A turbofan nonlinear dynamic model is described in the paper. It has been developed for the computation of loads in the engine frame after fan blade-out (FBO) event. The model includes reduced dynamic finite element models of rotors and casings and also nonlinear elements for simulation of "rotor-casing" contact interactions. Thorough attention has been paid to mounts modeling with possible mechanisms taken into account. The engine dynamic behavior during its rotors deceleration to the autorotation mode after the FBO event has been simulated for the following two forward mount arrangement variants: fastening to the inner part of the intermediate casing; fastening to the outer part of the intermediate casing. The effect of load reduction device (LRD)-special elements which are introduced to fan supports, destroyed under certain force and don't transfer improper loads to the engine casing system after the FBO event, has been studied. The analysis of maximum loads on engine mounts has been performed for the two listed design variants for both cases: with and without an LRD in fan supports.
This paper proposes an approach to construct a nonlinear dynamic model of a whole turbofan engine using the static condensation technique. Nonlinear dynamic behavior of the engine is described by a matrix differential equation, where the right side of the equation represents unbalance load and contact loads between the blades and casings, low-pressure (LP) shaft and high-pressure shaft. Elements of the matrices are calculated by static condensation of three-dimensional finite element models of rotors, casings, engine mounts, and wing attachment system. On the basis of the proposed approach, a model of the entire engine was constructed. The model considered contact interactions as well as effects associated with both instantaneous application of the unbalance load and the passage of the LP rotor through the critical rotational speed during the deceleration phase. The model has a modular structure that allows for the easy replacement of individual components and analysis of the various engine structural frame options. The results of engine structural frame load calculations after a fan blade-out event and during deceleration of the rotors to windmill mode are presented in this paper. In addition, the influence of the flexibility of fan supports, blade wheel nonlinear radial stiffness, and slowdown rates of rotors on load magnitudes are analyzed.
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