Volume 37 Issue 11
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ZOU Zhengping, XUAN Liming, FU Chao. Progress on mechanism of flow and heat transfer and modeling of turbine blade squealer tip[J]. Journal of Aerospace Power, 2022, 37（11）：2560-2573 doi: 10.13224/j.cnki.jasp.20220207
Citation: ZOU Zhengping, XUAN Liming, FU Chao. Progress on mechanism of flow and heat transfer and modeling of turbine blade squealer tip[J]. Journal of Aerospace Power, 2022, 37（11）：2560-2573 doi: 10.13224/j.cnki.jasp.20220207
shu

Progress on mechanism of flow and heat transfer and modeling of turbine blade squealer tip

doi: 10.13224/j.cnki.jasp.20220207
  • 1.

    Research Institute of Aero-Engine，Beihang University，Beijing 102206，China

  • 2.

    National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics， Beihang University，Beijing 102206，China

  • 3.

    School of Energy and Power Engineering，Beihang University，Beijing 102206，China

  • Received Date: 2022-04-13
    Available Online: 2022-09-20
    Abstract

  • According to the flow mechanism and organization method of squealer tip, the analysis of aerodynamic and heat transfer characteristics of squealer tip considering cooling, and the modeling of leakage flow of squealer tip were summarized. The results showed that the flow inside the cavity had an obvious effect on the heat transfer. There was a strong interaction between the cooling gas in the cavity and the leakage flow. Reasonable cavity shape and jet hole position can effectively improve the aerodynamic performance and reduce the heat load of the blade tip; The uncertainty of blade tip machining and aerodynamic parameters could significantly affect the performance of squealer tip. By modeling the vortex structure in the cavity, the performance prediction model of the squealer tip considering the compressibility of air jet was verified by experiment and numerical simulation results. The model can effectively evaluate the performance of the squealer tip and provide a reference for engineering design.

     

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