Effects of Blowing Ratio and Land Extension on Blade Trailing Edge Cutback Film Cooling Effectiveness

HE Kun; WANG Xi; YAN Xin

doi:10.7652/xjtuxb202405010

您当前的位置：

首页 >

文章列表页 >

Effects of Blowing Ratio and Land Extension on Blade Trailing Edge Cutback Film Cooling Effectiveness

更新时间：2025-07-28

- Effects of Blowing Ratio and Land Extension on Blade Trailing Edge Cutback Film Cooling Effectiveness
- Vol. 58, Issue 5, Pages: 99-110(2024)
- 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/xjtuxb202405010
  CLC： TK47
- Online First：10 May 2024，
  
  Published：2024
- 稿件说明：
移动端阅览
HE Kun, WANG Xi, YAN Xin. Effects of Blowing Ratio and Land Extension on Blade Trailing Edge Cutback Film Cooling Effectiveness[J]. 2024, 58(5): 99-110.
DOI：

HE Kun, WANG Xi, YAN Xin. Effects of Blowing Ratio and Land Extension on Blade Trailing Edge Cutback Film Cooling Effectiveness[J]. 2024, 58(5): 99-110. DOI： 10.7652/xjtuxb202405010.

摘要

为了阐明吹风比和肋板对燃气透平叶片尾缘开缝区域气膜冷却性能的影响

采用延迟-分离涡模拟方法求解了尾缘开缝模型的流量系数、非定常流场结构和气膜冷却效率

采用实验数据考核了延迟-分离涡模拟方法对流量系数和气膜冷却效率预测的有效性

获得了使尾缘开缝壁面气膜冷却效率最佳吹风比。结果表明:流量系数随吹风比增加而增大

但吹风比大于0.65后

流量系数几乎不受吹风比影响; 在吹风比0.20～0.65范围内

尾缘开缝壁面气膜冷却效率随吹风比增加而增加; 在吹风比0.80～1.25范围内

冷热气掺混剧烈

冷却效率略微下降; 肋板结构增加了冷气通道的阻塞效应

并限制了开缝区域冷气旋涡的发展

导致展向涡提前扭曲、变形和分解; 相对于无肋板结构

带肋尾缘开缝结构的流量系数下降了约5%

气膜冷却性能提升了约10.8%。开缝下游的旋涡脱落和冷热气流间的掺混是影响开缝壁面冷却效率的主要原因

综合考虑冷气消耗和气膜冷却效率

无肋板时最佳吹风比为0.65

带肋板时最佳吹风比为0.5。

Abstract

To investigate the effects of blowing ratio and land extensions on the film cooling performance of a gas turbine blade trailing edge cutback

the delayed-detached eddy simulation(DDES)is utilized to compute the discharge coefficient

transient flow structures

and film cooling effectiveness of a trailing edge cutback model

and the experimental data is adopted to validate the reliability of DDES for the discharge coefficient and film cooling effectiveness predictions. As a result

the study determined the optimum blowing ratio for ensuring the film cooling effect at the trailing edge cutback. The findings show that the discharge coefficient rises in correspondence with an increase in the blowing ratio. However

once the blowing ratio surpasses 0.65

its impact on the discharge coefficient diminishes significantly. For the blowing ratio ranging from 0.20 to 0.65

the film cooling effectiveness at the trailing edge cutback improves with an increase in the blowing ratio. As the blowing ratio increases from 0.80 to 1.25

interactions between the coolant and hot mainstream are intensified

resulting in a slight reduction in the cooling effect. The existence of land extensions amplifies the blockage of cooling slot and inhibits the development of coolant vortices in the trailing edge cutback region

leading to premature twisting

distortion

and fragmentation of the transverse vortex system. Compared to the trailing edge cutback without land extensions

the discharge coefficient for the configuration with land extensions decreases by about 5% while the film cooling effectiveness increases by about 10.8%. The vortex shedding downstream the cooling slot and interactions between coolant and hot mainstream are the main reasons affecting the cooling effect at the trailing edge cutback. Considering both coolant consumption and film cooling effectiveness

the optimal blowing ratio for the trailing edge cutback without land extensions is identified as 0.65. Contrastingly

for the trailing edge cutback with land extensions

the preferred blowing ratio stands at 0.5.

关键词

Keywords

references

HAN J C, DATTA S, EKKAD S. Gas turbine heat transfer and cooling technology [M]. 2nd ed. Boca Raton, FL: 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.

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, 2013: GT2013-94174.

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.

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.

CHEN Yude, MATALANIS C G, EATON J K. High resolution PIV measurements around a model turbine blade trailing edge film-cooling breakout [J]. Experiments in Fluids, 2008, 44(2): 199-209.

AMES F E, FIALA N J, JOHNSON J D. Gill slot trailing edge heat transfer: effects of blowing rate, Reynolds number, and external turbulence on heat transfer and film cooling effectiveness [C]//ASME Turbo Expo 2007: Power for Land, Sea, and Air. New York, USA: ASME, 2007: 351-362.

FIALA N J, JASWAL I, AMES F E. Letterbox trailing edge heat transfer: effects of blowing rate, Reynolds number, and external turbulence on heat transfer and film cooling effectiveness [J]. Journal of Turbomachinery, 2010, 132(1): 011017.

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.

ABDEH H, BARIGOZZI G. A parametric investigation of vane pressure side cutback film cooling by dual luminophor PSP [J]. International Journal of Heat and Fluid Flow, 2018, 69: 106-116.

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.

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.

HOLLOWAY D S, LEYLEK J H, BUCK F A. Pressure-side bleed film cooling: part Ⅰ steady framework for experimental and computational results [C]//ASME Turbo Expo 2002: Power for Land, Sea, and Air. New York, USA: ASME, 2002: 835-843.

HOLLOWAY D S, LEYLEK J H, BUCK F A. Pressure-side bleed film cooling: part Ⅱ unsteady framework for experimental and computational results [C]//ASME Turbo Expo 2002: Power for Land, Sea, and Air. New York, USA: ASME, 2002: 845-853.

MARTINI P, SCHULZ A, WHITNEY C F, et al. Experimental and numerical investigation of trailing edge film cooling downstream of a slot with internal rib arrays [J]. Proceedings of the Institution of Mechanical Engineers: Part A Journal of Power and Energy, 2003, 217(4): 393-401.

MARTINI P, SCHULZ A. Experimental and numerical investigation of trailing edge film cooling by circular coolant wall jets ejected from a slot with internal rib arrays [J]. Journal of Turbomachinery, 2004, 126(2): 229-236.

KRUECKELS J, GRITSCH M, SCHNIEDER M. Design considerations and validation of trailing edge pressure side bleed cooling [C]//ASME Turbo Expo 2009: Power for Land, Sea, and Air. New York, USA: ASME, 2009: 63-70.

EFFENDY M, YAO Yufeng, YAO Jun, et al. DES study of blade trailing edge cutback cooling performance with various lip thicknesses [J]. Applied Thermal Engineering, 2016, 99: 434-445.

YAO Yufeng, EFFENDY W, YAO Jun. Comparison study of turbine blade with trailing-edge cutback coolant ejection designs [C]//51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, VA, USA: AIAA, 2013: AIAA 2013-548.

EFFENDY M, YAO Yufeng, YAO Jun, et al. Detached eddy simulation of blade trailing-edge cutback cooling performance at various ejection slot angles [J]. International Journal of Heat and Fluid Flow, 2019, 80: 108487.

EFFENDY M, YAO Yufeng, SUGATI D, et al. Numerical study of pin-fin cooling on gas turbine blades [J]. AIP Conference Proceedings, 2019, 2114(1): 060022.

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.

NAQAVI I Z, TUCKER P G, LIU Yan. Large-eddy simulation of the interaction of wall jets with external stream [J]. International Journal of Heat and Fluid Flow, 2014, 50: 431-444.

IVANOVA E, LEDEZMA G, WANG Guanghua, et al. Experimental and numerical investigations of the heat transfer and flow field in a trailing edge cooling geometry: part 2 LES and hybrid RANS/LES study [C]//ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. New York, USA: ASME, 2015: V05BT12A041.

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, 183.

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, 183.

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.

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Research on Film Cooling Characteristics of Trailing Edge Cutback with Dimples

Investigation of Unsteady Cooling Performance in a Trailing Edge Cutback Model with Land Extensions

An Experimental Investigation of Improving Film Cooling Effectiveness for Turbine Vane Endwalls Using Curtain Cooling

Effects of Expansion Angle Crater Film Hole on the Film Cooling Characteristics of a Double-Wall Structure

Research and Application Progress on Damage Detection for High-Temperature Structures of the Aero-Engines

Related Author

王茜

何坤

晏鑫

YANG Xing

ZHAO Qiang

WU Hang

FENG Zhenping

WANG Xiangyu

Related Institution

School of Energy and Power Engineering, Xi’an Jiaotong University

School of Energy and Power Engineering, Xi'an Jiaotong University

Shaanxi Engineering Laboratory of Turbomachinery and Power Equipment

Xi'an Aerospace Propulsion Institute

School of Mechanical Engineering，Xi'an Jiaotong University

⁰