Abstract: Dispersoids 7xxx aluminum alloy products with enhanced fatigue crack growth deviation and Environmentally Assisted Cracking (EAC) resistance are disclosed. The 7xxx aluminum alloy comprises 1 to 3 wt. % Cu, 1.2 to 3 wt. % Mg, 4 to 8.5 wt. % Zn, up to 0.3 wt. % Mn, up to 0.15 wt. % Zr, up to 0.3 wt. % Cr dispersoid elements, incidental elements, and the balance Al. In one embodiment, the alloy includes Zr + Cr + Mn in the range of 0.2 to 0.8 wt. %. In another embodiment, the alloy includes Zr + Mn in the range of 0.07 to 0.7 wt. %. This alloy can be fabricated to plate, extrusion, or forging products, and is especially suitable for aerospace structural components. The products have enhanced EAC resistance and fatigue crack growth deviation resistance. Meanwhile, the products have an excellent combination of strength, fracture toughness, ductility at different orientations, and Stress Crack Corrosion (SCC), and exfoliation corrosion resistance suitable for aerospace application.

Abstract: High strength and high fracture toughness 7xxx aluminum alloy products comprise 6.5 to 7.2 wt. % Zn, 1.55 to 1.95 wt. % Cu, 1.75 to 2.15 wt. % Mg, 0.095 to 0.15 wt. % Zr, incidental elements, and the balance Al. In one embodiment, the aluminum alloy product includes Mg/Cu and Zn/Mg ratios in the range of 1.05 to 1.35, and 3.2 to 4.0, respectively. This aluminum alloy product can be fabricated to produce plate, extrusion or forging products, and is especially suitable for aerospace structural components. The products have an excellent combination of strength, fracture toughness, Kmax at the fatigue crack deviation point, ductility in different orientations, and corrosion resistance suitable for aerospace application.

Abstract: The high strength 7xxx aluminum alloy products and methods of making such products are disclosed resulting in better fatigue crack deviation performance, and high anisotropic ductility. The 7xxx aluminum alloy product comprises 7.0 to 7.8 wt. % Zn, 1.1 to 2.2 wt. % Cu, and 1.1 to 2.1 wt. % Mg. This 7xxx aluminum alloy product can be fabricated to produce plate, extrusion or forging products, and is especially suitable for aerospace structural components, especially large commercial airplane wing structure applications. The minimum tensile yield strength (TYS) along rolling (LT) direction is higher than 65 ksi for 4 to 5 inch plate. The minimum Kmax at crack deviation point is higher than 31 ksi*in1/2 for 4 to 5 inch plate. The minimum elongation is 1.4% for all tensile orientations including lowest orientations of ST-22.5 to ST-45. The 7xxx aluminum alloy product provides high damage tolerance performance as well as better corrosion resistance performance suitable for aerospace application.

Abstract: The present invention is directed to aluminum-lithium alloys, specifically aluminum—copper—lithium—magnesium—manganese alloys. The aluminum-lithium alloy of the present invention comprises from 3.6 to 4.1 wt. % Cu, 0.8 to 1.05 wt. % Li, 0.6 to 1.0 wt. % Mg, 0.2 to 0.6 wt. % Mn, up to 0.12 wt. % Si, up to 0.15 wt. % Fe, from 0.03 to 0.16 wt. % of at least one grain structure control element selected from the group consisting of Zr, Sc, Cr, V, Hf, and other rare earth elements, up to 0.10 wt. % Ti, up to 0.15 wt. % incidental elements with the total of incidental elements not exceeding 0.35 wt. %, and the balance being aluminum. Preferably, Ag is not intentionally added and should not be more than 0.05 wt. % as a non-intentionally added element. Preferably, Zn is not intentionally added and should not be more than 0.2 wt. % as a non-intentionally added element. The amount of Cu in weight percent is at least equal to or higher than four times the amount of Li in weight percent.

Abstract: A low cost, substantially Zr-free, low density 2xxx aluminum-lithium alloy is disclosed. The aluminum-lithium alloy can be produced to high formability sheet products capable of being formed into wrought products with a thickness of 0.01? to 0.249?. Aluminum-lithium alloys of the invention comprise from 3.2 to 4.1 wt. % Cu, 1.0 to 1.8 wt. % Li, 0.8 to 1.2 wt. % Mg, 0.10 to 0.50 wt. % Zn, 0.10 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 0.15 wt. % incidental elements, with the total of these incidental elements not exceeding 0.35 wt. %, and the balance being aluminum. Ag should not be intentionally added and should not be more than 0.1 wt. % as a non-intentionally added element. Zr should not be intentionally added and should not be more than 0.05 wt. % as a non-intentionally added element. Mg is at least equal to or higher than 2*Zn in weight percent in the invented alloy.

Abstract: A high strength, high formability and low cost 2xxx aluminum-lithium alloy is disclosed. The aluminum-lithium alloy is capable of being formed into wrought products with a thickness of from about 0.01? to about 0.249?. Aluminum-lithium alloys of the invention generally comprise from about 3.5 to 4.5 wt. % Cu, 0.8 to 1.6 wt. % Li, 0.6 to 1.5 wt. % Mg, from 0.03 to 0.6 wt. % of at least one grain structure control element selected from the group consisting of Zr, Sc, Cr, V, Hf, and other rare earth elements, and 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 0.05 wt. % of any other element, with the total of these other elements not exceeding 0.15 wt. %, and the balance being aluminum. Ag should not be more than 0.5 wt. % and is preferably not intentionally added. Mg is at least equal or higher than Zn in weight percent in the invented alloy.

Abstract: The present invention is directed to a thick plate high strength 7xxx aluminum alloy product comprising 8.0 to 8.4 wt. % Zn, 1.5 to 2.0 wt. % Mg, 1.1 to 1.5 wt. % Cu, and 0.05 to 0.15 wt. % Zr, 4.0 to 5.3 of Zn/Mg weight percentage ratio, 0.14 to 0.19 of Cu/Zn weight percentage ratio, and 10.7 to 11.6 wt. % of Cu+Mg+Zn. This alloy can be fabricated to produce 3-10 inch thick plate, extrusion or forging products, and is especially suitable for aerospace structural components, especially large commercial airplane wing structure applications. The product provides high strength, high damage tolerance performance as well as better corrosion resistance performance suitable for aerospace application.

Abstract: A high strength, high formability and low cost 2xxx aluminum-lithium alloy is disclosed. The aluminum-lithium alloy is capable of being formed into wrought products with a thickness of from about 0.01? to about 0.249?. Aluminum-lithium alloys of the invention generally comprise from about 3.5 to 4.5 wt. % Cu, 0.8 to 1.6 wt. % Li, 0.6 to 1.5 wt. % Mg, from 0.03 to 0.6 wt. % of at least one grain structure control element selected from the group consisting of Zr, Sc, Cr, V, Hf, and other rare earth elements, and 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 0.05 wt. % of any other element, with the total of these other elements not exceeding 0.15 wt. %, and the balance being aluminum. Ag should not be more than 0.5 wt. % and is preferably not intentionally added. Mg is at least equal or higher than Zn in weight percent in the invented alloy.

Abstract: The present invention is directed to an ultra-thick high strength aluminum alloy, comprising 7.5 to 8.4 wt. % Zn, 1.6 to 2.3 wt. % Mg, 1.4 to 2.1 wt. % Cu, and 0.05 to 0.15 wt. % Zr. This alloy can be fabricated to produce 2-10 inch thick plate, extrusion or forging products, and is especially suitable for aerospace structural components, especially large commercial airplane wing structure applications. The aluminum product has a minimum yield strength of [75 ksi?0.8×(thickness in inch?3.94 inch)] in LT direction and [76 ksi?0.8×(thickness in inch?3.94 inch)] in L direction for more than 2 inch thick product in T7651 temper. Besides strength, product provides necessary damage tolerance performance as well as corrosion resistance performance suitable for aerospace application.