A time domain fluid-solid interaction numerical calculation method was applied to study the static aeroelastic problems of transonic fan blades under aerodynamic and centrifugal forces. The blade deformation rules and its effects on aerodynamic performance were analyzed under various working conditions. Static aeroelastic simulation of the NASA rotor 67 indicates that the aerodynamic contribution to the maximum blade deformation accounts for 13.07% of the total deformation

and the passage shockwave position and strength are altered due to the blade deformation. The static aeroelastic simulation of a wide-chord hollow transonic fan blades reveals that the effects of blade deformation on the aerodynamic efficiency is 0.15%-0.5%. The aerodynamic contribution to total deformation at leading edge is up to 41% and the aerodynamic characteristic map of this fan is shifted rightwards with the increasing mass flow rate. The overall results show that the nonlinearity of aerodynamic force has significant effects on the static aeroelastic property of transonic fan blades

and the blade un-running design in industrial practice should adopt a fluid-solid interaction method to attain more accurate blade shapes.