Forced Vibrations of a Single Stage Axial Compressor Rotor

Abstract

A semi-empirical method, utilizing modal analysis based on experimentally obtained modeshapes has been used to study the vibration response of a 23 bladed axial compressor rotor. The system modeshapes, characterized by the blade deflections at resonance, are more or less irregular depending upon the proximity of the system frequencies to the blade cantilever frequencies. The response of the detuned bladed disk assembly to various types of harmonic excitations are shown to be predictable if sufficient experimental information is available about the resonant modes and frequencies of the system.