| Summary: | 碩士 === 國防大學中正理工學院 === 兵器系統工程研究所 === 94 === The main purpose of this research to investigate the flow field characteristics of a transonic one-stage compressors. The understanding of gas dynamics in the compressors and developing the capability of using computational fluid dynamic method is useful to the design and analysis of an axial compressor.
In this study, the CFD software CFX-Tascflow is applied for solving the complex flow field in a compressor and examing its performance. The model is based on the NASA Stage 36 axial-flow transonic compressor. The influences and differences of two interface models, Stage and Frozen, on the internal flow variations in the single stage compressor are discussed. The comparison between experiment data of NASA Stage 36 and the results obtained by the Tascflow calculation indicated that, the numerical sinulation operated with the standard model and interface model STAGE-SATGE has the best agreement. Then the rotating speeds from 50 to 100 percent of design speed are tested for performance analysis. It concluded that, the position of shock wave, the trends of the pressure and the temperature and performance curved are in good accord with the gas dynamics characteristics in an axial-flow transonic compressor stage.
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