Numerical simulation of supersonic gaseous film cooling

The SSTk^-ω turbulence model was employed to simulate numerically 3Dviscous 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,the adiabatic film cooling effectiveness is enhanced with the increase of the blowing rate.Through different cooling channels,the film cooling has different distribution rules,the cuboids channel is the worst one.The film cooling effectiveness is different between2 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.