透平级带压力侧小翼凹槽叶顶的传热与气膜冷却性能研究

吴琛琦; 何坤; 晏鑫

doi:10.7652/xjtuxb202203015

您当前的位置：

首页 >

文章列表页 >

透平级带压力侧小翼凹槽叶顶的传热与气膜冷却性能研究

更新时间：2025-07-09

- 透平级带压力侧小翼凹槽叶顶的传热与气膜冷却性能研究
- Investigation into Heat Transfer and Film Cooling Performance at Pressure-Side Winglet-Squealer Tip in a Turbine Stage
- 西安交通大学学报 2022年56卷第3期页码：147-159
- 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：
  
  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：
  
  : 2021-09-09。作者简介: 吴琛琦(1997—),女,硕士生;晏鑫(通信作者),男,教授。基金项目: 国家自然科学基金资助项目(52076165)
- DOI：10.7652/xjtuxb202203015
  中图分类号： TK474.7
- 网络首发：2022-03-10，
  
  纸质出版：2022
- 稿件说明：
移动端阅览
吴琛琦, 何坤, 晏鑫. 透平级带压力侧小翼凹槽叶顶的传热与气膜冷却性能研究[J]. 西安交通大学学报, 2022,56(3):147-159.

Investigation into Heat Transfer and Film Cooling Performance at Pressure-Side Winglet-Squealer Tip in a Turbine Stage[J]. 2022, 56(3): 147-159.
吴琛琦, 何坤, 晏鑫. 透平级带压力侧小翼凹槽叶顶的传热与气膜冷却性能研究[J]. 西安交通大学学报, 2022,56(3):147-159. DOI： 10.7652/xjtuxb202203015.

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.

关键词

Keywords

references

YARAS M, ZHU Yingkang, SJOLANDER S A. Flow field in the tip gap of a planar cascade of turbine blades [J]. Journal of Turbomachinery, 1989, 111(3): 276-283.

HAN J C, DUTTA S, EKKAD S. Gas turbine heat transfer and cooling technology [M]. New York, USA: Taylor Francis, 2000.

KWAK J S, HAN J C. Heat transfer coefficient and film-cooling effectiveness on the squealer tip of a gas turbine blade [C]∥ASME Turbo Expo 2002: Power for Land, Sea, and Air. New York, NY, USA: ASME, 2002: 1073-1082.

LEDEZMA G A, ALLEN J, BUNKER R S. An experimental and numerical investigation into the effects of squealer blade tip modifications on aerodynamic performance [C]∥ASME 2013 Turbine Blade Tip Symposium. New York, NY, USA: ASME, 2013: V001T03A002.

PAPA M, GOLDSTEIN R J, GORI F. Effects of tip geometry and tip clearance on the mass/heat transfer from a large-scale gas turbine blade [J]. Journal of Turbomachinery, 2003, 125(1): 90-96.

CHEON J H, LEE S W. Winglet geometry effects on tip leakage loss over the plane tip in a turbine cascade [J]. Journal of Mechanical Science and Technology, 2018, 32(4): 1633-1642.

YAN Xin, HUANG Yan, HE Kun, et al. Numerical investigations into the effect of squealer-winglet blade tip modifications on aerodynamic and heat transfer performance [J]. International Journal of Heat and Mass Transfer, 2016, 103: 242-253.

ZHOU Chao, HODSON H, TIBBOTT I, et al. The aerothermal performance of a cooled winglet tip in a high pressure turbine cascade [J]. Journal of Turbomachinery, 2013, 135(3): 031005.

KWAK J S, HAN J C. Heat transfer coefficients and film cooling effectiveness on the squealer tip of a gas turbine blade [J]. Journal of Turbomachinery, 2003, 125(4): 648-657.

黄琰, 晏鑫, 何坤, 等. 气膜孔分布对凹槽叶顶传热和冷却性能的影响 [J]. 西安交通大学学报, 2016, 50(5): 101-107.

HUANG Yan, YAN Xin, HE Kun, et al. Effect of cooling-hole distributions on heat transfer and cooling effectiveness on turbine blade tip [J]. Journal of Xi'an Jiaotong University, 2016, 50(5): 101-107.

YAN Xin, HUANG Yan, HE Kun. Effect of ejection angle and blowing ratio on heat transfer and film cooling effect on a winglet tip [J]. International Journal of Heat and Mass Transfer, 2018, 125: 357-374.

WANG Haichao, TAO Zhi, ZHOU Zhiyu, et al. A study for the film cooling performance on the turbine blade suction side tip region under rotating conditions [J]. International Journal of Heat and Mass Transfer, 2019, 138: 483-495.

叶明亮, 晏鑫, 何坤. 隔板位置对透平级凹槽叶顶传热和冷却性能的影响 [J]. 西安交通大学学报, 2018, 52(5): 116-124.

YE Mingliang, YAN Xin, HE Kun. Effect of rib location on the heat transfer and cooling characteristics at the squealer tip in turbine stage [J]. Journal of Xi'an Jiaotong University, 2018, 52(5): 116-124.

于金杏, 叶明亮, 晏鑫. 发动机工况下透平级凹槽叶顶冷却传热性能研究 [J]. 西安交通大学学报, 2021, 55(7): 106-116.

YU Jinxing, YE Mingliang, YAN Xin. Investigations on the heat transfer and film cooling effect at squealer tip of a turbine stage under engine conditions [J]. Journal of Xi'an Jiaotong University, 2021, 55(7): 106-116.

HALILA E E, LENAHAN D T, THOMAS T T. Energy efficient engine high pressure turbine test hardware detailed design report [EB/OL].(1982-06-01)[2021-08-10]. https: ∥ntrs.nasa.gov/citations/1985 0002687.

黄琰, 晏鑫, 何坤, 等. 压力面侧小翼结构对凹槽叶顶冷却传热性能的影响 [J]. 西安交通大学学报, 2017, 51(7): 51-56.

HUANG Yan, YAN Xin, HE Kun, et al. Effect of pressure side winglet on film cooling and heat transfer performance of blade squealer tip [J]. Journal of Xi'an Jiaotong University, 2017, 51(7): 51-56.

YAN Xin, HUANG Yan, HE Kun. Investigations into heat transfer and film cooling effect on a squealer-winglet blade tip [J]. International Journal of Heat and Mass Transfer: Part B, 2017, 115: 955-978.

ANSYS INC. ANSYS CFX-solver theory guide: version 11.0 [EB/OL]. [2021-08-10]. http: ∥www. doc88.com/p-080655015405.html.

KWAK J S, HAN J C, et al. Heat transfer coefficients on the squealer tip and near squealer tip regions of a gas turbine blade [J]. Journal of Heat Transfer, 2003, 125(4): 669-677.

屠珊, 孙弼, 毛靖儒. 用Richardson外推法分析流动传热层流问题的不确定度 [J]. 西安交通大学学报, 1999, 33(11): 47-50.

TU Shan, SUN Bi, MAO Jingru. Uncertainty analysis of laminar flow and heat transfer problems by Richardson extrapolation [J]. Journal of Xi'an Jiaotong University, 1999, 33(11): 47-50.

姜世杰, 李志刚, 李军. 凹槽状小翼对涡轮动叶叶顶气动和传热性能的影响 [J]. 西安交通大学学报, 2019, 53(9): 7-14, 41.

JIANG Shijie, LI Zhigang, LI Jun. Effects of squealer winglet on the aerodynamic and heat transfer performances of turbine rotor blade tip [J]. Journal of Xi'an Jiaotong University, 2019, 53(9): 7-14, 41.

杨佃亮, 丰镇平. 叶顶形状对动叶顶部流动和传热的影响研究 [J]. 西安交通大学学报, 2008, 42(5): 537-541.

YANG Dianliang, FENG Zhenping. Effect of squealer geometry arrangements on tip leakage flow and heat transfer for turbine blade [J]. Journal of Xi'an Jiaotong University, 2008, 42(5): 537-541.

高杰, 郑群. 叶顶凹槽形态对动叶气动性能的影响 [J]. 航空学报, 2013, 34(2): 218-226.

GAO Jie, ZHENG Qun. Effect of squealer tip geometry on rotor blade aerodynamic performance [J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(2): 218-226.

浏览量

下载量

CSCD

文章被引用时，请邮件提醒。

提交

工具集

关联资源

压力面侧小翼结构对凹槽叶顶冷却传热性能的影响

隔板位置对凹槽叶顶传热和冷却性能的影响

射流角对带小翼凹槽叶顶冷却传热性能的影响

压力侧冷却流对凹槽叶顶气膜冷却与传热性能的影响

透平叶片双工质冷却特性的实验研究