Firstly

by introducing the aerodynamic influence coefficient

a linear relation between aerodynamic force and the vibrating displacement was established. Based on this relation

a linear vibration equation of aeroelastic coupling of bladed disk structure was deduced. Then

the piezoelectric network was introduced into the bladed disk structure

and the fluidmechanicelectro coupling dynamic equation was established. The lumped parameter equivalent model was adopted to study the influence of the piezoelectric network on the aerodynamic damping of the bladed disk

and the eigenvalue problem of the fluidmechanicelectro coupling system was solved. The aerodynamic damping ratio of the system was obtained as the criterion of the aeroelastic stability of the system. The results show that the piezoelectric network can effectively improve the aeroelastic stability of the bladed disk vibrating in nodal diameter modes

which are main vibrating modes of the bladed disk; the electrical parameters of the piezoelectric network can be optimized to extend the flutter boundary in a large frequency domain of the bladed disk; the aerodynamic damping of the bending vibration of the blade is better than that of the coupled bending and torsional vibration.