| Summary: | 碩士 === 國防大學理工學院 === 機械工程碩士班 === 106 === The high-thrust-to-weight ratio aircraft engine needs a high performance compressor. The axial flow compressor is able to offer more mass flow rate and reach higher pressure ratio by employing multi-stage compression i.e. series combinations. Therefore, axial flow compressor becomes the main application in engines, and, moreover, its rotor is the significant key to the compressor operating performance.
In this study, the performance and flow field characteristics of axial compressor rotor are simulated and analyzed by using Computational Fluid Dynamic (CFD). In order to validate the applicability of the built numerical CFD model, a NASA Rotor 67 has been used as a reference rotor. Comparing simulations and experiments show that the numerical CFD model of the compressor rotor is able to predict the pressure ratio and isentropic efficiency correctly and is also able to simulate the relative Mach number distributions accurately within the rotor passage. In addition, the positions of shock waves, the complexity of the flow field near hub and shroud also can be characterized properly within the rotor passages.
The numerical CFD simulation model of a compressor rotor established in this study can be applied in investigate the performance of the compressor rotor and the flow field characteristics within the rotor’s passages. It also can be used as a reference model for the designing of a compressor rotor at the earlier stage.
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