Abstract
One of the criteria for evaluating the reliability of the aviation gas turbine engine housing is their ability to retain broken elements of the rotors and, primarily, the fan blades. The paper presents the results of numerical simulation of deformation and fracture of the aviation gas turbine engine housing after a high-speed collision with a fan blade at its emergency breakage. Parameters of Johnson-Cook model, describing the behavior of alloys VT6, OT4 and OT4-0, is verified. Comparison with experimental data showed a good agreement for the flying residual velocity of the broken blade and forms of punched holes. It is shown that depending on the housing material, its thickness and blade breakage velocity, there is a possibility of penetration of the housing by a broken blade and its departure beyond or localization of the broken blade inside the housing.
Keywords: deformation, fracture, strain rate, plasticity, LS-DYNA, Johnson-Cook model.
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