Bird impact analysis on aeroengine fan blades

摘要

The smooth particle hydrodynamics (SPH) method was developed to provide a transient structural analysis of fan blades during bird strikes. The projectile is modeled by a set of Lagrangian particles, and a specific state equation evaluates the pressure in the bird. This SPH method is coupled with finite elements by a contact algorithm and implemented in the fast dynamic code CASTEM-PLEXUS. Unlike the classical Lagrangian formulations, this model avoids the severe distortions of projectile mesh during the impact phase. Uniform bird slicing by the rotating blades is not assumed prior to the calculation. The method is applied to compute the response and the residual deformations of a complete fan stage.