DOI: 10.5176/2251-1911_CMCGS14.40
Authors: A. Ajin Kisho, G. Dinesh Kumar, John Mathai, M.Vickram
Abstract: Certification requirement demand for civil aircraft and military aircraft to withstand foreign object damage at different flight conditions. Experimental tests for conducting bird strike analysis and impact analysis is costly and time consuming, and thus an accurate solution for designing a component against bird impact is important. Bird impact on aircraft is a soft body impact, it requires the density of a fluid, viscosity, shape of bird projectile and length to diameter ratio should be precisely selected. This paper investigates the effect and influence of all such parameters due to bird impact. The initial degradation and failure of individual compressor blades struck by a bird were investigated. Subsequent damage to other fan blades and engine components are also evaluated. Results will be compared in terms of pressure profile, and stagnation pressure at the center of the impact and the bird trajectory after the impact. The bird strike velocity varied from 190 to 250 m/s. A numerical model of this problem has been developed with the finite, non-nuclear element program LS-DYNA. This paper presents the bird strike analysis using Lagrangian, Arbitrary Lagrangian Eulerian (ALE) method and Smooth Particle Hydrodynamic (SPH) technique in LS-DYNA. Throughout the study, the most influencing parameters have been identified and peak pressures and forces are compared to those results available in the literature.
Keywords: Bird strike, LS Dyna, Compressor Blade, Lagrange, ALE, SPH
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