涡轮端壁前缘缝型孔-通道水滴形孔组合气膜冷却实验研究

叶林; 邓伟; 孙诚; 梁喜源; 王雨; 刘存良

doi:10.13224/j.cnki.jasp.20250473

涡轮端壁前缘缝型孔-通道水滴形孔组合气膜冷却实验研究

doi: 10.13224/j.cnki.jasp.20250473

叶林^1,,
邓伟¹,
孙诚²,
梁喜源¹,
王雨¹,
刘存良^1,*, ,

1.
西北工业大学动力与能源学院，西安 710129
2.
中国航发四川燃气涡轮研究院，成都 610500

基金项目: 国家自然科学基金（52406056，U2241268）；中国航发四川燃气涡轮研究院外委课题（STH-2023-0002）

详细信息

作者简介:
叶林（1992-），男，教授，博士，研究领域为空天动力装备主动热防护技术。E-mail：linye@nwpu.edu.cn

通讯作者:
刘存良（1983-），男，教授，博士，研究领域为航空宇航推进系统传热与冷却技术。E-mail：liucunliang@nwpu.edu.cn

中图分类号: V231.1
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出版历程
- 收稿日期: 2025-10-16
- 网络出版日期: 2025-12-24

Experimental study of combined film cooling on turbine endwall using leading-edge slot holes coupled with passage teardrop-shaped holes

YE Lin^1
,,
DENG Wei¹,
Sun Cheng²,
LIANG Xiyuan¹,
WANG Yu¹,
LIU Cunliang^{1,*
, ,}

1.
School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China
2.
Sichuan Gas Turbine Establishment，Aero Engine Corporation of China，Chengdu 610500，China

摘要

摘要:
涡轮叶片端壁面积大，常采用分区多排气膜孔进行有效热防护，但由于端壁表面不同区域的燃气流动特征差异大，且受涡轮叶栅流场中的通道涡裹挟作用，易于导致端壁气膜均匀覆盖难。扩张型气膜孔因其出口动量的调节或使得冷气射流易于贴附表面，数值仿真分析了不同端壁区域下异形孔气膜冷却特性的影响规律，采用基于传热传质类别的压力敏感漆（PSP）技术实验测量了不同密度比（DR）和吹风比（M）下圆柱孔群布局结构及前缘缝孔-叶栅通道水滴孔结构对端壁表面气膜冷却效率的影响。结果表明，高吹风比下冷气高动量特征致使两种结构端壁前缘均出现了冷气吹飞现象。端壁前缘缝孔结构有效地削弱了叶栅通道内通道涡的强度，且叶栅通道内水滴孔结构具有抵御压力面侧马蹄涡分支破坏作用的能力，从而使得端壁气膜冷却效率在密度比为1.4和吹风比为 3.0下分别最大增加了80.18%和66.16%。随着吹风比的增大，端壁气膜冷却效率呈现先增大后减小的趋势，密度比为1.4且吹风比大于 3.0和密度比为3.0且吹风比大于4.0时出现冷效衰退现象，冷却效率峰值吹风比与密度比、端壁压力梯度因素相关。
- 涡轮导叶端壁 /
- 压力敏感漆 /
- 密度比 /
- 缝型孔 /
- 水滴形孔 /
- 气膜冷却效率
Abstract:
Turbine vane endwall with large surface area is commonly protected by zoned, multi-row film cooling arrays; however, the strong spatial variation of mainstream flow and entrainment by passage vortices within the turbine cascade flow field frequently impede uniform film coverage. Expansion-shaped film cooling holes by modulating exit momentum can promote coolant adherence to the surface. By combining numerical simulations and pressure-sensitive paint (PSP) experiments, the film cooling characteristics of shaped holes in different endwall regions were investigated, and the endwall film cooling effectiveness of a baseline cylindrical hole configuration and a combined leading-edge slot hole–passage teardrop-shaped hole configuration under varying density ratios and blowing ratios was quantified. Results showed that, at high blowing ratios, the elevated coolant momentum induced blow-off at the endwall leading edge for both configurations. The leading-edge slot holes substantially attenuated passage-vortex strength, while the passage teardrop-shaped holes demonstrated enhanced resilience against disruption by pressure side horseshoe-vortex branches; as a result, the combined configuration produced maximum increases in endwall film cooling effectiveness of 80.18% at density ratio of 1.4 and 66.16% at density ratio of 3.0. With blowing ratio increasing, endwall film cooling effectiveness exhibited a rise-then-fall behavior: cooling degradation was observed at density ratio of 1.4 when blowing ratio exceeded 3.0 and at density ratio of 3.0 when blowing ratio exceeded 4.0. The blowing ratio corresponding to peak cooling effectiveness was influenced by density ratio and the local endwall pressure gradient.
- turbine vane endwall /
- pressure-sensitive paint /
- density ratio /
- slot hole /
- teardrop-shaped hole /
- film cooling effectiveness

HTML

图 1 试验段结构

Figure 1. Structural schematic of test section

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图 2 实验通道周期性验证

Figure 2. Experimental channel periodicity verification

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图 3 冷却结构II与冷却结构I气膜孔布局示意图

Figure 3. Schematic of film cooling hole layout with hybrid configuration: cooling structure I and cooling structure II

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图 4 异形气膜孔结构示意图

Figure 4. Schematic of shaped film cooling holes

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图 5 吸力侧圆柱孔结构及排布示意图

Figure 5. Schematic diagram of the cylindrical cooling hole structure and arrangement on the suction side

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图 7 不同密度比下，冷却结构I端壁表面气膜冷却效率分布云图

Figure 7. Contour plots of film cooling effectiveness distribution on the endwall surface of the cooling structure I under different density ratios

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图 6 实验原理及实验数据采集装置

Figure 6. Experimental principle and data acquisition system

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图 8 不同密度比下，冷却结构I端壁表面展向平均气膜冷却效率

Figure 8. Spanwise-averaged film cooling effectiveness on the endwall surface of the cooling structure I under different density ratios

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图 9 冷却结构I面平均气膜冷却效率

Figure 9. Surface-averaged film cooling effectiveness of the cooling structure I

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图 10 冷却结构I气膜有效度

Figure 10. Film cooling effectiveness of the cooling structure I

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图 11 不同密度比下，冷却结构II端壁表面气膜冷却效率分布云图

Figure 11. Contour plots of film cooling effectiveness distribution on the endwall surface of the cooling structure II under different density ratios

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图 12 不同密度比下，冷却结构II与冷却结构I端壁表面气膜冷却效率展向均值对比

Figure 12. Spanwise-averaged comparison of endwall surface film cooling effectiveness between the cooling structure II and cooling structure I under different density ratios

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图 13 冷却结构II与冷却结构I端壁表面面平均气膜冷却效率对比

Figure 13. Comparison of surface-averaged film cooling effectiveness on the endwall surface between the cooling structure II and cooling structure I

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图 14 冷却结构II与冷却结构I端壁表面气膜有效度对比

Figure 14. Comparison of film cooling effectiveness on the endwall surface between the cooling structure II and cooling structure I

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表 1 水滴孔几何参数

Table 1. Geometric parameters of teardrop-shaped film cooling holes

参数数值

孔倾角α/（°） 75
扩张角γ/（°） 15
扩张段长度L₁/mm 7L/12
扩张宽度L_w/mm 0.8
孔长L/mm 4.4～4.8
孔径D/mm 0.8

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表 2 PSP测量气膜有效度的相对不确定度

Table 2. Relative uncertainty of PSP measurement of film cooling effectiveness

η （∆η/η）/%
密度比1.4 密度比为3.0

0.05 37.08 77.92
0.1 17.31 35.64
0.2 7.47 14.71
0.3 4.22 7.92
0.5 1.70 2.83
0.6 1.09 1.70
0.8 0.38 0.50
0.9 0.16 0.19

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