跨声轴流压气机激波/泄漏涡/边界层分离相互作用的影响

谢芳; 楚武利; 张皓光

跨声轴流压气机激波/泄漏涡/边界层分离相互作用的影响

1.
西北工业大学动力与能源学院, 西安 710072
2.
西安高技术研究所204室, 西安 7100725

基金项目: 国家自然科学基金(51006084)

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出版历程
- 收稿日期: 2011-05-09
- 修回日期: 2011-08-02
- 刊出日期: 2012-02-28

Influence of shock waves/leakage vortex/boundary layer separation interaction in a single-stage transonic axial compressor

1.
School of Power and Energy, Northwestern Polytechnical University, Xi’an 710072
2.
The 204 Office, Xi’an Institute of High Technology, Xi’an 710025, China

摘要

摘要: 对跨声速转子Rotor37进行三维定常数值模拟,将设计间隙与零间隙进行对比研究,分析激波、边界层分离、间隙泄漏涡相互作用影响.数值计算显示:激波、泄漏涡、边界层分离相互影响,加速了失速的发生;减小间隙可以起到扩稳的作用.根据边界层分离、间隙泄漏涡在叶栅高度上的影响范围,提出利用抽吸技术进行被动控制改善流道流动状况时抽吸点的设置位置.
- 跨声速 /
- 轴流压气机 /
- 激波 /
- 间隙泄漏涡 /
- 边界层分离
Abstract: Three-dimensional(3-D) numerical simulations were conducted to analyze the flow field in transonic rotors Rotar 37. The results with design tip clearance were compared with no tip clearance condition. Mutual influence of shock, boundary layer separation, clearance leakage the vortex accelerated the occurrence of stalled. Reduce clearance can enlarge the steady border. The suction position applied on passive control technology to improve port flow condition was given.
- transonic /
- axial compressor /
- shock /
- tip leakage vortex (TLV) /
- boundary layer separation

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参考文献(12)

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