亚声速扩压平面叶栅尾迹动态压力场测量与分析  

Measurement and Analysis on Dynamic Pressure Field of Subsonic Compressor Plane Cascade Wake

作　　者：幸晓龙[1,2] 马昌友[2] 梁俊[2] 黄磊[2] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016 [2]中国燃气涡轮研究院,四川江油621703

出　　处：《燃气涡轮试验与研究》2014年第6期13-17,共5页Gas Turbine Experiment and Research

摘　　要：为研究叶片在不同攻角下引起的气流分离对叶栅出口气流紊流度的影响,借助动态压力测量设备和测试技术,完成了某扩压平面叶栅在进口马赫数为0.677,攻角分别为0°、-10°和+8°三种典型工况下,尾迹非定常流动的测量。通过测量尾迹区域沿栅距方向和轴向的尾迹动态压力,并对动态压力数据进行时域分析,得到叶栅尾迹非定常流动的时均总压和压力脉动云图,揭示出尾迹区流动过程,同时还与叶栅的气动性能和气流稳定性进行了关联。Using dynamic pressure measuring equipment and technology, dynamic pressure in the wake re？gion of plane compressor cascade under the incidence of 0°,-10°,＋8° with 0.677 inlet Mach number was measured to study the impact of flow separation on cascade outlet flow turbulence. Pressure measured in the tangential direction and axial direction was processed in time-domain analysis. Dimensionless time average total pressure and pressure fluctuation contour were obtained through the process. Flow structure in the wake region was revealed and related to aerodynamic characteristics and flow stability.

关 键 词：平面叶栅 尾迹测量 动态压力 时域分析 稳定性 

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]