“主孔扩张、两侧副孔收缩”组合孔气膜冷却特性与损失机理

冯国淼; 李国庆; 白晓晖; 刘佳林; 李润东; 卢新根

doi:10.13224/j.cnki.jasp.20240770

“主孔扩张、两侧副孔收缩”组合孔气膜冷却特性与损失机理

doi: 10.13224/j.cnki.jasp.20240770

冯国淼^{1, 2, 3,},
李国庆^{2, 3, 4,*, ,},
白晓晖^{2, 3, 5},
刘佳林^{2, 3, 4},
李润东¹,
卢新根^{2, 3, 4}

1.
沈阳航空航天大学能源与环境学院，沈阳 110136
2.
中国科学院工程热物理研究所，北京 100190
3.
中国科学院轻型涡轮动力全国重点实验室，北京 100190
4.
中国科学院大学航空宇航学院，北京 100049
5.
中国科学技术大学工程科学学院，合肥 230027

基金项目: 国家自然科学基金（52376038）；航空发动机及燃气轮机基础科学中心项目（P2022-B-Ⅱ-006-001）

详细信息

作者简介:
冯国淼（2000-），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（1981-），男，研究员，博士，主要从事航空发动机气动与传热研究。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: 2024-11-14
- 网络出版日期: 2025-10-24

Film cooling characteristics and loss mechanism of combined construct with expansive main hole and contractive secondary holes

FENG Guomiao^{1, 2, 3
,},
LI Guoqing^{2, 3, 4,*
, ,},
BAI Xiaohui^{2, 3, 5},
LIU Jialin^{2, 3, 4},
LI Rundong¹,
LU Xingen^{2, 3, 4}

1.
College of Energy and Environment，Shenyang Aerospace University，Shenyang 110136，China
2.
Institute of Engineering Thermophysics，Chinese Academy of Sciences，Beijing 100190，China
3.
National Key Laboratory of Science and Technology on Advanced Light-duty Gas-turbine，Chinese Academy of Sciences，Beijing 100190，China
4.
School of Aeronautics and Astronautics，University of Chinese Academy of Sciences，Beijing 100049，China
5.
School of Engineering Science，University of Science and Technology of China，Hefei 230027，China

摘要

摘要:
采用数值模拟的方法，在主流马赫数为0.6条件下，对比分析了三圆柱形组合孔、变截面圆柱形组合孔、新月形组合孔在不同吹风比（0.5～2.0）的气膜冷却特性与气动损失机理。提出了“主孔扩张、两侧副孔收缩”的新月形组合孔结构，中间的扩张主孔抑制了主流穿透，两侧的收缩副孔有利于冷气沿流向发展，主副孔压力梯度不同诱导了反肾形涡形成，从而改变了孔外的掺混结构，促进了冷气的横向发展，减少了掺混总压损失。结果表明：吹风比为1.5、2.0时，与三圆柱形组合孔相比，新月形组合孔的气膜冷却效率分别提高了17.8%、29.7%，气膜冷却带来的掺混总压损失减少了51%、43%。
- 气膜冷却 /
- 涡轮叶片 /
- 损失机理 /
- 异形组合孔 /
- 孔内流动
Abstract:
Film cooling characteristics and aerodynamic loss mechanism were numerically simulated under a mainstream Mach number of 0.6. Three-cylindrical combination holes, variable cross-section cylin-drical combination holes and crescent combination holes were compared at the blowing ratio varying from 0.5 to 2.0. In a crescent combination holes with expansive main hole and contractive secondary holes, main-stream penetration was prevented in the mid-expansion hole. As for the side-contraction holes, the anti-kidney vortex was promoted due to acceleration. The mixing structure was changed due to different pre-ssure gradients of holes. When the blowing ratio was 1.5 and 2.0, compared with three-cylindrical combi-nation holes, the film cooling effectiveness increased by 17.8% and 29.7%, respectively, and the mixing pressure loss due to film cooling declined by 51% and 43%, respectively, in crescent combination holes.
- film cooling /
- turbine blade /
- loss mechanism /
- shaped combination holes /
- flow in holes

HTML

图 1 计算域模型

Figure 1. Computational domain model

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图 2 气膜孔结构示意图

Figure 2. Schematic of film cooling hole configuration

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图 3 数值模拟网格

Figure 3. Numerical simulation grids

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图 4 计算湍流模型验证

Figure 4. Verification of computational turbulence model

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图 5 网格无关性验证

Figure 5. Grid independence verification

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图 6 组合孔绝热气膜冷却效率分布

Figure 6. Adiabatic film cooling effectiveness distribution of combination holes

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图 7 横向平均冷却效率

Figure 7. Laterally averaged film cooling effectiveness

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图 8 气膜孔中心面马赫数与矢量云图

Figure 8. Mach number distribution with flow vectors on center plane of film cooling holes

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图 9 新月形组合孔截面马赫数云图和流线

Figure 9. Cross section Mach number cloud diagram and streamline of crescent combination hole

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图 10 气膜孔出口处Y方向速度云图

Figure 10. Y-velocity contours along exit planes of film holes

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图 11 气膜孔出口处Z方向速度云图

Figure 11. Z-velocity contours along exit planes of film holes

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图 12 3种组合孔X/D=5，10，20，30截面温度云图和流线图

Figure 12. Temperature contours and streamlines of the three combination holes on planes X/D = 5，10，20，30

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图 13 3种气膜孔结构的总压损失系数

Figure 13. Total pressure loss coefficient of three kinds of film hole structure

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图 14 3种气膜孔结构的孔内总压损失系数

Figure 14. Total pressure loss coefficient in the hole of three kinds of film hole structure

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图 15 3种气膜孔结构的掺混总压损失系数

Figure 15. Mixing pressure loss coefficient of three kinds of film hole

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表 1 气膜孔出口参数

Table 1. Exit parameters of film cooling hole configuration

气膜孔形状	出口截面积/mm²
气膜孔形状	主孔	副孔
三圆柱形组合孔（3CY）	14.14	14.14
变截面圆柱形组合孔（NSIS）	25.13	6.28
新月形组合孔（CRESCENT）	35.45	10.04

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表 2 边界条件设置

Table 2. Boundary conditions

边界条件	设计值
冷气进口温度T_c/K	300
主流进口马赫数	0.6
主流出口静压p_out/Pa	101325
冷气与主流温比T_c/T_m	0.55
冷气与主流密度比ρ_c/ρ_m	1.8
吹风比M	0.5～2.0

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