吹风比对带有异型气膜孔涡轮叶片综合冷却效率的影响

龙琏; 张慧骝; 王钦钦; 黄玥; 崔亭亭; 朱晓华

doi:10.13224/j.cnki.jasp.20250005

吹风比对带有异型气膜孔涡轮叶片综合冷却效率的影响

doi: 10.13224/j.cnki.jasp.20250005

龙琏^1,,
张慧骝^1,*, ,,
王钦钦²,
黄玥¹,
崔亭亭²,
朱晓华²

1.
厦门大学航空航天学院，福建厦门 361005
2.
中国航发四川燃气涡轮研究院，成都 610500

详细信息

作者简介:
龙琏（1999-），女，硕士生，主要研究方向为涡轮叶片冷却结构设计。E-mail：ll18845592973@163.com

通讯作者:
张慧骝（1961-），男，教授，博士，主要从事传热、航空发动机设计研究。E-mail：huiliuzhang@xmu.edu.cn

中图分类号: V232.1
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出版历程
- 收稿日期: 2025-01-03
- 网络出版日期: 2026-04-05

Influence of blowing ratio on comprehensive cooling efficiency of turbine blades with shaped film hole

1.
School of Aerospace Engineering，Xiamen University，Xiamen Fujian 361005，China
2.
Sichuan Gas Turbine Establishment，Aero Engine Corporation of China，Chengdu 610500，China

摘要

摘要:
为了探究气膜孔形状以及吹风比大小对气膜冷却特性和流动结构的影响，开展了涡轮一级动叶综合冷却效率的数值研究。建立并验证了涡轮动叶共轭传热数值模型，对比分析了圆柱形、簸箕形和燕尾形这3种异型气膜孔在不同工况条件下叶片综合冷却效率，阐明了位于吸力侧不同曲率位置的气膜冷却混合特性。结果表明：采用的共轭传热数值模型能够很好地预测叶片表面的冷却效率分布。对于讨论的涡轮叶片而言，3种气膜孔结构的理想吹风比值皆为1.0。在相同吹风比条件下，SS₂位置处的射流混合范围相较于SS₁位置明显更大，其射流混合更加强烈。在叶片的吸力侧采用簸箕形孔能够得到更好的经济效益。
- 气膜冷却 /
- 异型气膜孔 /
- 综合冷却效率 /
- C3X叶片 /
- 共轭传热
Abstract:
In order to investigate the influence of the geometry of the air film hole and their blowing ratio on the cooling characteristics and flow structure of the air film, a numerical study on the comprehensive cooling efficiency of the first stage turbine moving blade was conducted. A conjugate heat transfer numerical model of the turbine rotor blade was established and verified. The comprehensive cooling efficiencies of the blade with three special-shaped film holes (cylindrical, dustpan and dovetail) under different operating conditions were compared and analyzed. The mixing characteristics of film cooling at different curvature positions on the suction side were clarified. The results showed that the conjugate heat transfer numerical model adopted can well predict the distribution of the cooling efficiency on the blade surface. For the turbine blade discussed, the ideal blowing ratios for all three film- hole structures were 1.0. Under the same blowing ratio, the jet mixing range at the SS₂ position was significantly larger than that at the SS₁ position, and the jet mixing was more intense. Using dustpan-shaped holes on the suction side of the blade can achieve better economic benefits.
- film cooling /
- shaped holes /
- comprehensive cooling efficiency /
- C3X vane /
- conjugate heat transfer

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图 1 C3X横截面与几何结构

Figure 1. C3X cross-sectional and geometry structure

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图 2 C3X网格结构与网格无关性验证

Figure 2. C3X grid structure and grid independence verification

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图 3 C3X叶片表面温度分布和横截面温度云图

Figure 3. C3X blade surface temperature distribution and cross-sectional temperature distribution

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图 4 叶片几何计算模型

Figure 4. Blade geometry calculation model

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图 5 叶片中间截面结构

Figure 5. Blade cross-sectional structure

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图 6 气膜孔几何结构

Figure 6. Geometry structure of film holes

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图 7 3种孔形的冷却效率云图

Figure 7. Cooling efficiency contour plots for three hole shapes

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图 8 冷却效率分布曲线

Figure 8. Distribution curve of cooling efficiency

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图 9 冷却效率随吹风比的变化

Figure 9. Variation of cooling efficiency with blowing ratio

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图 10 不同吹风比工况下冷却效率分布云图

Figure 10. Cooling efficiency distribution contour under different blowing ratio conditions

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图 11 3种孔形冷却效率随吹风比的变化

Figure 11. Variation of cooling efficiency with blowing ratio for three hole shapes

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图 12 气膜孔下游3个截面的位置（单位：mm）

Figure 12. Location of the three sections downstream of the film hole （unit：mm）

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图 13 不同吹风比下3个截面上冷却效率分布云图

Figure 13. Cooling efficiency distribution contour of three cross-sections under different blowing ratios

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图 14 不同吹风比下3种孔形的3个截面上冷却效率分布云图

Figure 14. Cooling efficiency distribution contour of three cross-sections for three hole shapes under different blowing ratios

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表 1 主流边界条件

Table 1. Mainstream boundary conditions

参数	数值
进口总压$ p_{\text{hin}}^{*} $/kPa	285.13
进口总温$ T_{\mathrm{\infty }}^{\mathrm{*}} $/K	701.00
进口湍流度I	0.065
出口静压$ p_{\text{hout}}^{\mathrm{*}} $/kPa	190.00

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表 2 C3X叶片材料特性

Table 2. C3X blade material properties

参数	数值
密度ρ/（kg/m³）	7900
比热容c/（kJ/（kg·K））	582
导热系数ω/（W/（m·K））	6.13+0.0182T

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表 3 径向孔边界条件

Table 3. Radial hole boundary conditions

孔编号	质量流量$ \dot{m} $/（g/s）	温度T/K
1	7.84	425.25
2	7.93	367.06
3	7.94	350.79
4	8.26	402.94
5	7.48	325.10
6	6.91	326.76
7	7.52	360.59
8	7.70	422.46
9	4.73	379.99
10	3.57	421.32

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表 4 前缘腔室供气参数

Table 4. Leading edge chamber air supply parameters

腔室编号	压力比 $ {p}_{\mathrm{c}}/p_{\text{hin}}^{\mathrm{*}} $	温度比 T_c/$ T_{\mathrm{\infty }}^{\mathrm{*}} $	质量流量 $ \dot{m} $/（g/s）
A₁	1.051	0.85	13.40
A₂	1.048	0.86	6.83
A₃	1.050	0.83	7.52

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