In order to improve the aerodynamic performance of twin centrifugal compressors used in a V-type turbocharged engine

the distortion of inlet flow field caused by its common inlet manifold were studied. To this end

the initial performance of the twin compressors was tested on a test bed

and the simulation model was calibrated. Then

the distribution characteristics of inlet flow fields of the twin compressors were analyzed. Results indicate that sharing a single inlet manifold has a significant impact on the aerodynamic performance of the twin compressors

resulting in a reduction of blockage flow and a decline in compressor efficiency from the blockage point to the highest efficiency point. Not only that

the performance of the right compressor is more likely to deteriorate than the left compressor. The mechanism that causes this phenomenon is that due to the limitation of installation space

the flow field distortion of the right compressor is higher than the left compressor under the superimposed effect of airflow at the throat and inlet

regardless of the circumferential and blade height direction. Moreover

the distortion of inlet flow field will continue to extend inside the compressor impeller

making the compressor performance worse.