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

被引:0
|
作者
Zhang S. [1 ,2 ]
Li G. [1 ,2 ]
Liu H. [1 ,2 ]
Kang Z. [1 ,3 ]
Zhang Y. [1 ,2 ]
Lu X. [1 ,2 ]
机构
[1] Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing
[2] School of Aeronautics and Astronautics, University of Chinese Academy of Sciences, Beijing
[3] School of Energy, Power and Mechanical Engineering, North China Electric Power University, Beijing
来源
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2024年 / 39卷 / 03期
关键词
film cooling; film cooling effectiveness; multi region compound angle; passage secondary flow; turbine guide vane;
D O I
10.13224/j.cnki.jasp.20220177
中图分类号
学科分类号
摘要
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. © 2024 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.
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