Robust Bird-Strike Modeling Based on ALE Formulation Using LS-DYNA

Goyal, Vijay K.; Huertas, Carlos A.; Leutwiler, Tomas; Borrero, Jose; Vasko, Thomas J.

doi:10.2514/6.2006-1759

Cited by 15 publications

(12 citation statements)

References 2 publications

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“…The LS-DYNA code is a general purpose FEM program that has been used extensively to model bird-strike problems, and it has proven itself to be a reliable tool for modeling blade damage. 10 The simulated bird-strike event mimics a typical bird-strike experimental test sequence in vacuum: spin the fan stage at a specified engine rotational speed, fire a bird at the fan stage, continue to spin the engine until the transient response of the blades subsides, slow the fan stage to zero engine rotational speed. In this process, the rotating fan stage is referred to as "hot" and differs from the non-rotating "cold" fan stage due to centrifugal effects.…”

Section: Fan Blade Geometrymentioning

confidence: 99%

“…9 Computational structural dynamics (CSD) based on the finite element method (FEM) are typically used to model the bird impact and resulting structural response since it can represent complex material behavior and non-linear geometric deformations. [10][11][12][13][14][15][16] Computational fluid dynamics (CFD) is required to accurately capture the complex flow phenomena associated with bird damaged turbofans. 17,18 Reliable CSD and CFD methods exist to compute the bird impact, structural dynamic response, and unsteady aerodynamic loads of a damaged fan blade.…”

Section: Nomenclaturementioning

confidence: 99%

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Aeroelastic Response of Bird-Damaged Fan Blades Using a Coupled CFD/CSD Framework

Muir

Friedmann

2014

55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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The aeroelastic response of a bird-damaged fan stage at the inlet of a high-bypass ratio turbofan engine is examined using a combined CFD/CSD model. ANSYS CFX is used for the computational fluid dynamic (CFD) calculations combined with the ANSYS Multifield (MFX) solver that couples ANSYS CFX with ANSYS Mechanical APDL to perform aeroelastic response calculations. The damaged fan sector consists of 5 blades that represent the geometry resulting from a numerical bird strike simulation. The forced response of the undamaged blades downstream of the damaged sector exhibits the highest level of structural response. The structural response of these undamaged blades is dominated by the first bending mode and increases in amplitude with time. The aeroelastic response shows a similar behavior, with the downstream undamaged blades exhibiting a growing structural response that is dominated by the first bending mode. The aeroelastic response of the damaged blades also contains contributions from the second torsion mode. An examination of the work exerted by the aerodynamic forces suggests that the growth in blade response for the upstream damaged blade is due to an aeroelastic behavior that may be indicative of a potential instability. Nomenclature D Number of RBF driver pointṡ mMass flow ratė m R Referred mass flow rate q m

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Section: Fan Blade Geometrymentioning

confidence: 99%

Section: Nomenclaturementioning

confidence: 99%

Aeroelastic Response of Bird-Damaged Fan Blades Using a Coupled CFD/CSD Framework

Muir

Friedmann

2014

55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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“…Numerical simulation is an important approach to investigate the birdstrike problem. Goyal et al (2006Goyal et al ( , 2013a modeled birdstrike based on the Lagrangian Formulation, ALE method and SPH using LS-DYNA and found that SPH could avoid distortion caused by large deformation, which was important in high-speed impact simulation. At present, most bird strike numerical studies adopt SPH method (Lavoie et al 2007).…”

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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“…Computational structural dynamics (CSD) based on the finite element method (FEM) are typically used to model the bird impact and resulting structural response since it can represent complex material behavior and nonlinear geometric deformations. [9][10][11][12][13][14][15] Computational fluid dynamics (CFD) is required to accurately capture the complex flow phenomena associated with bird damaged turbofans. [16][17][18][19] Reliable CSD and CFD methods exist to compute the bird impact, structural dynamic response, and unsteady aerodynamic loads of a damaged fan blade.…”

Section: Introduction Background and Objectivesmentioning

confidence: 99%

Forced and Aeroelastic Response of Bird-Damaged Fan Blades - A Comparison and Its Implications

Muir

Friedmann

2015

56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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The aeroelastic response of a bird-damaged fan stage at the inlet of a high-bypass ratio turbofan engine is examined using a combined computational fluid dynamics and computational structural dynamics framework. The damaged fan sector consists of 5 blades obtained from accurate numerical simulation of the bird impact. Forced and aeroelastic response calculations are performed and compared to assess the role of aeroelastic coupling. The calculations are performed at 100%, 75%, and 60% throttle setting to investigate the role of engine speed on the fan response. Results from the forced response and aeroelastic response calculation indicate that the undamaged blades opposite the damaged sector exhibit the highest level of structural response. Comparing the forced response with the aeroelastic response shows increased particiation of the higher structural modes, especially for the damaged blades, that grow in time or exhibit beating. Examination of the work performed by the aerodynamic forces suggests that the growth in blade response is due to aeroelastic phenomena and can cause a potential instability. The results illustrate the importance of aeroelastic effects when predicting the post bird strike fan response.

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Robust Bird-Strike Modeling Based on ALE Formulation Using LS-DYNA

Cited by 15 publications

References 2 publications

Aeroelastic Response of Bird-Damaged Fan Blades Using a Coupled CFD/CSD Framework

Aeroelastic Response of Bird-Damaged Fan Blades Using a Coupled CFD/CSD Framework

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

Forced and Aeroelastic Response of Bird-Damaged Fan Blades - A Comparison and Its Implications

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