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Development of a Generic Gas-Turbine Engine Fan Blade-Out Full-Fan Rig Model
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2015-08-01
[PDF-5.39 MB]
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Abstract:This report describes the development of a generic fan blade-off (FBO) full-fan rig model that could be used to assess modeling approaches for whether the case will contain the fan blade and simulate the initial and post-containment interactions that occur during the three revolutions following blade release. Though the model includes the level of detail necessary to evaluate continued rotation and post-containment interactions between the fully bladed disk and fan case, it does not represent a fully installed engine and, therefore, would not have all the system dynamics characteristics necessary to assess full rundown. The initial containment event includes the initial blade release, release blade contact with the case, and release blade impact with the trail blade. The model uses a hard-mount fan bearing and operates below the first shaft bending critical; therefore, if running with the full fan (all blades represented), the model can assess initial contact (rubs) of the heavy side fan blades with the case, but if running with the counter-balanced three-blade fan, there will be no trail blade tip rubs—they are on the light side of the disk—unless a fragment from the release blade is caught between the blades and case. With the modeling assumptions and simplifications incorporated in this model, it is possible to capture the relevant physics of the fan blade-out event from release through initial and post-containment. The LS-DYNA was used as a nonlinear explicit dynamics finite element code for the simulations. Simulation results were consistent with reported results of actual FBO rig tests.
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