Aeroelastic stability analysis of compressor rotor blades

including up- and downstream blade rows interaction

was conducted by self-developed fluid-structure coupled simulation programs. Blade aerodynamic damping values under different vibration modes were calculated through the time trace of the blade vibration amplitude induced by the unsteady flow field

using a whole assembly aeroelastic model. And the influence of wakes and potential waves on the aerodynamic damping values was studied for different axial gaps. Interaction effects on the flutter characteristics of rotor-stator and inlet guide vane-rotor configurations were assessed by comparing the damping data with that of the single rotor. The results show that the aeroelastic stability is not changed monotonically with the axial gap value for the first bending modal. The results also illustrate that the intensified wake and potential wave effects could destabilize the first torsional modal

but stabilize the first bending-torsion coupled modal.