基于表面热膜测试的低速风扇附面层流动研究  

Flow in Boundary Layer of Low-Speed Fan Based on Hot Film

作　　者：周仕佶 周创鑫 赵胜丰[1,2,3] 韩戈 ZHOU Shi-ji;ZHOU Chuang-xin;ZHAO Sheng-feng;HAN Ge(Key Laboratory of Light-Duty Gas-Turbine,Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China;School of Aeronautics and Astronautics,University of Chinese Academy of Sciences,Beijing 100049,China;Innovation Academy for Light-Duty Gas Turbine,Chinese Academy of Science,Beijing 100190,China)

机构地区：[1]中国科学院工程热物理研究所轻型动力重点实验室,北京100190 [2]中国科学院大学航空宇航学院,北京100049 [3]中国科学院轻型动力创新研究院,北京100190

出　　处：《推进技术》2023年第5期257-264,共8页Journal of Propulsion Technology

基　　金：国家科技重大专项(J2019-Ⅱ-0004-0024);民用飞机科研专项(MJ-2018-D-27)。

摘　　要：压气机转子叶片表面附面层分离/再附、转捩机制较为复杂,数值模拟方法受到了极大的限制,因此需要新的试验技术测量旋转状态下转子叶片表面附面层的发展状态。本文采用表面热膜测试技术对某风扇叶片表面附面层分离/再附、转捩等流动现象进行了试验研究,获得了旋转状态下风扇叶片表面的准壁面剪切应力。试验结果表明,在上游尾迹周期性扫掠的作用下,叶片表面附面层转捩、再附点提前,分离泡范围减小。表面热膜测试技术可较为准确地捕捉旋转叶片表面附面层的转捩、再附点,为旋转状态下转子表面附面层的流动测量提供了一种解决途径。In the rotating state,the separation/re-attachment and transition mechanism of the surface boundary layer of the compressor rotor blade is complicated,and the numerical simulation method is greatly limit⁃ed.To investigate the flow details in the fan blade channel under the rotating state,an experimental technique of measuring the rotating blade with the hot film was proposed to study the development process of the surface boundary layer of the fan blade.With the help of the hot film test technology,the quasi-wall shear stress on the surface of the fan blade in the rotating state is obtained.The experimental result shows that under the action of pe⁃riodical sweep of the wake,the boundary layer transition and reattachment point advance,and the separation bubble range decreases.The hot film can accurately capture transition and re-attachment points of the surface boundary layer of rotating blades,which provides a solution for flow measurement of rotor surface boundary layer in the rotating state.

关 键 词：压气机 风扇 转子 表面热膜 低速 转捩 试验 附面层 

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]