The Effect and Mechanism of Blade Deformation on Aerodynamic Performance of Centrifugal Compressor Used in Turbocharger
In order to study the effect of blade deformation on the aerodynamic performance of a centrifugal compressor used for turbocharger,the fluid-structure coupling method was used to calculate the compressor performance at three operating conditions,i.e.,near-surge point,peak efficiency point and near-choke point at the design rotational speed.The results show that the blade deformation is mainly affected by centrifugal load,which accounts for 92.11％～97.22％,the maximum deformation of the blade occurs at the tip of leading edge of the main blade,and the maximum stress of the impeller occurs at the bottom of the impeller shaft hole;from the near-choke point to near-surge point,the blade deformation caused by aerodynamic load increases continuously,accounting for 2.78％～8.33％of the total blade deformation;after deformation,the compressor efficiency and pressure ratio increase by 0.3％and 0.15％respectively,and the choking mass flow decreases;it is found that the deformation direction caused by aerodynamic load is opposite to that caused by centrifugal load,and the blade deformation mainly affects the aerodynamic performance of centrifugal compressor by changing the tip clearance.The research results provide reference for aerodynamic and pre-deformation design optimization of centrifugal compressor.
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