气膜孔堵塞对凹槽叶顶冷却传热性能的影响

徐柯文; 何坤; 晏鑫

doi:10.7652/xjtuxb202406013

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气膜孔堵塞对凹槽叶顶冷却传热性能的影响

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- 气膜孔堵塞对凹槽叶顶冷却传热性能的影响
- Effects of Film Cooling Hole Blockage on Cooling and Heat Transfer Performance at Squealer Tip
- 西安交通大学学报 2024年58卷第6期页码：139-152
- 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：
  
  : 2023-12-07。作者简介: 徐柯文(2001—),男,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)
- 基金信息：
  
  : 2023-12-07。作者简介: 徐柯文(2001—),男,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/xjtuxb202406013
  中图分类号： TK474.7
- 网络首发：2024-06-10，
  
  纸质出版：2024
- 稿件说明：
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徐柯文, 何坤, 晏鑫. 气膜孔堵塞对凹槽叶顶冷却传热性能的影响[J]. 西安交通大学学报, 2024,58(6):139-152.

XU Kewen, HE Kun, YAN Xin. Effects of Film Cooling Hole Blockage on Cooling and Heat Transfer Performance at Squealer Tip[J]. 2024, 58(6): 139-152.
徐柯文, 何坤, 晏鑫. 气膜孔堵塞对凹槽叶顶冷却传热性能的影响[J]. 西安交通大学学报, 2024,58(6):139-152. DOI： 10.7652/xjtuxb202406013.

XU Kewen, HE Kun, YAN Xin. Effects of Film Cooling Hole Blockage on Cooling and Heat Transfer Performance at Squealer Tip[J]. 2024, 58(6): 139-152. DOI： 10.7652/xjtuxb202406013.

摘要

采用数值方法

研究了燃气透平叶片气膜孔堵塞条件下凹槽叶顶的冷却传热性能

获得了3种吹风比M=0.5

1.0

1.5和不同堵塞比B=0

0.2

0.4

0.6

0.8条件下的凹槽叶顶的气膜冷却效率和传热系数分布。研究表明:气膜孔堵塞会导致凹槽叶顶气膜冷却性能下降、热负荷升高

堵塞比越大

凹槽叶顶的冷却传热性能越差。气膜孔堵塞显著改变了叶顶区域的流场结构

加剧冷气的抬升效应

导致冷气过早离开凹槽。吹风比是影响堵塞工况下凹槽叶顶冷却传热性能的重要因素

吹风比为1.0、堵塞比为0.8时

凹槽叶顶的面积平均气膜冷却效率相比于未堵塞时下降了64.88%、传热系数上升了13.01%。减小吹风比可以改善小堵塞比工况下的叶顶气膜冷却性能

吹风比为0.5、堵塞比为0.4时

叶顶平均气膜冷却效率仅下降了6.82%

但小吹风比会导致大堵塞比工况下的气膜冷却性能恶化严重

吹风比为0.5、堵塞比为0.8时

平均气膜冷却效率下降了82.09%。增大吹风比

可改善大堵塞比工况下的叶顶气膜冷却性能

吹风比为1.5、堵塞比为0.8条件下叶顶平均气膜冷却效率下降了51.34%、传热系数上升了11.52%。

Abstract

Film cooling and heat transfer performance on the squealer tip with different degrees of cooling-hole blockage are investigated using numerical methods. The film cooling effectiveness and heat transfer coefficient distribution on the squealer tip are obtained under three blowing ratios(M=0.5

1.0

and 1.5)and five different blockage ratios(B=0

0.2

0.4

0.6

and 0.8). The results show that the cooling-hole blockage causes decrease of film cooling effect and increase of thermal load on the squealer tip. The film cooling effect and heat transfer performance on the squealer tip are deteriorated with increasing the blockage ratio. The blockage in film cooling holes significantly alters the flow structures in the squealer tip gap. With cooling-hole blockage

the lift-off effect of coolant in the squealer cavity will be aggravated

resulting in earlier leave of cooling flow from the squealer cavity. Generally

the blowing ratio is an important factor that affects the heat transfer and film cooling effect on the squealer tip under blockage conditions. Compared with the unblocked cases

the area-averaged film cooling effectiveness on the squealer tip decreases by 64.88%

and the heat transfer coefficient increases by 13.01%

at blowing ratio M=1.0 and blockage ratio B=0.8. Reducing the blowing ratio is conducive to the improvement of film cooling effectiveness on the squealer tip with small blockage ratio. The area-averaged film cooling effectiveness on the squealer tip only decreases by 6.82% at blowing ratio M=0.5 and blocking ratio B=0.4. However

in the case of small blow ratio

for example M=0.5

the film cooling effect on the squealer tip is deteriorated significantly under the condition of large blockage ratio. At blowing ratio M=0.5 and blocking ratio B=0.8

the area-averaged film cooling effectiveness on the squealer tip decreases by 82.09% compared with the unblocked case. The increase in blowing ratio can improve the film cooling effect on the squealer tip with large blockage ratio. Compared with the unblocked case

the area-averaged film cooling effectiveness on the squealer tip only decreases by 51.34% and the heat transfer coefficient increases by 11.52% at blowing ratio M=1.5 and blockage ratio B=0.8.

关键词

Keywords

references

TAKEISHI K, KREWINKEL R. Advanced gas turbine cooling for the carbon-neutral era [J]. International Journal of Turbomachinery, Propulsion and Power, 2023, 8(3): 19.

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

戴萍, 林枫. 燃气轮机叶片气膜冷却研究进展 [J]. 热能动力工程, 2009, 24(1): 1-6.

DAI Ping, LIN Feng. Recent advances in the study of air-film-cooled gas turbine blades [J]. Journal of Engineering for Thermal Energy and Power, 2009, 24(1): 1-6.

ZHOU Zhihua, CHEN Shaowen, LI Weihang, et al. Thermal performance of blade tip and casing coolant injection on a turbine blade with cavity and winglet-cavity tip [J]. International Journal of Heat and Mass Transfer, 2019, 130: 585-602.

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]. Journal of Xi'an Jiaotong University, 2022, 56(7): 27-37.

于金杏, 叶明亮, 何坤, 等. 压力侧冷却流对凹槽叶顶气膜冷却与传热性能的影响 [J]. 西安交通大学学报, 2022, 56(3): 160-172.

YU Jinxing, YE Mingliang, HE Kun, et al. Effect of pressure-side cooling flow on film cooling and heat transfer performance at squealer tip [J]. Journal of Xi'an Jiaotong University, 2022, 56(3): 160-172.

秦正, 何坤, 晏鑫. 双肩壁凹槽叶顶冷却传热性能的优化研究 [J]. 西安交通大学学报, 2024, 58(1): 68-80.

QIN Zheng, HE Kun, YAN Xin.A study of film cooling and heat transfer optimization for double-rim squealer tip [J]. Journal of Xi'an Jiaotong University, 2024, 58(1): 68-80.

NEMDILI F, AZZI A, JUBRAN B A. Numerical investigation of the influence of a hole imperfection on film cooling effectiveness [J]. International Journal of Numerical Methods for Heat Fluid Flow, 2011, 21(1): 46-60.

KIM J, DUNN M G, BARAN A J, et al.Deposition of volcanic materials in the hot sections of two gas turbine engines [J]. Journal of Engineering Gas Turbines and Power, 1993, 115(3): 641-651.

LIU Zhengang, ZHANG Fei, LIU Zhenxia, et al. An experimental study of the effects of different transverse trenches on deposition on a turbine vane with film-cooling at high temperature [J]. Aerospace Science and Technology, 2020, 107: 106340.

JOVANOVIC' M B, DE LANGE H C, VAN STEENHOVEN A A. Influence of hole imperfection on jet cross flow interaction [J]. International Journal of Heat and Fluid Flow, 2006, 27(1): 42-53.

JOVANOVI' M B, DE LANGE H C, VAN STEENHOVEN A A. Effect of hole imperfection on adiabatic film cooling effectiveness [J]. International Journal of Heat and Fluid Flow, 2008, 29(2): 377-386.

黄珂楠, 张靖周, 郭文. 气膜孔内局部堵塞对气膜冷却特性的影响 [J]. 航空动力学报, 2014, 29(6): 1330-1338.

HUANG Kenan, ZHANG Jingzhou, GUO Wen. Effect of partial blockage inside film hole on film cooling characteristics [J]. Journal of Aerospace Power, 2014, 29(6): 1330-1338.

WHITFIELD C A, SCHROEDER R P, THOLE K A, et al.Blockage effects from simulated thermal barrier coatings for cylindrical and shaped cooling holes [J]. Journal of Turbomachinery, 2015, 137(9): 091004.

WANG Fuqiang, PU Jian, WANG Jianhua, et al. Numerical investigation of effects of blockage, inclination angle, and hole-size on film cooling effectiveness at concave surface [J]. Journal of Turbomachinery, 2021, 143(2): 021007.

TIAN Ke, WANG Jin, LIU Chao, et al. Effect of blockage configuration on film cooling with and without mist injection [J]. Energy, 2018, 153: 661-670.

LEE Sanga, HWANG W, YEE K. Robust design optimization of a turbine blade film cooling hole affected by roughness and blockage [J]. International Journal of Thermal Sciences, 2018, 133: 216-229.

BAI Bo, LI Zhigang, ZHANG Kaiyuan, et al. Effects of hole blockage on endwall film cooling and vane phantom cooling performances of a transonic turbine vane [J]. Journal of Engineering for Gas Turbines and Power, 2023, 145(4): 041001.

ZHANG Wei, ZENG Rui, LIU Song, et al. Effect of blockage inside holes on film cooling performance on the suction side of a turbine guide vane [J]. Energies, 2022, 15(8): 2935.

周君辉, 张靖周. 气膜孔局部堵塞对叶片压力面冲击-扰流柱-气膜结构综合冷却效率的影响 [J]. 航空学报, 2016, 37(9): 2729-2738.

ZHOU Junhui, ZHANG Jingzhou. Effects of partial blockage inside film holes on overall cooling effectiveness of an integrated impingement-fin-film cooling configuration on blade pressure side [J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(9): 2729-2738.

CHUNG H, PARK J S, SOHN H S, et al. Trailing edge cooling of a gas turbine blade with perforated blockages with inclined holes [J]. International Journal of Heat and Mass Transfer, 2014, 73: 9-20.

BOGARD D G, SCHMIDT D L, TABBITA M.Characterization and laboratory simulation of turbine airfoil surface roughness and associated heat transfer [J]. Journal of Turbomachinery, 1998, 120(2): 337-342.

HALILA E E, LENAHAN D T, THOMAS T T. High pressure turbine test hardware detailed design report [M]. Cleveland, Ohio, USA: National Aeronautics and Space Administration, Lewis Research Center, 1982.

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.

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

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