MATEC Web Conf.
Volume 326, 2020The 17th International Conference on Aluminium Alloys 2020 (ICAA17)
|Number of page(s)||9|
|Section||Durability: Fatigue, Fracture, Corrosion & Surface Treatments|
|Published online||05 November 2020|
Comparison of long-term natural aging to artificial aging in Duralumin
1 CEMES, CNRS, Université de Toulouse, 29 rue Jeanne Marvig, BP 94347 31055 Toulouse Cedex 4, France
2 CIRIMAT, Université de Toulouse, CNRS, INP Toulouse, UPS, 4 allée Emile Monso, 31030 Toulouse, France
* Corresponding author: firstname.lastname@example.org
The understanding of long-term aging of aeronautical materials, in particular aluminium alloys used in the fuselage and structure of aircraft is of extreme importance for airline fleets. In this work, a plate from an old aircraft (Breguet) was retrieved and studied in terms of microstructure and mechanical properties. A comparison was made between this naturally-aged alloy and a modern alloy on which different artificial aging conditions were applied. The old alloy exhibits a precipitation of θ-Al2Cu at grain boundaries and of Ω-Al2Cu on dispersoids. This non-expected nanostructure for an alloy in T4 state was attributed to the heat that the plate experienced during the aircraft cycles. However, it is shown that this aging is reversible (after a solution treatment). Moreover, the very long time of outdoors exposure seems to have caused intergranular corrosion causing the early failure during tensile tests on some of the specimens. The artificial aging (low temperature, 100°C for up to 10,000h) applied on the modern 2017A alloy did not allow to reproduce the nanostructure of the old plate, meaning that isothermal conditions for artificial aging might not be appropriate in this case.
© The Authors, published by EDP Sciences, 2020
This is an Open Access article distributed under the terms of the Creative Commons Attribution License 4.0, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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