Abstract

Dynamic mode decomposition (DMD) is performed to investigate the unsteady flow field in the tip region of transonic axial compressor NASA Rotor35 at 100% design rotating speed. With DMD technology, the complex flow field containing spatial and temporal information can be decomposed hierarchically. The results show that DMD obtain the oscillation frequency 5.60 kHz of the unsteady flow field in the tip region at low mass flow condition, and the corresponding modes with large scale oscillation structure at blade pressure side show the flow field fluctuating nature. In addition, flow field reconstruction is conducted by the second DMD mode and the oscillations alternating positive and negative is the main unsteady flow source for the compressor. The oscillation in the tip region conducts as like a standing wave.

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