytechnical Univ., Xian, China Xian Aerospace Propulsion Institute, Xian, China School of Aerospace, North Western Polytechnical Univ., Xian, China Xian Aerospace Propulsion Inst
国际会议
The 11th International Space Conference of Pacific-basin Societies(第11届环太平洋国际航天会议)
北京
英文
94-101
2007-05-16（万方平台首次上网日期，不代表论文的发表时间）