Numerical Analysis of Aircraft Engine Fan Blade-Out

Shmotin, Yuri N.; Габов, Д. Н.; Ryabov, A. A.; Kukanov, S. S.; Rechkin, V. N.

doi:10.2514/6.2006-4620

Cited by 20 publications

(11 citation statements)

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“…As shown in the Campbell Chart, the frequency margin between the second modal frequency (f2) and three times excitation was only 0.35% on working condition2 which may be dangerous of resonance. Bird-strike analysis was carried out with fluid-structure coupling method by LS-DYNA [6][7][8]. As shown in Fig.…”

Section: Enforcement Structure a Bmentioning

confidence: 99%

Topology Optimization Method Research on Hollow Wide-chord Fan Blade of a High-bypass Turbofan Engine

Meng¹,

Liao²,

Li³

et al. 2015

Procedia Engineering

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In order to realize lightweight design of a high-bypass turbofan engine, topology optimization of vacuum structure on a widechord fan blade was carried out regarding mixed loading conditions as static strength, vibration and bird-strike. Without changing the leaf shape, relationship of performance indices on vacuum structure was analyzed with simplified mechanical model of loading conditions. Topology optimization designs were carried out according to the highly sensitive conditions. Vacuum structure layout of fan blade was constructed integrating the major load transfer paths in each design proposal. Performance indices of different fan blade structures were compared. Result shown that optimized fan blade can realize lightweight as well as meeting the strength design requirement.

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Section: Enforcement Structure a Bmentioning

confidence: 99%

Topology Optimization Method Research on Hollow Wide-chord Fan Blade of a High-bypass Turbofan Engine

Meng¹,

Liao²,

Li³

et al. 2015

Procedia Engineering

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“…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].…”

Section: Introductionmentioning

confidence: 99%

“…Therefore, to make a deep investigation into the impact process and figure out the energy absorption mechanisms of the casing, ex- periments were conducted with the release speed of the fan blade high enough to perforate the casing. In order to simplify the analysis, a test with only one pair of blades opposite each other on the rotor is presented and multi-blade effects are not considered here although they have obvious influences on the impact process [7,20,25,26]. Numerical simulations with a sufficiently refined finite element model were also carried out.…”

Section: Introductionmentioning

confidence: 99%

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

Liu

et al. 2013

Aerospace Science and Technology

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“…Losing a blade from a turbofan rotor during its normal operation either due to bird-strike or due to fatigue is a real possibility, and as such it is a major safety concern in commercial civil aviation [1][2][3][4][5] . This possibility has led to the certification requirements of demonstrating the engine capability by running a successful Fan Blade-Out (FBO) test and being able to shut-it off successfully in 15 seconds.…”

Section: Introductionmentioning

confidence: 99%

Rotordynamic Analysis of Asymmetric Turbofan Rotor Due to Fan Blade-out Event with Contact-Impact Rub Loads

Sinha¹,

Ojha²

2012

53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

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Loss of a blade from a running turbofan rotor introduces not only huge imbalance into the dynamical system rather it makes the entire rotor asymmetric as well. In an asymmetric rotor, the various terms of mass, gyroscopic and stiffness matrices also become time-dependent. In this paper, all the dynamical equations include the effect of the rotary inertia and gyroscopic moments as a result of both shaft bending as well as staggered blades flexing in-and-out of the plane of the disk. The governing equations also account for internal material damping in the shaft and the external damping in the bearing. In addition to the unbalance load at the disk location, the shaft may also be subjected to a torque and axial forces. Here, the fan blades are modeled as pre-twisted thin shallow shells. They have coupled flexural-torsional motion as well as extensional degrees-of-freedom in the longitudinal spanwise direction of the blade. The effect of blade tip rub forces being transmitted to the shaft are analyzed in terms of the dynamic stability of the rotor, especially during windmilling.

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Numerical Analysis of Aircraft Engine Fan Blade-Out

Cited by 20 publications

References 0 publications

Topology Optimization Method Research on Hollow Wide-chord Fan Blade of a High-bypass Turbofan Engine

Topology Optimization Method Research on Hollow Wide-chord Fan Blade of a High-bypass Turbofan Engine

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

Rotordynamic Analysis of Asymmetric Turbofan Rotor Due to Fan Blade-out Event with Contact-Impact Rub Loads

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