A numerical method based on staggered algorithm was used to simulate aeroelastic response in compressor rotor blades.The finite element structural solver was used for structure dynamic analysis

and the unsteady flow solver developed by others was introduced to provide aerodynamic force.The structural solver could transfer the motion of blade to the flow solver

the flow solver advanced the fluid system to obtain new pressure field on blade

and a procedure was used to exchange the interface information between two solvers.Numerical results indicate that staggered algorithm yields transient response of rotor

thus helping to judge whether flutter can occur.