Volume 40 Issue 1
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CHEN Caiyan, ZHANG Yanfeng, ZHANG Jianshe, et al. Influence mechanism of blade vibration on boundary layer flow in high subsonic compressor under low Reynolds number conditions[J]. Journal of Aerospace Power, 2025, 40（1）：20230086 doi: 10.13224/j.cnki.jasp.20230086
Citation: CHEN Caiyan, ZHANG Yanfeng, ZHANG Jianshe, et al. Influence mechanism of blade vibration on boundary layer flow in high subsonic compressor under low Reynolds number conditions[J]. Journal of Aerospace Power, 2025, 40（1）：20230086 doi: 10.13224/j.cnki.jasp.20230086
shu

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

doi: 10.13224/j.cnki.jasp.20230086
  • 1.

    Key Laboratory of Light-Duty Gas-Turbine，Institute of Engineering Thermophysics，Chinese Academy of Sciences，Beijing 100190，China

  • 2.

    School of Aeronautics and Astronautics，University of Chinese Academy of Sciences，Beijing 100049，China

  • 3.

    Innovation Academy for Light-duty Gas Turbine，Chinese Academy of Science，Beijing 100190，China

  • 4.

    School of Energy，Power and Mechanical Engineering，North China Electric Power University，Beijing 102206，China

  • Received Date: 2023-02-19
    Available Online: 2024-03-22
    Abstract

  • 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 low-energy 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.

     

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