ミスチューンがある翼・ディスク系の応答解析(綴り翼構造)(機械力学,計測,自動制御)

概要

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When calculating the resonant response of bladed turbine disks, it has proved useful to assume that all blades on a given disk are identical. This leads to the prediction that all blades experience the same amplitude of displacement and stress when excited by forces harmonically related to the rotor speed. However, it has been shown experimentally that significant variations in these amplitudes occur for different blades on the same disk. These variations arise due to the effects of mistuning, which refers to small differences in the blade characteristics. In this paper, vibrational characteristics of a bladed disk of mistuned grouped blades is studied using the substructure synthesis method and modal analysis. It is found that a bladed disk system of grouped blades is very sensitive to mistuning, and the fundamental vibrational characteristics of grouped blades with mistuning is shown.
社団法人日本機械学会の論文
1997-06-25