压气机转子通道内尖区三维平均流场  

THREE-DIMENSIONAL FLOW FIELD INSIDE A COMPRESSOR ROTOR TIP REGION

作　　者：马宏伟[1] 蒋浩康[1] 

机构地区：[1]北京航空航天大学

出　　处：《航空动力学报》1997年第2期167-171,共5页Journal of Aerospace Power

基　　金：国家攀登计划资助

摘　　要：在低速大尺寸压气机试验台上，借助旋转四坐标全电动探针位移机构，用锥形五孔压力探针分别测量压气机设计状态和近失速状态转子通道内尖区的三维平均流场。An experimental study of the three-dimensional flow field inside the tip region of a low-speed,large-scale axial-flow compressor rotor has been completed.With the help of a rotating four-coordinate probe traverse mechanism,the measurements were conducted with a five-hole conical probe in both design condition and near stall condition.The results indicate that the tip leakage vortex plays a decisive role in the tip region flow in the design condition,leading to substantial flow loss and blockage in the passage.In near stall condition,flow separation occurs on the blade suction surface while radial migration of the boundary layer on the suction surface is strong,which makes more low-energy fluid accumulate at the corner between the casing annual wall and the suction surface.A corner vortex is induced by the tip leakage flow, and the low-energy fluid migrates to the pressure side due to the effect of the leakage vortex.Strong flow mixing among the corner vortex,the leakage vortex,the boundary layer on the casing wall and the main flow occurs at median part of the passage,which leads to substantial deficiencies of relative total pressure and relative velocity.

关 键 词：压气机 转子 端部效应 三维边界层 

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]