Abstract
In practical aero-engine bladed disk structure of blade mistuning is inevitable, and seriously affects the vibration characteristics of bladed disk system also on the whole aero-engine performance and life. Through the analysis, the blades arrangement order of a set of mistuned blade can greatly influence the vibration of bladed disk system, on this foundation; put forward a kind of new localization level of vibration parameters method for the characterization of mistuned system vibration localization degree. Furthermore, genetic particle swarm algorithm is used to optimize the blade arrangement sequence. The research shows that the selection of appropriate blade arrangement sequence can effectively reduce the bladed disk system forced vibration amplitude and the localization level of forced vibration.
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