端壁-吸力面一体化造型在压气机级中的应用

周倩; 李相君; 尤付浩; 朱政宇; 孔令晨

doi:10.13224/j.cnki.jasp.20230524

端壁-吸力面一体化造型在压气机级中的应用

doi: 10.13224/j.cnki.jasp.20230524

大连海事大学船舶与海洋工程学院，辽宁大连 116026

基金项目: 国家自然科学基金青年项目（51906027）；辽宁省博士科研启动基金计划项目（2019-BS-027）；中央高校基本科研业务费专项资金（3132020112）；国家科技重大专项（J2019-Ⅰ-0011）；辽宁省教育厅基本科研项目面上项目（JYTMS20230160）

详细信息

作者简介:
周倩（2000-），女，硕士生，主要从事叶轮机械气动热力学研究。E-mail：zhouqian20001103@163.com

通讯作者:
李相君（1989-），男，讲师、硕士生导师，博士，主要从事叶轮机械气动热力学研究。E-mail：xjli@dlmu.edu.cn

中图分类号: V231.3
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出版历程
- 收稿日期: 2023-08-12
- 网络出版日期: 2025-04-16

Application of endwall-suction surface integrated contouring in a compressor stage

Naval Architecture and Ocean Engineering College，Dalian Maritime University，Dalian Liaoning 116026，China

摘要

摘要:
为了解决高负荷轴流压气机端壁角区分离问题，将一种多局部控制通道二次流、适用于多工况的吸力面及端壁联合造型方法应用于2.5级压气机末级静子中，探究造型方法在面对流动情况复杂的压气机环境时，所带来的效率提升或损失控制的效果。通过对最高效率点进行单目标优化，使压气机的末级峰值效率提高了约0.3%。流场分析显示，在多级压气机环境中应用端壁-吸力面一体化造型设计时，造型虽位于静子，但转子通流乃至效率亦受到一定程度的级间干涉。由于原型压气机端区流动结构不同，最优造型流动控制机理与在前期叶栅研究中所得结论有所差异。如此，可在一定程度上证明本文所采用的端壁-吸力面一体化造型方法于多种流动结构控制的可行性，其在压气机环境中的应用效果得到验证。
- 角区分离 /
- 压气机 /
- 端壁-吸力面一体化造型 /
- 流动控制 /
- 优化设计
Abstract:
In order to solve the problem of end-wall corner separation in high-load axial compressors, a combined contouring method of suction surface and end-wall with multiple local control channels for secondary flow applicable to multiple working conditions was applied to the final stage static sub of a 2.5-stage compressor, and the effects of the contouring method in terms of efficiency enhancement or loss control in the face of complex flow conditions of the pressurized gas environment were explored. A single-objective optimization of the highest efficiency point resulted in an improvement of about 0.3% in the final stage peak efficiency of the compressor. The flow field analysis showed that when the integrated end wall-suction surface contouring design was applied in a multi-stage compressor environment, the contouring was located in the static sub, but the rotor flux and even the efficiency were also subjected to a certain degree of interstage interference. Due to different flow structures in the end zone of the prototype compressor, the optimal modeling flow control mechanism differed from the conclusions obtained in the previous vane grid study. In this way, the feasibility of the integrated end-wall-suction surface contouring method adopted to the control of various flow structures can be proved to a certain extent, and its application in the compressor environment has been verified.
- corner separation /
- compressor /
- endwall-suction surface integrated contouring /
- flow control /
- optimization design

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图 1 全局造型单元面定义

Figure 1. Definition of full-area modeling unit

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图 2 局部造型单元定义

Figure 2. Definition of localized modeling unit

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图 3 权重控制变量对吸力面及端壁造型结果的影响（I= l₁w₁+l₂u₂）

Figure 3. Influence of weight factor on variation of suction and endwall contouring （I= l₁w₁+l₂u₂）

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图 4 一点由标准空间向压气机吸力面及端壁空间映射示例

Figure 4. Example of mapping a point from standard space to suction and endwall region of a compressor passage

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图 5 压气机末级网格图

Figure 5. Compressor final stage grid diagram

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图 6 不同网格数量特性线

Figure 6. Overall performance on different number of grids

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图 7 CFD与实验结果特性线

Figure 7. Overall performance obtained by CFD and experiment

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图 8 不同部位总压比沿叶高分布

Figure 8. Spanwise total pressure ratio of different parts

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图 9 压气机末级静子三维流场

Figure 9. Three dimensional stator flow field of compressor final stage

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图 10 优化设计流程（多岛遗传算法）

Figure 10. Processing of optimization design（multi island genetic algorithm）

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图 11 压气机末级静子优化造型结果高度云图

Figure 11. Height contours of compressor final stage stator optimization modeling results

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图 12 原型与优化造型末级总压比

Figure 12. Pressure ratio of final stage between original case and optimized case

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图 13 原型与优化造型末级效率

Figure 13. Efficiency of final stage between original case and optimized case

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图 14 静子造型前后末级转子的性能变化

Figure 14. Change of final rotor performance before and after stator endwall modeling

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图 15 末级静子进口绝对气流角造型与原型差值

Figure 15. Modeling and prototype difference of final stator inlet absolute flow angle

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图 16 末级静子流动参数沿叶高的分布

Figure 16. Spanwise distribution of flow parameters of final stator

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图 17 末级静子端壁-吸力面一体化造型前后耗散函数等值面及流线

Figure 17. Dissipation function and streamlines before and after final stator endwall-suction surface integrated contouring

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图 18 末级静子端壁-吸力面一体化造型前后涡量图

Figure 18. Vorticity before and after final stator endwall-suction surface integrated contouring

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图 19 流向速度定义示意图

Figure 19. Flow velocity definition diagram

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图 20 末级静子端壁-吸力面一体化造型前后流场比较

Figure 20. Comparison of flow field before and after final stator endwall-suction surface integrated contouring

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图 21 末级静子端壁-吸力面一体化造型前后端壁横向与流向速度云图

Figure 21. Lateral and flow velocity cloud maps before and after final stator endwall-suction surface integrated contouring

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表 1 压气机级设计参数

Table 1. Design parameters of compressor cascade

设计参数数值

转子展弦比 0.8
转子叶尖稠度 2.06
转子轮毂比 0.74
转子叶尖速度 0.96Ma
静子折转角/（°） 67
静子轮毂比 2.21

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表 2 各部分效率值

Table 2. Efficiency value of each part

参数数值/%

Δη 0.334

Δη_r 0.0236

Δη_s 0.3645

Δη_τ −0.0540

下载: 导出CSV

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