Investigation into Heat Transfer and Film Cooling Performance at Pressure-Side Winglet-Squealer Tip in a Turbine Stage

doi:10.7652/xjtuxb202203015

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Investigation into Heat Transfer and Film Cooling Performance at Pressure-Side Winglet-Squealer Tip in a Turbine Stage

更新时间：2025-07-09

- Investigation into Heat Transfer and Film Cooling Performance at Pressure-Side Winglet-Squealer Tip in a Turbine Stage
- Vol. 56, Issue 3, Pages: 147-159(2022)
- 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：
- DOI：10.7652/xjtuxb202203015
  CLC： TK474.7
- Online First：10 March 2022，
  
  Published：2022
- 稿件说明：
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Investigation into Heat Transfer and Film Cooling Performance at Pressure-Side Winglet-Squealer Tip in a Turbine Stage[J]. 2022, 56(3): 147-159.
DOI：

Investigation into Heat Transfer and Film Cooling Performance at Pressure-Side Winglet-Squealer Tip in a Turbine Stage[J]. 2022, 56(3): 147-159. DOI： 10.7652/xjtuxb202203015.

摘要

采用数值方法研究了发动机工况下燃气透平第一级动叶带压力侧小翼的凹槽叶顶冷却传热性能

分析了7种小翼结构(等截面小翼、扭曲型小翼等)对透平级气动性能与传热系数分布的影响

对比了单排气膜孔、双排气膜孔条件下传统凹槽叶顶、无压力侧肩壁凹槽叶顶、带压力侧小翼凹槽叶顶的冷却传热效果。结果表明:传统凹槽叶顶槽底存在高传热区

合理的压力侧小翼结构设计能有效消除槽底高传热区、降低凹槽叶顶的平均传热系数; 相对于传统凹槽叶顶

带圆角扭曲型小翼凹槽叶顶的平均传热系数下降了约16.45%。叶顶气膜孔能有效降低叶顶的平均传热系数

且双排孔结构下叶顶气膜冷却效率有明显提升。对于单排气膜冷却孔结构

带压力侧小翼凹槽叶顶气膜冷却效率优势不明显

可通过加入压力侧气膜孔提升其传热与冷却性能; 在双排孔冷却结构下

带压力侧小翼凹槽叶顶平均传热系数比传统凹槽叶顶减小0.76%

比无压力侧肩壁凹槽叶顶减小7.84%

气膜冷却效率比传统凹槽叶顶增大9.13%

比无压力侧肩壁凹槽叶顶增大9.6%。

Abstract

Numerical simulation methods were adopted to investigate the heat transfer and film cooling effect at the pressure-side winglet-squealer tip in the first stage of a gas turbine. The effects of seven different tip geometries(e.g.uniform cross-section winglet and distortion winglet)on the aerodynamic performance of turbine stage and the heat transfer coefficient distributions at the tip were analyzed. The film cooling and heat transfer performances at the conventional squealer tip

non-pressure-side rim tip and pressure-side winglet tip with two different hole arrangements(single row of hole-array and double rows of hole-array)were compared. The result shows that a high heat transfer area appears on the cavity floor of the conventional squealer tip. A proper design of pressure-side winglet is able to effectively eliminate the high heat transfer area on the cavity floor and also reduce the averaged heat transfer coefficient at the squealer tip. Compared with the conventional squealer tip

the averaged heat transfer coefficient at the distorted winglet tip with round corners is reduced by about 16.45%. The single row of tip cooling holes has a significant effect on reducing the averaged heat transfer coefficient of squealer tips

while the film cooling effectiveness at different squealer tips is significantly improved with the double rows of hole-arrays. For the single row of hole-array cases

the advantage of film cooling effect on the winglet-squealer tip is not obvious. The heat transfer and film cooling effect can be improved significantly by adding film cooling holes at the blade pressure side. With both tip and pressure-side cooling hole-arrays

the averaged heat transfer coefficient at the winglet-squealer tip is about 0.76% lower than that of the conventional squealer tip

and 7.84% lower than that of non-pressure side rim tip. The film cooling effectiveness at the winglet-squealer tip is about 9.13% higher than that of the conventional squealer tip

and 9.6% higher than that of the non-pressure side rim tip.

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references

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State Key Laboratory for Manufacturing System Engineering, Xi'an Jiao tong University

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