An Efficient Multi-Disciplinary Simulation of Engine Fan-Blade Out Event Using MD Nastran

Bi-objective optimization of pylon-engine-nacelle assembly: weight vs. tip clearance criterion

“…This would make the overall simulation of the whole FBO difficult to achieve with one specified type of numerical scheme. To overcome such difficulties, MD NASTRAN recently offered the capability to mix different levels of models and different numerical schemes for the same time simulation of FBO event [11].…”

“…As described in [11], a full FBO analysis requires three consecutive steps 1. Pre-stress step: Fan blade pre-stresses due to thrust, gravity and gyroscopic effects are computed.…”

“…However, in the related literature, these two different analyses are often treated separately, see [15], [30] for the first analysis and [12] for the second. In [11], the authors offer a solution to bridge the gap between the two types of analysis by mixing different models and numerical schemes while keeping proprietary information confidential.…”

“…Our main objective is to provide a realistic optimization process of engine installation taking into account several phenomena and criteria using middle-range fidelity numerical models. By 'middle-range fidelity models', we mean that we do not use a very detailed finite element model of the engine as the ones used by aero-engine manufacturers (with several millions degrees of freedom (DoF)) neither do we use a very simple model of the engine (as the ones typically used by airframe manufacturers) with several thousands DoF, as explained in [1] and [11]. Thanks to the context of this study, we have the opportunity to use not only a relatively sophisticated finite element model of the engine (several hundred thousands DoF) but also preliminary sizing models for pylon and nacelle.…”

Perforation of aero-engine fan casing by a single rotating blade

“…Two major impact regions on the containment ring were found both in experimental results and numerical simulations and the second one was more seriously damaged. In the last 5 years, an analysis of the aero-engine fan blade-out event was also conducted by Cosme et al [7], Shmotin et al [26], Heidari et al [14], Sinha et al [27], and Jain [15]. Most of their emphasis was on the modeling methodology and structure dynamics of the fan blade-out event, and all the cases studied were that the fan casing was not perforated and successfully contained the released blade, complying with the containment requirements specified in the regulations [4,5,8,11,22].…”