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AssigneeAluminum Company of America
InventorsWarren H. Hunt, Jr., James T. Staley, David A. Lukasak, David B. Reiser, Rebecca K. Wyss, Lynette M. Angers
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An alloy product having improved combinations of strength, density, toughness and corrosion resistance, said alloy product consisting essentially of about 7.6 to 8.4% zinc, about 1.8 to 2.2% magnesium, about 2 to 2.6% copper and at least one element selected from zirconium, vanadium and hafnium present in a total amount not exceeding about 0.5%, preferably about 0.05 to 0.25% zirconium, the balance aluminum and incidential elements and impurities. The alloy product, suitable for aerospace applications, exhibits high yield strength, at least about 10% greater yield strength than its 7X50-T6 counterpart, with good toughness and corrosion resistance properties typically comparable to or better than those of its 7X50-T76 counterpart. Upper wing members made from this alloy typically have a yield strength over 84 ksi, good fracture toughness and an EXCO exfoliation resistance level of "EC" or better, typically "EB".
An aluminum alloy product having good strength along with good toughness or corrosion resistance, or both, said alloy consisting essentially of about, by weight, 7.6 to about 8.4% zinc, about 1.8 to about 2.2% magnesium, about 2.1 to about 2.6% copper and at least one element present in an amount not exceeding about 0.5%, said element selected from zirconium, vanadium and hafnium, the balance substantially aluminum and incidental elements and impurities.
An alloy product having good yield strength together with good toughness or corrosion resistance, or both, said alloy consisting essentially of, by weight, about 7.6 to about 8.4% zinc;
An aluminum alloy product having good strength along with good toughness or corrosion resistance, or both, said alloy consisting essentially of about, by weight, 7.6 to about 8.4% zinc, about 1.8 to about 2.2% magnesium, about 2.1 to about 2.6% copper, about 0.03 to about 0.3% zirconium, the balance substantially aluminum and incidental elements and impurities.
An alloy product suitable for aerospace applications and having good strength and toughness combined with an EXCO exfoliation corrosion resistance level of "EC" or better, said product comprising an alloy consisting essentially of, by weight, about 7.8 to about 8.2% zinc, about 1.8 to about 2.1% magnesium, about 2.2 to about 2.5% copper, about 0.03 to about 0.25% zirconium, the balance substantially aluminum and incidental elements and impurities.
A plate product having a cross-sectional thickness between about 0.3 and 3 inches, about 84 ksi or better minimum yield strength, a Kr25 fracture toughness of about 70 ksi-in.sup.1/2 or better, and an EXCO exfoliation corrosion resistance level of "EC" or better, said plate product comprising an alloy consisting essentially of about 7.6 to about 8.4% zinc, about 1.8 to about 2.2% magnesium, about 2.1 to about 2.6% copper, about 0.03 to about 0.25% zirconium, the balance substantially aluminum and incidental elements and impurities.
An extrusion having a cross-section including a thickness less than about 3 inches, yield strength greater than 86 ksi, a Kr25 fracture toughness of about 70 ksi-in.sup.1/2 or better, and an EXCO exfoliation resistance level of "EC" or better, said extrusion comprising an alloy consisting essentially of, by weight, about 7.6 to about 8.4% zinc, about 1.8 to about 2.2% magnesium, about 2.1 to about 2.6% copper, about 0.03 to about 0.2% zirconium, the balance substantially aluminum and incidental elements and impurities.
An aerospace structural member having a yield strength of at least 84 ksi, good fracture toughness and an EXCO exfoliation resistance level of "EC" or better, said structural member comprising an alloy consisting essentially of, by weight, about 7.6 to about 8.4% zinc, about 1.8 to about 2.2% magnesium, about 2.1 to about 2.6% copper, about 0.03 to about 0.3% zirconium, not more than about 0.2% iron and not more than about 0.2% silicon, the balance substantially aluminum and incidental elements and impurities.
A wrought alloy product having good strength, toughness and corrosion resistance properties, said product comprising an alloy consisting essentially of, by weight, about 7.6 to about 8.4% zinc, about 1.8 to about 2.2% magnesium, about 2.2 to about 2.6% copper, and about 0.03 to about 0.2% zirconium, the balance substantially aluminum and incidental elements and impurities.
An alloy product suitable for aerospace applications and having a minimum yield strength of at least about 85 ksi and good toughness and an EXCO exfoliation corrosion resistance level of "EC" or better, said alloy product comprising an alloy consisting essentially of about 7.8 to about 8.2% zinc, about 1.8 to about 2.1% magnesium, about 2.2 to about 2.5% copper, about 0.03 to about 0.25% zirconium, the balance substantially aluminum and incidental elements and impurities.
In an airplane, an assembly or subassembly comprising an aluminum alloy member, said alloy consisting essentially of about, by weight, 7.6 to about 8.4% zinc, about 1.8 to about 2.2% magnesium, about 2.1 to about 2.6% copper, about 0.03 to about 0.3% zirconium, the balance substantially aluminum and incidental elements and impurities.
In an airplane, an assembly or subassembly comprising an aluminum alloy wing member, said alloy consisting essentially of about, by weight, 7.6 to about 8.4% zinc, about 1.8 to about 2.2% magnesium, about 2.1 to about 2.6% copper, about 0.03 to about 0.3% zirconium, the balance substantially aluminum and incidental elements and impurities.
An airplane assembly or subassembly comprising an aluminum alloy member, said alloy consisting essentially of about, by weight, 7.6 to about 8.4% zinc, about 1.8 to about 2.2% magnesium, about 2.1 to about 2.6% copper, about 0.03 to about 0.3% zirconium, the balance substantially aluminum and incidental elements and impurities, said member having a longitudinal yield strength of at least 84 ksi and an EXCO exfoliation corrosion resistance of "EC" or better and good fracture toughness.
An airplane assembly or subassembly comprising an aluminum alloy member, said alloy consisting essentially of about, by weight, 7.6 to about 8.4% zinc, about 1.8 to about 2.2% magnesium, about 2 to about 2.6% copper, about 0.03 to about 0.3% zirconium, the balance substantially aluminum and incidental elements and impurities, said member having a longitudinal yield strength greater than 84 ksi together with good fracture toughness or good corrosion resistance, or both.
An airplane assembly or subassembly comprising an aluminum alloy wing member, said alloy consisting essentially of about, by weight, 7.6 to about 8.4% zinc, about 1.8 to about 2.2% magnesium, about 2.1 to about 2.6% copper, about 0.03 to about 0.3% zirconium, the balance substantially aluminum and incidental elements and impurities, said wing member having a longitudinal yield strength of at least 84 ksi and an EXCO exfoliation corrosion resistance of "EC" or better and good fracture toughness.
An airplane assembly or subassembly comprising an aluminum alloy wing member, said alloy consisting essentially of about, by weight, 7.6 to about 8.4% zinc, about 1.8 to about 2.2% magnesium, about 2 to about 2.6% copper, about 0.03 to about 0.3% zirconium, the balance substantially aluminum and incidental elements and impurities, said wing member having a longitudinal yield strength of at least 84 ksi together with good fracture toughness or good corrosion resistance, or both.
In an airplane, as assembly or subassembly comprising a member comprising an aluminum alloy, said alloy consisting essentially of about, by weight 7.6 to about 8.4% zinc, about 1.8 to about 2.1% magnesium and about 2.2 to about 2.6% copper, about 0.03 to about 0.3% zirconium, the balance substantially aluminum and incidental elements and impurities.
Dependencies are inferred from the claim text.