小型轴流压气机静叶排出口尾迹流动特性  

Flow Characteristics of Stator Wake in Small Axial Compressor

作　　者：项效镕[1] 刘波[1] 王庆伟[1] 陈云永[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《航空学报》2009年第11期2045-2051,共7页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(50476071)

摘　　要：基于小型轴流压气机实验台,运用热线风速仪(HWA),对不同转速、流量工况下,静叶排出口尾迹流动特性进行实验研究。对同一工况下尾迹区时均速度及湍流度分布规律的研究表明:受前排动叶的影响,静叶排不同叶展截面处尾迹大小、尾迹中心位置存在着明显差异;沿展向叶根、叶尖附近湍流度明显高于主流区。同时,还对不同工况下静叶排尾迹区各统计参数的变化规律进行了研究,较为系统地总结出轴流压气机工况变化对静叶排出口尾迹大小、尾迹中心位置、尾迹区湍流强度以及雷诺应力大小的影响。An experimental study of the stator blade wake in a small axial compressor is performed by using a hot-wire anemometer （HWA） under different rotating speeds and mass flow conditions. The mean velocity and turbulence intensity distribution among the stator blade wake region under the same operating condition indicate that the size of the wake region and the position of the wake core vary at different span sections owing to the effect of the upstream rotor blades. The turbulence intensity is significantly higher near the hub and shroud than in the main flow field. A study of the variation of the statistical parameters under different operation conditions reveals systematically the influence of the changing operating conditions of the axial compressor on wake-region size, wake-core position, turbulence intensity and Reynolds stresses.

关 键 词：热线风速仪 轴流压气机 尾迹 湍流度 雷诺应力 

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]