涡轮叶片径向倾斜尾缘劈缝减阻能力数值研究

孔星傲; 吕东; 王晓放; 王楠; 梁彩云

doi:10.13224/j.cnki.jasp.20210307

涡轮叶片径向倾斜尾缘劈缝减阻能力数值研究

doi: 10.13224/j.cnki.jasp.20210307

孔星傲¹,
吕东^1,*, ,,
王晓放¹,
王楠¹,
梁彩云²

1.
大连理工大学能源与动力学院涡轮叶片创新实验室，辽宁大连 116024
2.
中国航发沈阳发动机研究所，沈阳 110015

基金项目: 航空发动机涡轮叶片尾缘劈缝结构多学科耦合优化设计研究（DUT19RC(3)005）

详细信息

作者简介:
孔星傲（1997-），男，博士生，主要从事涡轮叶片冷却方面的研究

通讯作者:
吕东（1979-），男，教授、博士生导师，博士，主要从事涡轮叶片冷却方面的研究。E-mail：ld@dlut.edu.cn

中图分类号: V231.3
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- 被引次数: 0
出版历程
- 收稿日期: 2021-06-17
- 网络出版日期: 2023-05-15

Numerical study on the flow resistance reduction capability of turbine blade radial tilted trailing edge slots

1.
Innovation Lab of Gas Turbine Blade，School of Energy and Power Engineering， Dalian University of Technology，Dalian Liaoning 116024，China
2.
Shenyang Engine Research Institute， Aero Engine Corporation of China，Shenyang 110015，China

摘要

摘要:
针对传统水平排气劈缝结构流动损失大的问题，提出了径向倾斜排气的设计思想，并围绕其进一步提出了直线式和曲线式两种倾斜劈缝结构。基于数值仿真研究了其内部流场，揭示了倾斜劈缝可减小冷气转折角，抑制旋涡产生，使流动更加平缓，从而减小流阻的机理。通过与水平劈缝的对比分析，初步验证了两种新型劈缝结构使总压损失分别降低了约10%～12%和13%～15%。进一步考虑了燃气外流与冷却气掺混过程对劈缝内流动的影响，仿真结果同样印证了倾斜劈缝对于内流减阻能力的提高。但同时也发现了此类倾斜射流导致掺混损失增大的现象，通过给出两类劈缝结构的涡轮叶栅整体流动损失变化规律为叶片综合性能优化提供了参考。
- 涡轮叶片 /
- 尾缘劈缝 /
- 径向倾斜 /
- 流动阻力 /
- 总压损失
Abstract:
According to the defect of high flow resistance in current horizontal exhaust trailing edge slots, the scheme of radially tilted ones was proposed. Based on the improvements, the linear and curved tilted designs were further put forward. 3D numerical simulation methods were applied to these typical structures, then the internal flow fields were obtained and comprehensively compared. The results uncovered the mechanisms on flow resistance reduction of the new structures, by decreasing the coolant turning angle and suppressing the vortex in venting slots. In detail, the total pressure loss of typical linear and curved tilted designs could be reduced by about 10%−12% and 13%−15% compared with the horizontal one. The mixing processes of coolant injection and gas flow were simulated, which confirmed the previous conclusions, although the total losses of the novel cascade flow slightly increased. These facts and characteristic curves provided a guidance for the turbine blade’s comprehensive performance optimization.
- turbine blade /
- trailing edge slot /
- radial tilted /
- flow resistance /
- total pressure loss

HTML

图 1 两种高压涡轮导叶尾缘劈缝结构对比

Figure 1. Comparison of two high pressure turbine vane trailing edge slots

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图 2 尾缘结构的简化和特征化方法

Figure 2. Simplification and characterization of trailing edge

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图 3 两种劈缝结构参数定义

Figure 3. Structural parameter definitions of two slots

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图 4 尾缘劈缝区域的面网格细节

Figure 4. Surface mesh details of trailing edge slots

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图 5 进出口边界条件设置

Figure 5. Boundary conditions of inlets and outlets

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图 6 两种劈缝的三维流线和速度矢量图

Figure 6. 3D streamlines and velocity vectors of two slots

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图 7 两种劈缝流动沿程相对总压变化

Figure 7. Relative total pressure along streamlines of two slots

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图 8 两种劈缝相对总压分布图

Figure 8. Relative total pressure contours of two slots

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图 9 两种劈缝通道内的涡核

Figure 9. Vortex cores in two slots

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图 10 曲线劈缝结构和参数定义

Figure 10. Scheme and structural parameter definitions of curved slots

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图 11 ${\sigma _{{\rm{slots}}}}$随Re的变化趋势

Figure 11. Variation trend of ${\sigma _{{\rm{slots}}}}$ with Re

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图 12 掺混流动的计算域

Figure 12. Simulation domains of mixing flow

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图 13 掺混流动${p^*}/p_{\text{c}}^*$分布云图

Figure 13. ${p^*}/p_{\text{c}}^*$ contours of mixing flow

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图 14 ${\sigma _{{\rm{slots}}}}$随ζ的变化趋势

Figure 14. Variation trend of ${\sigma _{{\rm{slots}}}}$ with ζ

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图 15 ${\sigma _{{\rm{cascade}}}}$随ζ的变化趋势

Figure 15. Variation trend of ${\sigma _{{\rm{cascade}}}}$ with ζ

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表 1 两种劈缝的结构参数

Table 1. Structural parameters of 2 slots

模型 n b/mm s/b l/s d/s r/mm α/（°）

水平劈缝 10 4 0.4 1.875 0.25 0.5 0
倾斜劈缝 10 4 0.4 1.875 0.25 0.5 30

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表 2 曲线劈缝的结构参数

Table 2. Structural parameters of curved slots

参数数值

n 10
b/mm 4
s/b 0.4
l/s 1.875
d/s 0.25
r/mm 0.5
β₁/（°） 40
β₂/（°） 30

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