The unsteady flow phenomenon of a transonic axial compressor NASA Rotor 36 was investigated. Based on the unsteady simulation results, proper orthogonal decomposition (POD) modes and time coefficients were obtained with POD method, and the flow characteristics of the tip clearance flow field at near stall conditions were further analyzed. Results showed that: at near stall condition, the dominant frequency of tip clearance flow field was the tip leakage vortex frequency, about 0.6 times blade passing frequency; the POD mode with higher energy determined the fluctuation frequency and amplitude of tip leakage vortex, and the POD mode with lower energy determined the fine structure of the flow field; the first 5 POD modes reconstructed the flow field very well, providing a theoretical guidance for the establishment of the low-order model.
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傅珏,杨波,钟芳源.基于POD方法的跨声速轴流压气机转子叶顶间隙流场分析[J].航空动力学报,2019,34(9):2048~2055. Analysis of transonic axial compressor tip clearance flow field with POD method[J]. Journal Of Aerospace Power,2019,34(9):2048-2055.