Numerical Simulation of Supersonic Gaseous Film Cooling
The SST κ-ω turbulence model is employed to compute the 3D viscous mixing flow field in order to investigate the supersonic gaseous film cooling injected from different cooling channels tangentially. Results show that blowing rate is an important factor,along with the increase of which,the adiabatic film cooling effectiveness is enhanced. Through different cooling channels, the film cooling conduces diverse effectiveness distributing, the cuboids channel is the worst one. The film cooling effectiveness is different between the 2 kinds of centerlines in the discrete coolant channels, which can be avoided by the β angle. The distribution of adiabatic film cooling effectiveness on the wall indicates that the outspread hole and column with β are better in the foreside, but decline more quickly. 3 valuable parameters are introduced to evaluate the supersonic film cooling.
Supersonic Gaseous Film Cooling Numerical Simulation Adiabatic Film Cooling Effectiveness
Wang Jian Sun Bing
School of Astronautics, Beijing University of Aeronautics and Astronautics,Beijing 100083,China School of Astronautics, Beijing University of Aeronautics and stronautics,Beijing 100083,China
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
290-296
2007-05-16（万方平台首次上网日期，不代表论文的发表时间）