Targeting the forced vibration of bladed-disk in aero-engine

the impact of the severity of resonances induced by flow-wake of stator was studied. On the basis of the numerical simulation of unsteady stator-rotor interface flow

both frequency spectrum and spatial spectrum of aerodynamic pressure on the rotor surface were obtained respectively by fast Fourier transformation. Meanwhile

the excitability of wake was defined as the projection of aerodynamic pressure on the modal space

also called modal force

so as to evaluate the strength of resonant response of bladed disk. The analysis shows that the excitability of wake to a non-primary resonance is much less than a primary resonance. As a result

it is reasonable that in the operating speed region of aero-engine

the existence of high-order resonances with small complementary angle between aerodynamic force and modal displacement of bladed disk (small excitability)

should be accepted.