冲角对压气机叶栅内二次涡的影响

Influence of Incidence on Secondary Vortex in the Compressor Cascade

1.
School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China
2.
School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China

摘要: 在实验结果的基础上,通过数值模拟,并应用拓扑学原理和壁面流谱规律,分析了不同冲角下压气机叶栅内的二次涡的发展过程,给出了其拓扑结构。结果表明:随着冲角增加,叶栅吸力面的分离尺度增加,流动非定常性增强,并且分离形态由开式分离向闭式分离转化;而壁角涡对冲角变化不敏感。最后提出了新的压气机平面叶栅内的旋涡模型。
- 航空、航天推进系统 /
- 拓扑 /
- 压气机叶栅 /
- 冲角 /
- 分离形态
Abstract: Through numerical simulation based on the experimental results,the topology theory and the rules of surface pattern were used to analyze the development of the secondary vortex with several different incidences in the compressor cascade.Then the topology patterns of the separation structures were presented.The result shows that the range of the suction surface separation expands and the unsteady effect of the flow field increases with the increase of the incidence.At the same time,the separation model transits from the open separation to the closed separation.And the corner vortex is not sensitive to the variation of the incidence.At last,the author proposed a new vortex model for the compressor cascades.
- aerospace propulsion system /
- topology /
- compressor cascade /
- incidence /
- separation mode

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