Analysis finds improved flow stability in centrifugal compressors through energy transfer regulation, suggesting significant implications for aviation power systems.
Compressor flow instability significantly constrains the development of aviation power systems. Improving flow stability of compressor is usually challenging without deteriorating aerodynamic performances. In this study, a new method for improving compressor flow stability is proposed based on regulating energy transfer among flow field dynamic modes. Firstly, dynamic mode decomposition (DMD) is conducted on the compressor flow field to identify the dominant dynamic modes and the corresponding evolution characteristics. It is found that the BPF (Blade-Passing-Frequency) mode and its harmonics represent the rotor-stator interactions of the flow field, and they are named as inherent mode. The 0.11RF (Rotor Frequency) mode, which is caused by large-scale low-frequency disturbances downstream of the rotor, characterizes periodic fluctuations of the compressor flow field, and it is recognized as characteristic mode. DMD analyses on the compressor throttling process reveals that the essential feature of compressor flow instability is the energy transfer from the inherent mode to the characteristic mode. Then, an optimization method is proposed for improving flow stability by maximizing inherent mode energy and minimizing characteristic mode energy. Optimization based on this approach has resulted in a 25.4% increase in the energy-ratio of the inherent mode at the compressor near-stall condition, alongside a 51.84% reduction in the energy-ratio of the characteristic mode. The compressor stall flow rate is decreased by 8.45% and the choke flow rate is increased by 5.11%, and the overall aerodynamic performances are maintained.
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Xie et al. (2025) studied this question.
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