关键词: 跨音速压气机;转子;失速;泄漏;数值仿真

Abstract: The single-passage steady and multi-passages steady/unsteady numerical simulation of the transonic axial-flow compressor-NASA Rotor 37 were investigated.The numerical results agreed well with experimental test data with estimation of the global performance.For the multi-passages unsteady computation,detailed analysis of the internal flow field with the NASA Rotor 37 led to some preliminary conclusion for unsteady behavior of the tip leakage flow,the interaction of the vortex and the shock wave and trigger spike type rotating stall inception.It is the forward spillage of the tip leakage flow at the leading edge that induces the spike stall inception.The rotating stall cell is first generated at the blade tip region and the rotating speed is about 80% of the rotor speed.As the mass flow ratio decreases,the rotating stall cell is far developed.At the stalled passages,the passage shock is fully detached from the leading edge,and the reverse tip clearance flow is initiated at trailing edge plane.When the rotor is fully stalled,the rotating stall cell is covered almost 4 passages in blade to blade direction,and it occupies nearly half of the blade span.

Key words: Transonic compressor;Rotor;Stalling;Leakage;Numerical simulation