基于时间推进法的涡轮通流设计

蒋筑宇; 范召林; 邱名; 叶文明

doi:10.13224/j.cnki.jasp.20220072

基于时间推进法的涡轮通流设计

doi: 10.13224/j.cnki.jasp.20220072

蒋筑宇^1,,
范召林²,
邱名^1,*, ,,
叶文明¹

1.
中国空气动力研究与发展中心空天技术研究所，四川绵阳 621000
2.
中国空气动力研究与发展中心，四川绵阳 621000

详细信息

作者简介:
蒋筑宇（1991-），男，博士生，主要从事叶轮机气动热力学研究

通讯作者:
邱名（1984-），男，副研究员、硕士生导师，博士，主要从事叶轮机气动热力学研究。E-mail：qiu_ming_abc@163.com

中图分类号: V231.1
计量
- 文章访问数: 20
- HTML浏览量: 11
- PDF量: 6
- 被引次数: 0
出版历程
- 收稿日期: 2022-02-17
- 网络出版日期: 2024-03-14

Turbine through flow design based on time-marching method

JIANG Zhuyu^1
,,
FAN Zhaolin²,
QIU Ming^{1,*
, ,},
YE Wenming¹

1.
Institute of Aerospace Technology，China Aerodynamics Research and Development Center，Mianyang Sichuan 621000，China
2.
China Aerodynamics Research and Development Center，Mianyang Sichuan 621000，China

摘要

摘要:
为建立合理的涡轮设计参数计算方法，保证设计准确性，基于Euler方程时间推进通流设计方法，提出了一种基于二次函数的叶排通道S2流面周向角和堵塞系数近似计算方法。通流设计方法利用有限体积法求解正交曲线坐标系下的二维非守恒型Euler方程，使用Riemann精确解确定网格单位界面参数，采用具有TVD性质的3阶精度Godunov格式，时间方向采用半隐式格式。利用经验损失模型计算叶型损失、二次流损失和叶尖间隙泄漏流损失，并将二次流损失和叶尖间隙泄漏流损失沿径向进行重新分布，而激波损失被认为是可以准确计算。对某型单级涡轮进行了通流设计研究，并根据通流设计结果进行了三维叶片造型，利用三维黏性CFD软件对涡轮进行数值模拟，校验了通流设计方法的有效性。当涡轮进出口条件一定时，相比于三维CFD结果，通流流量结果高约1.46%，膨胀比低0.005，绝热效率高0.0077。最后可以得到如下结论：通流设计方法所需网格量少，计算效率高，收敛性好；叶排通道S2流面周向角和堵塞系数计算方法合理；涡轮总体性能参数，以及流量系数、载荷系数和反力度等无量纲参数计算准确度较高。
- 轴流涡轮 /
- 通流设计 /
- 时间推进法 /
- S2流面周向角 /
- 堵塞系数
Abstract:
To establish reasonable turbine design parameter calculation method and guarantee the accuracy of design work on the basis of quadratic function, an approximate computation method of S2 stream surface circumferential angle and blockage coefficient inside blade row passage was proposed for Euler equation time-marching through design method. The through-flow design method utilized finite volume method to solve 2D unconservative Euler equation in orthogonal curvilinear coordinate. Exact Riemann solution was used to calculate interface parameters of grid element. And third order Godunov scheme with TVD property was implemented. While semi-implicit scheme was employed in temporal discretization., the blade profile loss, secondary loss, and blade tip clearance leakage loss were computed by empirical loss model. Then secondary loss and tip clearance leakage loss could be redistributed radially. On the other hand, shock wave loss was regarded as accurate after solution. A single stage turbine was then designed with the through flow design method. After that, 3D blade shapes were profiled according to through flow result. Next, 3D viscous CFD software was used to simulate turbine and verify the effectiveness of through flow design method. Given the same inlet and outlet conditions, compared with 3D result, through flow mass flow result was about 1.46% higher, expansion ratio was 0.005 lower, and isentropic efficiency was 0.0077 higher. Finally, it can be concluded that through flow design method required fewer number of grid points, featuring higher computation efficiency with favorable convergence. Besides, the calculation method of blade row passage S2 stream surface circumferential angle and blockage coefficient was rational. And also, accurate results of turbine overall performance, and dimensionless parameter like flow coefficient, loading coefficient, and reaction can be obtained.
- axial turbine /
- through flow design /
- time-marching method /
- S2 stream surface circumferential angle /
- blockage coefficient

HTML

图 1 坐标参数

Figure 1. Coordinate parameters

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图 2 叶型中弧线周向坐标

Figure 2. Circumferential coordinate of blade profile

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图 3 叶栅通道宽度

Figure 3. Cascade passage width

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图 4 二次流损失分布

Figure 4. Secondary loss distribution

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图 5 叶尖间隙泄漏流损失分布

Figure 5. Blade tip clearance leakage loss distribution

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图 6 计算网格

Figure 6. Computation grid

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图 7 流量变化

Figure 7. Mass flow variation

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图 8 堵塞系数

Figure 8. Blockage coefficient

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图 9 叶型截面

Figure 9. Blade profile sections

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图 10 子午面马赫数

Figure 10. Meridional Mach number

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图 11 子午面相对马赫数

Figure 11. Meridional relative Mach number

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图 12 叶排出口气流角

Figure 12. Blade row exit flow angle

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图 13 叶排出口总压恢复系数

Figure 13. Blade row exit total pressure recovery

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图 14 叶排出口环量

Figure 14. Blade row exit circulation

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图 15 转子进口流量系数

Figure 15. Rotor inlet flow coefficient

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图 16 载荷系数

Figure 16. Loading coefficient

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图 17 转子反力度

Figure 17. Rotor reaction

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表 1 涡轮总体性能

Table 1. Turbine overall performance

计算方法	G/（$ {\text{kg}} \cdot \sqrt {\text{K}} \cdot {{\text{s}}^{ - 1}} \cdot {\text{kP}}{{\text{a}}^{ - 1}} $）	π	η
通流设计	0.5015	2.552	0.9291
三维CFD	0.4943	2.557	0.9214

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