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通过理论分析提出一种考虑叶片端部间隙影响的叶片力亏损模型,并对三种轴流压气机叶栅的端壁边界层及叶片力亏损进行了数值计算。计算结果与实验结果比较表明吻合程度较好,说明提出的叶片力亏损模型具有可行性和通用性。数值分析也表明端壁边界层流动与叶片力亏损存在着紧密的关联:端壁边界层的偏转程度对切向叶片力亏损有明显影响;边界层轴向动量增长率对轴向叶片力亏损起主要作用。
A model of blade force loss considering the effect of blade tip clearance was proposed through theoretical analysis. The boundary layer and blade force losses of the three kinds of axial compressor blades were numerically calculated. Comparing the calculated results with the experimental results shows that the agreement is good, which shows that the proposed blade loss model is feasible and universal. The numerical analysis also shows that there is a close relationship between the flow in the boundary layer and the blade force loss: the degree of deflection in the boundary layer of the end wall has a significant effect on the force and loss of the tangential blade; the increase rate of axial momentum in the boundary layer main effect.