Effect of Localized Corrosion on Fatigue–Crack Growth in 2524-T3 and 2198-T851 Aluminum Alloys Used as Aircraft Materials

Moreto, Jéferson Aparecido; Broday, Evandro Eduardo; Rossino, Luciana Sgarbi; Fernandes, Jorge Cruz; Filho, Waldek Wladimir Bose

doi:10.1007/s11665-018-3244-7

Cited by 28 publications

(9 citation statements)

References 16 publications

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“…It presents high damage-tolerance and excellent fatigue properties [1]. However, both the AA2024-T3 and AA2524-T3 alloys possess a large amount of intermetallic particles (IMCs) in their microstructure, and this is the main reason for their high susceptibility to localized corrosion such as pitting and stress corrosion cracking [3][4][5][6][7][8]. Localized corrosion in aluminium alloys uses to be caused by microgalvanic effects between IMCs and the matrix [7][8][9][10].…”

Section: Introductionmentioning

confidence: 99%

“…Very few studies can be found concerning AA2524 [4,[33][34][35][36][37], and only a few studies compare this alloy to the AA2024, focusing on its mechanical properties [2,38]. Although it is generally accepted that the localized corrosion caused by the IMCs is the nucleation site for other types of corrosion in high strength Al alloys [23,24], the role of the IMCs on these alloys' corrosion initiation has not been well established yet.…”

Section: Introductionmentioning

confidence: 99%

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Comparison of Corrosion Resistance of the AA2524-T3 and the AA2024-T3

Queiroz

Terada

Bugarin

et al. 2021

Metals

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The 2XXX Al alloys are characterized by their superior mechanical properties resulting from alloying elements and precipitation hardening treatments. The AA2524-T3 alloy was developed to replace the AA2024-T3 alloy in the aerospace industry. However, both alloys present many intermetallic particles (IMCs) in their microstructure, and this is the main reason for their high susceptibility to localized corrosion (such as pitting and stress corrosion cracking). Despite the similarities between these alloys (e.g., chemical composition and type of intermetallics) the literature comparing their properties is scarce and focuses mainly on their mechanical properties, not their corrosion resistances. In this investigation, the corrosion resistance of the AA2524-T3 alloy was compared to the AA2024-T3 alloy. The microstructure of both alloys was analyzed by Scanning Electron Microscopy before and after immersion in the test electrolyte, and the number and area fraction of intermetallics of each alloy was determined. The corrosion resistance of both alloys was monitored as a function of exposure time by electrochemical impedance spectroscopy and the results were fitted using electrical equivalent circuits. The AA2524-T3 alloy presented not only higher impedance values but also less corroded areas than the AA2024-T3 alloy.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Comparison of Corrosion Resistance of the AA2524-T3 and the AA2024-T3

Queiroz

Terada

Bugarin

et al. 2021

Metals

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“…[6][7][8][9][10][11][12][13][14][15] Some works showed that these attacks are harmful to aircraft structures. [16][17][18][19] Consequently, many research studies have been developed to understand the influence of Al alloys' microstructural features in the propagation of these kinds of corrosion morphologies. [20][21][22][23][24][25][26] The effects of the fabrication process [27][28][29][30][31] and heat treatment [32][33][34][35][36][37][38][39][40][41] on the microstructural features, and thus on the corrosion behavior are commonly investigated.…”

Section: Introductionmentioning

confidence: 99%

Exfoliation and intergranular corrosion resistance of the 2198 Al–Cu–Li alloy with different thermomechanical treatments

Araujo

Milagre

Ferreira

et al. 2020

Materials & Corrosion

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In this study, the resistance to exfoliation and intergranular corrosion (IGC) of the 2198 Al-Cu-Li alloy submitted to different thermomechanical treatments (T3, T8, and T851) was investigated. The tests were carried out following the standard practices, ASTM G34-18 and ASTM G110-15, respectively. All the tested alloys showed susceptibility to exfoliation and some alloys showed susceptibility to IGC, but the artificially aged alloys presented a higher tendency to exfoliation. The extensive hydrogen evolution reaction (HER) was observed on the surfaces of artificially aged alloys when immersed in the EXCO solution. The HER resulted in an increase in solution pH with the time of immersion. Also, the weight losses related to the artificially aged alloys were higher than that of the naturally aged ones. The T8 treatment was the only condition that resulted in susceptibility to both, intergranular and transgranular corrosion, whereas the T851 treatment did not show IGC susceptibility, only transgranular corrosion. Finally, the 2198-T3 condition showed the highest corrosion resistance among the thermomechanical treatments tested. The results of the 2198 alloy subjected to various treatments were compared with that of the 2024-T3 alloy. This last alloy showed higher resistance to exfoliation and IGC as compared with the 2198 alloy.

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Section: Introductionmentioning

confidence: 99%

“…The AA2524-T3 (Solution Heat Treated and Cold Worked) alloy produced by ALCOA may be used as fuselage skin material and represents a potential replacement for the AA2024 alloy, widely used by the aircraft industry [11][12][13][14][15] . Recent studies 11,14,10 have shown that the fatigue behaviour of the AA2524-T3 alloy depends on experimental conditions (eg, applied stress, loading rate, environment as well as the crystalline orientation of the sample). With regarding to the electrochemical tests, it was possible to verify that the corrosion potential (E corr ) and the pit nucleation potential (E pit ) values are quite similar and the variation in the ratio of passive/active areas and/or cathode/anode, which may be related to the presence of different types of IMs 12,15 .…”

Section: Introductionmentioning

confidence: 99%

Corrosion and Micro-abrasive Wear Behaviour of 2524-T3 Aluminium Alloy with PAni-NPs/PSS LbL Coating

et al. 2019

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In this paper, we present an alternative method to obtain thin films for coating protection on the surface of the AA2524-T3 Al-alloy by using the Layer-by-Layer (LbL) technique. The LbL films were fabricated by alternated immersion of the Al-alloy into a poly(styrene sulfonate) (PSS) and polyaniline nanoparticles (PAni-NPs) solutions, obtaining a PAni-NPs/PSS bilayer architecture. The LbL films were characterized by ultraviolet-visible spectroscopy (UV-Vis), Fourier-transform infrared spectroscopy (FTIR), atomic force microscopy (AFM), electrochemical and micro-abrasive wear tests. The results show that the number of bilayers promotes shifts to less negative potentials, indicating an optimized system, in which the best performance was observed for a 15-bilayer PAni/PSS LbL film. The pitting potential (E pit) values shifted 130 mV (from-610 mV to-480 mV) in comparing a bare Al-alloy. The predominantly wear mechanism for AA2524-T3 with PAni-NPs/PSS bilayers was scratching whereas for the bare material there was an equivalence between scratching and rolling mechanisms. The results proved that the incorporation of PAni-NPS by the LbL method may be propitious as protective coating against corrosion in AA2524-T3 alloy.

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Effect of Localized Corrosion on Fatigue–Crack Growth in 2524-T3 and 2198-T851 Aluminum Alloys Used as Aircraft Materials

Cited by 28 publications

References 16 publications

Comparison of Corrosion Resistance of the AA2524-T3 and the AA2024-T3

Comparison of Corrosion Resistance of the AA2524-T3 and the AA2024-T3

Exfoliation and intergranular corrosion resistance of the 2198 Al–Cu–Li alloy with different thermomechanical treatments

Corrosion and Micro-abrasive Wear Behaviour of 2524-T3 Aluminium Alloy with PAni-NPs/PSS LbL Coating

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