Understanding and Modelling the Mechanical and Corrosion Properties of 6056 for Aerospace Applications

Dif, Robert; Bes, Bernard; Ehrström, J. C.; Sigli, Christophe; Mayet, H.; Lassince, Ph.; Ribes, H.

doi:10.4028/www.scientific.net/msf.331-337.1613

Cited by 34 publications

(19 citation statements)

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“…The base material compositions are shown in Table 1. AA6056 is a new fusion weldable aerospace alloy that can be precipitation hardened to different strength levels [37,38]. Ti6Al4V is already a widely used alloy in aerospace.…”

Section: Methodsmentioning

confidence: 99%

Improving interfacial properties of a laser beam welded dissimilar joint of aluminium AA6056 and titanium Ti6Al4V for aeronautical applications

et al. 2010

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of the original manuscript:Vaidya, W.V.; Horstmann, M.; Ventzke, V.; Petrovski, B.; Kocak, M.; Kocik, R.; Tempus, G.: AbstractDissimilar welds of aluminium alloy AA6056 and titanium alloy Ti6Al4V were produced by a novel technique. AA6056 sheet was machined at one end to a U-slot shape, enabling the intake of the Ti6Al4V sheet. The Al-alloy U-slot was then butt welded by split laser beam without using a filling wire, thus making a weld by melting only the Al-alloy.Thereby the intermetallic brittle phase TiAl 3 formed at the weld interface and affected mechanical properties. As a continuation of the previous work, the joint design was modified by chamfering Ti6Al4V to reduce the formation of interfacial TiAl 3 . It is shown in this work how this seemingly insignificant joint modification has refined microstructure and increased hardness and strength. The most impressive feature was the improved resistance to fatigue crack propagation whereby the fracture type in the fusion zone of AA6056 adjacent to the weld interface changed from partially intercrystalline to completely transcrystalline. Possible metallurgical processes leading to the property improvements are discussed.

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Section: Methodsmentioning

confidence: 99%

Improving interfacial properties of a laser beam welded dissimilar joint of aluminium AA6056 and titanium Ti6Al4V for aeronautical applications

et al. 2010

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“…3,[41][42][43] Whereas AA2024 is likely to be prone to hot cracking by conventional fusion welding, 1 AA6056 is fusion weldable and is suitable for welded integral constructions. 3,[41][42][43] The sheets investigated were bare and had a nominal thickness of 6 mm (=B). The reason for using thicker sheets for this investigation was the sharp weld residual stress profile and the high relative peak stress value (190 MPa), which was about 90% weld material yield strength.…”

Section: E X P E R I M E N T a L P R O C E D U R Ementioning

confidence: 99%

“…Whereas the fatigue (S‐N) behaviour of laser beam welded Al‐alloys has received attention, 38,39 data on fatigue crack propagation are scarce 40 and are lacking completely for a crack perpendicular to the weld. Therefore, this work was undertaken to study the effect of crack orientation 22 , 24–34 and the distance between the notch tip and the weld 22,25,30,31 on fatigue crack propagation in a laser beam welded butt joint of the airframe Al‐alloy AA6056 41–43 …”

Section: Introductionmentioning

confidence: 99%

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Fatigue crack propagation into the residual stress field along and perpendicular to laser beam butt‐weld in aluminium alloy AA6056

Vaidya

Staron

Horstmann

2011

Fatigue Fract Eng Mat Struct

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A B S T R A C T Laser beam butt welds in Al-alloys are very narrow and are accompanied by steep residual stress gradients. In such a case, how the initial crack orientation and the distance of the notch tip relative to the weld affect fatigue crack propagation has not been investigated. Therefore, this investigation was undertaken with two different crack orientations: along the mid-weld and perpendicular to the weld. Fatigue crack propagation 'along the midweld' was found to be faster in middle crack tension specimens than in compact tension specimens. For the crack orientation 'perpendicular to the weld', the relative distance between the notch tip and the weld was varied using compact tension specimens to generate either tensile or compressive residual stresses near the notch tip. When tensile residual stresses were generated near the notch tip, fatigue crack propagation was found to be faster than that in the base material, irrespective of the difference in the initial residual stress level and whether the crack propagated along the mid-weld or perpendicular to the weld. In contrast, when compressive weld residual stresses were generated near the notch tip, fatigue crack arrest, slow crack propagation, multiple crack branching and out of plane deviation occurred. The results are discussed by considering the superposition principle and possible practical implications are mentioned.

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“…The material to be studied is an AA6156 Al-Si-Mg-Cu alloy, which has recently been developed for its combination of high strength aluminium and weldability, which makes it suitable for airframe applications [6]. AA6X56 Al-Si-Mg-Cu alloys display good weldability, low density, good corrosion resistance and equivalent mechanical properties to established damage tolerant alloys such AA2024, and hence may be considered as potential replacements.…”

Section: Introductionmentioning

confidence: 99%

Quench sensitivity of toughness in an Al alloy: Direct observation and analysis of failure initiation at the precipitate-free zone

et al. 2008

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Analysis of toughness in 6156 Al-Mg-Si-Cu sheet has been performed using enhanced Kahn tear tests on samples quenched at different rates. Crack initiation energies were hardly affected by changing water quench temperature from 20°C to 60°C; however a significant reduction was evident on air cooling. Crack propagation energy was reduced for both 60°C water quenched and air cooled materials. Observation of failure initiation through synchrotron radiation computed tomography (SRCT), for the 60°C water quenched material revealed failure ahead of the crack tip of grain boundaries oriented at 45° to the main loading axis and crack "tongues" extending into the material ahead of the main crack. Failure was predominantly intergranular. Fractographic assessment revealed predominantly voiding and shear decohesion in the 20°C water quenched material. With the aid of the new findings past models on the influence of precipitate free zone parameters on toughness have been revised.

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Understanding and Modelling the Mechanical and Corrosion Properties of 6056 for Aerospace Applications

Cited by 34 publications

References 0 publications

Improving interfacial properties of a laser beam welded dissimilar joint of aluminium AA6056 and titanium Ti6Al4V for aeronautical applications

Improving interfacial properties of a laser beam welded dissimilar joint of aluminium AA6056 and titanium Ti6Al4V for aeronautical applications

Fatigue crack propagation into the residual stress field along and perpendicular to laser beam butt‐weld in aluminium alloy AA6056

Quench sensitivity of toughness in an Al alloy: Direct observation and analysis of failure initiation at the precipitate-free zone

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