涡轮凹槽叶尖气膜孔形对叶尖冷却特性影响的数值研究

杜昆; 王旭博; 惠娜; 黄小杨; 刘存良

doi:10.13224/j.cnki.jasp.20240510

涡轮凹槽叶尖气膜孔形对叶尖冷却特性影响的数值研究

doi: 10.13224/j.cnki.jasp.20240510

杜昆^{1, 2, 3, 4,},
王旭博¹,
惠娜⁵,
黄小杨⁶,
刘存良^{1, 3, 4,*, ,}

1.
西北工业大学动力与能源学院，西安 710072
2.
西北工业大学轻型涡轮动力全国重点实验室，江苏太仓 215400
3.
西北工业大学陕西省航空动力系统热科学重点实验室，西安 710129
4.
西北工业大学西北工业大学-喀山国立技术大学先进航空发动机热结构国际联合实验室，西安 710129
5.
中国航发西安动力控制科技有限公司，西安 710077
6.
中国航发四川燃气涡轮研究院，成都 610500

基金项目: 国家自然科学基金（52476036）；陕西省重点研发计划一般项目（2024GX-YBXM-404）；航空发动机及燃气轮机基础科学中心项目（2022-DC-I-002-001）；中央高校基本科研业务费专项资金（3102018zy019，3102020OMS701）

详细信息

作者简介:
杜昆（1989-），男，副教授，博士，主要从事航空发动机高效热管理方面的研究。E-mail：kun.du@nwpu.edu.cn

通讯作者:
刘存良（1983-），男，教授，博士，主要从事航空动力系统高效冷却结构及其精细化热分析方面的研究。E-mail：liucunliang@nwpu.edu.cn

中图分类号: V232.4
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出版历程
- 收稿日期: 2024-07-27
- 网络出版日期: 2024-11-30

Numerical study on influences of hole shapes on turbine cavity tip film cooling characteristics

DU Kun^{1, 2, 3, 4
,},
WANG Xubo¹,
HUI Na⁵,
HUANG Xiaoyang⁶,
LIU Cunliang^{1, 3, 4,*
, ,}

1.
School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China
2.
National Key Laboratory of Science and Technology on Advanced Light-duty Gas-turbine，Northwestern Polytechnical University，Taicang Jiangsu 215400，China
3.
Shaanxi Key Laboratory of Thermal Sciences in Aero-Engine System，Northwestern Polytechnical University，Xi’an 710129，China
4.
NPU-KAI International Joint Laboratory of Advanced Aero-Engine Thermal Structure，Northwestern Polytechnical University，Xi’an 710129，China
5.
Xi’an Engine Control Technology Company，Aero Engine Corporation of China，Xi’an 710077，China
6.
Sichuan Gas Turbine Establishment，Aero Engine Corporation of China，Chengdu 610500，China

摘要

摘要:
为了研究叶尖气膜孔形对涡轮动叶气动与冷却性能的影响，采用数值模拟方法，在考虑了吹风比M影响的情况下，针对圆柱孔、圆锥孔、圆角缝孔，楔形孔以及扇形孔5种孔形对于叶尖冷却特性的影响开展了研究。结果表明：5种孔形对应的叶尖面平均冷效均随着吹风比M的增大而增大，在M=2.0时达到最大值，圆柱孔和圆角缝孔冷气展向扩散更强，冷气整体覆盖更加均匀；而楔形孔和扇形孔高冷效区面积更大，高冷效区主要集中在近尾缘区域，两者面平均冷效相对于圆柱孔的变化率分别为−0.3%与10.7%。
- 涡轮动叶 /
- 凹槽叶尖 /
- 气膜冷却 /
- 冷却特性 /
- 异形气膜孔
Abstract:
In order to investigate the influences of different hole shapes on the aerodynamic and cooling performance of turbine blades, five shapes including cylinder holes, conical holes, fillet slot holes, wedge-shaped holes, and fan-shaped holes were studied, meanwhile, the effect of blowing ratio M was considered. The results showed that the average cooling effectiveness on the blade tip surface for all five hole shapes increased with an increasing blowing ratio and reached its maximum at M=2.0. Cylinder holes and fillet slot holes had stronger cooling air diffusion, leading to a more uniform overall coverage of cooling air. On the other hand, wedge-shaped holes and fan-shaped holes had a larger area of high cooling effectiveness, with the high cooling effectiveness zone primarily concentrated in the near-trailing edge region. The relative change in average cooling effectiveness compared with circular holes was −0.3% for wedge-shaped holes and 10.7% for fan-shaped holes.
- turbine blades /
- cavity tip /
- film cooling /
- cooling characteristics /
- shaped film cooling holes

HTML

图 1 数值模拟的计算域

Figure 1. Computational domain for numerical simulation

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图 2 叶尖冷却特性研究的计算模型

Figure 2. Computational model for cooling characteristics at blade tip

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图 3 数值模拟计算网格示意

Figure 3. Schematic of computational mesh for numerical simulation

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图 4 不同气膜孔的叶尖区域流动特征

Figure 4. Flow characteristics in blade tip region with different film holes

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图 5 无冷气射流时叶尖表面极限流线分布

Figure 5. Limit streamline distribution on blade tip surface without coolant jet injection

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图 6 不同气膜孔的叶尖表面极限流线

Figure 6. Limit streamlines on blade tip surface with different film holes

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图 7 不同气膜孔的叶尖表面切应力分布

Figure 7. Shear stress distribution on blade tip surface with different film holes

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图 8 不同气膜孔的叶尖气膜冷效分布

Figure 8. Film cooling effectiveness distribution on blade tip with different film holes

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图 9 不同气膜孔的叶尖气膜冷效展向分布（M=2.0）

Figure 9. Laterally-average of film cooling effectiveness distribution on blade tip with different film holes （M=2.0）

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图 10 不同气膜孔的叶尖面平均气膜冷效（M=2.0）

Figure 10. Average film cooling effectiveness values on blade tip with different film holes （M=2.0）

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图 11 不同M时叶尖气膜冷效分布

Figure 11. Film cooling effectiveness distribution on blade tip at different M

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图 12 不同M时叶尖面平均气膜冷效

Figure 12. Average film cooling effectiveness on blade tip at different M

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表 1 叶片模型几何参数

Table 1. Geometric parameters of blade model

参数	数值
叶片数目	67
叶片高度H/mm	121
叶片弦长C/mm	57.62
叶尖间隙G/mm	1

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表 2 数值模拟边界条件

Table 2. Numerical simulation calculation conditions

参数	数值或说明
主流进口总温/K	1741.9
主流进口总压/10⁵ Pa	8.629
出口背压/10⁵ Pa	4.006
二次流进口总温/K	724
二次流进口质量流量/（g/s）	0.8, 1.6, 2.4, 3.2
壁面温度	绝热
	叶根	21.6
进口气流角/（°）	叶中	21..0
	叶尖	20.6
转速/（r/min）	7150
进口湍流度/%	5

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表 3 网格无关性验证结果

Table 3. Grid independence verification results

网格方案	网格数目/10⁴	面积平均传热系数 h/（W/（m²·K））
网格1	200	1766.3
网格2	240	1894.5
网格3	280	2005.1
网格4	400	2003.7

下载: 导出CSV

参考文献(18)

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涡轮凹槽叶尖气膜孔形对叶尖冷却特性影响的数值研究

doi: 10.13224/j.cnki.jasp.20240510

作者简介:
杜昆（1989-），男，副教授，博士，主要从事航空发动机高效热管理方面的研究。E-mail：kun.du@nwpu.edu.cn

通讯作者:
刘存良（1983-），男，教授，博士，主要从事航空动力系统高效冷却结构及其精细化热分析方面的研究。E-mail：liucunliang@nwpu.edu.cn

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Numerical study on influences of hole shapes on turbine cavity tip film cooling characteristics

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留言板

涡轮凹槽叶尖气膜孔形对叶尖冷却特性影响的数值研究

doi: 10.13224/j.cnki.jasp.20240510

作者简介: 杜昆（1989-），男，副教授，博士，主要从事航空发动机高效热管理方面的研究。E-mail：kun.du@nwpu.edu.cn

通讯作者: 刘存良（1983-），男，教授，博士，主要从事航空动力系统高效冷却结构及其精细化热分析方面的研究。E-mail：liucunliang@nwpu.edu.cn

计量

出版历程

Numerical study on influences of hole shapes on turbine cavity tip film cooling characteristics

计量

出版历程

目录

作者简介:
杜昆（1989-），男，副教授，博士，主要从事航空发动机高效热管理方面的研究。E-mail：kun.du@nwpu.edu.cn

通讯作者:
刘存良（1983-），男，教授，博士，主要从事航空动力系统高效冷却结构及其精细化热分析方面的研究。E-mail：liucunliang@nwpu.edu.cn