Investigations on the Heat Transfer and Film Cooling Effect at Squealer Tip of a Turbine Stage under Engine Conditions

doi:10.7652/xjtuxb202107012

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Investigations on the Heat Transfer and Film Cooling Effect at Squealer Tip of a Turbine Stage under Engine Conditions

更新时间：2025-07-09

- Investigations on the Heat Transfer and Film Cooling Effect at Squealer Tip of a Turbine Stage under Engine Conditions
- Vol. 55, Issue 7, Pages: 106-116(2021)
- 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/xjtuxb202107012
  CLC： TK474.7
- Online First：10 July 2021，
  
  Published：2021
- 稿件说明：
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Investigations on the Heat Transfer and Film Cooling Effect at Squealer Tip of a Turbine Stage under Engine Conditions[J]. 2021, 55(7): 106-116.
DOI：

Investigations on the Heat Transfer and Film Cooling Effect at Squealer Tip of a Turbine Stage under Engine Conditions[J]. 2021, 55(7): 106-116. DOI： 10.7652/xjtuxb202107012.

摘要

采用数值方法研究了发动机工况下透平级凹槽叶顶的冷却传热性能

获得了3种吹风比(M=0.5

1.0

2.0)和2种气膜孔布置(单排叶顶气膜孔、叶顶+压力面侧气膜孔)下凹槽叶顶的传热系数和气膜冷却效率分布。研究表明:凹槽腔室涡、刮削涡和冲击流是影响凹槽叶顶冷却传热性能的主要流场结构。在凹槽腔室涡的作用下

冷却流对凹槽底部前缘及压力侧形成了有效的冷却。在腔室涡与刮削涡的共同作用下

冲击流导致凹槽底部吸力侧形成高传热区。采用单排叶顶气膜孔时

随着吹风比的增大

凹槽叶顶的传热系数减小

气膜冷却效率提高。采用叶顶+压力面侧气膜孔时

与采用单排叶顶气膜孔相比

在吹风比为2.0的条件下

凹槽肩壁的平均传热系数降低了13.89%

平均气膜冷却效率升高了61.45%。

Abstract

Heat transfer and film cooling effect at squealer tip of a turbine stage were numerically investigated under engine conditions. The heat transfer coefficient and film cooling effectiveness at squealer tip with two cooling hole array arrangements(tip hole-array

and both tip and pressure-side hole-arrays)were obtained at three blowing ratios(M=0.5

1.0 and 2.0). The results show that the squealer cavity vortex

scraping vortex and impingement flow are the three main flow structures that influence the heat transfer and film cooling effect at squealer tip. Due to the influence of squealer cavity vortex

the cooling flow can effectively cool the cavity floor near the leading edge and the pressure side. Under the influences of cavity vortex and scraping vortex

the impingement flow induces a high heat transfer area on cavity floor near suction side. When the tip hole-array is employed

with the increase of blowing ratio

the overall heat transfer coefficient at squealer tip is decreased

and the overall film cooling effectiveness is increased. When both tip and pressure-side hole arrays are employed

compared with the tip hole array

the area-averaged heat transfer coefficient at squealer tip is decreased by 13.89%

and the area-averaged film cooling effectiveness is increased by 61.45% at M=2.0.

关键词

Keywords

references

BUNKER R S. Axial turbine blade tips: function, design, and durability [J]. Journal of Propulsion and Power, 2006, 22(2): 271-285.

HAN J C. Fundamental gas turbine heat transfer [J]. Journal of Thermal Science and Engineering Applications, 2013, 5(2): 021007.

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.

叶明亮, 黄琰, 晏鑫, 等. 隔板位置对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(3): 55-62.

YE Mingliang, HUANG Yan, YAN Xin, et al. Effect of rib location on the heat transfer and cooling characteristics of squealer tip [J]. Journal of Xi'an Jiaotong University, 2018, 52(3): 55-62.

JEONG J Y, KIM W, KWAK J S, et al. Heat transfer coefficient and film cooling effectiveness on the partial cavity tip of a gas turbine blade [J]. Journal of Turbomachinery, 2019, 141(7): 071007.

SAKAOGLU S, KAHVECI H S. Effect of turbine blade tip cooling configuration on tip leakage flow and heat transfer [J]. Journal of Turbomachinery, 2020, 142(2): 021008.

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 heat transfer and cooling effect of a squealer tip in turbine stage [J]. Journal of Xi'an Jiaotong University, 2018, 52(5): 116-124.

SUNDEN B, XIE G. Gas turbine blade tip heat transfer and cooling: a literature survey [J]. Heat Transfer Engineering, 2010, 31(7): 527-554.

LU S, MA H, ZHANG Q, et al. Cutback squealer tip trailing edge cooling performance [J]. International Journal of Heat and Mass Transfer, 2020, 154: 119632.

PARK J S, LEE D H, RHEE D H, et al. Heat transfer and film cooling effectiveness on the squealer tip of a turbine blade [J]. Energy, 2014, 72: 331-343.

MA H, ZHANG Q, HE L, et al. Cooling injection effect on a transonic squealer tip: Part II Analysis of aerothermal interaction physics [J]. Journal of Engineering for Gas Turbines and Power, 2017, 139(5): 052507.

WANG J, LIU Y, WANG X, et al. Characteristics of tip leakage flow of the turbine blade with cutback squealer and coolant injection [C]∥ASME Turbo Expo 2010: Power for Land, Sea, and Air. New York, USA: ASME, 2010: 1243-1251.

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.

NASIR H, EKKAD S V, BUNKER R S. Effect of tip and pressure side coolant injection on heat transfer distributions for a plane and recessed tip [J]. Journal of Turbomachinery, 2007, 129(1): 151-163.

KWAK J S, AHN J, HAN J C, et al. Heat transfer coefficients on the squealer tip and near-tip regions of a gas turbine blade with single or double squealer [J]. Journal of Turbomachinery, 2003, 125(4): 778-787.

HALILA E E, LENAHAD D T, THOMAS T T. High pressure turbine test hardware detailed design report: CR-167955 [R]. Cleveland, Ohio, USA: NASA, 1982.

陶文铨. 计算传热学的近代进展 [M]. 北京: 科学出版社, 2000: 362-363.

HAYDT S, LYNCH S. Heat transfer coefficient augmentation for a shaped film cooling hole at a range of compound angles [C]∥ASME Turbo Expo 2019: Power for Land, Sea, and Air. New York, USA: ASME, 2019: V05BT19A026.

AGA V, ABHARI R S. Influence of flow structure on compound angled film cooling effectiveness and heat transfer [J]. Journal of Turbomachinery, 2011, 133(3): 031029.

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