压气机不同状态下转子出口三维紊流流场  

3D TURBULENT FLOW AT COMPRESSOR ROTOR EXITUNDER DIFFERENT FLOW CONDITIONS

作　　者：马宏伟[1] 蒋浩康[1] 

机构地区：[1]北京航空航空大学

出　　处：《航空动力学报》1997年第3期268-272,共5页Journal of Aerospace Power

基　　金：国家攀登计划资助

摘　　要：用单斜热丝、圆柱单孔高频压力探针等手段，详细测量了单级压气机转子出口的三维紊流流场，揭示压气机在不同流量状态下转子出口的流动结构和紊流特性。Detailed measurements of three-dimensional turbulent flow field at the exit of an axial flow single-stage compressor rotor were made under different conditions.The flow structures were surveyed with both hot-wire probe and high frequency pressure probe.Under the design condition,substantial blockage,loss and turbulence mainly emerge in the tip mid-passage,in the wake and the corner between the suction surface and the hub,and the tip leakage vortex exists in the mid-passage at the exit.When the mass flow reduces,the flow becomes more turbulent.As a result,flow mixing is more,and the leakage vortex is far away from the suction surface,that leads to more substantial blockage,loss and turbulence in the tip region.Under the near stall condition,the radial migration of the blade suction surface boundary layer and the tangential migration of the endwall flow play a more important role in the flow field of the passage.

关 键 词：压气机 转子 紊流流动 航空发动机 三维 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]