In order to study the effects of boundary layer suction (BLS) on counter-rotating compressors in multistage environment

numerical investigations were performed on the rotors of a dual stage counter-rotating compressor with BLS method. Three different suction slots in chord direction were set up on the front rotor (R1) and rear rotor (R2) suction surface to study the effects of flow structure and performance on different suction ways

and independent suctions were carried out on R1 and R2 respectively at different suction locations and suction air rate in counter-rotating compressor. By BLS of individual R1

the efficiency increases with the rise of suction air rate. But the aerodynamic performance matching R1 with R2 becomes worse and makes R2 fall directly. The overall efficiency is also represented by the fluctuation from going up to down. The best suction location of R1 is near the trailing edge. By BLS of R2 individually

the efficiency of R2 keeps the trend from increase to reduction with the rise of suction rate

while the efficiency and flow field of R1 remain unchanged nearly. The best suction location of R2 is near the trailing edge. The deviation angles reduce obviously after the BLS. The above results demonstrate that matching of aerodynamic parameters between blades rows is a main factor to be considered after BLS in multistage environment.