Abstract
In order to investigate the mechanism of a rotor system with unbalance and blade-casing rubbing coupling faults, the vibration and rub force in a rotor system resulting from unbalance and blade-casing rubbing coupling faults are simulated. At first, a dynamic model of 0-2-1 form rotor is established, and a blade-casing model, which considered blade number, clearance between the blade tip and stator, stiffness and size of the blade, is introduced to the rotor model. The characteristics of unbalance and blade-casing rubbing coupling faults are analyzed by waterfall plot, spectrum, time domain chart of vibration and rub force, and the effects of speed and clearance between the blade tip and stator. Secondly, a rotor system tester is established according to the model structure. The experimental test of rubbing is simulated by adjusting the Feeding Device to control the clearance between the blade and stator. After simulation and experimental results were compared, it was found that fraction frequencies and high integer frequencies were affected by a blade-casing rubbing fault, the clearance and speed had different influence on the dynamic characteristic of rotor system with blade-casing rubbing fault.
Highlights
The clearance between the blade tip and inner casing face has a great influence on compressor efficiency and fuel consumption of aero-engine
The Feeding Device is adjusted to control the clearance between the blade and stator, and the displacement data and force signals are collected to analyze the accuracy of the blade-casing rub model
A model of blade-casing rub which considers the number, stiffness and size of blade is developed and applied on a “0-2-1” form rotor system with bearing and coupling, the characteristics of vibration and rub force signal are studied under different rotor speeds and clearances
Summary
The clearance between the blade tip and inner casing face has a great influence on compressor efficiency and fuel consumption of aero-engine. On the basis of this study, Jiang [3] deduced a model of normal rubbing force between the blade and casing with the consideration of Centrifugal Force and rotating speed. Nan [7] deduced a blade model according to the cantilever beam assumption and analyzed the effects of stiffness, mass and excitation force on impact vibration of the system. Sinha [8] derived the basic dynamical equations for a rotating radial cantilever blade, and analyzing the transient response of displacement vibration and rub-force load; Almeida [9] studied the influence of friction on the blade response by time-frequency graph to show the spectrum of a contact force that followed exactly Signorini’s
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