Vibration reduction of mistuned blade-disc by ant colony algorithm and modal localization parameter

A typical model of lumped parameters of blade-disc structure was developed to solve the problems of the difficult post-processing for the superstandard vibration of aero-engine caused by mistuned blade-disc structure. The effect of the sequential arrangements of mistuned blades on modal localization was studied, and the ant colony optimization technique was applied to the optimal design of positioning every blade. Simulation results showed that for the definite mistuned blades the different sequential arrangements will affect the inherent characteristics of the blade disc system very greatly and, simultaneously, verified that the ant colony algorithm can provide the sequential arrangements of blades quickly and accurately so as to improve obviously the modal localization of the blade disc, thus providing an efficient way available to the trouble-shooting of the blade disc system.