Abstract: Aluminum alloy products about 4 inches thick or less that possesses the ability to achieve, when solution heat treated, quenched, and artificially aged, and in parts made from the products, an improved combination of strength, fracture toughness and corrosion resistance, the alloy consisting essentially of: about 6.8 to about 8.5 wt. % Zn, about 1.5 to about 2.00 wt. % Mg, about 1.75 to about 2.3 wt. % Cu; about 0.05 to about 0.3 wt. % Zr, less than about 0.1 wt. % Mn, less than about 0.05 wt. % Cr, the balance Al, incidental elements and impurities and a method for making same. The instantly disclosed alloys are useful in making structural members for commercial airplanes including, but not limited to, upper wing skins and stringers, spar caps, spar webs and ribs of either built-up or integral construction.

Abstract: Aluminum alloy products about 4 inches thick or less that possesses the ability to achieve, when solution heat treated, quenched, and artificially aged, and in parts made from the products, an improved combination of strength, fracture toughness and corrosion resistance, the alloy consisting essentially of: about 6.8 to about 8.5 wt. % Zn, about 1.5 to about 2.00 wt. % Mg, about 1.75 to about 2.3 wt. % Cu; about 0.05 to about 0.3 wt. % Zr, less than about 0.1 wt. % Mn, less than about 0.05 wt. % Cr, the balance Al, incidental elements and impurities and a method for making same. The invention alloy is useful in making structural members for commercial airplanes including, but not limited to, upper wing skins and stringers, spar caps, spar webs and ribs of either built-up or integral construction. The invention alloy may be aged by 2 or 3 step practices while exceeding the SCC requirements for applications for which the invention alloy is primarily intended.

Abstract: An aluminum casting alloy, comprises, in weight percent, about 4-9% Zn; about 1-4% Mg; about 1-2.5% Cu; less than about 0.1% Si; less than about 0.12% Fe; less than about 0.5% Mn; about 0.01-0.05% B; less than about 0.15% Ti; about 0.05-0.2% Zr; about 0.1-0.5% Sc; no more than about 0.05% each miscellaneous element or impurity; no more than about 0.15% total miscellaneous elements or impurities.

Abstract: An assembly and method of making the assembly are provided. The assembly includes: a first 7xxx series aluminum alloy member comprising not greater than 1 wt. % Cu; a second 7xxx series aluminum alloy member comprising at least 1 wt % Cu; a joint between the first member and the second member that joins the first member to the second member; wherein the assembly comprises a stress corrosion cracking resistance for a marine environment.

Abstract: The present application discloses wrought 2xxx Al—Li alloy products that are work insensitive. The wrought aluminum alloy products generally include from about 2.75 wt. % to about 5.0 wt. % Cu, from about 0.2 wt. % to about 0.8 wt. % Mg, where the ratio of copper-to-magnesium ratio (Cu/Mg) in the aluminum alloy is in the range of from about 6.1 to about 17, from about 0.1 wt. % to 1.10 wt. % Li, from about 0.3 wt. % to about 2.0 wt. % Ag, from 0.50 wt. % to about 1.5 wt. % Zn, up to about 1.0 wt. % Mn, the balance being aluminum, optional incidental elements, and impurities. The wrought aluminum alloy products may realize a low strength differential and in a short aging time due to their work insensitive nature.

Abstract: The present invention provides an aluminum casting alloy with a composition including 4%-9% Si; 0.1%-0.7% Mg; less than or equal to 5% Zn; less than 0.15% Fe; less than 4% Cu; less than 0.3% Mn; less than 0.05% B; less than 0.15% Ti; and the remainder consisting essentially of aluminum. The inventive AlSiMg composition provides increased mechanical properties (Tensile Yield Strength and Ultimate Tensile Strength) in comparison to similiarly prepared E357 alloy at room temperature and high temperature. The present invention also includes a shaped casting formed from the inventive composition and a method of forming a shaped casting from the inventive composition.

Abstract: Aluminum alloy products about 4 inches thick or less that possesses the ability to achieve, when solution heat treated, quenched, and artificially aged, and in parts made from the products, an improved combination of strength, fracture toughness and corrosion resistance, the alloy consisting essentially of: about 6.8 to about 8.5 wt. % Zn, about 1.5 to about 2.00 wt. % Mg, about 1.75 to about 2.3 wt. % Cu; about 0.05 to about 0.3 wt. % Zr, less than about 0.1 wt. % Mn, less than about 0.05 wt. % Cr, the balance Al, incidental elements and impurities and a method for making same. The instantly disclosed alloys are useful in making structural members for commercial airplanes including, but not limited to, upper wing skins and stringers, spar caps, spar webs and ribs of either built-up or integral construction.

Abstract: The present invention provides an aluminum casting alloy with a composition including 4%-9% Si; 0.1%-0.7% Mg; less than or equal to 5% Zn; less than 0.15% Fe; less than 4% Cu; less than 0.3% Mn; less than 0.05% B; less than 0.15% Ti; and the remainder consisting essentially of aluminum. The inventive AlSiMg composition provides increased mechanical properties (Tensile Yield Strength and Ultimate Tensile Strength) in comparison to similiarly prepared E357 alloy at room temperature and high temperature. The present invention also includes a shaped casting formed from the inventive composition and a method of forming a shaped casting from the inventive composition.

Abstract: A recrystallized aluminum alloy having brass texture and Goss texture, wherein the amount of brass texture exceeds the amount of Goss texture, and wherein the recrystallized aluminum alloy exhibits at least about the same tensile yield strength and fracture toughness as a compositionally equivalent unrecrystallized alloy of the same product form and of similar thickness and temper.

Abstract: Aluminum alloy products about 4 inches thick or less that possesses the ability to achieve, when solution heat treated, quenched, and artificially aged, and in parts made from the products, an improved combination of strength, fracture toughness and corrosion resistance, the alloy consisting essentially of: about 6.8 to about 8.5 wt. % Zn, about 1.5 to about 2.00 wt. % Mg, about 1.75 to about 2.3 wt. % Cu; about 0.05 to about 0.3 wt. % Zr, less than about 0.1 wt. % Mn, less than about 0.05 wt. % Cr, the balance Al, incidental elements and impurities and a method for making same. The invention alloy is useful in making structural members for commercial airplanes including, but not limited to, upper wing skins and stringers, spar caps, spar webs and ribs of either built-up or integral construction. The invention alloy may be aged by 2 or 3 step practices while exceeding the SCC requirements for applications for which the invention alloy is primarily intended.

Abstract: An aluminum casting alloy, comprises, in weight percent, about 4-9% Zn; about 1-4% Mg; about 1-2.5% Cu; less than about 0.1% Si; less than about 0.12% Fe; less than about 0.5% Mn; about 0.01-0.05% B; less than about 0.15% Ti; about 0.05-0.2% Zr; about 0.1-0.5% Sc; no more than about 0.05% each miscellaneous element or impurity; no more than about 0.15% total miscellaneous elements or impurities.

Abstract: An aluminum casting alloy comprises, in weight percent: about 4-5% Zn; about 1-3% Mg; about 0-1% Cu; less than about 0.3% Si; less than about 0.12% Fe; less than about 0.5% Mn; about 0.01-0.05 wt % B; less than about 0.15% Ti; about 0.05-0.2% Zr; about 0.1-0.5% Ag; no more than about 0.05% each miscellaneous element or impurity; no more than about 0.15% total miscellaneous elements or impurities; balance aluminum. The alloy may advantageously be used in either T5 or T6 tempers.

Abstract: An aluminum alloy for shaped castings, the alloy having the following composition ranges in weight percent: about 6.0–8.5% silicon, less than 0.4% magnesium, less than 0.1% cerium, less than 0.2% iron, copper in a range from about 0.1% to about 0.5% and/or zinc in a range from about 1% to about 4%, the alloy being particularly suited for T5 heat treatment.

Abstract: The present invention provides an aluminum casting alloy with a composition including 4%-9% Si; 0.1%-0.7% Mg; less than or equal to 5% Zn; less than 0.15% Fe; less than 4% Cu; less than 0.3% Mn; less than 0.05% B; less than 0.15% Ti; and the remainder consisting essentially of aluminum. The inventive AlSiMg composition provides increased mechanical properties (Tensile Yield Strength and Ultimate Tensile Strength) in comparison to similiarly prepared E357 alloy at room temperature and high temperature. The present invention also includes a shaped casting formed from the inventive composition and a method of forming a shaped casting from the inventive composition.

Abstract: A heat treatable aluminum alloy for shaped castings includes from about 3.5-5.5% Zn, from about 1-3% Mg, about 0.05-0.5% Cu, and less than about 1% Si.

Abstract: A heat treatable aluminum alloy for shaped castings includes from about 3.5-5.5% Zn, from about 1-1.5% Mg, less than about 1% Si, less than about 0.30% Mn, and less than about 0.3% Fe and other incidental impurities.

Abstract: An aluminum alloy for shaped castings, the alloy having the following composition ranges in weight percent: about 6.0-8.5% silicon, less than 0.4% magnesium, less than 0.1% cerium, less than 0.2% iron, copper in a range from about 0.1% to about 0.5% and/or zinc in a range from about 1% to about 4%, the alloy being particularly suited for T5 heat treatment.