Abstract: A high-strength welding wire includes, in weight percentage, 5.8% Cu, 0.2% Mn, 0.1% V, 0.2% Zr, 0.2% Si, 0.3% Fe, 0.1% Zn, 1.4% compensation element, 0.2% hydrogen evolution element, 1.2% nanoceramic particle, and Al for the balance. Various powdered raw materials are mixed, wrapped with an aluminum strip, rolled and subjected to wiredrawing to form the high-strength welding wire. In a welding method for the high-strength welding wire, a K-shaped groove is formed between a stringer and a panel, and an inclined angle of the welding gun and a distance between the welding gun and the weld are adjusted. Then the angle between the wire-feeding tube and the welding gun and the striking mechanism and the weld are adjusted. Protective gas is supplied to the welding pool, and a laser is activated to perform welding. A striking mechanism is started to strike the weld.

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: The invention relates to a method for manufacturing a laminated or forged material, the thickness of which is 14 to 100 mm. The materials according to the invention are particularly suitable for manufacturing airplane underwing elements.

Abstract: A method for making an aluminum alloy includes steps of (1) weighing out starting materials to achieve a mass of material having a composition that includes aluminum, about 1.8 to about 5.6 percent by weight copper, about 0.6 to about 2.6 percent by weight lithium, and at least one of lanthanum up to about 1.5 percent by weight, strontium up to about 1.5 percent by weight, cerium up to about 1.5 percent by weight, and praseodymium up to about 1.5 percent by weight; (2) loading said starting materials into a crucible; (3) inserting said crucible into a chamber; (4) evacuating said chamber to a predetermined vacuum level; (5) melting said starting materials to form a molten mass; and (6) casting said molten mass into a mold.

Abstract: Some variations provide an aluminum alloy feedstock for additive manufacturing, the aluminum alloy feedstock comprising from 79.8 wt % to 88.3 wt % aluminum; from 1.1 wt % to 2.1 wt % copper; from 3.0 wt % to 4.6 wt % magnesium; from 7.1 wt % to 9.0 wt % zinc; and from 0.5 wt % to 2.8 wt % zirconium as a grain-refiner element. The aluminum alloy feedstock may be in the form of an ingot powder. In some variations, the aluminum alloy feedstock comprises from 81.3 wt % to about 87.8 wt % aluminum; from 1.2 wt % to 2.0 wt % copper; from 3.2 wt % to 4.4 wt % magnesium; from 7.3 wt % to 8.7 wt % zinc; and from 0.5 wt % to 2.8 wt % zirconium.

Abstract: The present invention relates to an aluminum base alloy with high thermal conductivity, and more particularly, to an alloy for die casting that does not become brittle and has high thermal conductivity, so as to be easily used for LED lighting parts, and contains 0.2 to 2.0 wt % of Mg, 0.1 to 0.3 wt % of Fe, 0.1 to 1.0 wt % of Co, with the remainder being Al.

Abstract: An induction furnace comprising a upper furnace vessel; an induction coil positioned below the upper furnace vessel; and a melt-containing vessel positioned inside the induction coil and communicably connected to the upper furnace vessel, wherein the positioning of the melt-containing vessel inside the induction coil defines a gap between an outside surface of the melt-containing vessel and an inside surface of the induction coil. A system for direct-chill casting comprising at least one an induction furnace; at least one in-line filter operable to remove impurities in molten metal; at least one gas source coupled to a feed port associated with the gas; and at least one device for solidifying metal by casting. A method of cooling an induction furnace comprising introducing a gas into a gap between an induction coil and a melt-containing vessel positioned inside the induction coil; and circulating the gas through the gap.

Abstract: An aluminium-copper alloy comprising substantially insoluble particles which occupy the interdendritic regions of the alloy, provided with free titanium in quantity sufficient to result in a refinement of the grain structure in the cast alloy.

Abstract: The present disclosure provides improved processes and compositions for continuously casting aluminum alloys. The resulting aluminum alloy sheet is useful for container body stock.

Abstract: New 2xxx aluminum alloys containing vanadium are disclosed. In one embodiment, the aluminum alloy includes 3.3-4.1 wt. % Cu, 0.7-1.3 wt. % Mg, 0.01-0.16 wt. % V, 0.05-0.6 wt. % Mn, 0.01 to 0.4 wt. % of at least one grain structure control element, the balance being aluminum, incidental elements and impurities. The new alloys may realize an improved combination of properties, such as in the T39 or T89 tempers.

Abstract: An aluminum alloy comprising 2.1 to 2.8 wt. % Cu, 1.1 to 1.7 wt. % Li, 0.1 to 0.8 wt. % Ag, 0.2 to 0.6 wt. % Mg, 0.2 to 0.6 wt. % Mn, a content of Fe and Si less or equal to 0.1 wt. % each, and a content of unavoidable impurities less than or equal to 0.05 wt. % each and 0.15 wt. % total, and the alloy being substantially zirconium free.

Abstract: An aluminium-copper alloy comprising substantially insoluble particles which occupy the interdendritic regions of the alloy, provided with free titanium in quantity sufficient to result in a refinement of the grain structure in the cast alloy.

Abstract: Disclosed is an Al—Mg—Si aluminum alloy sheet that can prevent ridging marks during press forming and has good reproducibility even with stricter fabricating conditions. In an Al—Mg—Si aluminum alloy sheet of a specific composition, hot rolling is performed on the basis of a set relationship between the rolling start temperature Ts and the rolling finish temperature Tf° C., whereby the relationship of the cube orientation distribution profile in the horizontal direction of the sheet with the cube orientation alone or another crystal orientation distribution profile at various locations in the depth direction of the sheet is made more uniform, suppressing the appearance of ridging marks that develop during sheet press forming.

Abstract: The present invention relates to extruded, rolled and/or forged products. Also provided are methods of making such products based on aluminum alloy wherein a liquid metal bath is prepared comprising 2.0 to 3.5% by weight of Cu, 1.4 to 1.8% by weight of Li, 0.1 to 0.5% by weight of Ag, 0.1 to 1.0% by weight of Mg, 0.05 to 0.18% by weight of Zr, 0.2 to 0.6% by weight of Mn and at least one element selected from Cr, Sc, Hf and Ti, the quantity of said element, if it is selected, being 0.05 to 0.3% by weight for Cr and for Sc, 0.05 to 0.5% by weight for Hf and 0.01 to 0.15% by weight for Ti, the remainder being aluminum and inevitable impurities. The products and methods of the present invention offer a particularly advantageous compromise between static mechanical strength and damage tolerance and are particularly useful in the field of aeronautical design.

Abstract: New 2xxx aluminum alloys containing vanadium are disclosed. In one embodiment, the aluminum alloy includes 3.3-4.1 wt. % Cu, 0.7-1.3 wt. % Mg, 0.01-0.16 wt. % V, 0.05-0.6 wt. % Mn, 0.01 to 0.4 wt. % of at least one grain structure control element, the balance being aluminum, incidental elements and impurities. The new alloys may realize an improved combination of properties, such as in the T39 or T89 tempers.

Abstract: Improved 5xxx aluminum alloys having an improved combination of properties are disclosed. The new 5xxx aluminum alloys generally contain 0.50 to 3.25 wt. % Mg, 0.05 to 0.20 wt. % Sc, 0.05 to 0.20 wt. % Zr, up to 0.50 wt. % in total of Cu and Ag, less than 0.10 wt. % Mn, up to 0.30 wt. % in total of Cr, V and Ti, up to 0.50 wt. % in total of Ni and Co, up to 0.25 wt. % Fe, up to 0.25 wt. % Si, up to 0.50 wt. % Zn, and 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. The new 5xxx aluminum alloys may be used in high strength electrical conductor products, among others.

Abstract: A wear-resistant aluminum alloy material excellent in workability and wear-resistance is provided. A wear-resistant aluminum alloy material excellent in workability includes Si: 13 to 15 mass %, Cu: 5.5 to 9 mass %, Mg: 0.2 to 1 mass %, Ni: 0.5 to 1 mass %, P: 0.003 to 0.03 mass %, and the balance being Al and inevitable impurities. An average particle diameter of primary Si particles is 10 to 30 ?m, an area occupancy rate of the primary Si particles in cross-section is 3 to 12%, an average particle diameter of intermetallic compounds is 1.5 to 8 ?m, and an area occupancy rate of the intermetallic compounds in cross-section is 4 to 12%.

Abstract: Aluminum-based alloys for casting or wrought processing having improved combinations of properties, including improved high temperature strength, are provided. The alloys generally comprise copper, magnesium, silver, and titanium, along with scandium and/or cobalt. Zirconium, zinc, and/or vanadium may also optionally be present in the alloy. When cobalt is present in the alloy, nickel may also optionally be present. Cast and wrought products, as well as methods of making the same using the alloys, are also disclosed.

Abstract: Improved aluminum-copper-lithium alloys are disclosed. The alloys may include 3.4-4.2 wt. % Cu, 0.9-1.4 wt. % Li, 0.3-0.7 wt. % Ag, 0.1-0.6 wt. % Mg, 0.2-0.8 wt. % Zn, 0.1-0.6 wt. % Mn, and 0.01-0.6 wt. % of at least one grain structure control element, the balance being aluminum and incidental elements and impurities. The alloys achieve an improved combination of properties over prior art alloys.

Abstract: An aluminum alloy extruded product includes an aluminum alloy including 6.0 to 7.2 mass % of Zn, 1.0 to 1.6 mass % of Mg, 0.1 to 0.4 mass % of Cu, at least one component selected from the group consisting of Mn, Cr, and Zr in a respective amount of 0.25 mass % or less and a total amount of 0.15 to 0.25 mass %, 0.20 mass % or less of Fe, and 0.10 mass % or less of Si, with the balance substantially being aluminum, the aluminum alloy extruded product having a hollow cross-sectional shape, a recrystallization rate of 20% or less of a cross-sectional area of the extruded product, and a 0.2% proof stress of 370 to 450 MPa.

Abstract: The present disclosure relates to an alloy containing aluminum including, as a % by weight, 2.1 to 2.4% of Cu, 1.3 to 1.6% of Li, 0.1 to 0.5% of Ag, 0.2 to 0.6% of Mg, 0.05 to 0.15% of Zr, 0.1 to 0.5% of Mn, 0.01 to 0.12% of Ti, optionally at least one element chosen from among Cr, Sc, and Hf, the quantity of the element, if it is chosen, being from 0.05 to 0.3% for Cr and Sc, 0.05 to 0.5% for Hf, a quantity of Fe and Si each less than or equal to 0.1 and inevitable impurities at a rate of less than or equal to 0.05 each and 0.15 in total. The alloy can be used to produce extruded, rolled and/or forged products particularly suitable for the manufacture of elements for the lower wing skin of aircrafts.

Abstract: An aluminum alloy wire material, which has an alloy composition containing: 0.1 to 0.4 mass % of Fe, 0.1 to 0.3 mass % of Cu, 0.02 to 0.2 mass % of Mg, and 0.02 to 0.2 mass % of Si, and further containing 0.001 to 0.01 mass % of Ti and V in total, with the balance being Al and unavoidable impurities, in which a grain size is 5 to 25 ?m in a vertical cross-section in a wire-drawing direction thereof, and an average creep rate between 1 and 100 hours is 1×10?3 (%/hour) or less by a creep test under a 20% load of a 0.2% yield strength at 150° C.

Abstract: Provided are an aluminium alloy and a manufacturing method thereof. In the method, aluminium and a master alloy containing a calcium (Ca)-based compound are provided. A melt is prepared, in which the master alloy and the Al are melted. The aluminum alloy may be manufactured by casting the melt.

Abstract: Provided are an aluminium alloy and a manufacturing method thereof. In the method, aluminium and a magnesium (Mg) master alloy containing a calcium (Ca)-based compound are provided. A melt is prepared, in which the Mg master alloy and the Al are melted. The aluminum alloy may be manufactured by casting the melt.

Abstract: High strength heat treatable aluminum alloys that can be used at temperatures from about ?420° F. (?251° C.) up to about 650° F. (343° C.) are described. The alloys are strengthened by dispersion of particles based on the L12 intermetallic compound Al3X. These alloys comprise aluminum, copper, magnesium, at least one of scandium, erbium, thulium, ytterbium, and lutetium; and at least one of gadolinium, yttrium, zirconium, titanium, hafnium, and niobium.

Abstract: Improved 5xxx aluminum alloys and products made therefrom are disclosed. The new 5xxx aluminum alloy products may achieve an improved combination of properties due to, for example, the presence of copper. In one embodiment, the new 5xxx aluminum alloy products are able to achieve an improved combination of properties by solution heat treatment.

Abstract: High strength heat treatable aluminum alloys that can be used at temperatures from about ?420° F. (?251° C.) up to about 650° F. (343° C.) are described. The alloys are strengthened by dispersion of particles based on the L12 intermetallic compound Al3X. These alloys comprise aluminum, copper, magnesium, at least one of scandium, erbium, thulium, ytterbium, and lutetium; and at least one of gadolinium, yttrium, zirconium, titanium, hafnium, and niobium.

Abstract: New 2xxx aluminum alloys containing vanadium are disclosed. In one embodiment, the aluminum alloy includes 3.3-4.1 wt. % Cu, 0.7-1.3 wt. % Mg, 0.01-0.16 wt. % V, 0.05-0.6 wt. % Mn, 0.01 to 0.4 wt. % of at least one grain structure control element, the balance being aluminum, incidental elements and impurities. The new alloys may realize an improved combination of properties, such as in the T39 or T89 tempers.

Abstract: A low density aluminum based alloy useful in aircraft structure for fuselage sheet or light-gauge plate applications which has high strength, high fracture toughness and high corrosion resistance, comprising 2.7 to 3.4 weight percent Cu, 0.8 to 1.4 weight percent Li, 0.1 to 0.8 weight percent Ag, 0.2 to 0.6 weight percent Mg and a grain refiner such as Zr, Mn, Cr, Sc, Hf, Ti or a combination thereof, the amount of which being 0.05 to 0.13 wt. % for Zr, 0.1 to 0.8 wt. % for Mn, 0.05 to 0.3 wt. % for Cr and Sc, 0.05 to 0.5 wt. % for Hf and 0.05 to 0.15 wt. % for Ti. The amount of Cu and Li preferably corresponds to the formula Cu(wt. %)+5/3 Li(wt. %)<5.2.

Abstract: An aluminum alloy having improved strength and ductility, comprising: Cu 3.5-5.8 wt. %, Mg 0.2-1.5 wt. % Mn 0.2-0.5 wt. % Ag 0.2-0.8 wt. % Ti 0.02-0.12 wt. % and optionally one or more selected from the group consisting of Cr 0.1-0.8 wt. %, Hf 0.1-1.0 wt. %, Sc 0.03-0.6 wt. %, and V 0.05-0.15 wt. %, balance aluminum and incidental elements and impurities, and wherein the alloy is substantially zirconium-free.

Abstract: The present invention relates to aluminum-based alloy of Al—Cu—Mg—Li type and to an article made thereof which are intended to be used in aircraft and aerospace vehicles. While having high strength properties (ultimate strength level and yield strength level) the suggested alloy has a reduced sound conductivity upon acoustic influence. The invented alloy contains (mass. %): Li 1.7-2.0 Cu 1.6-2.0 Mg 0.7-1.1 Zr 0.04-0.2? Be 0.02-0.2? Ti 0.01-0.1? Ni 0.01-0.15 Mn 0.01-0.4? S 0.5 · 10?4-1.0 · 10?4 N 0.5 · 10?4-1.0 · 10?4 Co 0.5 · 10?6-1.0 · 10?6 Na 0.5 · 10?3-1.0 · 10?3 Al-balance Sheets of said alloy are particularly suited to be used as structural material for aircraft and aerospace vehicles in the form of skin and a primary sheets' set.

Abstract: A method for producing an integrated monolithic aluminum structure, including the steps of: (a) providing an aluminum alloy plate from an aluminum alloy with a predetermined thickness (y), (b) shaping or forming the alloy plate to obtain a predetermined shaped structure, (c) heat-treating the shaped structure, (d) machining, e.g. high velocity machining, the shaped structure to obtain an integrated monolithic aluminum structure.

Abstract: High strength heat treatable aluminum alloys that can be used at temperatures from about ?420° F. (?251° C.) up to about 650° F. (343° C.) are described. The alloys are strengthened by dispersion of particles based on the L12 intermetallic compound Al3X. These alloys comprise aluminum, copper, magnesium, at least one of scandium, erbium, thulium, ytterbium, and lutetium; and at least one of gadolinium, yttrium, zirconium, titanium, hafnium, and niobium.

Abstract: An aluminum alloy and a method of casting. At least one of zirconium, scandium, a nucleating agent selected from the group consisting of metal carbides, aluminides and borides, and rare earth elements are added to the alloy while in the molten state such that upon solidification, the cast alloy exhibits improved hot tear resistance. In a particular form, the nucleating agent may be titanium diboride for grain refining. Other agents that can be used for grain refining include scandium, zirconium, silicon, silver and one or more rare earth elements. In the case of rare earth elements, mischmetal may be used as a precursor. Combinations of titanium diboride and at least one other agent are especially effective in reducing the incidence of hot tearing in products cast from the modified aluminum alloy.

Abstract: An aluminium alloy product having high strength, excellent corrosion resistance and weldability, having the following composition in wt. %: Mg 3.5 to 6.0, Mn 0.4 to 1.2, Fe<0.5, Si<0.5, Cu<0.15, Zr<0.5, Cr<0.3, Ti 0.03 to 0.2, Sc<0.5, Zn<1.7, Li<0.5, Ag<0.4, optionally one or more of the following dispersoid forming elements selected from the group consisting of erbium, yttrium, hafnium, vanadium, each <0.5 wt. %, and impurities or incidental elements each <0.05, total <0.15, and the balance being aluminium.

Abstract: The invention relates to an aluminium alloy used as a coating for surfaces subjected to extreme friction stress, with an aluminium matrix incorporating at least a soft phase and a hard phase, as well as a process for producing the coating. The soft phase and/or the hard phase is essentially finely distributed in the aluminium matrix (20) and at least 80%, preferably at least 90%, of the soft phase or soft phase particles (18) have a mean diameter of a maximum of 3 ?m. The aluminium alloy is produced by depositing it on the base (11) by a process of deposition from a gas phase.

Abstract: The invention provides a 2000 series aluminum alloy having enhanced damage tolerance, the alloy consisting essentially of about 3.0-4.0 wt % copper; about 0.4-1.1 wt % magnesium; up to about 0.8 wt % silver; up to about 1.0 wt % Zn; up to about 0.25 wt % Zr; up to about 0.9 wt % Mn; up to about 0.5 wt % Fe; and up to about 0.5 wt % Si, the balance substantially aluminum, incidental impurities and elements, said copper and magnesium present in a ratio of about 3.6-5 parts copper to about 1 part magnesium. The alloy is suitable for use in wrought or cast products including those used in aerospace applications, particularly sheet or plate structural members, extrusions and forgings, and provides an improved combination of strength and damage tolerance.

Abstract: Disclosed is an Al—Cu alloy of the AA2000-series alloys with high toughness and an improved strength, including the following composition (in weight percent) Cu 4.5-5.5, Mg 0.5-1.6, Mn?0.80, Zr?0.18, Cr?0.18, Si?0.15, Fe?0.15, the balance essentially aluminum and incidental elements and impurities, and wherein the amount (in weight %) of magnesium is either: (a) in a range of 1.0 to 1.6%, or alternatively (b) in a range of 0.50 to 1.2% when the amount of dispersoid forming elements such as Cr, Zr or Mn is controlled and (in weight %) in a range of 0.10 to 0.70%.

Abstract: An aluminum-copper-magnesium alloy having ancillary additions of lithium. The alloy composition includes from about 3 to about 5 weight percent Cu, from about 0.5 to about 2 weight percent Mg, and from about 0.01 to about 0.9 weight percent Li. The combined amount of Cu and Mg is maintained below a solubility limit of the aluminum alloy. The alloys possess improved combinations of fracture toughness and strength, and also exhibit good fatigue crack growth resistance.

Abstract: A filler composition for welding onto a substrate is composed of 82.5˜96.5 wt %, aluminum, 3.0˜10.0 wt % copper, 0.2˜1.5 wt % magnesium, 0.1˜1.5 wt % silver, 0.1˜2.0 wt % scandium, 0˜1.5 wt % zirconium, and 0˜1.0 wt % titanium, and can be welded with a high success rate to a substrate (such as an aluminum-copper alloy substrate) and avoiding a hot cracking phenomenon and a low welding strength, so as to achieve the effects of enhancing the yield rate and lowering the cost of a product.

Abstract: A low density aluminum based alloy useful in aircraft structure for fuselage sheet or light-gauge plate applications which has high strength, high fracture toughness and high corrosion resistance, comprising 2.7 to 3.4 weight percent Cu, 0.8 to 1.4 weight percent Li, 0.1 to 0.8 weight percent Ag, 0.2 to 0.6 weight percent Mg and a grain refiner such as Zr, Mn, Cr, Sc, Hf, Ti or a combination thereof, the amount of which being 0.05 to 0.13 wt. % for Zr, 0.1 to 0.8 wt. % for Mn, 0.05 to 0.3 wt. % for Cr and Sc, 0.05 to 0.5 wt. % for Hf and 0.05 to 0.15 wt. % for Ti. The amount of Cu and Li preferably corresponds to the formula Cu(wt. %)+5/3 Li(wt. %)<5.2.

Abstract: The present invention relates to aluminium-based alloy of Al—Cu—Mg—Li type and to an article made thereof which are intended to be used in aircraft and aerospace vehicles. While having high strength properties (ultimate strength level and yield strength level) the suggested alloy has a reduced sound conductivity upon acoustic influence. The invented alloy contains (mass. %): Li 1.7-2.0 Cu 1.6-2.0 Mg 0.7-1.1 Zr 0.04-0.2? Be 0.02-0.2? Ti 0.01-0.1? Ni 0.01-0.15 Mn 0.01-0.4? S 0.5 · 10?4-1.0 · 10?4 N 0.5 · 10?4-1.0 · 10?4 Co 0.5 · 10?6-1.0 · 10?6 Na 0.5 · 10?3-1.0 · 10?3 Al-balance Sheets of said alloy are particularly suited to be used as structural material for aircraft and aerospace vehicles in the form of skin and a primary sheets' set.

Abstract: The invention provides a 2000 series aluminum alloy having enhanced damage tolerance, the alloy consisting essentially of about 3.0-4.0 wt % copper; about 0.4-1.1 wt % magnesium; up to about 0.8 wt % silver; up to about 1.0 wt % Zn; up to about 0.25 wt % Zr; up to about 0.9 wt % Mn; up to about 0.5 wt % Fe; and up to about 0.5 wt % Si, the balance substantially aluminum, incidental impurities and elements, said copper and magnesium present in a ratio of about 3.6-5 parts copper to about 1 part magnesium. The alloy is suitable for use in wrought or cast products including those used in aerospace applications, particularly sheet or plate structural members, extrusions and forgings, and provides an improved combination of strength and damage tolerance.

Abstract: An aluminum-copper-magnesium alloy having ancillary additions of lithium. The alloy composition includes from about 3 to about 5 weight percent Cu, from about 0.5 to about 2 weight percent Mg, and from about 0.01 to about 0.9 weight percent Li. The combined amount of Cu and Mg is maintained below a solubility limit of the aluminum alloy. The alloys possess improved combinations of fracture toughness and strength, and also exhibit good fatigue crack growth resistance.

Abstract: A compressor wheel made of a cast aluminum alloy, wherein the cast aluminum alloy contains Cu 1.4 to 3.2 mass %, Mg 1.0 to 2.0 mass %, Ni 0.5 to 2.0 mass %, Fe 0.5 to 2.0 mass %, and at least one selected from the group consisting of Ti 0.01 to 0.35 mass %, Zr 0.01 to 0.30 mass %, Sc 0.01 to 0.8 mass %, and V 0.01 to 0.5 mass %, with the balance being aluminum and inevitable impurities, with the [(Cu content)+0.5×(Mg content)] being 3.8 mass % or less, and with a secondary dendrite arm spacing being 50 ?m or less, wherein the cast aluminum alloy is being reinforced by a solution treatment and an aging treatment, and wherein the compressor wheel shows good heat resistant strength, and is for use in a turbocharger.

Abstract: The invention provides a 2000 series aluminum alloy having enhanced damage tolerance, the alloy consisting essentially of about 3.0-4.0 wt % copper; about 0.4-1.1 wt % magnesium; up to about 0.8 wt % silver; up to about 1.0 wt % Zn; up to about 0.25 wt % Zr; up to about 0.9 wt % Mn; up to about 0.5 wt % Fe; and up to about 0.5 wt % Si, the balance substantially aluminum, incidental impurities and elements, said copper and magnesium present in a ratio of about 3.6-5 parts copper to about 1 part magnesium. The alloy is suitable for use in wrought or cast products including those used in aerospace applications, particularly sheet or plate structural members, extrusions and forgings, and provides an improved combination of strength and damage tolerance.

Abstract: Disclosed is a high damage tolerant Al—Cu alloy of the AA2000 series having a high toughness and an improved fatigue crack growth resistance, including the following composition (in weight percent) Cu 3.8-4.7, Mg 1.0-1.6, Zr 0.06-0.18, Cr<0.15, Mn>0-0.50 , Fe?0.15, Si?0.15, and Mn-containing dispersoids, the balance essentially aluminum and incidental elements and impurities, wherein the Mn-containing dispersoids are at least partially replaced by Zr-containing dispersoids. There is also disclosed a method for producing a rolled high damage tolerant Al—Cu alloy product having a high toughness and an improved fatigue crack growth resistance, and applications of that product as a structural member of an aircraft.

Abstract: The invention relates to a work-hardened product, particularly a rolled, extruded or forged product, made of an alloy with the following composition (% by weight): Cu 3.8-4.3; Mg 1.25-1.45; Mn 0.2-0.5; Zn 0.4-1.3; Fe<0.15; Si<0.15; Zr?0.05; Ag<0.01, other elements <0.05 each and <0.15 total, remainder Al treated by dissolution, quenching and cold strain-hardening, with a permanent deformation of between 0.5% and 15%, and preferably between 1.5% and 3.5%. Cold strain-hardening can be achieved by controlled tension and/or cold transformation, for example rolling, die forging or drawing. This cladded metal plate type product is a suitable element to be used as aircraft fuselage skin.

Abstract: New alloys for potential use in applications such as in lower wing skins and fuselage skins are disclosed. Specifically, Mn-free 2×24 alloys potentially suitable for thick plate and thin plate and sheet applications are believed to be novel and to provide unexpectedly superior properties.

Abstract: An aluminum alloy having improved strength and ductility, comprising: Cu 3.5–5.8 wt. %, Mg 0.1–1.8 wt. % Mn 0.1–0.8 wt. % Ag 0.2–0.8 wt. % Ti 0.02–0.12 wt. % and optionally one or more selected from the group consisting of Cr 0.1–0.8 wt. %, Hf 0.1–1.0 wt. %, Sc 0.03–0.6 wt. %, and V 0.05–0.15 wt. %. balance aluminum and incidental elements and impurities, and wherein the alloy is substantially zirconium-free.