| 低雷诺数下跨声速转子周向槽处理机匣扩稳研究 |
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| 引用本文： | 夏钦斌,王如根,李勇,郭飞飞.低雷诺数下跨声速转子周向槽处理机匣扩稳研究[J].空气动力学学报,2011,29(2). |
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| 作者姓名： | 夏钦斌 王如根 李勇 郭飞飞 |
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| 作者单位： | 空军工程大学工程学院,西安,710038 |
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| 基金项目： | APTD研究项目(APTD-1504-04-07) |
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| 摘 要： | 采用数值方法模拟了低雷诺数条件下NASA Rotor 37跨声速压气机转子内部流场。结果表明,附面层径向涡是该压气机转子流动失稳的一个很重要的原因。周向槽处理机匣结构对压气机流场的改善较为有限,而引入抽吸处理机匣后,抽吸槽可以将叶顶间隙涡和附面层径向涡及其引发的低能阻塞流团抽吸至处理槽内,叶顶流场大为改善,有效地提高了压气机转子的失速裕度。
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| 关 键 词： | 压气机 流动失稳 低雷诺数 机匣处理 附面层径向涡 |
The effects of a transonic compressor rotor with circumferential grooves casing treatment at low Reynolds number |
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| XIA Qin-bin,WANG Ru-gen,LI Yong,GUO Fei-fei.The effects of a transonic compressor rotor with circumferential grooves casing treatment at low Reynolds number[J].Acta Aerodynamica Sinica,2011,29(2). |
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| Authors: | XIA Qin-bin WANG Ru-gen LI Yong GUO Fei-fei |
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| Abstract: | The flow instability of NASA Rotor 37 transonic compressor rotor at low Reynolds number was investigated by numerical simulation.Result shows that the boundary layer radial vortex becomes an important factor for triggering off the compressor flow instability.The effects of the transonic compressor rotor with circumferential grooves casing treatment and suction groove casing treatment were investigated.It is showed that the effects of circumferential grooves are not very obvious.The suction groove casing tre... |
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| Keywords: | compressor flow instability low Reynolds number casing treatment boundary layer radial vortex |
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