摘要
本文给出一种计算压气机叶栅流场和气动性能的无粘流-边界层迭代方法.这种方法能够计算叶片后缘附近有紊流边界层分离的流动,考虑了尾迹对主流的位移效应.对一个高亚音速压气机叶栅的最小损失工况,计算得到的叶片型面M数分布、叶栅出口气流角、总压损失系数和试验值符合良好.
The inverse mode of lag-entrainment method is used to predict both separated turbulent boundary layers and wakes, a new iteration technique suggested by Carter is applied to combine the inverse mode boundary layer calculation with a time marching in-viscid flow analysis. It is found that this technique is applicable to obtain a converge solution for separated cascade flow. For a high subsonic double-circular-arc axial compressor cascade the calculated Mach number distributions on the blades, downstream flow angles and total pressure loss coefficients are in good agreement with experiment in the optimum incidence range. In the design incidence range the agreement between calculated results and experiment is not satistaetory.
出处
《工程热物理学报》
EI
CAS
1985年第3期226-231,共6页
Journal of Engineering Thermophysics
