涡轮叶片前缘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

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涡轮叶片前缘复合冷却特性实验研究

更新时间：2026-07-29

- 涡轮叶片前缘复合冷却特性实验研究
- Experimental Investigation on the Combined Cooling Characteristics of the Leading Edge of Turbine Vanes
- 西安交通大学学报 2026年
- 作者机构：
  
  1.西安交通大学热流科学与工程教育部重点实验室，能源与动力工程学院，710049，西安
  2.中国航空发动机研究院，101300，北京
- 作者简介：
- 基金信息：
- DOI：
  中图分类号： V231.1
- 收稿：2026-02-06，
  
  修回：2026-04-14，
  
  录用：2026-05-25，
- 稿件说明：
移动端阅览
马阳泽龙, 程想, 冀文涛, 等. 涡轮叶片前缘复合冷却特性实验研究[J/OL]. 西安交通大学学报, 2026.

MA Yangzelong, CHENG Xiang, JI Wentao, et al. Experimental Investigation on the Combined Cooling Characteristics of the Leading Edge of Turbine Vanes[J/OL]. JOURNAL OF XI’AN JIAOTONG UNIVERSITY, 2026.
马阳泽龙, 程想, 冀文涛, 等. 涡轮叶片前缘复合冷却特性实验研究[J/OL]. 西安交通大学学报, 2026. DOI：

MA Yangzelong, CHENG Xiang, JI Wentao, et al. Experimental Investigation on the Combined Cooling Characteristics of the Leading Edge of Turbine Vanes[J/OL]. JOURNAL OF XI’AN JIAOTONG UNIVERSITY, 2026. DOI：

摘要

为研究叶片前缘吸力面的气膜冷却及冲击冷却特性，选用完整金属叶片为研究对象，设计具有单排典型冲击/气膜复合冷却结构的叶片进行了中温条件下的流动换热性能实验。实验通过红外热成像的方法测试冷却效率，研究了吹风比及主流雷诺数在展向、型线方向上，对叶片前缘吸力面的复合冷却性能的影响。结果表明，提高吹风比可以强化冲击/气膜复合冷却，但吹风比达到1.2后，由于气膜覆盖形成的热防护已较为充分，对冷却效果的提升作用有限；由于在前缘吸力面叶表曲率较大，气膜孔后会出现展向平均综合冷却效率快速下降区域

S/L大于0.25部分占总降幅的40%；在中吹风比时，主流雷诺数1.8×105、2.8×105、3.8×105在叶片相同位置处的展向平均综合冷却效率处呈1、0.75、0.64的倍数关系；叶片整体平均综合冷却效率随吹风比的变化集中于低吹风比0.2-0.8范围内，接近线性增长，占总提升的75%；且在不同吹风比时，叶片整体平均综合冷却效率均受主流雷诺数的广泛影响。针对涡轮叶片的前缘吸力面在不同吹风比、主流雷诺数下，进行复合冷却时出现的冷却效率差异以及冷却不均问题，进行了单排冲击/气膜复合冷却结构叶片的流动换热实验。通过红外热成像法，具体研究并分析了在叶片前缘展向、流向上，吹风比和主流雷诺数两参数耦合影响下的复合冷却效果。结果表明，提高吹风比可以强化前缘的冲击/气膜复合冷却，主流雷诺数则相反；前缘展向上的冷却均匀程度主要受吹风比影响，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%；前缘流向上，由于叶表曲率变化，膜孔后s/L≥0.25部分出现的综合冷却效率快速下降40%的区间；而对整体平均综合冷却效率，会在吹风比0.2到0.8范围内提高线性倍增，同时随每1×10

的主流雷诺数改变有近30%的变化。该研究可为后续优化叶片前缘冷却相关参数配置，以及提升复合冷却均匀性提供参考。

(对应第一位审稿人的第1、2个意见，第二位审稿人的第2个意见)

Abstract

In order to investigate the characteristics of film and impingement cooling compound method on the suction surface of the leading edge of the vane

the flow and heat transfer performance of the vane with a single row of typical impingement/film cooling structure was tested by selecting the real metal vane. The cooling effectiveness of the vane was tested by infrared thermal imaging

and the effects of blowing ratio and mainstream Reynolds number on the comprehensive cooling performance of the suction surface at the leading edge of the vane in the spanwise and profile directions were studied. The results show that increasing the blowing ratio can enhance the impingement/film cooling

but

after the blowing ratio reaches 1.2

the enhancement of the cooling effectiveness is more constrained due to the fact that the thermal protection provided by the film coverage is more adequate; at the leading edge of the suction surface

due to the large curvature

the spanwise-averaged integrated cooling effectiveness after the film hole will decrease rapidly

40% of total reduction in regions with S/L greater than 0.25; At medium blowing ratios

when the mainstream Reynolds number is 1.8×10⁵

2.8×10⁵

and 3.8×10⁵

the spanwise-averaged integrated cooling effectiveness at the same positions are observed to exhibit a multiplicative relationship of 1

0.75

and 0.64

respectively. The change in the overall-averaged integrated cooling effectiveness of the vane with blowing ratio is concentrated in the low blowing ratio range of 0.2-0.8

with a near linear increase

and the improvement accounts for 75% of the total improvement; And at different blowing ratios

the mainstream Reynolds number all have a significant impact on the overall-averaged integrated cooling effectiveness of the vane. To investigate the differences in cooling effectiveness and the cooling non-uniformity on the suction side near the leading edge of a turbine vane under different blowing ratios and mainstream Reynolds numbers

flow and heat transfer experiments were conducted on a metal vane with a single-row impingement/film combined cooling configuration. Using infrared thermography

the combined cooling performance under the coupled effects of blowing ratio and mainstream Reynolds number was systematically investigated and analyzed in both the spanwise and streamwise directions near the vane leading edge. The results indicate that increasing the blowing ratio enhances the impingement/film combined cooling at the leading edge

whereas increasing the mainstream Reynolds number produces the opposite effect. The cooling uniformity in the spanwise direction near the leading edge is mainly governed by the blowing ratio. And when the blowing ratio incr

eases from 0.8 to 1.6

the variation rate of the spanwise peak cooling effectiveness decreases from 65.4% to 56.6%. In the streamwise direction near the leading edge

owing to the variation in vane surface curvature

a region with a rapid 40% decrease in overall cooling effectiveness appears downstream of the film hole for

≥0.25. For the overall-averaged cooling effectiveness

it increases almost linearly within the blowing ratio range from 0.2 to 0.8

while it changes by nearly 30% for every variation of 1×10

in the mainstream Reynolds number. This study provides a reference for the subsequent optimization of cooling-related parameter configurations at the vane leading edge and for improving the uniformity of combined cooling.

(对应第一位审稿人的第1、2个意见)

关键词

Keywords

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