Abstract: In order to improve the computational efficiency of the dynamic characteristics analysis in the aeroengine with the computational accuracy, an improved hybrid interface substructural component modal synthesis method (HISCMSM) is proposed due to the problem of the large amount of calculation via the traditional HISCMSM when the substructures are assembled. The comprehensive model is further reduced by this method. The assembled structural parametric model of blades and disks is built by this method to establish each substructural finite element model (FEM) and the natural frequency and modal shape are obtained. Compared with the overall structure FEM, the computational time and the modal deviation are respectively shortened by 23.86%-35.74%, 14.63%-29.20% and 0%-0.49%, 0%-0.57% via the improved method and the traditional method. So the improved method is much more efficient than the traditional method, especially in the high order modal solution which is much clear, meanwhile, modal displacement, modal stress and modal strain energy of the tuned and mistuned bladed disk assemblies are investigated, the symmetry of the tuned bladed disk assemblies is damaged and the localization phenomenon is observed which reinforces with the mistuned amplitude increasing. Gradually, the vibration is localized in a few blades and the phenomenon is getting more and more obvious, which can settle the foundation of the further research on dynamic response and the probability analysis of the mistuned bladed disk assemblies.

Key words: aeroengine, computational accuracy, computational efficiency, finite element model, hybrid interface substructural component modal synthesis method, mistuned bladed disk assemblies