In order to obtain a better understanding of the secondary flow effects on blade stall flutter

this paper presents an approximate method to analyse the effects of secondary flow on blade aeroelastical stability.The method combines conventional streamline curvature methods with the secondary flow model to obtain the stationary flow with circumferential nonuniformity

and then incorporates the non constant phase angle deforming actuator disk method.Several secondary flow effects on aeroelastical stability were analysed respectively.The results show that the effects of the secondary flow on the aeroelastical stability are different.The tip leakage vortex may have greater effect than other vortexes

that is consistent with the experimental results.