| Summary: | 碩士 === 國防大學中正理工學院 === 兵器系統工程研究所 === 92 === The flow field within the blade rows of a multistage axial compressor is extremely complex. This includes transonic flows, turbulence, secondary flows, tip clearance flows, inter-blade row interference, etc. The blade shape in transonic axial compressor is complex too, including high twist, high aspect ratio, thinner thickness, etc. Hence, the fully three-dimensional approach is the only plausible way to numerically investigate the flow variation in compressor field.
Various computer algorithms and CFD codes are being proposed to satisfy this need, TurboGrid in constructed O-H grid system and TASCflow in solving the Reynolds-averaged Navier-Stokes equations by control volume finite element method, are used in this study. The validation of CFD codes is conducted by comparing the predictions with a benchmark database acquired experimentally on a FAN ROTOR-67 NASA transonic fan. Then, the simulation and analysis of one stage transonic axial compressor is performed.
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