Abstract: Methods of making new 2xxx aluminum alloy sheet products are disclosed. In one approach, a method comprises artificially aging a 2xxx aluminum alloy in at least two-steps. In one embodiment, the first aging step comprises first aging a 2xxx aluminum alloy at a first temperature of from 300° F. to 450ºF and for a first aging time of from 4 to 120 hours, and second aging the 2xxx aluminum alloy at a second temperature for a second aging time of from 30 minutes to 120 hours, wherein the second temperature is from 20° F. to 150° F. lower than the first temperature. The new two-step artificial aging step may facilitate an improved combination of properties, such as an improved combination of two or more of strength, ductility, fracture toughness, and corrosion resistance.

Abstract: Disclosed are improved thick wrought 7xxx aluminum alloy products, and methods for producing the same. The new 7xxx aluminum alloy products may realize an improved combination of properties, such as an improved combination of two or more of environmentally assisted crack resistance, strength, elongation, and fracture toughness, among other properties. The new 7xxx aluminum alloy products may include 5.5-6.5 wt. % Zn, 1.3-1.7 wt. % Mg, and 1.7-2.3 wt. % Cu.

Abstract: New 2xxx aluminum alloys having are disclosed. The new 2xxx aluminum alloys generally include 2.5-3.9 wt. % Cu, 0.82-1.20 wt. % Li, 0.5-2.0 wt. % Zn, 0.10-0.60 wt. % Mn, 0.05-0.35 wt. % Mg, from 0.05 to 0.50 wt. % of at least one grain structure control element, wherein the at least one grain structure control element is selected from the group consisting of Zr, Sc, Cr, V, Hf, other rare earth elements, and combinations thereof, up to 0.22 wt. % Ag, up to 0.15 wt. % Fe, up to 0.12 wt. % Si, and up to 0.15 wt. % Ti, the balance being aluminum, incidental elements and impurities. The new 2xxx aluminum alloys may realize an improved combination of two or more of strength, fracture toughness, elongation, and corrosion resistance.

Abstract: New 7xxx aluminum alloys are disclosed. The new 7xxx aluminum alloys generally include from 0.05 to 1.0 wt. % Ag. In one approach, a new 7xxx aluminum alloy includes from 0.05 to 1.0 wt. % Ag, from 5.5 to 9.0 wt. % Zn, from 1.2 to 2.6 wt. % Cu, from 1.3 to 2.5 wt. % Mg, up to 0.60 wt. % Mn, up to 1.0 wt. % of at least one grain structure control material, wherein the at least one grain structure control material is selected from the group consisting of Zr, Cr, V, Hf, other rare earth elements, and combinations thereof, up to 0.30 wt. % Fe, up to 0.30 wt. % Si, up to 0.15 wt. % Ti, not greater than 0.08 wt. % Sc, and not greater than 0.05 wt. % Li, the balance being aluminum, optional incidental elements and impurities.

Abstract: New 2xxx aluminum alloys are disclosed. The new 2xxx aluminum alloys generally include from 0.08 to 0.20 wt. % Ti. The new 2xxx aluminum alloys may realize an improved combination of two or more of strength, fracture toughness, elongation, and corrosion resistance, for instance.

Abstract: Disclosed are improved thick wrought 7xxx aluminum alloy products, and methods for producing the same. The new 7xxx aluminum alloy products may realize an improved combination of environmentally assisted crack resistance and at least one of strength, elongation, and fracture toughness, among other properties. The new 7xxx aluminum alloy products generally include high amounts of manganese. The new 7xxx aluminum alloy products thus generally include from 0.15 to 0.50 wt. % Mn in combination with 5.5-7.5 wt. % Zn, 0.95-2.20 wt. % Mg, and 1.50-2.40 wt. % Cu.

Abstract: Improved wrought 7xxx aluminum alloy products are disclosed. The improved wrought 7xxx aluminum alloy products generally include 6.0-10.0 wt. % Zn, 1.4-2.2 wt. % Mg, 1.3-2.5 wt. % Cu and 0.080-0.250 wt. % Cr. The improved wrought 7xxx aluminum alloy products generally have a thickness of from 3.0 inches to 12 inches, and realize an improved combination of properties, such an improved combination of crack deviation resistance, strength, fracture toughness and corrosion resistance.

Abstract: New 2xxx aluminum lithium alloys are disclosed. The aluminum alloys include 3.5-4.4 wt. % Cu, 0.45-0.75 wt. % Mg, 0.45-0.75 wt. % Zn, 0.65-1.15 wt. % Li, 0.1-1.0 wt. % Ag, 0.05-0.50 wt. % of at least one grain structure control element, up to 1.0 wt. % Mn, up to 0.15 wt. % Ti, up to 0.12 wt. % Si, up to 0.15 wt. % Fe, up to 0.10 wt. % of any other element, with the total of these other elements not exceeding 0.35 wt. %, the balance being aluminum.

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 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 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 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: Wrought 2xxx aluminum lithium alloy products having a thickness of from 0.040 inch to 0.500 inch are disclosed. The wrought aluminum alloy products contain from 3.00 to 3.80 wt. % Cu, from 0.05 to 0.35 wt. % Mg, from 0.975 to 1.385 wt. % Li, wherein ?0.3*Mg?0.15Cu+1.65?Li??0.3*Mg?0.15Cu+1.85, from 0.05 to 0.50 wt. % of at least one grain structure control element, wherein the grain structure control element is selected from the group consisting of Zr, Sc, Cr, V, Hf, other rare earth elements, and combinations thereof, up to 1.0 wt. % Zn, up to 1.0 wt. % Mn, up to 0.12 wt. % Si, up to 0.15 wt. % Fe, up to 0.15 wt. % Ti, up to 0.10 wt. % of any other element, with the total of these other elements not exceeding 0.35 wt. %, the balance being aluminum.

Abstract: New 2xxx aluminum lithium alloys are disclosed. The aluminum alloys include 3.5-4.4 wt. % Cu, 0.45-0.75 wt. % Mg, 0.45-0.75 wt. % Zn, 0.65-1.15 wt. % Li, 0.1-1.0 wt. % Ag, 0.05-0.50 wt. % of at least one grain structure control element, up to 1.0 wt. % Mn, up to 0.15 wt. % Ti, up to 0.12 wt. % Si, up to 0.15 wt. % Fe, up to 0.10 wt. % of any other element, with the total of these other elements not exceeding 0.35 wt. %, the balance being aluminum.

Abstract: Thick wrought 2xxx aluminum lithium alloy products are disclosed. The wrought aluminum alloy products have a thickness of at least 12.7 mm and contain from 3.00 to 3.80 wt. % Cu, from 0.05 to 0.35 wt. % Mg, from 0.975 to 1.385 wt. % Li, wherein ?0.3*Mg?0.15Cu+1.65?Li??0.3*Mg?0.15Cu+1.85, from 0.05 to 0.50 wt. % of at least one grain structure control element, wherein the grain structure control element is selected from the group consisting of Zr, Sc, Cr, V, Hf, other rare earth elements, and combinations thereof, up to 1.0 wt. % Zn, up to 1.0 wt. % Mn, up to 0.12 wt. % Si, up to 0.15 wt. % Fe, up to 0.15 wt. % Ti, up to 0.10 wt. % of any other element, with the total of these other elements not exceeding 0.35 wt. %, the balance being aluminum.

Abstract: The present invention includes a process for manufacturing metal sheets or plates and a machined metal part as well as machined products, structural components and their uses in various applications. Manufacture of a metal sheet or plate by a process of the present invention comprises casting of a rolling ingot, optionally followed by homogenisation, one or more hot or cold rolling operations, optionally separated by one or more re-heating operations, to obtain a sheet, or plate and optionally one or more sheet or plate cutting or finishing operations. The sheet is pre-machined on one or both sides so as to obtain a pre-machined stock, and subjected to solution heat treatment, quenching treatment, and optionally, one or more of the following steps: controlled stretching, aging treatment, and/or cutting.

Abstract: In accordance with the present invention, there are provided methods for the manufacture of aluminum alloy plates having reduced levels of residual stress as well as plates and products employing such plates. Processes of the present invention involve providing a solution heat-treated and quenched aluminum alloy plate with a thickness of at least 5 inches, and stress relieving the plate by performing at least one compressing step at a total rate of 0.5 to 5% permanent set along the longest or second longest edge of the plate. In the method, the dimension of the plate where the compression step is performed is along the longest or second longest edge of the plate, which is preferably no less than twice and no more than eight times the thickness of the plate. In further accordance with the present invention, there are provided stress-relieved alloys and plates that are provided with superior Wtot properties as well as reduced residual stress and heterogeneity values.

Abstract: The present invention includes a process for manufacturing metal sheets or plates and a machined metal part as well as machined products, structural components and their uses in various applications. Manufacture of a metal sheet or plate by a process of the present invention comprises casting of a rolling ingot, optionally followed by homogenization, one or more hot or cold rolling operations, optionally separated by one or more re-heating operations, to obtain a sheet, or plate and optionally one or more sheet or plate cutting or finishing operations. The sheet is pre-machined on one or both sides so as to obtain a pre-machined stock, and subjected to solution heat treatment, quenching treatment, and optionally, one or more of the following steps: controlled stretching, aging treatment, and/or cutting.

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 relates to an extruded, rolled and/or forged product made of an aluminum alloy. Alloys of the present invention may comprise (by mass): Zn 6.7-7.5% Cu 2.0-2.8% Mg 1.6-2.2% at least one element selected from the group composed of: i Zr 0.08-0.20% Cr 0.05-0.25% Sc 0.01-0.50% Hf 0.05-0.20% and V 0.02-0.20% Fe+Si<0.20% other elements ?0.05 each and ?0.15 total, balance aluminum. Products of the present invention in some embodiments have an improved compromise between static mechanical strength and damage tolerance.