端壁射流跨区域改善叶片吸力面气膜冷却特性

赵长宇; 何海超; 张魏; 刘松; 赵志奇; 李广超

doi:10.13224/j.cnki.jasp.20240080

端壁射流跨区域改善叶片吸力面气膜冷却特性

doi: 10.13224/j.cnki.jasp.20240080

赵长宇^1,,
何海超¹,
张魏¹,
刘松²,
赵志奇¹,
李广超^1,*, ,

1.
沈阳航空航天大学航空发动机学院，沈阳 110136
2.
中国航发四川燃气涡轮研究院，四川绵阳 610500

基金项目: 国家自然科学基金（52376028）；辽宁省自然科学基金（2022-MS-296）

详细信息

作者简介:
赵长宇（1976-），男，工程师，博士，研究方向为航空发动机气动传热。E-mail：10875925@qq.com

通讯作者:
李广超（1979-），男，教授，博士，研究方向为航空发动机气动传热。E-mail：ligc706@163.com

中图分类号: V232.4
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出版历程
- 收稿日期: 2024-02-05
- 网络出版日期: 2025-09-29

Improvement of film cooling performance on blade suction surface by the endwall jet across regions

1.
School of Aero-engine，Shenyang Aerospace University，Shenyang 110136，China
2.
Sichuan Gas Turbine Establishment，Aero Engine Corporation of China，Mianyang Sichuan 610500，China

摘要

摘要:
针对航空发动机叶片吸力面近端区烧蚀问题，在分析了气膜偏移冷却失效特性基础上，提出利用端壁气膜孔射流跨区域补偿冷却叶片吸力面近端区的设计方法。采用压力敏感漆实验技术和数值计算相结合方法研究了端壁气膜孔射流在叶栅内涡系作用下对叶片近端区形成气膜冷却的机制，分析了端壁气膜孔布局和吹风比对叶片近端区气膜效率改善效果。结果表明：通道涡和角涡是引起叶片吸力面近端区气膜偏移失效的主要原因，吹风比对失效区范围影响较弱。随着吹风比的增大，端壁气膜孔射流在吸力面近端区的气膜效率值和有效覆盖范围均增大。随着端壁气膜孔出口与叶片吸力面距离的增大，吸力面近端区气膜覆盖范围向叶根方向移动。与无端壁气膜孔射流情况相比，端壁射流使吸力面近端区面平均气膜效率提高65%以上，在一定程度上可以改善叶片鳃区气膜孔射流在近端区气膜冷却失效问题。
- 气膜效率 /
- 端壁射流 /
- 气膜失效 /
- 跨区域冷却 /
- 补偿冷却
Abstract:
Based on analysis of the cooling failure characteristics of the film migration, a design method was proposed to compensate the near end of the suction surface of an aero-engine blade using the film hole jet. Pressure sensitive paint experiment technique and numerical calculation method were used to study the mechanism of film cooling in the near end area of the blade under the action of the vortex system in the cascade. The effects of film hole layout and blow ratio on the film effectiveness in the near end area of the blade were analyzed. The results showed that the passage vortex and Corner vortex were the main causes of the failure of the film migration in the near end of the suction surface of the blade, and the blow ratio had a weak influence on the failure region. With the increase of blowing ratio, the film effectiveness value and effective coverage area of the endwall film hole jet in the near end of the suction surface increased. With the increase of the distance between the exit of the endwall film hole and the suction surface of the blade, the coverage area of the film near the suction surface moved towards the blade root. Compared with the non-endwall jet, the average film effectiveness of the near end region of the suction surface increased by more than 65%, and the film cooling failure of the film hole jet in the near end region of the blade can be improved to a certain extent.
- film effectiveness /
- endwall jet /
- film failure /
- cross-regional cooling /
- compensated cooling

HTML

图 1 叶片近端区烧蚀现象

Figure 1. Phenomenon of ablation on blade near the endwall

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图 2 实验风洞系统及叶栅几何参数

Figure 2. Experimental wind tunnel system and geometrical parameter of cascade

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图 3 PSP标定曲线

Figure 3. Calibration curve of PSP

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图 4 整体计算模型

Figure 4. Overall computational model

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图 5 不同湍流模型与实验结果对比

Figure 5. Comparison of different turbulence models with experimental results

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图 6 叶片吸力面及端壁网格

Figure 6. Grid on the suction surface and endwall

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图 7 叶栅通道旋涡结构

Figure 7. Cascade passage vortex structure

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图 8 叶栅通道壁面切应力

Figure 8. Wall shear stress of cascade passage

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图 9 不同吹风比下无端壁孔时叶片吸力面鳃区气膜孔射流气膜效率

Figure 9. Film effectiveness downstream of hole on suction side gill region with no endwall holes under different blowing ratios

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图 10 不同布局方案的叶片吸力面气膜效率

Figure 10. Film effectiveness of the suction surface of the blade with different layout schemes

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图 11 展向平均气膜效率沿主流流动流向变化

Figure 11. Spanwisely averaged film effectiveness along the mainstream direction

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图 12 主流与端壁射流的相互作用

Figure 12. Interaction between endwall jet and main stream

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图 13 3种气膜孔布置下端壁射流流线对比

Figure 13. Comparison of streamlines for endwall jets under three different film hole configurations

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图 14 面平均气膜效率

Figure 14. Surface average film effectiveness

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表 1 不同气膜效率下的不确定度

Table 1. Uncertainty at different film effectiveness

η （Δη/η）/%

0.1 16.2

0.2 8.5

0.3 5.1

0.5 2.7

下载: 导出CSV

参考文献(20)

[1]	WINKA J R, ANDERSON J B, BOYD E J, et al. Convex curvature effects on film cooling adiabatic effectiveness[J]. Journal of Turbomachinery, 2014, 136(6): 061015. doi: 10.1115/1.4025691
[2]	NICOLAS J, LE M A. Curvature effects on a turbine blade film cooling: 74-GT-156 [R]. Zurich, Switzerland : ASME, 1974.
[3]	ZHANG Fan, SONG Hui, LIU Cunliang, et al. Study on the film cooling effectiveness of shaped holes in the suction surface gill region of the turbine blade[J]. International Journal of Thermal Sciences, 2023, 184: 107977. doi: 10.1016/j.ijthermalsci.2022.107977
[4]	ITO S, GOLDSTEIN R J, ECKERT E R G. Film cooling of a gas turbine blade[J]. Journal of Engineering for Power, 1978, 100(3): 476-481. doi: 10.1115/1.3446382
[5]	JIANG H W, HAN J C. Effect of film hole row location on film effectiveness on a gas turbine blade[J]. Journal of Heat Transfer, 1996, 118(2): 327-333. doi: 10.1115/1.2825848
[6]	ERIKSEN V L, GOLDSTEIN R J. Heat transfer and film cooling following injection through inclined circular tubes[J]. ASME Journal of Heat Transfer, 1974, 96: 239-245. doi: 10.1115/1.3450171
[7]	MARKS C R, FLETCHER N, SONDERGAARD R. Vortex unsteadiness in the endwall region of a high-lift low-pressure turbine passage[R]. Rotterdam, The Netherlands: American Society of Mechanical Engineers, 2022.
[8]	PIERCE F J, SHIN J. The development of a turbulent junction vortex system (data bank contribution)[J]. Journal of Fluids Engineering, 1992, 114(4): 559-565. doi: 10.1115/1.2910068
[9]	张深, 李国庆, 刘浩, 等. 涡轮导叶压力面分区域复合角气膜冷却特性[J]. 航空动力学报, 2024, 39(3): 20220177. ZHANG Shen, LI Guoqing, LIU Hao, et al. Multi region compound angle film cooling characteristics on pressure side of turbine guide vane[J]. Journal of Aerospace Power, 2024, 39(3): 20220177. (in Chinese ZHANG Shen, LI Guoqing, LIU Hao, et al. Multi region compound angle film cooling characteristics on pressure side of turbine guide vane[J]. Journal of Aerospace Power, 2024, 39(3): 20220177. (in Chinese)
[10]	王磊, 李海旺, 谢刚, 等. 涡轮动叶吸力面气膜冷却径向差异对比[J]. 航空动力学报, 2024, 39(4): 20220349. WANG Lei, LI Haiwang, XIE Gang, et al. Comparison for radial difference of film cooling performance on suction surface of a rotor blade[J]. Journal of Aerospace Power, 2024, 39(4): 20220349. (in Chinese WANG Lei, LI Haiwang, XIE Gang, et al. Comparison for radial difference of film cooling performance on suction surface of a rotor blade[J]. Journal of Aerospace Power, 2024, 39(4): 20220349. (in Chinese)
[11]	WANG Lei, LI Haiwang, XIE Gang, et al. Effect of blowing ratio, rotation, and film hole row location on film cooling on the suction surface of a rotating turbine blade[J]. International Journal of Heat and Mass Transfer, 2023, 208: 124048. doi: 10.1016/j.ijheatmasstransfer.2023.124048
[12]	胡可欣, 张振, 苏欣荣, 等. 透平静叶叶身全覆盖气膜冷却有效度实验研究[J]. 工程热物理学报, 2023, 44(7): 1793-1799. HU Kexin, ZHANG Zhen, SU Xinrong, et al. An experimental investigation of full coverage film cooling effectiveness of a turbine vane[J]. Journal of Engineering Thermophysics, 2023, 44(7): 1793-1799. (in Chinese HU Kexin, ZHANG Zhen, SU Xinrong, et al. An experimental investigation of full coverage film cooling effectiveness of a turbine vane[J]. Journal of Engineering Thermophysics, 2023, 44(7): 1793-1799. (in Chinese)
[13]	陶皓杰, 迟重然, 臧述升. 涡轮动叶吸力侧单排气膜孔冷却性能研究[J]. 工程热物理学报, 2021, 42(3): 595-600. TAO Haojie, CHI Zhongran, ZANG Shusheng. Cooling performance of single-row cylindrical film holes on suction side of a rotor blade[J]. Journal of Engineering Thermophysics, 2021, 42(3): 595-600. (in Chinese TAO Haojie, CHI Zhongran, ZANG Shusheng. Cooling performance of single-row cylindrical film holes on suction side of a rotor blade[J]. Journal of Engineering Thermophysics, 2021, 42(3): 595-600. (in Chinese)
[14]	JIANG Yan, LI Haiwang, LIU Runzhou, et al. Film cooling comparison of shaped holes among the pressure surface, the suction surface and the leading edge of turbine vane[J]. Applied Thermal Engineering, 2023, 219: 119343. doi: 10.1016/j.applthermaleng.2022.119343
[15]	LI Guangchao, WAN Li. Film cooling improvement of dovetail hole compared to cylindrical hole at different hole row locations on nozzle guide vane[J]. Case Studies in Thermal Engineering, 2023, 45: 103015. doi: 10.1016/j.csite.2023.103015
[16]	ZHU Xingdan, ZHANG Jingzhou, TAN Xiaoming. Numerical assessment of round-to-slot film cooling performances on a turbine blade under engine representative conditions[J]. International Communications in Heat and Mass Transfer, 2019, 100: 98-110. doi: 10.1016/j.icheatmasstransfer.2018.12.008
[17]	杨卫华, 李永康, 张靖周, 等. 突片作用下气膜冷却效率的试验研究[J]. 航空动力学报, 2007, 22(3): 380-383. YANG Weihua, LI Yongkang, ZHANG Jingzhou, et al. Experimental study of cooling efficiency of film cooling with tab[J]. Journal of Aerospace Power, 2007, 22(3): 380-383. (in Chinese YANG Weihua, LI Yongkang, ZHANG Jingzhou, et al. Experimental study of cooling efficiency of film cooling with tab[J]. Journal of Aerospace Power, 2007, 22(3): 380-383. (in Chinese)
[18]	李广超, 高志阳, 张魏, 等. 双排孔顺-逆射流组合方式对气膜冷却的影响[J]. 推进技术, 2019, 40(3): 643-652. LI Guangchao, GAO Zhiyang, ZHANG Wei, et al. Effects of combination of forward jet and backward jet with two rows of holes on film cooling[J]. Journal of Propulsion Technology, 2019, 40(3): 643-652. (in Chinese LI Guangchao, GAO Zhiyang, ZHANG Wei, et al. Effects of combination of forward jet and backward jet with two rows of holes on film cooling[J]. Journal of Propulsion Technology, 2019, 40(3): 643-652. (in Chinese)
[19]	HATA D, KAKIO K, KAWATA Y, et al. Improvement of film cooling effectiveness in the gas turbine endwall by use of optimization framework[R]. San Francisco, US: American Society of Mechanical Engineers, 2019, 700-708.
[20]	DU Kun, SONG Liming, LI Jun, et al. Effects of the layout of film holes near the vane leading edge on the endwall cooling and phantom cooling of the vane suction side surface[J]. Numerical Heat Transfer, Part A: Applications, 2017, 71(9): 910-927. doi: 10.1080/10407782.2017.1326788