Blade containment evaluation of civil aircraft engines

Yang, Bin

doi:10.1016/j.cja.2012.12.001

Cited by 43 publications

(20 citation statements)

References 7 publications

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“…2 Because of the serious destruction of FBO incident, the authorities require the manufacturers to carry out a successful FBO test, which is very costly and time consuming to ensure the strength and integrity of engines. 3,4 Therefore, in order to predict the complicated vibration response of the whole aero-engine with blade off, it is necessary to develop the whole aero-engine model and conduct analytical and numerical simulations, which reduces the test cost and guides the structural safety design.…”

Section: Introductionmentioning

confidence: 99%

Prediction of transient vibration response of dual-rotor-blade-casing system with blade off

Wang

Liu

Jiang

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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Fan blade off occurring in a running rotor of the turbofan engine dual-rotor system will cause a sudden unbalance and inertia asymmetry, which results in large impact load and consequently induces the rubbing between blade and casing. In order to reveal the transient dynamic response characteristics of actual aero-engine when fan blade off event occurs, the dynamic model of dual-rotor-blade-casing system is developed, in which the distribution characteristics of the stiffness and mass, the load transfer, and the coupling effects of dual-rotor and casing are included. Considering several excitations caused by blade off, the physical process and mechanical characteristics of the fan blade off event are described qualitatively. Considering that only the casing acceleration signal can be used for condition monitoring in actual aero-engine, the transient response including rotor vibration displacement and casing vibration acceleration during the instantaneous status are obtained. Due to the time-varying and highly nonlinear characteristics of vibration responses, frequency slice wavelet transform is employed to isolate the vibration signal features. The results show that the impact load induced by the sudden imbalance causes significant increase of vibration amplitude. The rubbing action between blade and rotor will impose constraint effects on the rotor, which decreases the transient vibration amplitude. The inertia asymmetry has a big impact on the transient response. The vibration characteristics of casing acceleration under blade off are similar to those of rotor displacement, while casing acceleration response attenuates to stable value faster and is more sensitive to high-frequency components of vibration.

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Section: Introductionmentioning

confidence: 99%

Prediction of transient vibration response of dual-rotor-blade-casing system with blade off

Wang

Liu

Jiang

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Primary damage occurs when the liberated blade hits the casing. Moreover, if the case could not contain the blade, the fuselage would then suffer serious safety accidents [8,9]. Secondary damage is caused by the destruction of engine structure related to huge imbalance loads caused by the released blade.…”

Section: Introductionmentioning

confidence: 99%

Response of Aeroengine with Fusing Design Suffering FBO

Chen

Liu

et al. 2019

International Journal of Aerospace Engineering

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The loss of fan blades in an aeroengine, or fan-blade out (FBO), is a type of accident that causes a sudden imbalance and large impact load, which leads to complex vibration of a system. To conduct a dynamic analysis of an aeroengine rotor system is an important requirement for relevant departments. The purpose of this paper is to study the dynamic response of a complex dual-rotor system suffering FBO events and the protective effect of the fusing structure on the system. The dynamic model of an aeroengine dual-rotor system is established, and the response of the rotor system is obtained by calculation and analysis. The rear support bearing of the fan has a high reaction force, which may lead to bearing failure. The mechanism of a fusing structure is analyzed, and the results show that the sudden imbalance will produce impact loads on the rotor, resulting in a sharp increase in the vibration amplitude and reaction force, and then, attenuation to steady state. The fusing structure can reduce the amplitude of steady-state rotor vibration and reaction force on the support bearings. However, the transient response of the rotor will increase because of the sudden change in support stiffness.

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“…In recent years and due to financial and irrecoverable life damages, prevention of failure in rotating machines is vitally important. Many researches, by introducing the phenomenon of high cycle fatigue as the main cause of failure, have been determined blade as a critical component of machines [1][2][3][4][5][6]. Among researches performed by studying blade vibration under different condition [7][8][9][10], which have been provided diverse methods to reduce blade vibrations [11][12][13][14], centrifugal pendulum vibration absorber is a proper way to suppress blade vibration especially in resonance condition [15,16].…”

Section: Introductionmentioning

confidence: 99%

Optimum Design of Damped Vibration Absorber for Rotationally Periodic Structures

2016

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In this study, a damped centrifugally driven order-tuned vibration absorber designed for vibration reduction in rotating flexible structures, bladed disk assemblies and blisk such as turbine blades, compressor and fan blades, pump and helicopter rotor blades etc. during steady operation with constant speed and under engine order excitation (e.o excitation). Effect of mistuning is disregarded. System is assumed with fully cyclic symmetry. The disk is imposed as being rigid. Elastic behavior for blades is supposed. A model with two degree of freedom is extracted for the blades. Each blade is fitted with nominally identical damped order-tuned vibration absorber that is moved in a circular path. Aerodynamic damping and coupling effects between the blades are considered. Optimal values of parameters of the absorber, to suppress blade vibration especially in resonance condition, are derived by Genetic Algorithm (GA) and MATLAB software. H2 optimization criterion is used. It is observed that with the deviation of each parameter from the optimal condition, the system response is moved away from the ideal design situation and all of the absorbers’ design parameters have definite effects on the system frequency response and on the dissipated energy during vibration. Therefore, ignorance of the effect of one of those parameters (which was happened in literature) affected the system response completely. Literature is reviewed and validity of the results is confirmed.

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Blade containment evaluation of civil aircraft engines

Cited by 43 publications

References 7 publications

Prediction of transient vibration response of dual-rotor-blade-casing system with blade off

Prediction of transient vibration response of dual-rotor-blade-casing system with blade off

Response of Aeroengine with Fusing Design Suffering FBO

Optimum Design of Damped Vibration Absorber for Rotationally Periodic Structures

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