带球窝结构的尾缘开缝壁面气膜冷却特性研究

何坤; 王茜; 晏鑫

doi:10.7652/xjtuxb202412003

您当前的位置：

首页 >

文章列表页 >

带球窝结构的尾缘开缝壁面气膜冷却特性研究

—————————————————————— | 更新时间：2025-07-28

- 带球窝结构的尾缘开缝壁面气膜冷却特性研究
- Research on Film Cooling Characteristics of Trailing Edge Cutback with Dimples
- 西安交通大学学报 2024年58卷第12期页码：22-33
- 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：
  
  : 2024-03-22。作者简介: 何坤(1983—),女,副教授。基金项目: 陕西省自然科学基金资助项目(2023-JC-YB-340)
- 基金信息：
  
  : 2024-03-22。作者简介: 何坤(1983—),女,副教授。基金项目: 陕西省自然科学基金资助项目(2023-JC-YB-340);国家自然科学基金资助项目(52076165)。
- DOI：10.7652/xjtuxb202412003
  中图分类号： TK47
- 网络首发：2024-12-10，
  
  纸质出版：2024
- 稿件说明：
移动端阅览
何坤, 王茜, 晏鑫. 带球窝结构的尾缘开缝壁面气膜冷却特性研究[J]. 西安交通大学学报, 2024,58(12):22-33.

HE Kun, WANG Xi, YAN Xin. Research on Film Cooling Characteristics of Trailing Edge Cutback with Dimples[J]. 2024, 58(12): 22-33.
何坤, 王茜, 晏鑫. 带球窝结构的尾缘开缝壁面气膜冷却特性研究[J]. 西安交通大学学报, 2024,58(12):22-33. DOI： 10.7652/xjtuxb202412003.

HE Kun, WANG Xi, YAN Xin. Research on Film Cooling Characteristics of Trailing Edge Cutback with Dimples[J]. 2024, 58(12): 22-33. DOI： 10.7652/xjtuxb202412003.

摘要

为提升燃气透平叶片尾缘开缝区域的气膜冷却性能

将多排球窝结构应用于尾缘冷却通道下游开缝壁面

以增加近壁面区域的冷气覆盖。采用非定常延迟-分离涡模拟方法

研究了有、无球窝结构下尾缘开缝壁面的气膜冷却性能

获得了4种吹风比、3种球窝高径比以及2种球窝结构(球形球窝和泪滴形球窝)条件下尾缘开缝壁面的气膜冷却性能和流量系数

并利用已有实验数据考核了数值方法的有效性

阐明了球窝结构减小冷热气流掺混、改善尾缘开缝区域气膜冷却性能的作用机制。结果表明:球窝结构有利于冷气向壁面附近聚集

使得冷气不易被主流卷起

减小了冷热气流掺混

有效增加了开缝壁面沿流向的气膜覆盖面积; 相对于光滑尾缘开缝模型(无球窝结构)

带球形球窝结构的尾缘开缝模型流量系数增大了4.8%～6%

平均气膜冷却效率提高了4.6%～19%; 吹风比越大

球窝结构对冷气的吸附作用越显著

带球窝结构的尾缘开缝壁面平均气膜冷却效率越高; 球窝高径比越大

尾缘开缝壁面的气膜冷却效率越高且分布越均匀。泪滴形球窝可有效解决球形球窝内壁前缘冷却不足问题

相对于带球形球窝结构的尾缘开缝

带泪滴形球窝结构的尾缘开缝壁面的冷却效率提高了8.2%

流量系数提高了1.1%。

Abstract

To enhance the film cooling performance of the trailing edge cutback region in a gas turbine blade

multiple arrays of dimples are applied to the downstream cutback of the cooling slot to improve the coolant coverage near the wall. Using the delayed-detached eddy simulation method

the film cooling performance of the trailing edge cutback with/without dimples is investigated. The film cooling performance and flow coefficient of the trailing edge cutback are obtained under four blowing ratios

three dimple height-to-diameter ratios

and two dimple structures(spherical dimples and teardrop-shaped dimples). The effectiveness of the numerical method is verified using existing experimental data

elucidating the mechanism by which the dimple structure reduces the mixing of hot and cold airflows and improves the film cooling performance in the trailing edge cutback region. The results indicate that the dimple structure promotes the accumulation of cool air near the wall surface

preventing it from being easily entrained by the mainstream flow

thereby reducing the mixing of hot and cold airflows and effectively increasing the film coverage area along the cutback in the downstream direction. Compared to the smooth trailing edge cutback model(without dimple structure)

the flow coefficient of the trailing edge cutback model with spherical dimples increases by 4.8% to 6%

and the average film cooling efficiency increases by 4.6% to 19%. With increasing blowing ratio

the adsorption effect of the dimple structure on cool air becomes more significant

leading to higher average film cooling efficiency on the trailing edge cutback with a dimple structure. A higher dimple height-to-diameter ratio results in increased and more uniform film cooling efficiency on the trailing edge cutback. The teardrop-shaped dimples effectively address the issue of insufficient cooling at the leading edge of the spherical dimples: compared to the trailing edge cutback model with spherical dimples

the cooling efficiency of the trailing edge cutback with teardrop-shaped dimples increases by 8.2%

and the flow coefficient improves by 1.1%.

关键词

Keywords

references

HAN J C, DUTTA S, EKKAD S. Gas turbine heat transfer and cooling technology [M]. 2nd ed. Boca Raton, USA: CRC Press, 2013.

ZARETSKY E V, LITT J S, HENDRICKS R C, et al. Determination of turbine blade life from engine field data [J]. Journal of Propulsion and Power, 2012, 28(6): 1156-1167.

曾军, 乔渭阳, 孙大伟, 等. 带尾缘劈缝冷气喷射的涡轮叶栅性能实验及计算 [J]. 推进技术, 2008, 29(6): 710-715.

ZENG Jun, QIAO Weiyang, SUN Dawei, et al. Numerical simulation and experiment for turbine cascade with trailing edge coolant injection [J]. Journal of Propulsion Technology, 2008, 29(6): 710-715.

BUNKER R S. Turbine heat transfer and cooling: an overview [C]//ASME Turbo Expo 2013: Power for Land, Sea and Air. New York, USA: ASME, 2008: 710-715.

GURRAM N, IRELAND P T, WONG T H, et al. Study of film cooling in the trailing edge region of a turbine rotor blade in high speed flow using pressure sensitive paint [C]//ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. New York, USA: ASME, 2016: V05CT19A023.

YANG Zifeng, JOHNSON M, POSADA N, et al. Film cooling on the geometrically modified trailing edge model of gas turbine blade [J]. Journal of Turbomachinery, 2019, 141(9): 091012.

BARIGOZZI G, PERDICHIZZI A, RAVELLI S. Pressure side and cutback trailing edge film cooling in a linear nozzle vane cascade at different Mach numbers [J]. Journal of Turbomachinery, 2012, 134(5): 051037.

METZGER D E, BERRY R A, BRONSON J P. Developing heat transfer in rectangular ducts with staggered arrays of short pin fins [J]. Journal of Heat Transfer, 1982, 104(4): 700-706.

JASWAL I, AMES F E. Heat transfer and pressure drop measurements in constant and converging section pin and diamond pedestal arrays [J]. Journal of Thermal Science and Engineering Applications, 2009, 1(1): 011006.

MARTINI P, SCHULZ A, BAUER H J.Film cooling effectiveness and heat transfer on the trailing edge cutback of gas turbine airfoils with various internal cooling designs [J]. Journal of Turbomachinery, 2006, 128(1): 196-205.

LIANG Ce, RAO Yu, LUO Jiahao, et al. Experimental and numerical study of turbulent flow and heat transfer in a wedge-shaped channel with guiding pin Fins for turbine blade trailing edge cooling [J]. International Journal of Heat and Mass Transfer, 2021, 178: 121590.

HORBACH T, SCHULZ A, BAUER H J.Trailing edge film cooling of gas turbine airfoils: effects of ejection lip geometry on film cooling effectiveness and heat transfer [J]. Heat Transfer Research, 2010, 41(8): 849-865.

GAO Yan, YAN Xin, LI Jun, et al. Investigations into film cooling and unsteady flow characteristics in a blade trailing-edge cutback region [J]. Journal of Mechanical Science and Technology, 2018, 32(10): 5015-5029.

高炎, 晏鑫, 李军. 燃气透平叶片尾缘开缝结构冷却性能的数值研究 [J]. 西安交通大学学报, 2016, 50(3): 29-37.

GAO Yan, YAN Xin, LI Jun. Numerical investigations on the cooling performance of trailing edge cutback in gas turbine blade [J]. Journal of Xi'an Jiaotong University, 2016, 50(3): 29-37.

TASLIM M E, SPRING S D, MEHLMAN B P.Experimental investigation of film cooling effectiveness for slots of various exit geometries [J]. Journal of Thermophysics and Heat Transfer, 1992, 6(2): 302-307.

王茜. 燃气透平叶片尾缘开缝区域非定常冷却性能的研究 [D]. 西安: 西安交通大学, 2022.

HORBACH T, SCHULZ A, BAUER H J.Trailing edge film cooling of gas turbine airfoils: external cooling performance of various internal pin fin configurations [J]. Journal of Turbomachinery, 2011, 133(4): 041006.

BENSON M J, ELKINS C J, YAPA S D, et al. Effects of varying Reynolds number, blowing ratio, and internal geometry on trailing edge cutback film cooling [J]. Experiments in Fluids, 2012, 52(6): 1415-1430.[19] 叶林, 刘存良, 杨寓全, 等. V肋对尾缘劈缝气膜冷却特性的影响 [J]. 航空学报, 2021, 42(6): 206-217.

YE Lin, LIU Cunliang, YANG Yuquan, et al. Effect of V-shaped ribs on film cooling characteristics of Trailing-edge cutback [J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(6): 206-217.

王茜, 何坤, 晏鑫. 带肋尾缘开缝模型内的非定常冷却性能研究 [J]. 西安交通大学学报, 2020, 54(9): 128-135.

WANG Xi, HE Kun, YAN Xin. Investigation of unsteady cooling performance in a trailing edge cutback model with land extensions [J]. Journal of Xi'an Jiaotong University, 2020, 54(9): 128-135.

王瑞琴, 晏鑫, 何坤. 带肋板尾缘开缝叶片内的流动传热性能研究 [J]. 西安交通大学学报, 2020, 54(1): 150-161.

WANG Ruiqin, YAN Xin, HE Kun. Investigations of flow and heat transfer performance in a blade with trailing-edge cutback and lands [J]. Journal of Xi'an Jiaotong University, 2020, 54(1): 150-161.

王瑞琴, 何坤, 晏鑫. 肋板倾角和形状对尾缘开缝区域非定常冷却性能的影响 [J]. 西安交通大学学报, 2023, 57(12): 80-89.

WANG Ruiqin, HE Kun, YAN Xin. Effects of land angle and shape on unsteady cooling performance in trailing edge cutback region [J]. Journal of Xi'an Jiaotong University, 2023, 57(12): 80-89.

王瑞琴. 燃气透平叶片带肋尾缘开缝区域内非定常冷却特性的研究[D]. 西安: 西安交通大学, 2023.

YE Lin, LIU Cunliang, LIU Haiyong, et al. Numerical study on the effects of V-shaped rib angle on film cooling performance for turbine blade trailing edge [C]//ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. New York, USA: ASME, 2018: V05AT12A002.

MURATA A, NISHIDA S, SAITO H, et al.Effects of surface geometry on film cooling performance at airfoil trailing edge [J]. Journal of Turbomachinery, 2012, 134(5): 051033.

NISHIDA S, MURATA A, SAITO H, et al.Effects of shape and arrangement of dimples on film cooling performance over cutback surface at airfoil trailing edge [C]//ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. New York, USA: ASME, 2013: V03BT13A054.

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

吹风比和肋板对叶片尾缘开缝气膜冷却特性的影响

利用空气幕冷却提升涡轮叶栅端壁气膜冷却有效度的实验研究

张角凹坑气膜孔对双层壁气膜冷却特性的影响

航空发动机高温结构损伤检测研究与应用进展

带肋曲面双层壁偏转内流与传热冷却特性数值研究