Prediction of bird impact in hollow fan blades

Abstract

To treat the bird strike on fan blades, a new Smooth Particle Hydrodynamics (SPH) method was developed then implemented in the non-linear transient code CASTEM-PLEXUS. This meshless method is well-suited for the bird strike because the projectile behaves like a fluid during the impact. The bird is modeled by a set of Lagrangian particles and a specific state equation evaluates the pressure in the projectile. The rotor structures are still meshed with finite elements and the bird interacts with the engine thanks to a contact algorithm. This formulation has been applied to compute the response of a fan blade stage during the impact of a medium bird. The rotor is composed of wide chord t i tanium hollow blades. The results of the simulation show good agreements between calculations and tests. The final deformation of each fan blade depends effectively of its position on the rotor. Blades and bird interact and the slice cut by the airfoil is not regular. The experimental data confirm that the final deformation of leading edges and the buckling of stiffeners are well predicted. Copyright © 2000 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved