Vibrational response analysis of a mistuned bladed disk (grouped blade)

摘要

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 ampli- tudes occur for different blades on the same disk.