The StreamVane swirl distortion generator was combined with transonic compressor Stage 67 using numerical simulation to investigate the effect of swirl distortion generated by exit of S-duct inlet and hybrid wing body (HWB) on the performance and stability of compressor. The compressor characteristic map and flow field were obtained by this method and compared with characteristic map and flow field with uniform inflows. There existed a maximum decrease of pressure ratio

efficiency

stability mass flow rate and stability margin by 0.06%

0.85%

5.97% and 1.13%

respectively

with 100% corrected speed under the effect of the S-duct inlet swirl distortion. Both pressure ratio and efficiency characteristic lines moved to the lower left. There existed a maximum decrease of efficiency

stability mass flow rate and stability margin by 6.25%

26.88%

2.84% and a maximum increase pressure ratio by 6.61% respectively with 100% corrected speed under the effect of the HWB swirl distortion. The pressure ratio characteristic lines moved to the upper right

the efficiency characteristic lines moved to the lower right.