射流角和质量流量比对涡轮端壁气膜冷却特性的影响

张韦馨; 刘战胜; 杨星; 刘钊; 丰镇平

doi:10.7652/xjtuxb202104012

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射流角和质量流量比对涡轮端壁气膜冷却特性的影响

更新时间：2025-07-09

- 射流角和质量流量比对涡轮端壁气膜冷却特性的影响
- Effects of Mass Flow Ratio and Film Hole Orientation Angle on Turbine Endwall Film Cooling Characteristics
- 西安交通大学学报 2021年55卷第4期页码：107-115
- 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：
  
  : 2020-09-25。作者简介: 张韦馨(1996—),男,硕士生;刘钊(通信作者),男,副教授。基金项目: 国家科技重大专项资助项目(2017-Ⅲ-0009-0035)
- DOI：10.7652/xjtuxb202104012
  中图分类号： TK474.7
- 网络首发：2021-04-10，
  
  纸质出版：2021
- 稿件说明：
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张韦馨, 刘战胜, 杨星, 等. 射流角和质量流量比对涡轮端壁气膜冷却特性的影响[J]. 西安交通大学学报, 2021,55(4):107-115.

Effects of Mass Flow Ratio and Film Hole Orientation Angle on Turbine Endwall Film Cooling Characteristics[J]. 2021, 55(4): 107-115.
张韦馨, 刘战胜, 杨星, 等. 射流角和质量流量比对涡轮端壁气膜冷却特性的影响[J]. 西安交通大学学报, 2021,55(4):107-115. DOI： 10.7652/xjtuxb202104012.

Effects of Mass Flow Ratio and Film Hole Orientation Angle on Turbine Endwall Film Cooling Characteristics[J]. 2021, 55(4): 107-115. DOI： 10.7652/xjtuxb202104012.

摘要

为了提高实际燃机涡轮端壁的气膜冷却效率

对某航空发动机涡轮静叶端壁的气膜冷却特性进行了数值模拟研究。首先采用实验结果对湍流模型进行了校核

并验证了所研究模型的网格无关性

在此基础上研究了端壁离散气膜孔的气膜冷却特性

并采用给定实验端壁热流输入条件计算了整个端壁的换热特性; 分析了5种冷气质量流量比(1.4%、2.1%、2.7%、3.1%、3.8%)和5种气膜冷气射流角度(20°、25°、30°、35°、40°)下端壁离散气膜孔的流动特性、气膜冷却特性以及换热特性。计算结果表明:相同射流角(40°)条件下

冷气质量流量比为1.4%时

端壁平均气膜冷却效率达到0.21; 继续增大冷气质量流量比会导致气膜脱离端壁表面

使得端壁整体的气膜冷却效率下降; 随着冷气质量流量比增加

叶栅通道总压损失增加

强化了气膜孔出口处的气流掺混

增加了换热效率; 受到端壁二次流以及原有气膜孔结构的影响

气膜冷气射流角度为20°时冷却效果最佳

在相同质量流量比(1.4%)条件下

端壁平均气膜冷却效率达到0.27; 减小射流角度对端壁表面换热强度改变较小。

Abstract

The film cooling characteristics of the endwall surface of a turbine engine vane are numerically simulated to improve the cooling efficiency of the gas turbine endwall film. Firstly

the endwall film cooling performance with only discrete film holes is studied. Turbulence models are checked by experimental results

and the mesh independence of the models is verified. On this basis

the film cooling characteristics of the discrete film holes at the endwall under five mass flow ratios(1.4%

2.1%

2.7%

3.1%

and 3.8%)and five film hole orientation angles(20°

25°

30°

35°

and 40°)are studied. The heat transfer coefficients of the entire endwall are calculated by using the given experimental endwall heat flux input conditions. Calculation results show that the average adiabatic film cooling efficiency reaches to 0.21 when the mass flow ratio is 1.4% at the same injection angle(40°). A larger mass flow ratio over than 1.4% leads the coolant detach from the endwall surface

and then the film cooling efficiency of the endwall decreases. The total pressure loss of the cascade increases with the increase of the mass flow ratio. The increase of the mass flow ratio strengthens the flow mixing at the outlet of the hole and increases the heat exchange efficiency. Because of the influence of secondary endwall flow and the structure of film holes

the adiabatic film cooling effect is the highest when the film hole injection angle is 20°. Under the same mass flow ratio(1.4%)

the average film cooling efficiency of the end wall reaches 0.27. Reducing the injection angle has little effect on the heat exchange efficiency of the endwall surface.

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Keywords

references

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