冷却气进气角度对端壁泄漏流气膜冷却特性影响

唐润泽; 李海旺; 周志宇; 谢刚

doi:10.13224/j.cnki.jasp.20230762

冷却气进气角度对端壁泄漏流气膜冷却特性影响

doi: 10.13224/j.cnki.jasp.20230762

唐润泽^1,,
李海旺^{1, 2, 3},
周志宇¹,
谢刚^{2, 4,*, ,}

1.
北京航空航天大学航空发动机研究院，北京 100191
2.
北京航空航天大学航空发动机气动热力国家级重点实验室，北京 100191
3.
天目山实验室（浙江省航空实验室），杭州 311121
4.
北京航空航天大学飞行学院，北京 100191

基金项目: 自然科学基金（52306062，52306065）；航空发动机及燃气轮机基础科学中心项目（P2023-B-Ⅱ-003-001）；国家科技重大项目（J2019-Ⅲ-0008-0051）

详细信息

作者简介:
唐润泽（1994-），男，博士生，研究方向为涡轮叶片冷却。E-mail：tangrunze@buaa.edu.cn

通讯作者:
谢刚（1993-），男，讲师，博士，研究方向为涡轮叶片冷却。E-mail：xiegang_ht@163.com

中图分类号: V231.1
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- 文章访问数: 24
- HTML浏览量: 9
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- 被引次数: 0
出版历程
- 收稿日期: 2023-12-04
- 网络出版日期: 2024-03-28

Influence of coolant inlet angle on endwall leakage flow film cooling performance

TANG Runze^1
,,
LI Haiwang^{1, 2, 3},
ZHOU Zhiyu¹,
XIE Gang^{2, 4,*
, ,}

1.
Research Institute of Aero-Engine，Beihang University，Beijing 100191，China
2.
National Key Laboratory of Science and Technology on Aero-Engnie Aero-thermodynamics，Beihang University，Beijing 100191，China
3.
Tianmushan Laboratory （Zhejiang Provincial Laboratory for Aviation），Hangzhou 311121，China
4.
Flying College，Beihang University，Beijing 100191，China

摘要

摘要:
基于叶盘一体化模型，通过使用切应力输运（SST）模型对雷诺平均Naiver-Stokes（RANS）方程进行求解的方式研究了涡轮叶片端壁泄漏流气膜冷却特性，盘腔出口处的旋转雷诺数为1.5×10⁵。为保证冷气与主流的密度比，冷却气使用二氧化碳来模拟，其在盘腔和主流中的扩散通过求解湍流输运方程得到。通过传质模拟传热的方式研究了由二级导向器进入盘腔的冷却气进气角度（−45°，0°，+45°）对端壁绝热气膜冷却效率的影响。研究发现：改变冷却气进气角度对端壁冷却特性影响明显，−45°进气角度能明显提高各冷却气与主流质量流量比下的端壁气膜冷却效率。
- 燃气涡轮发动机 /
- 涡轮叶片 /
- 端壁 /
- 泄漏流 /
- 气膜冷却
Abstract:
By using an integrated model with disc cavity and turbine blade, the endwall film cooling effectiveness was investigated numerically by using the shear stress transfer (SST) model to solve the Reynolds-averaged Naiver-Stokes (RANS) equation. The rotational Reynolds number at the outlet of the disc cavity was 1.5×10⁵. Carbon dioxide was chosen as the coolant to maintain the coolant-to-mainstream density ratio. The diffusion process of coolant was characterized by solving the turbulent transport equation. The effect of coolant inlet angle (−45°, 0°, +45°) on the endwall film cooling effectiveness was investigated. It was found that the inlet angle of coolant had a significant impact on the endwall film cooling effectiveness, and the −45° inlet angle can significantly improve the endwall film cooling effectiveness at various coolant-to-mainstream mass flow rates.
- gas turbine engine /
- turbine blade /
- endwall /
- leakage flow /
- film cooling

HTML

图 1 数值仿真模型示意图

Figure 1. Schematic diagram of numerical simulation model

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图 2 盘腔结构示意图

Figure 2. Schematic diagram of disc cavity

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图 3 导向器叶片端壁示意图

Figure 3. Schematic diagram of vane endwall

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图 4 网格无关性验证

Figure 4. Grid independence verification

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图 5 网格细节

Figure 5. Grid details

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图 6 试验台示意图

Figure 6. Schematic diagram of test bench

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图 7 气膜冷却效率云图对比

Figure 7. Comparison of film cooling effectiveness contours

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图 8 端壁平均气膜冷却效率沿轴向分布对比

Figure 8. Comparison of axial distribution of average endwall film cooling effectiveness

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图 9 端壁气膜冷却效率云图

Figure 9. Endwall film cooling effectiveness contours

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图 10 端壁平均气膜冷却效率分布

Figure 10. Distribution of average endwall film cooling effectiveness

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图 11 上游腔室内流体平均旋流度沿径向分布

Figure 11. Radial distribution of average swirl ratio of fluid in upstream cavity

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表 1 数值仿真模型结构参数

Table 1. Structural parameters of numerical simulation model mm

参数	数值
涡轮盘半径R	180
二级导向器叶片轴向弦长L_cx	52
相邻二级导向器叶片周向距离D	40
AC 1	0
AC 2	0
SC 1	1.6
SC 2	3.6
SC 3	0.4
SC 4	0.4

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表 2 数值仿真边界条件

Table 2. Boundary conditions of numerical simulation

参数	数值
主流平均进气角度/（°）	19
主流进口总压/Pa	98467
主流进口静温/K	298
涡轮转速/（r/min）	750
主流出口静压/Pa	98000
冷却气主流质量流量比R_mf/%	1.0，1.5，2.0，2.5，3.0
冷却气进气角度/（°）	−45，0，+45
冷却气进口温度/K	298

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表 3 气膜冷却效率试验测量不确定度

Table 3. Uncertainty in test measurement of film cooling effectiveness

$ \eta $	$ （\mathrm{\delta}\eta） /\eta $/%
0.9	0.0864
0.7	0.4143
0.5	1.244
0.3	3.705
0.1	17.86

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表 4 从上游腔室流出的泄漏流R_mf1

Table 4. R_mf1 of leakage flow flowing out from upstream cavity

进气角度/（°）	从上游腔室流出的泄漏流R_mf1/%
进气角度/（°）	冷却气R_mf=1.5%	冷却气R_mf=2.5%
−45	1.102	2.036
0	1.262	2.248
+45	1.384	2.427

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