Volume 39 Issue 3
Mar.  2024
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ZHANG Shen, LI Guoqing, LIU Hao, et al. Multi region compound angle film cooling characteristics on pressure side of turbine guide vane[J]. Journal of Aerospace Power, 2024, 39(3):20220177 doi: 10.13224/j.cnki.jasp.20220177
Citation: ZHANG Shen, LI Guoqing, LIU Hao, et al. Multi region compound angle film cooling characteristics on pressure side of turbine guide vane[J]. Journal of Aerospace Power, 2024, 39(3):20220177 doi: 10.13224/j.cnki.jasp.20220177

Multi region compound angle film cooling characteristics on pressure side of turbine guide vane

doi: 10.13224/j.cnki.jasp.20220177
  • Received Date: 2022-03-31
    Available Online: 2023-10-30
  • In view of the phenomenon that the secondary flow in the channel causes the deflection of the film trajectory on the pressure surface, the concept of multi region compound angle along the spanwise direction was proposed. Numerical simulation was conducted to investigate the film cooling characteristics of turbine guide vane HS1A. The influences of secondary flow, compound angle and blowing ratio on the film cooling characteristics were analyzed under the condition of turbine outlet Reynolds number of 2.3×105. The results showed that the secondary flow in the near endwall had the ability to promote the spanwise coverage of the film, which improved the cooling effectiveness downstream the film hole outlet compared with the mid blade region, but also intensified the mixing of the jet and the mainstream, and reduced the effective coverage length of the film; according to the secondary flow in different spanwise regions, the film hole compound angle in each region was finely arranged, which can correct all the deflection angles of the film trajectory to 0°, and the average film cooling effectiveness was increased by 10.42%; the compound angle cooling model had good applicability within the range of blowing ratio of 0.5−1.0. When the blowing ratio increased to 1.3, the film trajectory could deflect reversely.

     

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