Abstract: A numerical simulation method for fluid-structure interaction(FSI) in turbomachinery bladings was presented to predict the aeroelastic stability of blades.The vibrational displacements of computational structural dynamics(CSD) nodes have been interpolated to computational fluid dynamics(CFD)grids at the blade surface using a data transfer method.In CFD analysis,the grid coordinates of the moveable region have been updated by multi-layer moving grid technique,and the finite volume method has been applied to calculate the Reynolds-averaged Navier-Stokes(RANS) equations closed by k-ε turbulent model.For NASA Rotor 67,the total work done by the unsteady aerodynamic force in one oscillating period and the corresponding aerodynamic modal damping ratios of the first four modes of blade vibration at the design speed have been predicted numerically,and the aeroelastic stability of blades has been analyzed preliminarily.The study shows that the developed FSI procedure is feasible to predict the aeroelastic stability of blades.