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压气机叶栅中激波附面层相互作用是十分复杂的问题,由于相互作用引起分离是决定跨音速压气机性能的重要因素之一。然而迄今为止,尚未深入进行过压气机叶栅激波附面层相互作用的研究,发表的文献极少。作者经过计算和分析,说明压气机叶栅流中主要的相互作用形式是叶栅槽道中激波和湍流附面层的相互作用。作者通过分析指出,研究压气机叶栅激波附面层相互作用,不能直接应用Pearcey分离准则。作者并提出了适用于压气机叶栅的分离准则的函数关系为f(M_1,p_1/p_(L.E.),P_(r.E.)/p_2,Re_0)=O。
Compressor cascade shock wave surface layer interaction is a very complex issue, due to the interaction caused by separation is one of the important factors that determine transonic performance of the compressor. However, up to now, there has been no further study on the interaction of the compressor cascade shocks with the published literature. After calculation and analysis, the author shows that the main interaction in the compressor cascade flow is the interaction between the shock wave and the turbulent boundary layer in the cascade channel. The author points out that the Pearcey separation criterion can not be directly applied to the study of the interaction of the shock cascade in the compressor cascade. The author also proposes the function relation of f (M_1, p_1 / p_ (L.E.), P_ (r.E./p_2, Re_0) = O) which is suitable for the criterion of compressor cascade separation.