Effect of crossflow on internal heat transfer of impingement-swirl-film cooling for leading edge of turbine blade

被引：0

作者：

Han, Feng ^{[1
,2
]}

Zhang, Shuhao ^{[1
,2
]}

Chen, Jiaona ^{[1
,2
]}

Wang, Lingyang ^{[3
]}

Chen, Honghua ^{[1
,2
]}

Yang, Ling ^{[1
]}

Mao, Junkui ^{[1
]}

机构：

[1] College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing

[2] Integrated Energy Institute, Nanjing University of Aeronautics and Astronautics, Nanjing

[3] Innovation Academy for Microsatellites, Chinese Academy of Sciences, Shanghai

来源：

Hangkong Dongli Xuebao/Journal of Aerospace Power | 2025年 / 40卷 / 04期

关键词：

composite cooling; crossflow; dimensionless correlation; leading edge; swirl cooling;

D O I：

10.13224/j.cnki.jasp.20240415

中图分类号：

学科分类号：

摘要：

The asymmetric impingement-swirl-film cooling channel of a realistic turbine blade leading edge was studied. Under two conditions—constant impingement inlet Reynolds number and constant total flow rate, the effect of active crossflow on the heat transfer performance of the cooling channel was numerically investigated by varying the crossflow ratio. Dimensionless Nusselt number correlations at both operating conditions were derived through curve fitting. The results indicated that, under a constant Reynolds number of the impingement inlet, increasing the crossflow ratio enhanced the overall heat transfer performance of the impingement target surface. Specifically, when the Reynolds number was 20 000, a crossflow ratio of 2 led to a 25.8% increase in the Nusselt number compared with the no-crossflow case. Conversely, under a constant total flow rate, increasing the crossflow ratio reduced the overall heat transfer performance of the impingement target surface. When the total flow rate was 0.023 6 kg/s, a crossflow ratio of 2 resulted in a 43.3% reduction in the Nusselt number compared with the no-crossflow case. The findings demonstrated that the cooling performance in the asymmetric impingement-swirl-film cooling channel was primarily governed by the impinging jet, while the effect of crossflow convection was relatively minor. The fitted Nusselt number correlations for both scenarios can provide a valuable guidance for the design and optimization of asymmetric leading-edge cooling structures in turbine blades. © 2025 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.

引用

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