An arbitrary airfoils blade design procedure was adopted to redesign a transonic fan with compound swept.by adjusting the distribution of crucial design parameters in the process of redesign

the loss of shock was depressed

the conflict of the high relative Mach number and low loss/high efficiency was overcome.Numerical simulation core and bypass indicate that

the efficiency of design point falls little

but the efficiency of take off point improves significantly

and the matching of core and bypass of the fan and booster is also promoted efficiently.