Abstract: A hypereutectic aluminum-silicon casting alloy having a refined primary silicon particle size and a modified silicon phase in the eutectic. The aluminum base alloy includes from 19% to 30% by weight of silicon and also contains 0.005% to 0.06% by weight of phosphorus, and 0.15% to 1.15% by weight of titanium. On cooling from solution temperature, the phosphorus serves as an active nucleant for the primary silicon phase, while at a lower temperature, a titanium-aluminum intermetallic compound is formed that is sheathed by the pseudoprimary .alpha.-aluminum and the sheathed particles act as a nucleant to modify the acicular silicon phase in the eutectic. The resulting alloy has primary silicon refinement coupled with eutectic silicon modification.

Abstract: A component composed of a rapidly solidified aluminum-lithium alloy is subjected to thermal treatment at a temperature greater than 500.degree. C. for a time period greater than 5 hours under a protective atmosphere. Thus case toughened, the component exhibits notched impact toughness from 40 to 250% greater than that exhibited prior to the thermal treatment.

Abstract: The present invention provides a process for making high strength, high ductility, low density rapidly solidified aluminum-base alloys, consisting essentially of the formula Al.sub.bal Zr.sub.a Li.sub.b X.sub.c, wherein X is at least one element selected from the group consisting of Cu, Mg, Si, Sc, Ti, U, Hf, Be, Cr, V, Mn, Fe, Co and Ni, "a" ranges from about 0.2-0.6 wt %, "b" ranges from about 2.5-5 wt %, "c" ranges from about 0-5 wt % and the balance is aluminum. The alloy is given multiple aging treatments after being solutionized. The microstructure of the alloy is characterized by the precipitation of a composite phase in the aluminum matrix thereof.

Abstract: 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".

Abstract: A method of improving strength in aluminum alloys. The method involves solution heat treating an aluminum alloy product, quenching the alloy product, warm working the alloy product without a pre-aging step, and aging the alloy product at 250.degree.-400.degree. F. (121.degree.-204.degree. C.). The method may be used on forgings, to impart T8-type hardness to alloys that previously could only obtain such hardness levels in non-forging applications, such as by using stretch/cold working techniques.

Abstract: A component consolidated from a rapidly solidified aluminum-lithium alloy containing copper, magnesium and zirconium is subjected to a preliminary aging treatment at a temperature of about 400.degree. C. to 500.degree. C. for a time period of about 0.5 to 10 hours; quenched in a fluid bath; and subjected to a final aging treatment at a temperature of about 100.degree. C. to 250.degree. C. for a time period ranging up to about 40 hours. The component exhibits increased strength and elongation, and is especially suited for use in lightweight structural parts for land vehicles and aerospace applications.

Abstract: A rapidly solidified aluminum base lithium containing alloy is subjected to at least one overaging treatment and a plurality of rolling passes. Upon completion of the process, the alloy is comprised of grains having an ultrafine grain size. A predominant number of the grains have grain boundaries pinned by the precipitation of Al.sub.3 Zr phase. The alloy has an elongation greater than 500% at temperature above about 500.degree. C. and a strain rate above about 4.times.10.sup.-2 /s.

Abstract: The invention relates to a process for the production of targets to be used in the vacuum deposition of aluminium alloy by cathodic sputtering.The process consists of a heat treatment of the aluminium alloy disks making it possible to obtain a fine grain. It is characterized by the dissolving of the silicon, followed by controlled cooling bringing about the fine precipitation of the silicon and an optional silicon spheroidization treatment. After cooling, the disks are deformed with the press and undergo a final recrystallization treatment.The process is applied to the production of targets or cathodes for the coating of semiconductor silicon wafers by cathodic sputtering.