Flow of stationary blade interference with the rotor wake was simulated using the large eddy simulation (LES) method. The coefficient of vorticity was used to reveal the evolution mechanism of rotor wake in the stator passage

and the pressure coefficient gradient was used to discriminate the shock structure and wave source. The flow characteristics of the temporal and spatial structures in the flow field were analyzed by dynamic mode decomposition (DMD). Result showed that three wave sources were found at the trailing edge of the moving blade

the leading edge of the stationary blade and the trailing edge. Multi-peak of the frequency spectrum was found in a stator passage flow field. The first order mode represented the transport of wake in the passageway and corresponded to the flow of rotor blade passing frequency (BPF)

its unsteady fluctuation was dominant in the flow field. The second order mode was twice of the rotor blade passing frequency and the spatial scale was half of the first order mode

representing smaller scale disturbances.