涡轮导叶压力面分区域复合角气膜冷却特性

张深; 李国庆; 刘浩; 康忠; 张燕峰; 卢新根

doi:10.13224/j.cnki.jasp.20220177

涡轮导叶压力面分区域复合角气膜冷却特性

doi: 10.13224/j.cnki.jasp.20220177

张深^{1, 2},
李国庆^{1, 2,*, ,},
刘浩^{1, 2},
康忠^{1, 3},
张燕峰^{1, 2},
卢新根^{1, 2}

1.
中国科学院工程热物理研究所，北京 100190
2.
中国科学院大学航空宇航学院，北京 100049
3.
华北电力大学能源动力与机械工程学院，北京 102206

基金项目: 国家自然科学基金（51976214）；航空发动机及燃气轮机基础科学中心项目（2022-B-Ⅱ-006-004)

详细信息

作者简介:
张深（1997-），男，硕士生，主要从事涡轮叶片气膜冷却研究

通讯作者:
李国庆（1982-），男，研究员，博士，主要从事涡轮热端部件先进冷却结构设计技术研究。E-mail：liguoqing@iet.cn

中图分类号: V231.1
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- 被引次数: 0
出版历程
- 收稿日期: 2022-03-31
- 网络出版日期: 2023-10-30

Multi region compound angle film cooling characteristics on pressure side of turbine guide vane

ZHANG Shen^{1, 2},
LI Guoqing^{1, 2,*
, ,},
LIU Hao^{1, 2},
KANG Zhong^{1, 3},
ZHANG Yanfeng^{1, 2},
LU Xingen^{1, 2}

1.
Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China
2.
School of Aeronautics and Astronautics, University of Chinese Academy of Sciences, Beijing 100049, China
3.
School of Energy, Power and Mechanical Engineering, North China Electric Power University, Beijing 102206, China

摘要

摘要:
针对通道二次流造成涡轮叶片压力面气膜轨迹发生偏转的现象，提出了沿展向分区域布置复合角的设计概念。以高压涡轮导叶HS1A为研究对象，采用数值模拟的方法，在出口雷诺数为2.3×10⁵的工况下，分析了二次流、复合角和吹风比对气膜冷却特性的影响。结果表明：近端区二次流产生的径向潜流具有促进气膜展向覆盖的能力，相较于叶中区提高了气膜孔出口下游的冷却效率，但也会加剧射流和主流的掺混，减小气膜的有效覆盖长度；针对不同展向区域的二次流大小，精细化布置各区域的气膜孔复合角，可以将气膜轨迹的偏转角度全部修正为0°，同时将平均气膜冷却效率提升了10.42%；复合角冷却模型在吹风比为0.5～1.0时具有较好的范围适用性，吹风比增大至1.3时气膜轨迹会发生反向偏转。
- 涡轮导叶 /
- 气膜冷却 /
- 通道二次流 /
- 分区域复合角 /
- 气膜冷却效率
Abstract:
In view of the phenomenon that the secondary flow in the channel causes the deflection of the film trajectory on the pressure surface, the concept of multi region compound angle along the spanwise direction was proposed. Numerical simulation was conducted to investigate the film cooling characteristics of turbine guide vane HS1A. The influences of secondary flow, compound angle and blowing ratio on the film cooling characteristics were analyzed under the condition of turbine outlet Reynolds number of 2.3×10⁵. The results showed that the secondary flow in the near endwall had the ability to promote the spanwise coverage of the film, which improved the cooling effectiveness downstream the film hole outlet compared with the mid blade region, but also intensified the mixing of the jet and the mainstream, and reduced the effective coverage length of the film; according to the secondary flow in different spanwise regions, the film hole compound angle in each region was finely arranged, which can correct all the deflection angles of the film trajectory to 0°, and the average film cooling effectiveness was increased by 10.42%; the compound angle cooling model had good applicability within the range of blowing ratio of 0.5−1.0. When the blowing ratio increased to 1.3, the film trajectory could deflect reversely.
- turbine guide vane /
- film cooling /
- passage secondary flow /
- multi region compound angle /
- film cooling effectiveness

HTML

图 1 气膜冷却模型

Figure 1. Film cooling model

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图 2 气膜冷却模型几何参数

Figure 2. Geometry of the film cooling model

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图 3 计算域网格示意图

Figure 3. Schematic diagram of computational domain grid

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图 4 等熵马赫数分布

Figure 4. Distribution of isentropic Mach numbers

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图 5 叶根至叶中边界层分布

Figure 5. Distribution of boundary layer from root to middle of the blade

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图 6 叶根附近三维流线

Figure 6. Three-dimensional streamlines near root of the blade

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图 7 偏转规律相似性对比

Figure 7. Comparison of deflection law similarity

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图 8 不同复合角气膜冷却效率云图

Figure 8. Contours of film cooling effectiveness at different compound angle

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图 9 不同复合角平均气膜冷却效率分布

Figure 9. Distribution of averaged film cooling effectiveness at different compound angle

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图 10 近端区气膜冷却效率分布

Figure 10. Distribution of film cooling effectiveness near endwall

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图 11 过渡区气膜冷却效率分布

Figure 11. Distribution of film cooling effectiveness in the transition zone

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图 12 不同区域气膜冷却效率分布

Figure 12. Distribution of film cooling effectiveness in different zones

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图 13 气膜孔出口下游流动结构

Figure 13. Flow structure downstream of the film hole

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图 14 不同吹风比工况下气膜冷却效率分布

Figure 14. Distribution of film cooling effectiveness under different blowing ratios

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图 15 TGV07近端区不同吹风比气膜冷却效率

Figure 15. Film cooling effectiveness of different blowing ratios near the endwall for TGV07

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表 1 叶片压力面气膜孔分区域复合角分布

Table 1. Composite angle distribution of single film holes on pressure side of blade （°）

工况	H1	H2	H3	H4	H5	H6	H7	H8	H9
TGV00	0	0	0	0	0	0	0	0	0
TGV01	−5	−3	−2	−1	0	2	4	6	10
TGV02	−15	−9	−6	−3	0	4	8	12	20
TGV03	−25	−15	−10	−5	0	6	12	18	30
TGV04	−35	−21	−14	−7	0	8	16	24	40
TGV05	−45	−27	−18	−9	0	10	20	30	50
TGV06	−53	−33	−22	−11	0	12	24	36	57
TGV07	−45	−30	−15	−7	0	7	15	30	45
注：复合角指向叶尖为负值，指向叶根为正值。

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