上游台阶结构对跨声速透平叶栅端壁气膜冷却性能的影响

白波 1; 李志刚 1; 李军 1; 2

doi:10.7652/xjtuxb202005001

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上游台阶结构对跨声速透平叶栅端壁气膜冷却性能的影响

更新时间：2025-07-09

- 上游台阶结构对跨声速透平叶栅端壁气膜冷却性能的影响
- Investigation on the Effect of Upstream Step Geometry on Endwall Film Cooling Characteristics of a Transonic Turbine Cascade
- 西安交通大学学报 2020年54卷第5期页码：1-8
- 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：
- 基金信息：
  
  : 2019-11-16。作者简介: 白波(1995—),男,博士生;李志刚(通信作者),男,副教授,博士生导师。基金项目: 国家自然科学基金资助项目(51776152)
- DOI：10.7652/xjtuxb202005001
  中图分类号： TK474.4
- 网络首发：2020-05-10，
  
  纸质出版：2020
- 稿件说明：
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白波 1, 李志刚 1, 李军 1, 等. 上游台阶结构对跨声速透平叶栅端壁气膜冷却性能的影响[J]. 西安交通大学学报, 2020,54(5):1-8.

Investigation on the Effect of Upstream Step Geometry on Endwall Film Cooling Characteristics of a Transonic Turbine Cascade[J]. 2020, 54(5): 1-8.
白波 1, 李志刚 1, 李军 1, 等. 上游台阶结构对跨声速透平叶栅端壁气膜冷却性能的影响[J]. 西安交通大学学报, 2020,54(5):1-8. DOI： 10.7652/xjtuxb202005001.

Investigation on the Effect of Upstream Step Geometry on Endwall Film Cooling Characteristics of a Transonic Turbine Cascade[J]. 2020, 54(5): 1-8. DOI： 10.7652/xjtuxb202005001.

摘要

为了评估上游台阶结构对端壁气膜冷却性能的影响

采用商用CFD软件ANSYS FLUENT数值研究了上游后向台阶结构对跨声速透平叶栅端壁上游双排离散气膜孔冷却效率的影响。模拟某工业燃气透平真实运行工况(进口湍流度T

=16%、出口马赫数Ma

=0.85、出口雷诺数Re

=1.5×10

)

采用基于两类热边界条件模型的壁面换热系数和绝热冷却效率数值预测方法

计算分析了在设计工况吹风比为2.5下

具有不同上游台阶高度(ΔH=0

6.78

10 mm)的跨声速透平叶栅端壁热负荷分布、气膜冷却效率分布和近端壁二次流场结构。研究结果表明:上游台阶结构改变了近端壁流场

在台阶下游形成强度较大的空腔涡等复杂涡系结构

显著影响了端壁的热负荷和冷却气膜覆盖分布; 随上游台阶高度的增加

叶栅通道上游端壁传热逐渐增强

形成显著的条状高传热区; 端壁冷却效率呈现先增大后减小的变化趋势

在ΔH=6.78 mm时

端壁气膜覆盖效果最好; 在ΔH=10 mm时

上游离散孔冷却射流被限制在近吸力面三角区域

端壁冷却效率低于无进口台阶结构。

Abstract

To evaluate the influences of the upstream step geometry on the endwall film cooling performance of the upstream double-row film holes

the commercial CFD software ANSYS FLUENT was used to predict the endwall film cooling efficiency. The endwall thermal load distribution

film cooling efficiency distribution and the secondary flow field were calculated and analy-ed for four different upstream step heights(-H=0

6.78

10 mm)at the practical design condition of an industrial gas turbine with the blowing ratio -

=2.5

inlet turbulence T

=16%

exit Mach number Ma

=0.85

exit Reynolds number Re

=1.5-10

by using the numerical method based on two types of thermal boundaries. Results show that flow filed near endwall is significantly influenced by the upstream step geometry due to the complex vortex structure such as the large cavity vortex downstream of the step

which obviously changes the endwall thermal load and film cooling

关键词

Keywords

references

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