In order to reduce the level of the vibration localization of a mistuned bladed disk system by means of the pre-stressed component mode synthesis method，a reduced finite element model of the bladed disk system of an aeroengine compressor is constructed． Then，the natural frequencies with different mode truncation numbers are calculated，and through comparative analysis，the minimum mode truncation number satisfying the calculation precision is obtained． Moreover，the degree of freedom of the global model is reduced． Based on the reduced model，a blade vibration arrangement optimization algorithm is put forward，and at each iteration of the algorithm，only the substructure of a switching blade position is generated，while other blades data files remain unchanged． The results show that the constructed optimization algorithm takes into account both the model accuracy and the calculation speed，and it can greatly reduce the blade vibration amplitude and thus significantly reduce the vibration localization of the bladed disk system．