An aeroelastic stability prediction approach derived from energy method was used to investigate the effects of several parameters on the aeroelastic stability of rotor blades in turbomachinery

and the mechanism of flutter was determined in some details.Taking the first stage compressor rotor of an engine as an example

the aeroelastic analysis was computed under different working conditions for the oscillating cascades with different blade modes.Some parameters

such as mode shape and interblade phase angle

were included to investigate their effects on the flutter in turbomachinery.And the flutter mechanisms were also concluded from the interaction of shock wave on the suction surface and separation area behind shock.The result shows that mode shape and interblade phase angle are key parameters affecting the flutter characteristics

while the shock wave on the suction surface and the separation area behind the shock wave are important factors to induce the blade flutter.