Influence of turbine stator blade profiles and film cooling holes optimization on the aerodynamic and cooling performances

LU Shao-peng; CHI Zhong-ran; WANG Long-fei; CAI Le; WANG Song-tao; FENG Guo-tai; WANG Zhong-qi

doi:10.13224/j.cnki.jasp.2014.06.007

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Influence of turbine stator blade profiles and film cooling holes optimization on the aerodynamic and cooling performances

更新时间：2026-07-07

- Influence of turbine stator blade profiles and film cooling holes optimization on the aerodynamic and cooling performances
- Issue 6, (2014)
- 作者机构：
  
  1. 哈尔滨工业大学能源科学与工程学院,哈尔滨,150001
  2. 清华大学热能工程系,北京,100084
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2014.06.007
  CLC：
- Published：2014
- 稿件说明：
移动端阅览
卢少鹏, 迟重然, 王龙飞, 蔡乐, 王松涛, 冯国泰, 王仲奇. 涡轮静叶叶型与气膜孔优化对气动与冷却性能影响[J]. 航空动力学报, 2014, (6): 1301-1311. doi: 10.13224/j.cnki.jasp.2014.06.007

LU Shao-peng, CHI Zhong-ran, WANG Long-fei, et al. Influence of turbine stator blade profiles and film cooling holes optimization on the aerodynamic and cooling performances[J]. 2014, (6).
卢少鹏, 迟重然, 王龙飞, 蔡乐, 王松涛, 冯国泰, 王仲奇. 涡轮静叶叶型与气膜孔优化对气动与冷却性能影响[J]. 航空动力学报, 2014, (6): 1301-1311. doi: 10.13224/j.cnki.jasp.2014.06.007 DOI：

LU Shao-peng, CHI Zhong-ran, WANG Long-fei, et al. Influence of turbine stator blade profiles and film cooling holes optimization on the aerodynamic and cooling performances[J]. 2014, (6). DOI： 10.13224/j.cnki.jasp.2014.06.007.

摘要

为研究气膜冷却涡轮叶片中叶型与气膜孔参数变化对涡轮静叶性能的影响，利用气膜冷却涡轮多目标优化平台对存在多列气膜孔的静叶进行多目标优化.获得在优化变量允许范围内针对气动效率与传热效果以及高温目标函数的Pareto前沿解集，整体性能得到了提高，不同方案中气动效率最高提升0.35%，叶片表面温度最大下降0.74%，高温函数降低的最大幅值为45.71%.结果表明：气动效率提升的主要原因是后弯角的提升使得叶型和二次流损失下降；接近驻点处前缘气膜孔方向的改变导致的冷气分流是叶片根部和前缘附近压力侧的冷却情况得到改善的主要原因.

Abstract

To study the influence of blade profiles and film cooling holes' parameter changes on the performance of the turbine blade

a blade stator with multi-row film cooling holes was optimized by multi-objective optimization algorithm to get the Pareto set; the overall performance of the blade was improved. The maximum aerodynamic efficiency increased by 0.35%; the maximum wall average temperature decrease was 0.74%; the maximum decrease of the high temperature function was 45.71%. The result shows that the increase of the backward curved angle can reduce the blade loss and second flow loss. The cooling effect improvement of the region near the leading edge is mainly due to the direction change of the film cooling holes near the leading edge stagnation point

as the direction change makes the cooling gas distribution reasonable.

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