单转子压气机出口三维流场紊流特性  

3-D Turbulent Characteristics at Exit of Compressor Rotor Passage

作　　者：马宏伟[1] 蒋浩康[1] 

机构地区：[1]北京航空航天大学404教研室,北京100083

出　　处：《航空动力学报》2000年第1期31-34,共4页Journal of Aerospace Power

基　　金：国家攀登计划项目B 资助

摘　　要：单转子压气机设计状态出口叶尖通道中部、叶根吸力面角区和转子尾迹内具有较强的紊流脉动,泄漏涡是造成尖部气流掺混的主要因素。近失速状态通道内气流脉动明显增强,并沿周向和径向呈现出较大的梯度,叶尖通道中部的紊流强度分布证实了气流剧烈交混的发生,0.87 叶高和0.25 叶高吸力面附近的强紊流中心来源于叶背附面层分离形成的旋涡。在出口测量截面上紊流强度3 个分量的最大值,径向分量最大,轴向分量次之,切向分量最小。流量减小,紊流强度尤其是径向紊流强度有大幅度的提高。The three-dimensional turbulent flow field at the exit of an axial single rotor compressor has been measured in detail with single-slant hot-wire probe.In the design condition,substantial turbulent pulsations mainly exist in the tip mid-passage,wake and the corner between the suction surface and the hub,and the tip leakage vortex plays a leading role in the tip flow mixing.In the near stall condition,the flow becomes more turbulent,which shows the strong flow mixing in the tip region,turbulence intensities,especially the radial turbulence intensity,increase rapidly;the flow separations of the boundary layer on the suction surface occur at 0 25 span and 0 87 span.At the rotor exit,the radial turbulence intensity is the largest,and the axial one is the second.

关 键 词：压气机 转子出口 紊流 三维流动 流场 

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] TH45[机械工程—机械制造及自动化]