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轴流压气机叶尖射流扩稳数值计算模型

时培杰 乔渭阳 魏佐君 许坤波

时培杰, 乔渭阳, 魏佐君, 许坤波. 轴流压气机叶尖射流扩稳数值计算模型[J]. 航空动力学报, 2013, 28(7): 1549-1556.
引用本文: 时培杰, 乔渭阳, 魏佐君, 许坤波. 轴流压气机叶尖射流扩稳数值计算模型[J]. 航空动力学报, 2013, 28(7): 1549-1556.
SHI Pei-jie, QIAO Wei-yang, WEI Zuo-jun, XU Kun-bo. Numerical calculation model of axial compressor stability enhancement bywith discrete tip injection[J]. Journal of Aerospace Power, 2013, 28(7): 1549-1556.
Citation: SHI Pei-jie, QIAO Wei-yang, WEI Zuo-jun, XU Kun-bo. Numerical calculation model of axial compressor stability enhancement bywith discrete tip injection[J]. Journal of Aerospace Power, 2013, 28(7): 1549-1556.

轴流压气机叶尖射流扩稳数值计算模型

Numerical calculation model of axial compressor stability enhancement bywith discrete tip injection

  • 摘要: 基于体积力方法将压气机叶片对气流的作用力和做功简化为源项,对环形无叶片通道求解带源项的Navier-Stokes(N-S)方程,实现了压气机全通道流场的计算,通过在转子上游机匣施加射流建立了轴流压气机叶尖射流扩稳数值模型.模型中的源项根据叶片排进口气流参数进行变化,通过判断施加的人工扰动变化确定压气机失稳边界.采用该模型对某跨声速单级压气机在有、无射流下的性能和稳定性进行了计算分析,无射流下计算的该压气机性能和稳定边界与试验结果都能较好地一致,其中稳定边界流量仅相差0.7%;有射流下射流对压气机具有明显的扩稳效果,将计算结果与国外公开文献的结果进行了对比,验证了模型的可靠性.

     

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出版历程
  • 收稿日期:  2012-09-28
  • 刊出日期:  2013-07-28

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