Abstract: The present invention is directed to a 6xxx series aluminum alloy composition, comprising, consisting essentially of, or consisting of (by weight %) of 0.5-1.5% Si, 0.1-0.7% Cu, 0.5-1.5% Mg, 0.3-1.2% Zn, 0.05-0.35% Cr and allowable impurities of 0.8% Fe, 0.8% Mn, 0.15% Zr, 0.15% Ti, with other elements restricted as unavoidable impurities limited to 0.05% each and 0.15% total with the balance being aluminum. This 6xxx series aluminum alloy is capable of being produced with high amounts of post-consumer recycled material which significantly reduces environmental impact from producing this material, while still meeting and in most cases exceeding material attribute requirements for general engineering applications.

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 present invention is directed to a 7xxx series aluminum alloy composition comprising, consisting essentially of, or consisting of (by weight %) of 1.0-1.8% Mg; 7.0-8.3% Zn; 0.10-0.25% Zr; with up to 0.80% Cu and allowable impurities of 0.3% Si, 0.4% Fe, 0.4% Mn, and 0.1% Ti, with other elements restricted as unavoidable impurities limited to 0.05% each and 0.15% total and MgZn2 range of 7.0-9.9% with the balance being aluminum. This 7xxx series aluminum alloy is capable of being produced to achieve its maximum strength by quenching from an elevated hot working operation, such as extrusion, forging or rolling. In one embodiment the alloy is capable of meeting strength levels in excess of 65 KSI/450 MPa yield tensile strength, 69 KSI/480 MPa ultimate tensile strength and 11% elongation.

Abstract: A substantially Pb-free aluminum alloy consisting essentially of (in weight percent) Si<0.40; Fe<0.70; Cu 5.0-6.0; Zn<0.30; Bi 0.20-0.80; Sn 0.10-0.50 with the remainder being aluminum and incidental impurities. In one embodiment for applications that are sensitive to cracking from stresses generated during machining, the Bi/Sn ratio (in terms of weight percent) is less than 1.32/1 and producing in a T8 temper. On another embodiment for applications that are not sensitive to cracking from stresses during machining but would benefit from smaller machine chip size and more aggressive material removal rates, the aluminum alloy is produced using a T6 temper. The substantially Pb-free aluminum alloy has mechanical properties that include Ultimate Tensile Strength ?45.0 KSI/311 MPa, Yield Strength ?38.0 KSI/262 MPa, and % Elongation ?10%.

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: A substantially Pb-free aluminum alloy consisting essentially of (in weight percent) Si<0.40; Fe<0.70; Cu 5.0-6.0; Zn<0.30; Bi 0.20-0.80; Sn 0.10-0.50 with the remainder being aluminum and incidental impurities. In one embodiment for applications that are sensitive to cracking from stresses generated during machining, the Bi/Sn ratio (in terms of weight percent) is less than 1.32/1 and producing in a T8 temper. On another embodiment for applications that are not sensitive to cracking from stresses during machining but would benefit from smaller machine chip size and more aggressive material removal rates, the aluminum alloy is produced using a T6 temper. The substantially Pb-free aluminum alloy has mechanical properties that include Ultimate Tensile Strength ?45.0 KSI/311 MPa, Yield Strength ?38.0 KSI/262 MPa, and % Elongation ?10%.

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: High strength aluminum alloys based on the Al—Zn—Mg—Cu alloy system preferably include high levels of zinc and copper, but modest levels of magnesium, to provide increased tensile strength without sacrificing toughness. Preferred ranges of the elements include by weight, 8.5-10.5% Zn, 1.4-1.85% Mg, 2.25-3.0% Cu and at least one element from the group Zr, V, or Hf not exceeding about 0.5%, the balance substantially aluminum and incidental impurities. In addition, small amounts of scandium (0.05-0.30%) are also preferably employed to prevent recrystallization. During formation of the alloys, homogenization, solution heat treating and artificial aging processes are preferably employed.

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: An automatic machine for sectioning poultry consisting of a series of rotatable blades for severing selected parts from the bird and a rotatable arbor associated with a conveyor belt to position the bird properly with respect to the blades.

Abstract: A process for reinforcing a thermoplastic body composed of an organic thermoplastic polymer which comprises extruding a strip of hot organic thermoplastic polymer, passing said strip of hot organic thermoplastic polymer and a strip of superimposed fabric onto a surface, applying pressure to said superimposed strips sufficiently to at least partially embed said fabric into said organic thermoplastic polymer and thereafter cooling the resulting product to obtain a permanent mechanical bond between said fabric and said organic thermoplastic polymer.