Abstract
In order to assess the vibration localization influences of different parameters of structural of the mistuned bladed disk system, the pre-stressed component mode synthesis method was adopted, and reduced-order models (ROMs) of the aero-engine compressor bladed disk system were built. Identification of the mistuning parameter was set based on the combination of blade static frequency, dichotomy and finite element analysis method. By Defining the vibration localization factor, the influence parameters such as the engine orders of excitation, mean frequency and stiffness ratio were considered, localization characteristics of the vibration response was analyzed, and the influence rule of different parameters on the vibration response were discussed. The result shows that the engine orders of excitation has significant influences on the frequency, displacement and strain energy distribution, with the increase of the engine orders of excitation, the relative localization factors firstly increase, and then decrease; the relative localization characteristics of the bladed disk system on the different mean frequencies were found out; with the increase of the stiffness ratio of the blade and disk, maximum vibration amplitude and strain energy of the bladed disk system gradually decline.
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