| 等离子体气动激励抑制压气机叶栅角区流动分离的仿真与实验 |
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| 引用本文： | 吴云,李应红,朱俊强,周敏,贾敏,苏长兵,宋慧敏.等离子体气动激励抑制压气机叶栅角区流动分离的仿真与实验[J].航空动力学报,2009,24(4):830-835. |
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| 作者姓名： | 吴云 李应红 朱俊强 周敏 贾敏 苏长兵 宋慧敏 |
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| 作者单位： | 1.空军工程大学 工程学院, 西安 710038 |
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| 摘 要： | 进行了等离子体气动激励抑制低速压气机叶栅角区流动分离的数值仿真研究,并进行了实验验证.小攻角情况下,叶片吸力面角区流动分离导致显著的尾迹总压损失.来流速度为50 m/s(雷诺数为223 000)时,等离子体气动激励可以有效的抑制角区流动分离,降低总压损失.激励电压、频率分别为10 kV和22 kHz时,50%叶高处的尾迹压力分布基本不变,60%和70%叶高处的最大总压损失分别减小了13.83%和10.74%.增加激励电极组数或激励电压,可以增强抑制效果.
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| 关 键 词： | 等离子体气动激励 压气机 叶栅 角区流动分离 |
| 收稿时间： | 2008/10/21 0:00:00 |
| 修稿时间： | 2/17/2009 3:54:46 PM |
Computational and experimental investigation of plasma aerodynamic actuation based corner flow separation control in a compressor cascade |
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| WU Yun,LI Ying-hong,ZHU Jun-qiang,ZHOU Min,JIA Min,SU Chang-bing and SONG Hui-min.Computational and experimental investigation of plasma aerodynamic actuation based corner flow separation control in a compressor cascade[J].Journal of Aerospace Power,2009,24(4):830-835. |
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| Authors: | WU Yun LI Ying-hong ZHU Jun-qiang ZHOU Min JIA Min SU Chang-bing and SONG Hui-min |
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| Institution: | 1.The Engineering Institute, Air Force Engineering University, Xi'an 710038, China2.Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China |
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| Abstract: | Plasma aerodynamic actuation based corner flow separation control in a compressor cascade was investigated computationally and experimentally.Three dimensional corner flow separation,which is formed over the suction surface and end wall corner of a compressor cascade blade passage,could cause significant total pressure loss even when the incidence is 0 deg.When the free stream velocity is 50m/s(corresponding Reynolds number is 223000),plasma aerodynamic actuation controls the corner flow separation effectiv... |
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| Keywords: | plasma aerodynamic actuation compressor cascade corner flow separation |
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