Abstract: A manufacturing process for a remelt block containing aluminum designed for making aluminum alloy for the aircraft industry in which scrap containing mainly aluminum alloys used in the aircraft industry is supplied during a supply stage, the scrap is melted in a smelting furnace in order to obtain an initial molten metal bath during a smelting stage, the initial molten metal bath is subjected to purification by fractional crystallization in order to obtain a solidified mass and a bath of residual liquid during a segregation stage, and the solidified mass is recovered in order to obtain a remelt block during a recovery stage. The invention is particularly useful for the recycling of aluminum alloys used in the aircraft industry as it makes it possible to purify scrap of series 2XXX or series 7XXX alloys for iron and silicon, without eliminating additive elements such as zinc, copper and magnesium.

Abstract: A manufacturing process for a remelt block containing aluminum designed for making aluminum alloy for the aircraft industry in which scrap containing mainly aluminum alloys used in the aircraft industry is supplied during a supply stage, the scrap is melted in a smelting furnace in order to obtain an initial molten metal bath during a smelting stage, the initial molten metal bath is subjected to purification by fractional crystallization in order to obtain a solidified mass and a bath of residual liquid during a segregation stage, and the solidified mass is recovered in order to obtain a remelt block during a recovery stage. The invention is particularly useful for the recycling of aluminum alloys used in the aircraft industry as it makes it possible to purify scrap of series 2XXX or series 7XXX alloys for iron and silicon, without eliminating additive elements such as zinc, copper and magnesium.

Abstract: The present invention is directed to a method for melting scrap of an aluminum alloy containing lithium. The steps include providing scrap containing aluminum-lithium-type alloys, preparing an initial liquid metal bed of a first composition in a smelting oven, loading the scrap onto the initial liquid metal bed so as to create a floating layer of the scrap with a controlled thickness at the surface of the liquid metal bed, partially melting the floating layer via contact with the metal bed so as to obtain a liquid metal bath having a second composition, and removing the liquid metal from the second composition of the liquid metal bath. The method has technical and economic advantages. It does not require investment in a particular installation and it requires minimal use of expensive expendable materials such as inert gas, because the formation of a floating layer having a controlled thickness makes it possible to effectively protect the surface of the liquid metal from oxidation.

Abstract: The present invention is directed to a method for melting scrap of an aluminum alloy containing lithium. The steps include providing scrap containing aluminum-lithium-type alloys, preparing an initial liquid metal bed of a first composition in a smelting oven, loading the scrap onto the initial liquid metal bed so as to create a floating layer of the scrap with a controlled thickness at the surface of the liquid metal bed, partially melting the floating layer via contact with the metal bed so as to obtain a liquid metal bath having a second composition, and removing the liquid metal from the second composition of the liquid metal bath. The method has technical and economic advantages. It does not require investment in a particular installation and it requires minimal use of expensive expendable materials such as inert gas, because the formation of a floating layer having a controlled thickness makes it possible to effectively protect the surface of the liquid metal from oxidation.

Abstract: A manufacturing process for an intermediate product made of a predetermined 7000 series alloy having a target content of at least one first anti-recrystallizing element Z1 selected from the group consisting of Zr and Cr. This process enables effective recycling of scrap, particularly machining scrap made of 7000 series alloys, in the manufacture of intermediated products with high added value.

Abstract: A mold for plastics made of a rolled, extruded or forged AlZnMgCu aluminum alloy product >60 mm thick, and having a composition including, in weight %: 5.7 < Zn < 8.7 1.7 < Mg < 2.5 1.2 < Cu < 2.2 Fe < 0.14 Si < 0.11 0.05 < Zr < 0.15 Mn < 0.02 Cr < 0.02 with Cu+Mg<4.1 and Mg>Cu, other elements<0.05 each and<0.10 in total, the product being treated by solution heat treating, quenching and aging to a T6 temper.

Abstract: A manufacturing process for an intermediate product made of a predetermined 7000 series alloy having a target content of at least one first anti-recrystallizing element Z1 selected from the group consisting of Zr and Cr. The product is produced by the steps of: a) supplying machining scrap including at least one second 7000 series alloy having a target content of at least one second anti-recrystallizing element Z2 selected from the group consisting of Zr and Cr, in an amount greater than a maximum accepted content of Z2 in the predetermined alloy; b) conducting at least one refining step of said scrap to reduce the amount of Z2 to a value below the maximum accepted content of Z2 in the predetermined alloy; c) producing a batch of liquid metal having nominal composition, in part or in whole, from the refined scrap; and d) forming the product by casting the liquid metal.

Abstract: A rolled, forged or extruded AlZnMgCu alloy product, used to manufacture structural elements for aircraft, particularly wing spars. The product is greater than 60 mm thick, and has a composition (% by weight):5.7<Zn<8.71.7<Mg<2.51.2<Cu<2.20.07<Fe<0.14Si<0.110.05<Zr<0.15Mn<0.02Cr<0.02with Cu+Mg<4.1, and Mg>Cu,other elements <0.05 each and <0.10 in total. The product is treated by solution heat treating, quenching and possibly aging, and has in the treated T7451 or T7452 temper the following properties:a) a yield strength measured at quarter-thickness>400 MPa in the L and TL directions,b) toughness under plane strain in the S-L direction>26 MPa.sqroot.m and in the L-T direction >74-0.08e-0.07R.sub.0.2L MPa.sqroot.m (e=thickness in mm), andc) a stress corrosion threshold>240 MPa.