雷诺数与密度比对弯扭涡轮叶片前缘气膜冷却的影响

韩枫; 浦昊天; 陈娇娜; 孙尤骐; 左世豪; 徐川; 毛军逵

doi:10.13224/j.cnki.jasp.20240417

雷诺数与密度比对弯扭涡轮叶片前缘气膜冷却的影响

doi: 10.13224/j.cnki.jasp.20240417

韩枫^{1, 2,},
浦昊天¹,
陈娇娜^{1, 2},
孙尤骐¹,
左世豪¹,
徐川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）；国家科技重大专项（Y2022-Ⅲ-0003-0012）；航空发动机及燃气轮机基础科学中心项目（P2022-A-Ⅱ-007-001）；中央高校基本科研业务费（NS2023010）

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: 2024-06-26
- 网络出版日期: 2026-01-14

Effect of Reynolds number and density ratio on the leading edge film cooling of twisted turbine blade

HAN Feng^{1, 2
,},
PU Haotian¹,
CHEN Jiaona^{1, 2},
SUN Youqi¹,
ZUO Shihao¹,
XU Chuan¹,
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:
针对涡轮叶片前缘容易被烧蚀问题，在旋转条件下开展了主流雷诺数、射流-主流密度比以及吹风比对弯扭涡轮叶片前缘气膜冷却特性影响的数值模拟研究。主流雷诺数分别为44200、55200和71800，在保证旋转数不变（0.0018）时，根据3种不同雷诺数对应的涡轮进口主流速度和速度三角形，获得对应的3种零攻角状态下涡轮转速：400、500 r/min和650 r/min。采用N₂和CO₂为冷却工质以实现射流-主流密度比分别为1.04和1.56。结果表明：当密度比和吹风比相同，弯扭涡轮叶片前缘气膜覆盖面积和冷却效率水平均随着雷诺数增大而增大；不论密度比大小，当吹风比相同，3种雷诺数下前缘压力面侧气膜冷却效率均高于吸力面侧；当冷却工质为N₂，在−5.5<X/D<0.5上平均气膜冷却效率随雷诺数增加而增加；当冷却工质为CO₂，在−3.75<X/D<0.5上展向平均气膜冷却效率随着雷诺数增加而增加；在吹风比不变，两种冷却工质获得的前缘区域面平均气膜冷却效率随着雷诺数的增大呈现增大趋势；整个前缘展向平均气膜冷却效率均随着吹风比的增大而增大；当吹风比相同，较高密度的冷却工质CO₂在整个前缘区域上提供的展向平均气膜冷却效率水平高于较低密度冷却工质N₂。
- 涡轮叶片 /
- 前缘 /
- 雷诺数 /
- 密度比 /
- 气膜冷却效率
Abstract:
Aiming at the problem that the turbine blade leading edge is easy to be ablated, the numerical simulation study is conducted to study the effects of mainstream Reynolds number, coolant-to-mainstream density ratio and blowing ratio on the film cooling characteristics on the leading edge of a rotating twisted turbine blade. The mainstream Reynolds numbers are 44200, 55200 and 71800, respectively. According to the turbine inlet mainstream speeds and velocity triangles corresponding to the three different Reynolds numbers while the rotational number is kept constant (0.0018), 400, 500 r/min and 650 r/min turbine speeds at zero angle of attack are obtained for three different Reynolds numbers. N₂ and CO₂ are used as coolants to achieve coolant-to-mainstream density ratios of 1.04 and 1.56, respectively. Results show that when the density ratio and blowing ratio are the same, the film covering area and cooling effectiveness of the twisted blade leading edge increase with the increase of Reynolds number. Regardless of the density ratio, when the blowing ratio is the same, the film cooling effectiveness on the pressure surface is higher than that on the suction surface under the three Reynolds numbers. For the N₂ case, the average film cooling effectiveness increases with the increase of Reynolds number at −5.5<X/D<0.5. For the CO₂ case, the average film cooling effectiveness increases with the increase of Reynolds number at −3.75<X/D<0.5. Under constant blowing ratio, the average film cooling effectiveness of the two types of coolant increases with the increase of Reynolds number. The average spanwise film cooling effectiveness of the whole leading edge increases with the blow ratio increases. When the blowing ratio is the same, the average film cooling effectiveness provided by the higher density coolant CO₂ is higher than that of the lower density coolant N₂.
- turbine blade /
- leading edge /
- Reynolds number /
- density ratio /
- film cooling effectiveness

HTML

图 1 叶片模型

Figure 1. Blade model

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图 2 叶片内部冷却通道

Figure 2. Blade internal cooling channels

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图 3 气膜孔倾角

Figure 3. Inclination of the film holes

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图 4 湍流模型验证

Figure 4. Turbulence model validation

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图 5 计算域和边界条件

Figure 5. Computational domains and boundary conditions

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图 6 叶片网格结构

Figure 6. Meshes structure of the blade

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图 7 网格无关性验证

Figure 7. Mesh-independent verification

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图 8 射流为N₂时气膜冷却效率分布云图（Re=44200）

Figure 8. Distributions of film cooling effectiveness with N₂ injection （Re=44200）

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图 9 射流为CO₂时气膜冷却效率分布云图（Re=44200）

Figure 9. Distributions of film cooling effectiveness with CO₂ injection （Re=44200）

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图 10 射流为N₂时气膜冷却效率分布云图（Re=55200）

Figure 10. Distributions of film cooling effectiveness with N₂ injection （Re=55200）

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图 11 射流为CO₂时气膜冷却效率分布云图（Re=55200）

Figure 11. Distributions of film cooling effectiveness with CO₂ injection （Re =55200）

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图 12 射流为N₂时气膜冷却效率分布云图（Re=71800）

Figure 12. Distributions of film cooling effectiveness with N₂ injection （Re=71800）

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图 13 射流为CO₂时气膜冷却效率分布云图（Re=71800）

Figure 13. Distributions of film cooling effectiveness with CO₂ injection （Re=71800）

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图 14 射流为N₂时气膜展向平均冷却效率（M=1.5）

Figure 14. Span-wise averaged film cooling effectiveness with N₂ injection （M=1.5）

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图 15 射流为CO₂时气膜展向平均冷却效率（M=1.0）

Figure 15. Span-wise averaged film cooling effectiveness with CO₂ injection （M=1.0）

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图 16 Li等^[21]实验中叶片前缘测试区域

Figure 16. Blade leading edge test area in Li et al. ^[21] experiment

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图 17 前缘腔中冷却工质受力分析

Figure 17. Analysis of coolant force in the leading edge cavity

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图 18 射流为CO₂，M=1.0，Re=44200时前缘气膜孔射流流线

Figure 18. Streamlines of the leading edge film holes under Re=44200 for M=1.0 with CO₂ injection

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图 19 射流为N₂，Re=71800时不同M下叶片中间高度流场温度云图及流线

Figure 19. Temperature distributions and streamlines of the flow field at the blade middle height under different M with N₂ injection and Re=71800

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图 20 不同雷诺数下面平均气膜效率（射流为N₂）

Figure 20. Averaged film cooling effectiveness under different Reynolds numbers （N₂ injection）

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图 21 不同雷诺数下面平均气膜效率（射流为CO₂）

Figure 21. Averaged film cooling effectiveness under different Reynolds numbers （CO₂ injection）

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图 22 射流为N₂时不同吹风比下展向平均气膜效率（Re=71800）

Figure 22. Span-wise averaged film cooling effectiveness under different blowing ratios with N₂ injection （Re=71800）

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图 23 射流为CO₂时不同吹风比下展向平均气膜效率（Re=71800）

Figure 23. Span-wise averaged film cooling effectiveness under different blowing ratios with CO₂ injection （Re=71800）

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图 24 射流为CO₂和N₂时在M=0.5和1.0下展向平均气膜效率（Re=71800）

Figure 24. Span-wise averaged film cooling effectiveness with CO₂ and N₂ injection in M=0.5 and 1.0 （Re=71800）

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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
动叶弦长C/mm	40
孔径D/mm	0.4
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
主流质量流量/（kg/s）	2.23, 2.79, 3.63
主流湍流度/%	5
涡轮进口速度/（m/s）	9.1, 11.3, 14.7
涡轮动叶进口相对风速/（m/s）	14.8, 18.5, 24.1
涡轮出口速度/（m/s）	18.9, 23.6, 30.7
主流雷诺数Re	44200，55200，71800
转速/（r/min）	400, 500, 650
旋转数R_o	0.0018
吹风比M	N₂: 0.5～2.0, CO₂: 0.5～1.25
密度比R_d	1.04, 1.56
主流温度T_m/K	315
射流温度T_c/K	298

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表 3 不同Re下前缘面平均气膜冷却效率

Table 3. Averaged film cooling effectiveness on the leading edge region at different Re

Re	冷却工质	面平均冷却效率
Re	冷却工质	M = 0.5	M = 1.0
44200	N₂	0.1931	0.3142
44200	CO₂	0.2385	0.3809
55200	N₂	0.1947	0.3196
55200	CO₂	0.2403	0.3884
71800	N₂	0.1983	0.3235
71800	CO₂	0.2444	0.3931

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