The aeroelastic stability prediction and the flutter margin point were achieved by energy method in original scheme of prototype compressor fan blade. The geometric modeling of aeroelastic unstable blade was modified to improve the aeroelastic stability. By comparison of blade geometric modeling

aerodynamic performance

vibration characteristic and aeroelastic stability in original and modified schemes

the blade flutter mechanism of compressor fan was analyzed on aerodynamic aspect. The effective engineering flutter suppression means for the compressor fan blade are achieved

such as increasing the chord length of blade and decreasing the aspect ratio

increasing the blade thickness and stiffness

decreasing the angle of incidence and improving the flow.