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

He, Qinggang; Hu, Xuan; Liu, Lulu; Hong, Weirong; Wu, Renyi

doi:10.1016/j.ast.2012.01.010

Cited by 52 publications

(18 citation statements)

References 22 publications

(27 reference statements)

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“…Johnson‐Cook material model was used to model the released blade in the containment test. The properties are listed in Table .…”

Section: Numerical Simulationmentioning

confidence: 99%

Containment capability of 2D triaxial braided tape wound composite casing for aero‐engine

Liu

et al. 2015

Polymer Composites

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Two-dimensional (2D) triaxial braided composites have been successfully used in aero-engine fan containment system for weight reduction. In the current study, blade containment tests were conducted on highspeed rotor spin tester to investigate the containment process and failure mechanisms of the composite casing. The composite casing was fabricated by winding 2D carbon fiber triaxial braided tape on a capstan into predetermined thickness and then infused with epoxy resin. Test results indicate that the damages to the containment casing increase significantly with the increase in blade released speed. In contained case, two damaged areas can be observed on the inner wall of the casing due to continued impacts of the released blade. However in uncontained case, a perforated hole was found in the casing. Finite element method was used to study this high-speed impact process using LS-DYNA. The influence of blade release speed and case thickness was also analyzed and found that the failure modes turns from tension to shear as the blade speed increases and casing is able to absorb more energy with increase in casing areal density. An empirical equation was derived for the triaxial braided composite casing, which can help in the design of the composite fan casing for aero-engine. POLYM.

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“…Johnson‐Cook material model was used to model the released blade in the containment test. The properties are listed in Table .…”

Section: Numerical Simulationmentioning

confidence: 99%

Containment capability of 2D triaxial braided tape wound composite casing for aero‐engine

Liu

et al. 2015

Polymer Composites

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“…x 16 High-pressure turbine disks, labyrinth disks, shafts, all levels of low vortex turbine disks and shafts low-cycle fatigue fracture 1 × 10 -6 5.56 × 10 -8…”

Section: Quantitative Analysis Of the Fault Treementioning

confidence: 99%

“…Uncontained engine failures were briefly reviewed in [15]. He et al [16] investigated an experimental and numerical study of an aero-engine fan blade/casing impact process. Noted that if there is no through-thickness crack in the bulge when the maximum interaction force arrives, the released blade will be contained within the casing.…”

Section: Introductionmentioning

confidence: 99%

“…For the components such as aero-engine rotors, it is difficult to estimate precise failure probabilities of individual components or failure events due to the insufficient available data and the variation in the estimated values. Fuzzy methods might be the only resort when very limited quantitative information is available for determining the parameters [16][17][18]. Fuzzy FTA has been used to predict reliability of the complex system in many fields [19][20], such as nuclear reactor, aerospace, petrochemical industry, pipelines, and so on.…”

Section: Introductionmentioning

confidence: 99%

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An Application of Fuzzy Fault Tree Analysis to Uncontained Events of an Areo-Engine Rotor

Huang²,

Zhu

et al. 2012

Int. J. Turbo Jet-Engines

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Fault tree analysis is an important tool for system reliability analysis. Fuzzy fault tree analysis of uncontained events for aero-engine rotor is performed in this article. In addition, a new methodology based on fuzzy set theory is also used in fault tree analysis to quantify the failure probabilities of basic events. The theory of fuzzy fault tree is introduced firstly. Then the fault tree for uncontained events of an aero-engine rotor is established, in which the descending method is used to determine the minimal cut sets. Furthermore, the interval representation and calculation strategy is presented by using the symmetrical L-R type fuzzy number to describe the failure probability, and the resulting fault tree is analyzed quantitatively in the case study.

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“…First, the release blade applies a large impact load on the containment system, which is generally a ring type of structure. During this phase of the impact event, depending upon the strength of the containment structure the release blade may or may not be able to punch a hole in the inner shell of the fan casing [9,10]. Most of the test data related to the full fan…”

Section: Introductionmentioning

confidence: 99%

Rotordynamic analysis of asymmetric turbofan rotor due to fan blade-loss event with contact-impact rub loads

Sinha

2013

Journal of Sound and Vibration

107

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Rotordynamic analysis of asymmetric turbofan rotor due to fan blade-loss event with contact-impact rub loads 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 a nonsymmetric rotor, the various terms of mass, gyroscopic and stiffness matrices also become timedependent. 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 support bearing system. 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 in the lateral out-of-plane direction as well as extensional degrees-of-freedom in the longitudinal spanwise direction of the blade airfoil. 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.1 Sunil K.Sinha GE Aviation, General Electric Company, Cincinnati, OH 45215, USA blade-loss event on an engine are of proprietary nature and are not currently available in public domain. Any experiment simulating blade-loss or tip-rub under controlled conditions [11] is not only extremely expensive, rather sometimes they involve serious risk to the safety of the rig and the test personnel as well. As such there is a scarcity of test data, to compare the results of any fan blade-out analytical model in the published literature. However there are ample information from the actual field events and their investigation reports [12], which provide the necessary evidence about the magnitude of the dynamic loads due to fan blade-loss under operating conditions of a turbofan engine.In the aftermath of blade-loss, the fan-disk rotating system starts moving off-center in the heavier side of the disk due to sudden large imbalance introduced on the rotor-shaft. This eccentric rotor no longer remains symmetric about its center of rotation, and the spinning of the asymmetric rotor introduces another set of nonlinearities. Recently an attempt has been made to analyze the free vibrational characteristics of a weakly asymmetric rotor [13]. The present work is the first paper of its kind in the field of rotormechanics which addresses the forced transient response of an asymmetric flexible bladed-rotor with also considering the casing rub-surface flexibility in its formulation while the outer fan-case is still effectively undeformed. The inner surface abradable flexibility is expressed by an equivalent term K Rub and its dynamic effect on the blade-tip is included using a penalty method approach.In this paper, we consider the transient dynamic response of a complete rotor system in a jet engine w...

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

Cited by 52 publications

References 22 publications

Containment capability of 2D triaxial braided tape wound composite casing for aero‐engine

Containment capability of 2D triaxial braided tape wound composite casing for aero‐engine

An Application of Fuzzy Fault Tree Analysis to Uncontained Events of an Areo-Engine Rotor

Rotordynamic analysis of asymmetric turbofan rotor due to fan blade-loss event with contact-impact rub loads

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