Vanadium-free aluminum alloy suitable for sheet and plate...

C - Chemistry – Metallurgy – 22 – C

Patent

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C22C 21/12 (2006.01) C22C 21/16 (2006.01) C22C 21/18 (2006.01) C22F 1/057 (2006.01)

Patent

CA 2281640

There is claimed a sheet or plate structural member suitable for aerospace applications and having improved combinations of strength and toughness. The member is made from a substantially vanadium-free aluminum-based alloy consisting essentially of: about 4.85-5.3 wt.% copper, about 0.5-1.0 wt.% magnesium, about 0.4-0.8 wt.% manganese, about 0.2-0.8 wt.% silver, about 0.05- 0.25 wt.% zirconium, up to about 0.1 wt.% silicon, and up to about 0.1 wt.% iron, the balance aluminum, incidental elements and impurities, the Cu:Mg ratio of said alloy being between about 5 and 9, and more preferably between about 6.0 and 7.5. The invention exhibits a typical tensile yield strength of about 77 ksi or higher at room temperature and can be processed into various lower wing members or into the fuselage skin of high speed aircraft.

On décrit un élément de structure à base de feuille ou de tôle qui convient pour des applications aérospatiales et apporte des améliorations alliant résistance et robustesse. Ledit élément est fabriqué à partir d'un alliage d'aluminium sensiblement exempt de vanadium, constitué essentiellement d'environ 4,85 à 5,3 % en poids de cuivre, 0,5 à 1,0 % en poids de magnésium, 0,4 à 0,8 % en poids de manganèse, 0,2 à 0,8 % en poids d'argent, 0,05 à 0,25 % en poids de zirconium, jusqu'à 0,1 % de silicium, et jusqu'à 0,1 % de fer, de l'aluminium d'équilibrage, d'éléments et impuretés accessoires. Dans ledit alliage, le rapport entre le cuivre et le magnésium est compris entre environ 5 et 9, mais de préférence entre environ 6,0 et 7,5. La structure de l'invention présente une limite conventionnelle d'élasticité d'environ 77 ksi ou plus à température ambiante, et peut être utilisée pour confectionner divers éléments inférieurs de voilure ou le revêtement de fuselage d'un avion à vitesse élevée.

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