Muwaffaq ali tawfik; Adel abd naif
Abstract
Abstract The research studies the effect of the blade vibration on the dynamic response of turbo - compressor rotor system . The design angles for the blades , gas entrance and exits ...
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Abstract The research studies the effect of the blade vibration on the dynamic response of turbo - compressor rotor system . The design angles for the blades , gas entrance and exits and the missing of a fraction of blade mass have been studied with the existence of the forced vibration . The critical speeds and the eigen modes have been computed taking into account the effect of the cited factors . Shear effect , gyroscopic effect , bearing damping and the unbalance forces are catered for the analysis of the system has been achieved using the transfer matrix method . The transfer matrices are developed to consider the complex system pattern which is composed of many branches meeting in point located on the system rotor , which represents a disk stage . The basic principles for designing the gas turbine have been adopted in calculating the subjecting forces of the gas along the blade surface using the triangle velocities diagram for the gas inlet and exist for each single stage . The results show clearly when the system looses a part or fraction of any blade , a sudden disturbance is noticed . An increase in the critical speed and the amplitudes of vibration are revealed . An effect of the gas and blade angles change on the critical speeds values and orders are noticed . The effect is only confined on the amplitude of vibration .
