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轴流压气机叶尖射流扩稳试验

时培杰 乔渭阳 王良锋 陈伟杰 许坤波

时培杰, 乔渭阳, 王良锋, 陈伟杰, 许坤波. 轴流压气机叶尖射流扩稳试验[J]. 航空动力学报, 2014, 29(2): 384-390. doi: 10.13224/j.cnki.jasp.2014.02.018
引用本文: 时培杰, 乔渭阳, 王良锋, 陈伟杰, 许坤波. 轴流压气机叶尖射流扩稳试验[J]. 航空动力学报, 2014, 29(2): 384-390. doi: 10.13224/j.cnki.jasp.2014.02.018
SHI Pei-jie, QIAO Wei-yang, WANG Liang-feng, CHEN Wei-jie, XU Kun-bo. Experiment on axial-compressor stability enhancement by blade tip injection[J]. Journal of Aerospace Power, 2014, 29(2): 384-390. doi: 10.13224/j.cnki.jasp.2014.02.018
Citation: SHI Pei-jie, QIAO Wei-yang, WANG Liang-feng, CHEN Wei-jie, XU Kun-bo. Experiment on axial-compressor stability enhancement by blade tip injection[J]. Journal of Aerospace Power, 2014, 29(2): 384-390. doi: 10.13224/j.cnki.jasp.2014.02.018

轴流压气机叶尖射流扩稳试验

doi: 10.13224/j.cnki.jasp.2014.02.018

Experiment on axial-compressor stability enhancement by blade tip injection

  • 摘要: 采用转子叶尖射流对轴流压气机进行了扩稳试验研究.试验中对无射流的轴流压气机失速起始类型进行了测量,发现该轴流压气机以尖峰波的形式进入旋转失速;之后采用叶尖射流发现射流对压气机的失速起始过程没有明显影响.试验中对射流孔数目、射流孔周向分布和射流偏转角3个参数对压气机扩稳效果的影响进行了分析.测量结果发现:保持总射流流量不变,增加射流孔数目会降低轴流压气机扩稳效果;而在单个射流孔流量不变的情况下,增加射流孔数目会增大扩稳效果;射流孔周向分布越均匀扩稳效果越明显;射流扩稳效果与转子相对坐标系下的气动参数有直接关系,故采用相对坐标系下射流零攻角方向的动量分量与主流动量比值对扩稳效果进行了关联.

     

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出版历程
  • 收稿日期:  2013-04-08
  • 刊出日期:  2014-02-28

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