In　order　to　study　the　shedding　and　propagation　of　compressor　rotors　at　high　angle　of　attack,　as　well　as　the　dynamic　response　under　this　transient　process,　a　model　with　a　stage　of　transonic　compressor　was　simulated　with　unsteady　numerical　method　and　double　direction　iteration　fluid-structure　coupled　numerical　method.　The　results　show　that　under　near-stall　condition,　the　separation　regions　at　suction　side　move　and　shed　periodically　along　axial　and　circumferential　directions.　The　axial　separation　may　influence　the　flow　field　and　vibration　performance　of　downstream　blade　rows,　while　the　circumferential　separation　can　impact　the　adjacent　rotor　blade,　with　an　excitation　brought　on　rotor　row　itself　and　an　influence　on　the　pressure　distribution　of　rotor　blades.　Furthermore,　the　circumferential　separation　may　cause　violent　dynamic　response　which　could　threaten　the　structural　strength　of　rotor　blades.　Unsteady/FSI　simulation　technology　has　the　ability　to　forecast　frequencies,　amplitudes　and　locations　of　the　excitation　sources　in　flow　field.　This　kind　of　work　should　be　emphasized　during　design　procedure　to　assess　the　resonance　and　dynamic　response　of　compressor　blades.　©　2017,　Editorial　Board　of　JBUAA.　All　right　reserved.