A parametric study of bird strike on engine blades

Vignjević, Rade; Orłowski, Michał; Vuyst, Tom De; Campbell, J.

doi:10.1016/j.ijimpeng.2013.04.003

Cited by 67 publications

(66 citation statements)

References 7 publications

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“…The results showed that the curvature had more influence on the damaged area than preload. In the case of curved aero-engine components, Vignjevic et al [15] referring to the work of Miyachi et al [16] highlighted the importance of including pre-stress in fan-blades subject to impact noting that the final deformed shape of a fan-blade is sensitive to the magnitude of centrifugal force.…”

Section: Contents Lists Available At Sciencedirectmentioning

confidence: 99%

The influence of preload and boundary conditions on pre-damaged composite plates subject to soft-body impact

McCallum

2015

Materials & Design

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Section: Contents Lists Available At Sciencedirectmentioning

confidence: 99%

The influence of preload and boundary conditions on pre-damaged composite plates subject to soft-body impact

McCallum

2015

Materials & Design

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“…So far most of the experimental and numeric studies (Mccarthy et al, 2004a, Mccarthy et al, 2004b, Kermanidis et al, 2005, ThKermanidis et al, 2006, Hedayati and Ziaeirad, 2011, Chan et al 2012, Guida et al, 2012, Hassan et al 2016, Goraj and Kustron, 2018 think the impact location at the forefront of the leading edge is the critical impact location and do not to strictly analyze whether it is. Some researchers (Vignjevic et al 2013, Orlando et al, 2018 have noticed that the impact position had a great effect on birdstrike damage.…”

Section: Introductionmentioning

confidence: 99%

Analytical determination of the critical impact location for wing leading edge under birdstrike

Xue

Yao

et al. 2019

Lat. Am. j. solids struct.

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The wing leading edge is one of the aircraft structures which are vulnerable to birdstrike. Therefore, Federal Aviation Regulation has clear requirements of anti-birdstrike performance for wing leading edge. However, the impact location is not specified in aviation regulation. The forefront of the wing leading edge is selected as a critical location for the birdstrike in most researches. But the rationality of the selection is not given. This paper proposes an analytical method for determining the critical location that causes the most severe damage under impact due to birdstrike. The analysis is based on the concept of effective impact, i.e. the component of the bird velocity perpendicular to the surface of wing leading edge. A birdstrike model is established using Pam-crash and used to validate the analytical prediction. The numerical model proves its effectiveness compared to the birdstrike test. The residual compressive strength of the spar when the birdstrike is at the critical impact location determined by the proposed method is 44.5% of that at the traditional impact location. Moreover, the critical penetrating velocity of the traditional impact location is not the lowest. In other words, the traditional impact location is not the weakest. Airworthiness verification experiment of birdstrike on wing structure should pay attention to this aspect.

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“…Sinha et al (Sinha, Turner, & Jain, 2011) investigated the dynamic loading on turbofan blades due to bird strike, where rectangular composite panel was adopted for model validation. Vignjevic et al (Vignjevic, Orłowski, De Vuyst, & Campbell, 2013) performed a parametric study of bird strike on engine blades. Amoo (Amoo, 2013) conducted a review on the design and structural analysis of jet engine fan blade structures, including the impact dynamics analysis under bird strike.…”

Section: Introductionmentioning

confidence: 99%

“…the carbon-fiber composite fan blades of GEnx engine (The GEnx Commercial Aircraft Engine, 2019), as shown in Fig. 1), the most susceptible regions are the impact contact area and the leading edges of the blade (Vignjevic et al, 2013), which slice the bird projectile. From the geometrical profile of the blade, the "stagger angle ϕ(s)" at the impact location s due to pretwist in the airfoil can be expressed as ϕ(s) = ϕ0 + ϕ's (Sinha et al, 2011).…”

Section: Introductionmentioning

confidence: 99%

“…The impact region experiences the maximum Hugoniot pressure (pH), which is evaluated by pH = ρ0V0Vs, where ρ0 is the initial density, V0 is the initial velocity and Vs is the velocity of shock wave. Vignjevic et al (Vignjevic et al, 2013) presented that there was a strong influence of bird impact location on the extent of blade deformations. In terms of simplified blade-like components in experiments, however, the maximum impact damages are always located at the root of cantilever slender plates (L. Liu et al, 2018b), which is determined by the characteristic of the structure and loading types.…”

Section: Introductionmentioning

confidence: 99%

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Impact responses of slender composite plates for bird-strike testing of fan blades

Zhou

Sun

Huang

2019

Lat. Am. j. solids struct.

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Bird-strike failure of fan blades is one of the basic challenges for the safety of aircraft engines. Simplified slender blade-like plates are always used to evaluate the impact-induced damage mechanism at design stage. One undesirable issue is the failure at the root of clamped slender plates, which cannot recover the real case of twisted blades. For this purpose, three different strategies were exploited to obtain desirable deformation and stress responses, namely the impact location, additional weight, and the boundary condition. Numerical models of the simplified slender blade and the bird projectile were constructed by using finite element method (FEM) and smoothed particle hydrodynamics (SPH) approaches. The impact deformations and stress distributions were comparatively investigated in detail. The numerical results show that changing the boundary condition is the most effective way to obtain preferable impact responses for further failure analysis of real fan blades. Present results will be useful to future experimental design of simplified bird-strike testing.

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A parametric study of bird strike on engine blades

Cited by 67 publications

References 7 publications

The influence of preload and boundary conditions on pre-damaged composite plates subject to soft-body impact

The influence of preload and boundary conditions on pre-damaged composite plates subject to soft-body impact

Analytical determination of the critical impact location for wing leading edge under birdstrike

Impact responses of slender composite plates for bird-strike testing of fan blades

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