Volume 39 Issue 6
Jun.  2024
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JIANG Hongmei, ZHANG Ziyang, LU Shaopeng. Influence of trailing edge designs of squealer tips on aerodynamic performance of high-pressure turbine[J]. Journal of Aerospace Power, 2024, 39(6):20230512 doi: 10.13224/j.cnki.jasp.20230512
Citation: JIANG Hongmei, ZHANG Ziyang, LU Shaopeng. Influence of trailing edge designs of squealer tips on aerodynamic performance of high-pressure turbine[J]. Journal of Aerospace Power, 2024, 39(6):20230512 doi: 10.13224/j.cnki.jasp.20230512

Influence of trailing edge designs of squealer tips on aerodynamic performance of high-pressure turbine

doi: 10.13224/j.cnki.jasp.20230512
  • Received Date: 2023-08-06
    Available Online: 2024-01-25
  • In this article, full cavity squealer tip and several pressure side and suction side cutback blade tips were designed, their detailed flow field and aerodynamic performance were compared with full cavity squealer tip numerically, including vortices inside cavity and flows around blade tip trailing edge, differences in tip leakage flow rate, downstream total pressure loss and entropy rise. The result indicated that pressure side cutback designs caused the cavity vortex leak earlier compared with full cavity tip, a small vortex formed at cut region leading to increase in total pressure loss of 7.1% at most; flow inside cavity left at cut region for suction side cutback designs instead of crossing over cavity wall, downstream total pressure loss was relatively smaller, with the reduction of 4.6% at most. Compared with full cavity and pressure side cutback squealer tip, suction side cutback designs have better aerodynamic performance.

     

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