低雷诺数下叶片振动对高亚声速压气机附面层流动的影响机制  

Influence mechanism of blade vibration on boundary layer flow in high subsonic compressor under low Reynolds number conditions

作　　者：陈才艳 张燕峰[1,2,3] 张建设 张英强 董旭 王名杨 卢新根[1,2,3] CHEN Caiyan;ZHANG Yanfeng;ZHANG Jianshe;ZHANG Yingqiang;DONG Xu;WANG Mingyang;LU Xingen(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;School of Energy,Power and Mechanical Engineering,North China Electric Power University,Beijing 102206,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 [4]华北电力大学能源动力与机械工程学院,北京102206

出　　处：《航空动力学报》2025年第1期477-488,共12页Journal of Aerospace Power

基　　金：国家自然科学基金(52276044)。

摘　　要：为了探索低雷诺数Re下高亚声速压气机叶片振动对附面层流动状态的影响,利用数值模拟手段分析了压气机叶片在不同振动频率下叶片表面附面层分离、再附及转捩的变化规律和流动损失的变化规律。研究表明,在Re=1.5×10~5条件下,叶片振动引起附面层垂直壁面法向的相对速度增加,使得分离后的附面层提前与主流发生掺混,促使转捩提前,此时壁面附近法向位置处的法向速度型更饱满,这提升了附面层抗分离的能力,限制了分离泡的发展。此外,叶片振动造成附面层和分离泡厚度变“薄”,这使得尾缘堆积的低能流体减少,削弱了尾缘附近流动堵塞和尾迹掺混,进而减少流动损失,改善了低Re条件下高亚声速压气机叶型的气动性能。In order to investigate the influence of high subsonic compressor blade vibration on the flow state of the boundary layer under low Reynolds number(Re)conditions,numerical simulations were conducted to analyze the rule of separation,reattachment,transition and flow loss of compressor blade surface boundary layer under different vibration frequencies.According to the simulation results,under the condition of Re=1.5×105,the increase in the normal relative velocity of the vertical wall of the boundary layer caused by blade vibration could trigger the mixing of the separated boundary layer with the mainstream in advance,which promoted the advance of transition.In this case,the normal velocity pattern at normal position near the wall was fuller,which improved the ability of the boundary layer to resist separation and limited the development of the separation bubble.In addition,the boundary layer and separation bubble thickness became“thin”due to blade vibration,which reduced the accumulation of lowenergy fluid at the trailing edge,and weakened flow blockage near the trailing edge and wakes mixing,thereby reducing flow loss and improving the aerodynamic performance of the high subsonic compressor blade under low Re conditions.

关 键 词：低雷诺数 压气机叶片 叶片振动 附面层分离 转捩 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]