Numerical investigations of mass-flux redistribution and performance prediction model on coupling effects of total pressure distortion-low Reynolds number in axial compressor

Abstract

Stability assessment is one of the important subjects in airworthiness certification. Many destabilizing factors can deteriorate the performance and stability margin of the compressor, and there are coupling effects between the external factors. This paper applies a computational method to investigate the coupling effects of total pressure distortion and low Reynolds number on an axial transonic compressor. The study was carried out on NASA stage 67, in which extensive open experimental data is available. Full annulus, steady, three-dimensional CFD has been used to study the coupling effects of 180-deg inlet distortion at low Reynolds number. The assessment of the stability margin loss under coupling effects by traditional methods results in a relative error of 27%. The local operating point of the rotor at different passages has been tracked, and the results reveal the reasons for the failure of model predictions. Combined with the analysis of the flow field under coupling effects, development solutions for the traditional model are proposed. The modifications to the model agree well with the calculation results. Finally, the improved model was validated. And according to the analysis of the rotor passage working points, the rationality of the model modification was verified.