涡轮叶片前缘冲击/气膜复合冷却特性实验研究

马阳泽龙; 程想; 冀文涛; 朱江楠; 温泉; 陶文铨

doi:10.7652/xjtuxb202609012

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涡轮叶片前缘冲击/气膜复合冷却特性实验研究

更新时间：2026-09-04

- 涡轮叶片前缘冲击/气膜复合冷却特性实验研究
- Experimental Study on Combined Impingement/Film Cooling Characteristics at the Leading Edge of a Turbine Vane
- 西安交通大学学报 2026年60卷第9期页码：120-130
- 作者机构：
  
  西安交通大学热流科学与工程教育部重点实验室，710049，西安
  西安交通大学能源与动力工程学院，710049，西安
  中国航空发动机研究院，101300，北京
- 作者简介：
  
  作者简介：马阳泽龙（2000—），男，硕士生；
  冀文涛（通信作者），男，教授，博士生导师。
- 基金信息：
  
  国家科技重大专项资助项目(J2019-Ⅲ-0007-0050);三维强化结构表面有机工质相变换热微观机理研究(52476089)
- DOI：10.7652/xjtuxb202609012
  中图分类号： V231.1
- 收稿：2026-02-06，
  
  网络首发：2026-06-23，
  
  纸质出版：2026-09-10
- 稿件说明：
移动端阅览
马阳泽龙, 程想, 冀文涛, 等. 涡轮叶片前缘冲击/气膜复合冷却特性实验研究[J]. 西安交通大学学报,2026,60 (9):120-130. https://doi.org/10.7652/xjtuxb202609012.

MAYang zelong, CHENG Xiang, JI Wentao, et al. Experimental Study on Combined Impingement/Film Cooling Characteristics at the Leading Edge of a Turbine Vane[J]. Journal of Xi'an Jiaotong University,2026,60 (9):120-130. https://doi.org/10.7652/xjtuxb202609012.
马阳泽龙, 程想, 冀文涛, 等. 涡轮叶片前缘冲击/气膜复合冷却特性实验研究[J]. 西安交通大学学报,2026,60 (9):120-130. https://doi.org/10.7652/xjtuxb202609012. DOI：

MAYang zelong, CHENG Xiang, JI Wentao, et al. Experimental Study on Combined Impingement/Film Cooling Characteristics at the Leading Edge of a Turbine Vane[J]. Journal of Xi'an Jiaotong University,2026,60 (9):120-130. https://doi.org/10.7652/xjtuxb202609012. DOI：

摘要

为研究涡轮叶片前缘在不同工况下进行冲击/气膜复合冷却的综合冷却效率以及冷却均匀性差异，对在前缘吸力面具有典型单排冲击/气膜复合冷却结构的真实叶型金属叶片，进行了中温（412 K）、中压（300 kPa）工况吹风实验。通过红外热成像法，完整且可视地测试了前缘叶表温度并得到综合冷却效率分布，定量研究了叶片前缘在展向、流向上，0.2～2.0范围吹风比和1.8×10

～3.8×10

范围主流雷诺数耦合影响下的复合冷却效果，总结了相关冷却特性。研究结果表明：叶片前缘的冲击/气膜复合冷却在研究参数范围内，前缘展向上出现了不同程度的冷却不均现象，高综合冷却效率区域集中于冷却气流进气侧展向无量纲位置

≥0.5区域；且当吹风比由0.8提升至1.6时，展向冷却峰值变化率从65.4%减小至56.6%，改变主流雷诺数影响综合冷却效率曲线形状分布不明显；前缘流向上，由于叶表曲率变化，气膜孔后流向无量纲位置

≥0.25部分出现综合冷却效率快速下降40%的区间；整体平均综合冷却效率在0.2≤

≤0.8范围内随吹风比提高近似线性倍增，而当主流雷诺数由1.8×10

增至3.8×10

时，不同吹风比下整体平均综合冷却效率降低约35.0%～54.3%。该研究可为后续优化叶片前缘冷却相关参数配置、提升复合冷却均匀性提供参考。

Abstract

To investigate the overall cooling effectiveness and differences in cooling uniformity of combined impingement/film cooling at the leading edge of a turbine vane under different operating conditions

blowing tests are conducted under medium-temperature and mediu

m-pressure conditions of 412 K and 300 kPa on a real-profile metallic vane with a typical single-row combined impingement/film cooling configuration on the leading-edge suction surface.The leading-edge surface temperature is fully visualized and measured using infrared thermography

and the overall cooling effectiveness distribution is obtained.The combined cooling performance in the spanwise and streamwise directions is quantitatively investigated under the coupled effects of blowing ratios ranging from 0.2 to 2.0 and mainstream Reynolds numbers ranging from 1.8×10

to 3.8×10

and the corresponding cooling characteristics are summarized.It is shown that

within the investigated parameter range

different degrees of spanwise cooling non-uniformity occur at the vane leading edge

and regions of high overall cooling effectiveness are concentrated on the coolant-inlet side at

≥0.5.When the blowing ratio increases from 0.8 to 1.6

the spanwise cooling peak variation rate decreases from 65.4% to 56.6%

while changes in the mainstream Reynolds number have no obvious effect on the shape of the overall cooling effectiveness distribution.In the streamwise direction

due to variations in vane surface curvature

a region in which the overall cooling effectiveness rapidly decreases by approximately 40% occurs downstream of the film holes at

≥0.25.The overall-averaged integrated cooling effectiveness increases approximately linearly and nearly doubles with the blowing ratio in the range of 0.2 ≤

≤0.8

whereas it decreases by approximately 35.0%—54.3% at different blowing ratios when the mainstream Reynolds number increases from 1.8 × 10

to 3.8 × 10

.The results provide a reference for optimizing the cooling parameter configuration at turbine vane leading edges and improving combined cooling uniformity.

关键词

Keywords

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