Numerical simulation of bird impact on bladed rotor stage by fluid-solid coupling method

An aeroengine rotor stage finite element method (FEM) model with aerodynamic load and constant rotational speed was studied by using fluid-solid coupling method with MSC. DYTRAN software in this paper to investigate its transient dynamic response while suffering various bird impacts. Results show that great instantaneous impact stress exists in the blades during the swift impact. The peak stress will rapidly increase if the velocity, density and size of the bird increase; nevertheless this ascendant tendency can be blunted after the potential of material hardening and deformation abilities have sufficiently developed. The result also reveal that raising hardening modulus of the blade material can increase the impact stress as well, whereas raising material yield strength will reduce the action time of impact stress. Finally, a more complicated simulation, in which material failure was included, was carried out to investigate the process of blade failure caused by bird impact.