射流角对带小翼凹槽叶顶冷却传热性能的影响

吴琛琦; 何坤; 晏鑫

doi:10.7652/xjtuxb202207004

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射流角对带小翼凹槽叶顶冷却传热性能的影响

专题流动与换热 | 更新时间：2025-07-09

- 射流角对带小翼凹槽叶顶冷却传热性能的影响
- Effect of Ejection Angle on Film Cooling and Heat Transfer of Winglet-Squealer Tip
- 西安交通大学学报 2022年56卷第7期页码：27-37
- 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：
  
  : 2022-02-04。作者简介: 吴琛琦(1997—),女,硕士生
  晏鑫(通信作者),男,教授,博士生导师。基金项目: 国家自然科学基金资助项目(52076165)
- 基金信息：
  
  : 2022-02-04。作者简介: 吴琛琦(1997—),女,硕士生;晏鑫(通信作者),男,教授,博士生导师。基金项目: 国家自然科学基金资助项目(52076165)
- DOI：10.7652/xjtuxb202207004
  中图分类号： TK474.7
- 网络首发：2022-07-10，
  
  纸质出版：2022
- 稿件说明：
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吴琛琦, 何坤, 晏鑫. 射流角对带小翼凹槽叶顶冷却传热性能的影响[J]. 西安交通大学学报, 2022,56(7):27-37.

WU Chenqi, HE Kun, YAN Xin. Effect of Ejection Angle on Film Cooling and Heat Transfer of Winglet-Squealer Tip[J]. 2022, 56(7): 27-37.
吴琛琦, 何坤, 晏鑫. 射流角对带小翼凹槽叶顶冷却传热性能的影响[J]. 西安交通大学学报, 2022,56(7):27-37. DOI： 10.7652/xjtuxb202207004.

WU Chenqi, HE Kun, YAN Xin. Effect of Ejection Angle on Film Cooling and Heat Transfer of Winglet-Squealer Tip[J]. 2022, 56(7): 27-37. DOI： 10.7652/xjtuxb202207004.

摘要

采用数值方法研究了发动机工况下透平级带压力侧小翼的凹槽叶顶冷却传热性能

计算获得了5种流向射流角、3种向压力侧偏转的气膜孔数量、4种向压力侧偏转的射流角布置时的带小翼凹槽叶顶的传热系数与气膜冷却效率

实现了带小翼凹槽叶顶冷却传热性能的提升。研究结果表明:倾斜的冷却射流能有效提升透平级带压力侧小翼凹槽叶顶的传热与冷却性能; 随着流向射流角的增大

叶顶传热系数先减小后增大

当流向射流角为120°时

相对于竖直射流

叶顶面积平均传热系数减小了28.26%、气膜冷却效率增大了33.86%; 靠近前缘的5个中弧线冷却孔向压力侧偏转能改善凹槽前部的冷却性能

与所有中弧线冷却孔均向吸力侧偏转的方案相比

叶顶面积平均传热系数减小15.65%、气膜冷却效率增大9.51%; 当靠近前缘的5个中弧线冷却孔向压力侧偏转的角度为60°时

小翼叶顶的冷却传热性能最佳

与竖直射流相比

其面积平均传热系数减小38.84%、气膜冷却效率增大42.24%

且冷却流对带小翼凹槽叶顶覆盖的均匀性显著提高。

Abstract

Numerical methods were adopted to study the film cooling and heat transfer performance on the pressure-side(P.S.)winglet-squealer tip of a turbine stage under engine condition. The heat transfer coefficient and film cooling effectiveness on the winglet-squealer tip were computed at five different streamwise ejection angles

three different numbers of cooling hole with P.S. defection

and four different P.S. defection angles. The improvement of the film cooling effect and mitigation of heat transfer on the winglet-squealer tip were achieved based on the present study. The results show that the inclined coolant ejection is effective to improve the film cooling effect and reduce the heat transfer on the P.S. winglet-squealer tip of a turbine stage. As the streamwise ejection angle increases

the heat transfer coefficient on tip decreased at first and then increased. If the streamwise ejection angle equals to 120 degree

the area-averaged heat transfer coefficient on the tip surface decreased by 28.26%

and the area-averaged film cooling effectiveness increased by 33.86% as compared with the vertical ejection case. Adjusting the ejection angles for five tip cooling holes near leading edge towards the P.S. is beneficial for film cooling effect improvement on the cavity floor near the front part. Compared to the case that all tip holes deflection towards the S.S.

the area-averaged heat transfer coefficient on the tip surface decreased by 15.65%

and the area-averaged film cooling effectiveness increased by 9.51%. As the ejection angles for five middle-camber holes near leading edge towards the P.S. equal to 60 degree

the best film cooling and heat transfer performance on the winglet-squealer tip are achieved. In this case

the area-averaged heat transfer coefficient on tip surface decreased by 38.84%

and the area-averaged film cooling effectiveness increased by 42.24%

as compared with the vertical ejection case. Moreover

the uniformity of film coolant coverage on the winglet-squealer tip is improved significantly.

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