透平动叶多凹槽叶顶气膜冷却特性的研究

李冯; 贾哲; 张韦馨; 刘钊; 石䶮; 丰镇平

doi:10.7652/xjtuxb202208016

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透平动叶多凹槽叶顶气膜冷却特性的研究

—————————————————————— | 更新时间：2025-07-09

- 透平动叶多凹槽叶顶气膜冷却特性的研究
- Study on the Film Cooling Characteristics of Multi-Cavity Turbine Blade Tips
- 西安交通大学学报 2022年56卷第8期页码：149-159
- 作者机构：
  
  西安交通大学能源与动力工程学院,西安,710049
- 作者简介：
  
  : 2022-02-18。作者简介: 李冯(1995—),男,博士生
  刘钊(通信作者),男,副教授。基金项目: 国家科技重大专项项目(2017-III-0009-0035)
- 基金信息：
  
  : 2022-02-18。作者简介: 李冯(1995—),男,博士生;刘钊(通信作者),男,副教授。基金项目: 国家科技重大专项项目(2017-III-0009-0035)
- DOI：10.7652/xjtuxb202208016
  中图分类号： V231.1
- 网络首发：2022-08-10，
  
  纸质出版：2022
- 稿件说明：
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李冯, 贾哲, 张韦馨, 等. 透平动叶多凹槽叶顶气膜冷却特性的研究[J]. 西安交通大学学报, 2022,56(8):149-159.

LI Feng, JIA Zhe, ZHANG Weixin, et al. Study on the Film Cooling Characteristics of Multi-Cavity Turbine Blade Tips[J]. 2022, 56(8): 149-159.
李冯, 贾哲, 张韦馨, 等. 透平动叶多凹槽叶顶气膜冷却特性的研究[J]. 西安交通大学学报, 2022,56(8):149-159. DOI： 10.7652/xjtuxb202208016.

LI Feng, JIA Zhe, ZHANG Weixin, et al. Study on the Film Cooling Characteristics of Multi-Cavity Turbine Blade Tips[J]. 2022, 56(8): 149-159. DOI： 10.7652/xjtuxb202208016.

摘要

为了提高透平动叶叶顶的气膜冷却性能

并降低由叶顶泄漏流引起的泄漏损失

开展了多凹槽叶顶气膜冷却特性研究。采用试验测试和数值模拟相结合的方法

研究了燃气透平动叶不同结构多凹槽叶顶的气膜冷却特性与气动特性

其结构包括单凹槽、二凹槽、三凹槽和四凹槽4种叶顶形式。在主流进口雷诺数为1.75×10

条件下应用压力敏感漆技术获得了1.0、1.5和2.0等3种吹风比下多凹槽叶顶表面的气膜冷却有效度分布

并采用经过校核的数值方法辅助分析了叶顶间隙内的流场结构及其气动性能。结果发现:多凹槽叶顶内的肋片改变了叶顶的流场结构

阻挡了冷气向下游发展。相比于传统的单凹槽叶顶

四凹槽叶顶在吹风比较大时能够提高叶顶中部的冷却效果

但在叶顶中后部依旧是单凹槽叶顶的冷却效果最好。同时

多凹槽叶顶能够显著降低叶栅的气动损失

相比于传统的单凹槽叶顶

二凹槽、四凹槽叶顶总压损失系数值分别降低了17.9%、20.9%。

Abstract

To improve the film cooling performance of turbine blade tips and reduce the leakage loss induced by the leakage flow at the tips

experimental investigation and numerical simulation were conducted to study the film cooling and aerodynamic characteristics of multi-cavity turbine blade tips

including one-cavity

two-cavity

three-cavity and four-cavity blade tips. Pressure sensitive paint technique was adopted to obtain the film cooling effectiveness distributions among these multi-cavity tips under a Reynolds number of 1.75×10

of the main flow inlet and three different coolant blowing ra

tios

including 1.0

1.5 and 2.0. A turbulence-validated computational method was employed to indicate the flow field and the aerodynamic performance of the multi-cavity tips. Results show that the ribs in the multi-cavity tips can alter the flow structure and prevent the coolant moving downstream. Compared with the traditional one-cavity tip

four-cavity tip can enhance the film cooling performance in the tip mid-to-rear part. However

one-cavity tip still achieve the best film cooling effectiveness in the tip mid-to-rear part. Meanwhile

as for the aerodynamic performance

multi-cavity tips can reduce the total pressure loss effectively. Compared with the one-cavity tip

the two-cavity and three-cavity tips can reduce the loss value by 17.9% and 20.9% respectively.

关键词

Keywords

references

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