旋转对弯扭涡轮叶片前缘气膜冷却数值模拟研究

韩枫; 陈娇娜; 浦昊天; 江文涛; 黄勇健; 毛军逵

doi:10.13224/j.cnki.jasp.20250426

旋转对弯扭涡轮叶片前缘气膜冷却数值模拟研究

doi: 10.13224/j.cnki.jasp.20250426

韩枫^{1, 2,},
陈娇娜^{1, 2},
浦昊天¹,
江文涛¹,
黄勇健¹,
毛军逵^1,*, ,

1.
南京航空航天大学能源与动力学院，南京 210016
2.
南京航空航天大学综合能源研究院，南京 210016

基金项目: 国家自然科学基金（52476077）；江苏省基础研究计划（BK20252025）；航空发动机及燃气轮机基础科学中心项目（P2022-A-Ⅱ-007-001）；国家科技重大专项（Y2022-Ⅲ-0003-0012）

详细信息

作者简介:
韩枫（1989-），男，副教授，博士，从事航空发动机热端部件流动与换热研究。E-mail：hanfeng@nuaa.edu.cn

通讯作者:
毛军逵（1976-），男，教授，博士，从事航空发动机热管理和高效热防护研究。E-mail：mjkpe@nuaa.edu.cn

中图分类号: V231.1
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出版历程
- 收稿日期: 2025-09-12
- 网络出版日期: 2026-07-31

Numerical simulation of leading-edge film cooling on the rotating twisted turbine blade

Han Feng^{1, 2
,},
Chen Jiaona^{1, 2},
Pu Haotian¹,
Jiang Wentao¹,
Huang Yongjian¹,
Mao Junkui^{1,*
, ,}

1.
College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
2.
Integrated Energy Institute，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

摘要

摘要:
在航空发动机及燃气轮机实际高速旋转条件下，流体受到哥氏力、离心力和浮升力等旋转多场力作用倍增，导致高速旋转状态下旋转（攻角）和吹风比（M）等参数对涡轮叶片前缘气膜冷却效率（η）影响规律与低转速实验存在差异。采用实际弯扭涡轮叶片，在实际高速旋转状态下，进行了旋转角速度和M对前缘区域气膜冷却特性影响的数值模拟研究。旋转角速度分别为1350 rad/s（正攻角）、1400 rad/s（零攻角）和1450 rad/s（负攻角），M范围为0.5～1.25，射流-主流密度比为1.04。本文揭示了高速旋转状态下旋转（攻角）和M对真实的弯扭涡轮叶片前缘η影响机理，发现了旋转（攻角）是决定前缘η分布的一个关键因素。随着旋转角速度的增大，滞止线从压力排和滞止线排孔之间，先移动至滞止线排孔中心连线附近，再移动至滞止线排和吸力排孔之间。前缘区域展向平均气膜冷却效率（$ \overline{\eta } $）随着M的增大呈现非线性变化规律，具体区域变化不同。当前缘无吹飞现象（M=0.5），前缘腔内冷气受到的哥氏力分量直接朝向滞止线排孔，不仅使得冷却工质更容易从滞止线排孔出流，而且使得更多流量的冷却工质从低半径位置出流，哥氏力另一分量使得冷却工质流向压力侧，有益于冷却工质从压力排孔出流。
- 旋转 /
- 吹风比 /
- 弯扭涡轮叶片 /
- 前缘 /
- 气膜冷却效率
Abstract:
Under actual high-speed rotation conditions of aero-engine and gas turbine, the fluid experienced enhanced effects from rotational forces including Coriolis force, centrifugal force, and buoyancy force. This resulted in differences in how parameters such as rotation (angle of attack) and blowing ratio (M) influenced the film cooling effectiveness (η) on turbine blade leading edges, compared with low-speed experimental conditions. A numerical simulation was performed under real aero-engine high-speed rotation conditions to investigate the effects of rotational angular velocity and M on the film cooling characteristics of an actual twisted turbine blade leading edge. The rotational angular velocities were set to 1350 rad/s (positive angle of attack), 1400 rad/s (zero angle of attack), and 1450 rad/s (negative angle of attack), with a M ranging from 0.5 to 1.25 and a jet-to-mainstream density ratio of 1.04. The mechanism by which rotation (angle of attack) and M affected the of the actual twisted turbine blade leading edge in a high-speed rotating state was revealed. Results indicated that the rotation (angle of attack) is a key factor determining the distribution on the leading edge. The stagnation line position shifted from the region between the pressure-side row and the stagnation row holes, first to near the stagnation row holes centerline, and then to the region between the stagnation row and the suction-side row holes. The spanwise-averaged film cooling effectiveness （$ \overline{\eta } $） on the leading edge region exhibited a nonlinear variation with the increasing M, and differences were observed in specific areas. When no take-off phenomenon occurred on the leading edge (M=0.5), the Coriolis force component acting on the coolant in the leading edge cavity was directly oriented toward the stagnation row of holes. This not only facilitated the outflow of coolant from the stagnation row holes but also promoted a greater flow rate of coolant discharging from lower-radius locations. Another component of the Coriolis force drove the coolant toward the pressure-side, making it beneficial for the coolant outflow from the pressure-side row holes.
- rotation /
- blowing ratio /
- twisted turbine blade /
- leading edge /
- film cooling effectiveness

HTML

图 1 带有前缘气膜冷却孔的弯扭涡轮叶片

Figure 1. Twisted turbine blade leading edge with film cooling holes

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图 2 弯扭涡轮叶片前缘冷却通道

Figure 2. Leading edge cooling channel of twisted turbine blade

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图 3 气膜孔倾斜角度

Figure 3. Film holes inclination angle

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图 4 进口角、进气角及攻角示意图

Figure 4. Illustration of inlet angle, air intake angle and angle of attack

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图 5 速度三角形

Figure 5. Velocity triangle diagram

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图 6 湍流模型验证

Figure 6. Turbulence model validation

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图 7 计算域与边界条件

Figure 7. Computational domains and boundary conditions

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图 8 叶片网格

Figure 8. Meshes of the blade

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图 9 网格无关性验证

Figure 9. Mesh independent verification

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图 10 旋转角速度为1350 rad/s时不同吹风比下的$ \eta $分布云图

Figure 10. $ \eta $ distribution under different blowing ratios when the rotational angular velocity is 1350 rad/s

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图 11 旋转角速度为1400 rad/s时不同吹风比下的$ \eta $分布云图

Figure 11. $ \eta $ distribution under different blowing ratios when the rotational angular velocity is 1400 rad/s

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图 12 旋转角速度为1450 rad/s时不同吹风比下的$ \eta $分布云图

Figure 12. $ \eta $ distribution under different blowing ratios when the rotational angular velocity is 1450 rad/s

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图 13 射流在叶片内部和外部流动轨迹^[16]

Figure 13. Flow trajectory of the jet inside the blade and in the external flow field

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图 14 当M=0.75，不同旋转角速度下参考截面流线和压力分布

Figure 14. Streamlines and pressure distribution of different rotational angular velocities when M=0.75

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图 15 当M=0.75，3排气膜孔内腔截面上的压力分布

Figure 15. Pressure distribution on the cross-section of the inner cavity of the three film holes when M=0.75

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图 16 旋转角速度为1350 rad/s时的$ \overline{\eta } $

Figure 16. $ \overline{\eta } $ at a rotational angular velocity of 1350 rad/s

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图 17 旋转角速度为1400 rad/s时的$ \overline{\eta } $

Figure 17. $ \overline{\eta } $ at a rotational angular velocity of 1400 rad/s

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图 18 旋转角速度为1450 rad/s时的$ \overline{\eta } $

Figure 18. $ \overline{\eta } $ at a rotational angular velocity of 1450 rad/s

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图 19 冷却工质受力分析

Figure 19. Analysis of the forces acting on the coolant

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图 20 M=0.5时的$ \overline{\eta } $

Figure 20. $ \overline{\eta } $ of M=0.5

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图 21 吹风比M=0.75时的$ \overline{\eta } $

Figure 21. $ \overline{\eta } $ of M=0.75

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图 22 吹风比M=1.0时的$ \overline{\eta } $

Figure 22. $ \overline{\eta } $ of M=1.0

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图 23 吹风比M=1.25时的$ \overline{\eta } $

Figure 23. $ \overline{\eta } $ of M=1.25

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图 24 吹风比M=0.75，不同转速下$ \overline{\eta } $

Figure 24. Effect of rotating speed on the $ \overline{\eta } $ when M=0.75

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表 1 涡轮转子参数

Table 1. Turbine rotor parameters

参数	数值
安装角/（°）	60
机匣直径/mm	782
轮毂直径/mm	646
叶高/mm	67
动叶中间高度弦长L/mm	40
孔径D/mm	0.4
孔出流角/（°）	45
叶片数	73

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表 2 计算边界条件

Table 2. Numerical boundary conditions

参数	数值
射流质量流量/（g/s）	5.79，8.69，11.59，14.49
涡轮进口速度/（m/s）	154
涡轮出口静压/MPa	0.77
主流湍流度T_u/%	5
主流雷诺数Re	395000，329000，286000
旋转角速度$ \mathit{\Omega } $/（rad/s）	1350，1400，1450
旋转数R_o	0.0034，0.0036，0.0037
吹风比M	0.5～1.25
密度比γ	1.04
主流温度T_m/K	1488
射流温度T_c/K	840

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表 3 不同条件下前缘3排孔的流量分配

Table 3. Flow distribution of the three rows of holes on the leading edge under different conditions

旋转角速度	孔排	流量/（g/s）	占比/%	当地吹风比
1350 rad/s （正攻角）	PS排	3.26	37.50	0.84
	滞止线排	2.60	29.92	0.67
	SS排	2.83	32.58	0.73
1400 rad/s （零攻角）	PS排	3.13	35.99	0.81
	滞止线排	2.88	33.17	0.74
	SS排	2.68	30.84	0.69
1450 rad/s （负攻角）	PS排	3.04	35.02	0.79
	滞止线排	3.03	34.84	0.78
	SS排	2.62	30.14	0.67

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表 4 不同工况下前缘$ \overline{{\boldsymbol{\eta}} } $_area数值

Table 4. $ \overline{{\boldsymbol{\eta}} } $_area on the leading edge surface at different operating conditions

旋转角速度/ （rad/s）	$\overline \eta_{\mathrm{area}} $
旋转角速度/ （rad/s）	M=0.5	M=0.75	M=1.0	M=1.25
1350	0.4156	0.4829	0.4843	0.4734
1400	0.4968	0.4883	0.4704	0.4355
1450	0.5069	0.4728	0.4438	0.4223

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参考文献(38)

[1]	孔祥灿, 张子卿, 朱俊强, 等. 航空发动机气冷涡轮叶片冷却结构研究进展[J]. 推进技术, 2022, 43(5): 200632. Kong Xiangcan, Zhang Ziqing, Zhu Junqiang, et al. Research progress on cooling structure of aeroengine air-cooled turbine blade[J]. Journal of Propulsion Technology, 2022, 43(5): 200632. (in Chinese doi: 10.13675/j.cnki.tjjs.200632 Kong Xiangcan, Zhang Ziqing, Zhu Junqiang, et al. Research progress on cooling structure of aeroengine air-cooled turbine blade[J]. Journal of Propulsion Technology, 2022, 43(5): 200632. (in Chinese) doi: 10.13675/j.cnki.tjjs.200632
[2]	Han Feng, Bi Shuai, Mao Junkui, et al. Film cooling effectiveness of a leading-edge cooling array of a rotating turbine blade with twist[J]. Applied Thermal Engineering, 2023, 225: 120175. doi: 10.1016/j.applthermaleng.2023.120175
[3]	Xie Gang, Tao Zhi, Zhou Zhiyu, et al. Hole arrangement effect to film cooling performance on leading edge region of rotating blade[J]. International Journal of Thermal Sciences, 2021, 169: 107034. doi: 10.1016/j.ijthermalsci.2021.107034
[4]	Han Feng, Wang Lingyang, Zhang Shuhao, et al. Experimental investigations on the heat transfer characteristic of impingement/swirl cooling structures inside turbine blade leading edge[J]. International Communications in Heat and Mass Transfer, 2024, 150: 107197. doi: 10.1016/j.icheatmasstransfer.2023.107197
[5]	Han Feng, Wang Lingyang, Pu Haotian, et al. Experimental investigations on flow characteristics of impingement/swirl cooling structures inside a blade leading edge[J]. Physics of Fluids, 2023, 35(11): 115103. doi: 10.1063/5.0172635
[6]	郭文, 王鹏飞. 涡轮叶片冷却技术分析[J]. 航空动力, 2020(6): 55-58. Guo Wen, Wang Pengfei. Analysis of cooling configurations for turbine blade[J]. Aerospace Power, 2020(6): 55-58. (in Chinese Guo Wen, Wang Pengfei. Analysis of cooling configurations for turbine blade[J]. Aerospace Power, 2020(6): 55-58. (in Chinese)
[7]	Park S H, Kang Y J, Seo H J, et al. Experimental optimization of a fan-shaped film cooling hole with 30 degrees-injection angle and 6-hole length-to-diameter ratio[J]. International Journal of Heat and Mass Transfer, 2019, 144: 118652. doi: 10.1016/j.ijheatmasstransfer.2019.118652
[8]	Mick W J, Mayle R E. Stagnation film cooling and heat transfer, including its effect within the hole pattern[J]. Journal of Turbomachinery, 1988, 110(1): 66-72. doi: 10.1115/1.3262169
[9]	Ekkad S V, Han J C, Du H. Detailed film cooling measurements on a cylindrical leading edge model: effect of free-stream turbulence and coolant density[J]. Journal of Turbomachinery, 1998, 120(4): 799-807. doi: 10.1115/1.2841792
[10]	Ou S, Rivir R B. Leading edge film cooling heat transfer with high free stream turbulence using a transient liquid crystal image method[J]. International Journal of Heat and Fluid Flow, 2001, 22(6): 614-623. doi: 10.1016/S0142-727X(01)00121-7
[11]	Kim Y J, Kim S M. Influence of shaped injection holes on turbine blade leading edge film cooling[J]. International Journal of Heat and Mass Transfer, 2004, 47(2): 245-256. doi: 10.1016/j.ijheatmasstransfer.2003.07.008
[12]	Liu Cunliang, Zhu Huiren, Zhang Xia, et al. Experimental investigation on the leading edge film cooling of cylindrical and laid-back holes with different radial angles[J]. International Journal of Heat and Mass Transfer, 2014, 71: 615-625. doi: 10.1016/j.ijheatmasstransfer.2013.12.050
[13]	Liu C L, Zhu H R, Zhang Z W. Experimental investigation on the leading edge film cooling of cylindrical and laid-back holes with different hole pitches[R]. International Journal of Heat and Mass Transfer, 2014, 71: 615-625.
[14]	Chowdhury N H K, Qureshi S A, Zhang Mingjie, et al. Influence of turbine blade leading edge shape on film cooling with cylindrical holes[J]. International Journal of Heat and Mass Transfer, 2017, 115: 895-908. doi: 10.1016/j.ijheatmasstransfer.2017.08.020
[15]	Dring R P, Blair M F, Joslyn H D. An experimental investigation of film cooling on a turbine rotor blade[J]. Journal of Engineering for Power, 1980, 102(1): 81-87. doi: 10.1115/1.3230238
[16]	Ahn J, Schobeiri M T, Han J C, et al. Film cooling effectiveness on the leading edge region of a rotating turbine blade with two rows of film cooling holes using pressure sensitive paint[J]. Journal of Heat Transfer, 2006, 128(9): 879-888. doi: 10.1115/1.2241945
[17]	Ahn J, Schobeiri M T, Han J C, et al. Effect of rotation on leading edge region film cooling of a gas turbine blade with three rows of film cooling holes[J]. International Journal of Heat and Mass Transfer, 2007, 50(1/2): 15-25.
[18]	Yang H T, Chen H C, Han J C, et al. Numerical prediction of film cooling and heat transfer on the leading edge of a rotating blade in a 1-1/2 turbine stage[R]. ASME Paper IMECE2004-59599, 2004.
[19]	Yang Huitao, Chen H C, Han J C, et al. Film-cooling prediction on rotor blade leading edge in 1-1/2 turbine stage[J]. Journal of Thermophysics and Heat Transfer, 2008, 22(2): 201-209. doi: 10.2514/1.30624
[20]	Li Haiwang, Han Feng, Wang Haichao, et al. Film cooling characteristics on the leading edge of a rotating turbine blade with various mainstream Reynolds numbers and coolant densities[J]. International Journal of Heat and Mass Transfer, 2018, 127: 833-846. doi: 10.1016/j.ijheatmasstransfer.2018.07.126
[21]	Li Haiwang, Han Feng, Zhou Zhiyu, et al. Experimental investigations of the effects of the injection angle and blowing ratio on the leading-edge film cooling of a rotating twisted turbine blade[J]. International Journal of Heat and Mass Transfer, 2018, 127: 856-869. doi: 10.1016/j.ijheatmasstransfer.2018.07.133
[22]	Li Haiwang, Han Feng, Ma Yiwen, et al. Experimental investigation on the effects of rotation and the blowing ratio on the leading-edge film cooling of a twist turbine blade[J]. International Journal of Heat and Mass Transfer, 2019, 129: 47-58. doi: 10.1016/j.ijheatmasstransfer.2018.09.005
[23]	Han Feng, Guo Hong, Ding Xiaofeng, et al. Experimental investigation on the effects of hole pitch and blowing ratio on the leading edge region film cooling of a rotating twist turbine blade[J]. International Journal of Heat and Mass Transfer, 2020, 150: 119380. doi: 10.1016/j.ijheatmasstransfer.2020.119380
[24]	Li Haiwang, Zhang Dawei, Han Feng, et al. Experimental investigation on the effect of hole diameter on the leading edge region film cooling of a twist turbine blade under rotation conditions[J]. Applied Thermal Engineering, 2021, 184: 116386. doi: 10.1016/j.applthermaleng.2020.116386
[25]	韩枫, 李海旺. 出流角对旋转涡轮叶片前缘气膜冷却影响[J]. 工程热物理学报, 2020, 41(2): 320-328. Han Feng, Li Haiwang. Effect of the injection angle on the leading edge film cooling of a rotating turbine blade[J]. Journal of Engineering Thermophysics, 2020, 41(2): 320-328. (in Chinese Han Feng, Li Haiwang. Effect of the injection angle on the leading edge film cooling of a rotating turbine blade[J]. Journal of Engineering Thermophysics, 2020, 41(2): 320-328. (in Chinese)
[26]	Yan H N, Liu C L, Zhang L, et al. Experimental investigation of the effects of thermal barrier coating on twisted blade full film cooling[R]. Rotterdam, Netherlands: ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition, 2022.
[27]	Zhao Y C, Gao H S, Wen Z X, et al. Film cooling of showerhead holes from the twisted leading edge of a gas turbine blade: Complex mainstream characteristics and reasonable angle arrangement[J]. Aerospace Science and Technology, 2021, 119: 107208. doi: 10.1016/j.ast.2021.107208
[28]	Zeng Lingyu, Chen Pingting, Li Xueying, et al. Influence of simplifications of blade in gas turbine on film cooling performance[J]. Applied Thermal Engineering, 2018, 128: 877-886. doi: 10.1016/j.applthermaleng.2017.09.008
[29]	Yeranee K, Rao Yu. A review of recent studies on rotating internal cooling for gas turbine blades[J]. Chinese Journal of Aeronautics, 2021, 34(7): 85-113. doi: 10.1016/j.cja.2020.12.035
[30]	Maikell J, Bogard D, Piggush J, et al. Experimental simulation of a film cooled turbine blade leading edge including thermal barrier coating effects[J]. Journal of Turbomachinery, 2011, 133: 011014. doi: 10.1115/1.4000537
[31]	Xie Gang, Tao Zhi, Zhou Zhiyu, et al. Effect of leading edge diameter ratio and mainstream Reynolds number on film cooling performance of rotating blade leading edge[J]. Applied Thermal Engineering, 2021, 186: 116047. doi: 10.1016/j.applthermaleng.2020.116047
[32]	谷萌, 谢刚, 周志宇, 等. 旋转条件下动叶前缘气膜孔排布局影响分析[J]. 航空动力学报, 2023, 38(6): 1340-1349. Gu Meng, Xie Gang, Zhou Zhiyu, et al. Analysis on film cooling hole arrangement effect for rotating blade leading edge[J]. Journal of Aerospace Power, 2023, 38(6): 1340-1349. (in Chinese doi: 10.13224/j.cnki.jasp.20210652 Gu Meng, Xie Gang, Zhou Zhiyu, et al. Analysis on film cooling hole arrangement effect for rotating blade leading edge[J]. Journal of Aerospace Power, 2023, 38(6): 1340-1349. (in Chinese) doi: 10.13224/j.cnki.jasp.20210652
[33]	Zheng Shaofei, Liu Guoqing, Lian Wenkai, et al. Fluid flow and heat transfer in a rectangular ribbed channel with a hierarchical design for turbine blade internal cooling[J]. Applied Thermal Engineering, 2022, 217: 119183. doi: 10.1016/j.applthermaleng.2022.119183
[34]	Zheng Shaofei, Liu Guoqing, Zhang Yi, et al. Performance evaluation with turbulent flow and heat transfer characteristics in rectangular cooling channels with various novel hierarchical rib schemes[J]. International Journal of Heat and Mass Transfer, 2023, 214: 124459. doi: 10.1016/j.ijheatmasstransfer.2023.124459
[35]	Menter F R. Two-equation eddy-viscosity turbulence models for engineering applications[J]. AIAA Journal, 1994, 32(8): 1598-1605. doi: 10.2514/3.12149
[36]	Schobeiri M T, Suryanarayanan A, Jermann C, et al. A comparative aerodynamic and performance study of a three-stage high pressure turbine with 3-D bowed blades and cylindrical blades[C]//ASME Turbo Expo 2004: Power for Land, Sea, and Air. Vienna, Austria: ASME, 2004: 1237-1246.
[37]	韩枫, 李海旺, 马薏文, 等. 旋转对弯扭涡轮叶片前缘气膜冷却的影响[J]. 航空动力学报, 2019, 34(6): 1352-1363. Han Feng, Li Haiwang, Ma Yiwen, et al. Effect of rotation on the leading-edge region film cooling of a twisted turbine blade[J]. Journal of Aerospace Power, 2019, 34(6): 1352-1363. (in Chinese doi: 10.13224/j.cnki.jasp.2019.06.018 Han Feng, Li Haiwang, Ma Yiwen, et al. Effect of rotation on the leading-edge region film cooling of a twisted turbine blade[J]. Journal of Aerospace Power, 2019, 34(6): 1352-1363. (in Chinese) doi: 10.13224/j.cnki.jasp.2019.06.018
[38]	Yang H T, Chen H C, Han J C, et al. Numerical prediction of film cooling and heat transfer on the leading edge of a rotating blade with two rows holes in a 1-1/2 turbine stage at design and off design conditions[R]. ASME Papaer GT2005-68335, 2005.