尾迹影响下有复合角扇形孔涡轮叶片表面的气膜冷却效率实验研究

李继宸 1; 朱惠人 1; 陈大为 1; 陈刚 2; 周道恩 1

doi:10.7652/xjtuxb201909022

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尾迹影响下有复合角扇形孔涡轮叶片表面的气膜冷却效率实验研究

更新时间：2025-07-09

- 尾迹影响下有复合角扇形孔涡轮叶片表面的气膜冷却效率实验研究
- Experimental Study on Film Cooling Effectiveness of the Turbine Blade with Compound-Angled Fan-Shaped Holes under Wake Influence
- 西安交通大学学报 2019年53卷第9期页码：167-175
- 作者机构：
  
  西北工业大学动力与能源学院,西安,710072
- 作者简介：
- 基金信息：
  
  : 2019-03-28。作者简介: 李继宸(1996—),男,硕士生;朱惠人(通信作者),男,教授,博士生导师。基金项目: 国家重点基础研究发展规划资助项目(2013CB035702)
- DOI：10.7652/xjtuxb201909022
  中图分类号： V231.1
- 网络首发：2019-09-10，
  
  纸质出版：2019
- 稿件说明：
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李继宸 1, 朱惠人 1, 陈大为 1, 等. 尾迹影响下有复合角扇形孔涡轮叶片表面的气膜冷却效率实验研究[J]. 西安交通大学学报, 2019,53(9):167-175.

Experimental Study on Film Cooling Effectiveness of the Turbine Blade with Compound-Angled Fan-Shaped Holes under Wake Influence[J]. 2019, 53(9): 167-175.
李继宸 1, 朱惠人 1, 陈大为 1, 等. 尾迹影响下有复合角扇形孔涡轮叶片表面的气膜冷却效率实验研究[J]. 西安交通大学学报, 2019,53(9):167-175. DOI： 10.7652/xjtuxb201909022.

Experimental Study on Film Cooling Effectiveness of the Turbine Blade with Compound-Angled Fan-Shaped Holes under Wake Influence[J]. 2019, 53(9): 167-175. DOI： 10.7652/xjtuxb201909022.

摘要

为研究尾迹影响下带有复合角扇形孔的涡轮叶片的气膜冷却效率变化规律

利用压敏漆技术获得了不同质量流量比、不同尾迹斯特劳哈尔数(0、0.12、0.36)下的涡轮叶片表面气膜冷却效率分布。研究结果表明:气膜孔复合角有利于射流的横向扩散

孔下游射流的覆盖面积较大; 在无尾迹条件下

质量流量比的增加使得带有复合角气膜孔的涡轮叶片前缘与压力面大部分区域的气膜冷却效率提高

使得吸力面气膜冷却效率下降

吸力面靠近叶顶的低气膜冷却效率区域面积变小; 在尾迹条件下

质量流量比的增加使得前缘、压力面以及吸力面靠近尾缘区域的气膜冷却效率提高

使得吸力面其他区域的气膜冷却效率降低; 尾迹会使叶片表面气膜冷却效率显著降低

在尾迹斯特劳哈尔数为0.36的条件下

小质量流量比时叶片表面气膜冷却效率的平均降幅为35%

大质量流量比时平均降幅为26%

气膜冷却效率的下降幅度减小。

Abstract

The film cooling effectiveness of the turbine blade with compound-angled fan-shaped holes was measured by the pressure sensitive paint technique.The wake's Strouhal number was varied from 0 to 0.36 and three mass flux ratios were determined.Results show that the compound-angled holes can enhance the lateral spreading of coolant

and the injection has a wider coverage area without wakes.The increase of the mass flux ratio causes an increase in the film cooling effectiveness over the leading edge and most area of the pressure surface with compound-angled holes

but a decrease on the suction surface.The increase of mass flux ratio also reduces the area near the tip on the suction side

where the film coverage is insufficient under wake influence

and causes an increase in the film cooling effectiveness over the leading edge

the pressure surface and the suction surface near the trailing edge

but decreases this effectiveness on the mid-chord region of the suction surface.The wake causes a

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Keywords

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