Aeroelastic stability of oscillating blades was simulated by solving unsteady compressible Navier-Stokes equations with dynamic deforming mesh

and the effect of frequency mistuning on aero-dynamic damping was investigated. The aeroelasticity algorithm was validated by the simulation of aeroelastic behavior of the 10th aeroelastic standard configuration. The aero-dynamic damping of the oscillating cascade was calculated with different inter-blade phase angles (IBPA) and reduced frequencies. The effects of mistuning pattern and frequency of mistuning on aero-dynamic damping and the mechanism of frequency mistuning on aeroelastic stability were studied. The results indicate that frequency mistuning is an effective method in improving aeroelastic stability and the coupling of the blade vibration and the effect of IBPA were weakened by frequency mistuning; the aeroelastic stability of blade increases with the increase of frequency mistuning. 3-D aeroelstic computation of the 4th aeroelastic standard configuration was performed to examine the effects of frequency mistuning on aeroelastic stability margin

and the laws of IBPA and aeroelastic stability increasing was validated.