关键词: 跨音速压气机;激波;损失;模型;数值仿真

Abstract: A physics-based shock loss model combined with streamline curvature is presented and implemented to better approximate the flow fields of transonic axial compression systems.The shock loss model accounts for shock geometry changes from near-choke to near-stall.The importance of accounting for shock geometry and loss changes with operating conditions is clearly demonstrated.Data from a two-stage transonic axial compressor provides the basis for experimental comparisons.Overall and spanwise comparisons demonstrate that the shock loss model can improve performance prediction,especially for adiabatic efficiency prediction,indicating better understanding for the blade effects and the flow physics.

Key words: Transonic compressor;Shock wave;Loss;Model;Numerical simulation