Bird impact on fan blade analysis using smooth particle hydrodynamics coupled with finite elements

A Smooth Particle Hydrodynamics method has been used to model bird strikes on turbofan blades. The SPH model used for the bird, has been coupled with the blade finite element model by a contact algorithm. The method has been implemented in a transient non-linear finite element code PLEXUS. A soft body impact on a flat plate with tapered leading edge has been simulated. The excellent agreement found with tests results reported in the literature served as validation. Bird strikes on actual fan blades have been computed. The methods capability to represent bird slicing when multiblades impacts occured is shown. Good agreement with spin rig tests results was found.