Numerical Simulation of Bird Impact on Hollow Blades of Titanium Fan Assembly

In this paper, a bird impact test was carried out on a static hollow blade, and a numerical model corresponding to the test was established based on the dynamic explicit finite-element software PAM-CRASH and its smoothed particle hydrodynamics (SPH) method. Good consistency between the simulating and experimental results proves the validation of the calculating method used in the model. Then, the numerical model of a rotary engine fan assembly with the same hollow blades was established, and its dynamic responses to bird impact were studied under different working conditions. Results show that the bird speed, mass, and impact location, and the rotating speed of the fan, have significant effects on the final deformation of the engine blades. The conclusions presented in this paper can provide a reference on anti-bird-strike design and airworthiness verification of the engine fan blade.