跨音压气机叶栅的激波结构模型及损失

在分析讨论激波与附面层相互作用和栅后背压引起激波形状及强度变化的基础上，给出了考虑激波／附面层相互作用及栅后背压的跨音叶栅激波结构的物理数学模型。应用本文所提出的模型分析了跨音叶栅的激波损失，其结果和实验结果一致。激波损失的精确得出，使得将激波与附面层相互作用所引起的流动分离损失从流动总损失中分离出来成为可能，有助于了解激波与附面层相互作用引起流动分离的机理。

SHOCK MODEL AND SHOCK LOSSES IN TRANSONIC COMPRESSOR CASCADES

The shock structure assumed by the Mille r-Lewis-Hartmann model is greatly differ ent from the actual situation at higher Mach numbers because of the strong shock /boundary layer interaction,and the over predicted shock losses.This paper presen ts a semi-empirical analytical shock str ucture model in which the shock/turbulen t boundary layer interaction and the bac k pressure are considered.The shock loss es estimated by the presented shock mode l are much lower than those by the M-L-H model and agree with experiments very w ell at higher inlet Mach numbers.The str ong shock/boundary layer interaction may lead to flow separation on the suction surface.The flow separation due to stron g shock/boundary layer interaction is al so discussed in this paper.