The dynamic characteristics of a bladed disk assembly are calculated by means of sector elements of thick plates and wave propagation technique of periodical structure. The method saves greatly the computing time and the storage of computer. The vibration characteristics between the bladed disk assembly and the single blade or disk are compared and the influences of the variation of geometric parameters of the bladed disk assembly on its vibration characteristics are considered. Some conclusions are drawn which will play an important part in further research on the vibration control of an aeroengine. A bladed disk assembly of an actual compressor is analyzed in this paper

and the results obtained coincide with the experimental data. Therefore

the presented method is applicable to the practical engineering.