Investigation on Film Cooling Performance of the Squealer Tip with Baffle in a Linear Turbine Cascade

LIU Yudong; LIU Zhao; TAO Yong; SHI Yan; FENG Zhenping

doi:10.7652/xjtuxb202505013

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Investigation on Film Cooling Performance of the Squealer Tip with Baffle in a Linear Turbine Cascade

更新时间：2025-08-26

- Investigation on Film Cooling Performance of the Squealer Tip with Baffle in a Linear Turbine Cascade
- Journal of Xi’an Jiaotong University Vol. 59, Issue 5, Pages: 130-142(2025)
- 作者机构：
  
  1.西安交通大学能源与动力工程学院， 710049，西安
  2.中国联合重型燃气轮机技术有限公司， 100015，北京
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202505013
  CLC： TK474.7
- Received：25 July 2024，
  
  Online First：08 January 2025，
  
  Published：10 May 2025
- 稿件说明：
移动端阅览
LIU Yudong, LIU Zhao, TAO Yong, et al. Investigation on Film Cooling Performance of the Squealer Tip with Baffle in a Linear Turbine Cascade[J]. Journal of Xi’an Jiaotong University, 2025, 59(5): 130-142.
DOI：

LIU Yudong, LIU Zhao, TAO Yong, et al. Investigation on Film Cooling Performance of the Squealer Tip with Baffle in a Linear Turbine Cascade[J]. Journal of Xi’an Jiaotong University, 2025, 59(5): 130-142. DOI： 10.7652/xjtuxb202505013.

摘要

为提高燃气透平动叶凹槽叶顶的气膜冷却有效度并且降低叶栅气动损失，基于平面叶栅试验台，采用压敏漆（PSP）测量技术结合数值模拟，对带挡板结构的凹槽叶顶冷却性能及叶栅气动特性进行了试验研究。分析了不同吹风比（分别为0.4、1.2、2.0）和不同挡板结构参数（挡板宽度、挡板角度和挡板高度）对叶顶气膜冷却的影响；湍流模型验证后，采用精度最高的SST

k-ω

湍流模型对叶顶气动特性进行了仿真分析。结果表明：在凹槽叶顶吸力面侧布置挡板能显著增大叶顶的气膜冷却有效度，并且随着吹风比的增大冷却有效度也有所提升。增大挡板的宽度会使得挡板下气膜孔两侧出现漩涡，该漩涡效应能够有效提升叶顶的冷却有效度；挡板角度会影响冷气冲击挡板下底面后的流向，当挡板角度为锐角时，挡板底部压力面侧会形成漩涡，使得冷气流向凹槽底部，从而提高叶顶的冷却有效度，而当挡板角度增大到钝角后，挡板上顶面与吸力面的夹角会出现漩涡，挡板对冷气的阻挡作用减弱，冷却有效度下降；挡板的高度对叶顶冷却性能无显著影响。此外，挡板结构能略微降低总压损失，减小气动损失，最大下降幅度为10.20%。该研究可为燃气透平改进叶顶结构、提高气膜冷却和气动性能提供一定的参考。

Abstract

In order to improve the film cooling effectiveness of the gas turbine squealer tips and reduce the aerodynamic loss of the cascade

an experimental investigation was conducted on the cooling performance of the squealer tip with baffle and the aerodynamic characteristics of the cascade

using pressure sensitive paint measurement technology (PSP) on a linear test cascade

in combination with numerical simulation. The effects of different blowing ratios (0.4

1.2 and 2.0) and different baffle s

tructures (with different width

angle and height) on the film cooling effectiveness at squealer tip were analyzed. After the turbulent model was validated

the SST

k-ω

turbulence model

known for its highest accuracy

was used to simulate and analyze the aerodynamic performance of the squealer tip. The results showed that the baffle could significantly increase the film cooling effectiveness of the squealer tip

and the film cooling effectiveness was also improved with the increase of the cooling gas blowing ratio. An increasing in the width of the baffle would cause vortices on both sides of the cooling gas holes under the baffle

effectively improving the film cooling effectiveness on the squealer tip. The angle of the baffle could affect the flow direction of the cooling gas after impinging the bottom surface under the baffle. When the baffle mounted in an acute angle

vortices would be formed on the pressure side of the bottom of the baffle

allowing the cooling gas to flow towards the bottom of the squealer

thereby improving the film cooling effectiveness on the squealer tip. When the angle increased up to an obtuse angle

vortices would appear on the angle between the top surface of baffle and the suction side of the squealer

weakening the blocking effect of the baffle on the cooling gas

and reducing the film cooling effectiveness on the squealer tip. The height of the baffle had no significant effect on the film cooling effectiveness of the squealer tip. In addition

the baffle could slightly reduce the total pressure loss and the aerodynamic loss

with a maximum reduction of 10.20%. This study could provide a reference for gas turbines design on improving the film cooling and aerodynamic performance.

关键词

Keywords

references

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