Based on the blade disk basic sector of certain stage compressor

blade disk finite element model considering non-linear tenon contact was established

free-interface substructure-fixed interface prestressed modal synthesis super element approximate analysis method was proposed

meanwhile

mistuned parameters recognition method of linear expression was fitted based on the blade static-frequency test and dichotomy combined with finite element analysis

exploring the effects of mistuning key factors on blade disk vibration. Results show that the non-linear tenon contact cannot be neglected

and the accuracy of super element method is 3.07%

so the proposed method meets the requirement. In addition

blades mean frequency

disk stiffness ratio and frequency veering have an effect on mistuned bladed disks vibration amplitude

resonance frequency and strain energy and other parameters.