张角凹坑气膜孔对双层壁气膜冷却特性的影响

汪翔宇; 许瑶; 徐孟娟; 刘钊; 丰镇平

doi:10.7652/xjtuxb202607004

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张角凹坑气膜孔对双层壁气膜冷却特性的影响

专题冷却特性研究 | 更新时间：2026-07-09

- 张角凹坑气膜孔对双层壁气膜冷却特性的影响
- Effects of Expansion Angle Crater Film Hole on the Film Cooling Characteristics of a Double-Wall Structure
- 西安交通大学学报 2026年60卷第7期页码：35-45
- 作者机构：
  
  西安交通大学能源与动力工程学院，710049，西安
  西安交通大学机械工程学院，710049，西安
- 作者简介：
  
  作者简介：汪翔宇（1992—），男，助理教授；
  刘钊（通信作者），男，教授，博士生导师。
- 基金信息：
  
  国家自然科学基金资助项目(52276037)
- DOI：10.7652/xjtuxb202607004
  中图分类号： TK474.7
- 收稿：2025-10-24，
  
  纸质出版：2026-07-10
- 稿件说明：
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汪翔宇, 许瑶, 徐孟娟, 等. 张角凹坑气膜孔对双层壁气膜冷却特性的影响[J]. 西安交通大学学报, 2026,60(7):35-45.

WANG Xiangyu, XU Yao, XU Mengjuan, et al. Effects of Expansion Angle Crater Film Hole on the Film Cooling Characteristics of a Double-Wall Structure[J]. Journal of Xi'an Jiaotong University, 2026, 60(7): 35-45.
汪翔宇, 许瑶, 徐孟娟, 等. 张角凹坑气膜孔对双层壁气膜冷却特性的影响[J]. 西安交通大学学报, 2026,60(7):35-45. DOI： 10.7652/xjtuxb202607004.

WANG Xiangyu, XU Yao, XU Mengjuan, et al. Effects of Expansion Angle Crater Film Hole on the Film Cooling Characteristics of a Double-Wall Structure[J]. Journal of Xi'an Jiaotong University, 2026, 60(7): 35-45. DOI： 10.7652/xjtuxb202607004.

摘要

为了进一步提高双层壁涡轮叶片的冷却效率，提出了一种新型的张角凹坑气膜孔，设计了3种张角（

为25°、35°、45°），分析了4种吹风比（

为0.5、1.0、1.5、2.0）下

对双层壁综合冷却效率及流场结构的影响。结果表明：相对于常规圆形气膜孔，张角凹坑气膜孔有利于气膜在流向和展向上的延伸，扩大冷气在壁面上的覆盖面积。吹风比

为0.5、1.0时，

为45°的凹坑气膜孔对双层壁冷却结构综合冷却效率改善效果最优。吹风比

为1.5、2.0时，

为25°、35°的凹坑气膜孔的综合冷却效率最好。新型张角凹坑气膜孔能够产生反向肾形涡，抑制肾形涡的发展，增强冷气的贴壁性。α越大，反向肾形涡在流向上削减的速度就越快。与常规圆形气膜孔相比，张角凹坑气膜孔增加了双层壁冷却结构的气动损失，吹风比

为0.5～1.5时，

为25°和35°凹坑气膜孔所产生的气动损失较小，仅超出常规圆形气膜孔5.07%～15.05%。该研究为气冷涡轮叶片的高冷效、低损失的气膜孔设计与选型提供了相应的数值支撑。

Abstract

To further enhance the cooling efficiency of double-wall turbine blades，a novel expansion angle crater film hole was conceived.Three expansion angles（

=25°，35°，45°）were designed，and the influences of

on the overall cooling effectiveness and flow field structure of the double-wall structure were analyzed under four blowing ratios（

=0.5，1.0，1.5，2.0）.The results indicate that，compared to conventional cylindrical film holes，the expansion angle crater film holes facilitate the extension of the film in both the streamwise and spanwise directions，thereby expanding the coverage area of the cooled air on the wall.At

= 0.5，1.0，the optimal improvement in the overall cooling effectiveness of the double-wall cooling structure was achieved with

=45°.However，at

=1.5，2.0，the crater film holes with

=25°，35°exhibited the best overall cooling performance.It was found that the novel expansion angle

crater film hole generates a counter-rotating kidney vortex pair（CRKVP），which suppresses the development of the kidney vortex and enhances the adhesion of the cooled air to the wall surface.Furthermore，the decay rate of the CRKVP in the streamwise direction increased with largerαvalues.Although the expansion angle crater film holes increased the aerodynamic loss of the double-wall cooling structure compared to conventional cylindrical film holes，the aerodynamic losses generated by the crater film holes with

=25°，35°were relatively low at

=0.5—1.5，exceeding those of conventional cylindrical film holes by only 5.07%—15.05%.These findings provide numerical support for the design and selection of film holes（with high cooling efficiency and low loss）for air-cooled turbine blades.

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