Targeting the resonant analysis of aero-engine bladed-disk structure

by studying the mathematical formula of the gas excitation and nodal diameter vibration in the revolving coordinate and based on the positive work condition when the gas excitation acted on the bladed-disk structure

a relational expression dm=kNv-nNb describing the relationship between the number of nodal diameter and rotor/stator was deduced while the structure was in resonance. Three numerical examples were given to illustrate the above relation: from the perspective of aerodynamic work and harmonic response

a bladed-disk structure was in resonance while the above relation existed and the excited frequency was equal to structural natural frequency

and moreover

partial blades may be in serious vibration state while the above-mentioned frequency was equal even if the fore-mentioned relation was not satisfied.