The invention relates to a thin sheet, the thickness of which is less than 12.7 mm, having an essentially recrystallised granular structure, made from an aluminium-based alloy comprising 2.5 to 3.5% by weight of Cu, 0.7 to 0.9% by weight of Li, 0.3 to 0.5% by weight of Mg, 0.2 to 0.5% by weight of Mn, 0.25 to 0.65% by weight of Zn, 0.01 to 0.15% by weight of Ti, 0 to 0.07% by weight of Ag, an amount of Fe and of Si of less than or equal to 0.1% by weight each, and inevitable impurities at a content of less than or equal to 0.05% by weight each and 0.15% by weight in total, with the remainder being aluminium.
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22C 21/18 - Alloys based on aluminium with copper as the next major constituent with zinc
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
2.
SUSTAINABLE REMELTING LINE FOR ALUMINIUM ALLOY SCRAP
The invention relates to a scrap remelting line comprising at least one storage silo configured to store scrap, at least two induction furnaces for remelting the scrap and obtaining the remelted liquid metal, a means for supplying the scrap to the at least two induction furnaces, at least one furnace receiving the liquid metal (6), and a means for transporting the remelted liquid metal (5, 15) to the receiving furnace. The invention also relates to the method for obtaining liquid metal from scrap remelted in induction furnaces.
The invention relates to the method for melting a charge of aluminium, comprising: procuring a charge (11, 12, 13) of aluminium of which at least 15 wt% is in the form of a bowl (11) of essentially cylindrical shape, of height h and maximum diameter d; loading the charge into a cylindrical induction furnace (10) of height H and of maximum inside diameter D, where the height direction of the bowl is substantially parallel to the height direction of the furnace; melting the charge using induction to obtain a bath of liquid metal (2); and optionally adjusting the composition of the liquid metal where d is in the range 0.7D to 0.97D and preferably in the range 0.84D to 0.92D.
F27B 14/06 - Crucible or pot furnacesTank furnaces heated electrically, e.g. induction crucible furnaces, with or without any other source of heat
F27B 14/08 - Details specially adapted for crucible, pot or tank furnaces
F27D 3/00 - ChargingDischargingManipulation of charge
F27D 11/06 - Induction heating, i.e. in which the material being heated, or its container or elements embodied therein, form the secondary of a transformer
4.
WROUGHT PRODUCTS MADE OF 2XXX ALLOY HAVING AN OPTIMIZED CORROSION RESISTANCE, AND METHOD FOR OBTAINING SAME
Method for thermomechanical treatment of wrought products made of 2000 series aluminum alloy comprising, in % by weight, Cu 3.5 - 5.8; Mg 0.2 - 1.5; Mn = 0.9; Fe = 0.15; Si = 0.15; Zr = 0.25; Ag = 0.8; Zn = 0.8; Ti 0.02-0.15; unavoidable impurities = 0.05 each and = 0.15 in total; remainder aluminum, enabling an improvement in the stress corrosion resistance. It comprises a tempering consisting of two sequences. The first sequence is defined by a maximum temperature T1max between 130°C and 180°C and by a hold time at a temperature between 130°C and 180°C which equates to an equivalent time (formula i) calculated at 160°C between 10 h and 80 h. The second sequence is defined by a temperature T2°c (t) below T1max and a hold time t2 at a temperature between 100°C and 130°C, which equates to an equivalent time (formula ii) calculated at 160°C such that (formula iii) is between 0.3% and 15% of the equivalent time (formula iv) calculated for the first sequence.
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
5.
USE OF PRODUCTS MADE FROM ALUMINIUM COPPER MAGNESIUM ALLOY THAT PERFORM WELL AT HIGH TEMPERATURE
The invention relates to the use of a wrought T8 aluminium alloy product with the following composition, in wt%, Cu: 3.6 4.4; Mg: 1.2 1.4; Mn: 0.5 0.8; Zr: = 0.15; Ti: 0.01 0.15; Si = 0.20; Fe = 0.20; Zn = 0.25; other elements < 0.05; the remainder being aluminium, in an application in which the product is kept at temperatures of between 80°C and 250°C for a significant period of at least 200 hours. The products intended for the use according to the invention are particularly useful in an application such as a rotor or another component of an air suction pump such as, in particular, a vacuum pump.
C22C 21/14 - Alloys based on aluminium with copper as the next major constituent with silicon
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22C 21/18 - Alloys based on aluminium with copper as the next major constituent with zinc
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
F04D 19/04 - Multi-stage pumps specially adapted to the production of a high vacuum, e.g. molecular pumps
The invention relates to a process for manufacturing a thin sheet made of an aluminum-based alloy comprising, in percent by weight, 2.2 to 2.7% Cu,1.3 to 1.6% Li, less than 0.1% Ag, 0.2 to 0.5% Mg, 0.1 to 0.5% Mn, 0.01 to 0.15% Ti, less than 0.3% Zn, no more than 0.1% Fe and no more than 0.1% Si, and inevitable impurities at a content of no more than 0.05% by weight each and 0.15% by weight in total, the remainder being aluminum, wherein, in particular, the hot-rolling input temperature is between 400°C and 460°C and the hot-rolling output temperature is less than 300°C, the mean heating rate during the solution heat treatment is at least approximately 17°C/min between 300°C et 400°C, and the tempering conditions such as the 0.2% offset yield strength in the transverse direction Rp0.2(TL) ranges from 350 to 380 MPa. The sheets according to the invention have advantageous mechanical properties and are used in particular for manufacturing aircraft fuselage panels.
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
Device for degassing liquid metal comprising an enclosure containing a bath of liquid metal, a device for circulating a gas through a purification chamber and in that the purification chamber comprises a getter material configured to trap the dihyrogen of the circulating gas. Method for degassing a bath of liquid metal in order to reduce the hydrogen concentration of the liquid metal, comprising the following steps a) producing a bath of liquid metal, preferably an aluminum alloy, b) circulating a gas, c) exchanging hydrogen from the circulating gas with the liquid metal so that the hydrogen dissolved in the bath of liquid metal diffuses into the circulating gas and enriches the circulating gas in dihydrogen, d) purifying the circulating gas enriched in dihydrogen in a purification chamber comprising a getter material configured to trap the dihydrogen of the circulating gas.
The invention relates to a rolled aluminum-based alloy product having a thickness of at least 80 mm comprising, (in weight %) : Zn 6.85 7.25, Mg 1.55 1.95, Cu 1.90 2.30, Zr 0.04 0.10, Ti 0 0.15, Fe 0 0.15, Si 0 0.15, other elements = 0.05 each and = 0.15 total, remainder Al, wherein at mid-thickness more than 75 % of grains are recrystallized or at mid-thickness 30 to 75 % of grains are recrystallized and non- recrystallized grains have an aspect ratio in a L/ST cross section less than 3. A process for the manufacture of a rolled aluminum-based alloy product comprises the steps of: (a) casting an ingot made in an alloy according to the invention, (b) conducting an homogenization of the ingot (c) conducting hot rolling of said homogenized ingot in one or more stages by rolling, (d) conducting a solution heat treatment a quench, (e) conducting stress relieving, and, (f) conducting an artificial aging treatment. The products of the invention are suitable for aircraft construction and have advantageous fatigue crack growth properties.
C22C 21/10 - Alloys based on aluminium with zinc as the next major constituent
C22F 1/053 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with zinc as the next major constituent
9.
METAL SHEET MADE OF HIGH-STRENGTH 2XXX ALLOY FOR AN AIRCRAFT FUSELAGE
The invention relates to a thin metal sheet which is made of an alloy based on substantially recrystallized aluminum and which has a thickness of 0.25 to 12 mm, the alloy comprising, in percent by weight, Cu 3.4-4.0; Mg 0.50.8; Mn 0.10.7; Fe = 0.15; Si = 0.15; Zr = 0.04; Ag = 0.65; Zn = 0.5; inevitable impurities = 0.05 each and = 0.15 in total, the remainder consisting of aluminum. The invention also relates to a process for manufacturing such a metal sheet and to the use thereof as a fuselage panel or sheet metal for the production of composite products such as fiber metal laminates (FML) for wing or fuselage applications in the aeronautical industry.
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22C 21/18 - Alloys based on aluminium with copper as the next major constituent with zinc
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
10.
THIN SHEETS MADE OF ALUMINIUM-COPPER-LITHIUM ALLOY FOR AIRCRAFT FUSELAGE MANUFACTURE
The invention concerns a method for manufacturing a thin sheet made of aluminium-based alloy comprising, in per cent by weight, 2.3 to 2.7% Cu,1.3 to 1.6% Li, 0.2 to 0.5% Mg, 0.1 to 0.5% Mn, 0.01 to 0.15% Ti, a quantity of Zn less than 0.3, a quantity of Fe and of Si less than or equal to 0.1% each, and unavoidable impurities at a content less than or equal to 0.05% by weight each and 0.15% by weight in total, wherein, in particular, the hot-rolling input temperature is between 400°C and 445°C and the hot-rolling output temperature is less than 300°C. The sheets according to the invention have advantageous mechanical properties and are used, in particular, for the manufacture of aircraft fuselage panels.
C22C 21/12 - Alloys based on aluminium with copper as the next major constituent
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
11.
ALLIAGE ALUMINIUM CUIVRE LITHIUM A RESISTANCE EN COMPRESSION ET TENACITE AMELIOREES
The invention relates to a product based on an aluminium alloy comprising, as percentages by weight, 4.0 to 4.6% by weight of Cu, 0.7 to 1.2% by weight of Li, 0.5 to 0.65% by weight of Mg, 0.10 to 0.20% by weight of Zr, 0.15 to 0.30% by weight of Ag, 0.25 to 0.45% by weight of Zn, 0.05 to 0.35% by weight of Mn, at most 0.20% by weight of Fe + Si, at least one element selected from Cr, Sc, Hf, V and Ti, the amount of said element, if selected, being from 0.05 to 0.3% by weight for Cr and for Sc, 0.05 to 0.5% by weight for Hf and for V and 0.01 to 0.15% by weight for Ti, the other elements being at most 0.05% by weight each and 0.15% by weight in total, the remainder being aluminium. The invention also relates to a method for obtaining such a product and to the use thereof as an aircraft structural element.
C22C 21/12 - Alloys based on aluminium with copper as the next major constituent
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22C 21/18 - Alloys based on aluminium with copper as the next major constituent with zinc
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
12.
METHOD FOR MANUFACTURING AN ALUMINUM-COPPER-LITHIUM ALLOY HAVING IMPROVED COMPRESSIVE STRENGTH AND IMPROVED TOUGHNESS
The invention relates to a manufacturing method in which an alloy is prepared that comprises 3.5 to 4.7 wt% of Cu; 0.6 to 1.2 wt% of Li; 0.2 to 0.8 wt% of Mg; 0.1 to 0.2 wt% of Zr; 0.0 to 0.3 wt% of Ag; 0.0 to 0.8 wt% of Zn; 0.0 to 0.5 wt% of Mn; at most 0.20 wt% of Fe + Si; optionally an element selected from Cr, Sc, Hf and V, the amount of said element, if selected, being from 0.05 to 0.3 wt% for Cr and for Sc, 0.05 to 0.5 wt% for Hf and for V; the other elements being at most 0.05 wt% each and 0.15 wt% in total, a refiner is introduced, the alloy is cast in a crude form, homogenized, hot-worked, solution heat-treated, quenched, cold-worked, and tempered, in which the refiner contains particles of TiC and/or the cold working is between 8 and 16%. The products obtained by the method according to the invention have an advantageous compromise between mechanical strength and toughness.
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22C 21/18 - Alloys based on aluminium with copper as the next major constituent with zinc
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
13.
IMPROVED PROCESS FOR MANUFACTURING SHEETS MADE OF ALUMINIUM-COPPER-LITHIUM ALLOY FOR AIRCRAFT FUSELAGE MANUFACTURE
The subject of the invention is a process for manufacturing a wrought product made of aluminium alloy comprising the following steps : a) casting a plate made of alloy comprising, in percentages by weight, Cu: 2.1 to 2.8; Li: 1.1 to 1.7; Mg: 0.2 to 0.9; Mn: 0.2 to 0.6; Ti: 0.010.2; Ag < 0.1; Zr < 0.08; Fe and Si = 0.1 each; unavoidable impurities = 0.05% each and 0.15% in total; remainder aluminium; b) homogenizing said plate at 480-520°C for 5 to 60 hours; c) hot-rolling and optionally cold-rolling said homogenized plate to give a sheet; d) solution annealing the sheet at 470-520°C for 5 minutes to 4 hours; e) quenching the solution-annealed sheet; f) controlled tensioning of the solution-annealed and quenched sheet with a permanent set of 1 to 6%; g) tempering of the tensioned sheet by heating at a temperature of at least 160°C for a maximum time of 30 hours.
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
14.
AL-ZN-CU-MG ALLOYS WITH HIGH STRENGTH AND METHOD OF FABRICATION
The invention relates to a rolled product made of aluminum alloy with a thickness of at least 50 mm comprising (in weight%): Zn 6.9 - 7.5; Mg 1.8 - 2.2; Cu 1.8 - 2.2, where the sum Cu + Mg is between 3.8 and 4.2; Zr 0.04 -0.14; Mn 0 - 0.1; Ti 0 - 0.15; V 0 - 0.1; Fe = 0.15; Si = 0.15; impurities = 0.05 each and = 0.15 total, balance aluminum. The invention also relates to the method of manufacturing such a product. The products according to the invention are particularly advantageous because they have a very favorable compromise between static mechanical strength, toughness and environmental-assisted cracking performance under conditions of high stress and humid environment.
C22C 21/10 - Alloys based on aluminium with zinc as the next major constituent
C22F 1/053 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with zinc as the next major constituent
15.
AL- ZN-CU-MG ALLOYS AND THEIR MANUFACTURING PROCESS
The invention concerns an extruded, rolled and/or forged aluminum-based alloy product having a thickness of at least 25 mm comprising (in weight %) :; Zn 6.70 7.40; Mg.50 1.80; Cu 2.20 2.60, with a Cu to Mg ratio of at least 1.30; Zr 0.04 0.14; Mn 0 0.5; Ti 0 0.15; V 0 0.15; Cr 0 0.25; Fe 0 0.15; Si 0 0.15; impurities = 0.0 each and = 0.15 total. The invention also concerns a method of making such a product. Products according to the invention are particularly advantageous because they exhibit simultaneously a low sensitivity to environmentally assisted cracking under conditions of high stress and humid environment, high strength and high toughness properties.
C22C 21/10 - Alloys based on aluminium with zinc as the next major constituent
C22F 1/053 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with zinc as the next major constituent
16.
THIN SHEETS MADE OF ALUMINIUM-COPPER-LITHIUM ALLOY FOR AIRCRAFT FUSELAGE MANUFACTURE
The invention concerns a method for manufacturing a brushed rolled product made from Al-Cu-Li alloy with a thickness of less than 12 mm, comprising the steps of producing a rolled product, solution heat treatment and quenching, stress relieving, optionally tempering, and brushing, characterised in that the brushing tool applies a force to the rolled product generating residual compressive stresses at the surface of the brushed product; eliminates a thickness of at least 9 µm from the surface of the non-brushed rolled product; wherein the brushing step comprises at least one circular brushing motion. The rolled product obtained by the method according to the invention is advantageous. The use of such a product in an aircraft fuselage panel is advantageous.
B23P 9/00 - Treating or finishing surfaces mechanically, with or without calibrating, primarily to resist wear or impact, e.g. smoothing or roughening turbine blades or bearingsFeatures of such surfaces not otherwise provided for, their treatment being unspecified
B24B 39/00 - Burnishing machines or devices, i.e. requiring pressure members for compacting the surface zoneAccessories therefor
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
17.
ALUMINIUM ALLOY COMPRISING LITHIUM WITH IMPROVED FATIGUE PROPERTIES
An aluminium alloy comprising lithium with improved mechanical strength and toughness. The invention relates to a 2XXX wrought alloy product comprising from 0.05 to 1.9% by weight of Li and from 0.005 to 0.045% by weight of Cr and/or of V. The invention also relates to an as-cast 2XXX alloy product comprising from 0.05 to 1.9% by weight of Li and from 0.005 to 0.045% by weight of Cr and/or of V. Finally, the invention relates to an aircraft structure element, preferably a lower surface or upper surface element, the skin and stiffeners of which originate from the same starting material, a spar or a rib, comprising a wrought product.
The invention relates to a product made of an aluminium-based alloy comprising, by wt. %, Cu: 2.4-3.2; Li: 1.6-2.3; Mg: 0.3-0.9; Mn: 0.2-0.6; Zr: 0.12-0.18; such that Zr = - 0.06*Li + 0.242; Zn: < 1.0; Ag: < 0.15; Fe + Si = 0.20; optionally, at least one element selected from Ti, Sc, Cr, Hf and V, the content of the element, if selected, being: Ti: 0.01-0.1; Sc: 0.01-0.15; Cr: 0.01-0.3; Hf: 0.01-0.5; V: 0.01-0.3; other elements = 0.05 each and = 0.15 in total; the remainder being aluminium. The invention also relates to a method for manufacturing an as-cast aluminum alloy product according to the invention, comprising the following steps: preparing a liquid metal bath; casting an as-cast shape from said liquid metal bath; and solidifying the as-cast shape into a billet, a rolling plate or a forging blank; characterised in that the casting is performed without adding any grain refiner, or by adding a refiner comprising (i) Ti and (ii) B or C, such that the content of B from the refiner is less than 45 ppm, and that of C is less than 6 ppm, and/or characterised in that the casting is carried out, for an as-cast shape of thickness E or with a diameter D greater than 150 mm, at a casting rate v (mm/min) greater than 30 for a plate-type as-cast shape or 9000/D for a billet-type as-cast shape.
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22C 21/18 - Alloys based on aluminium with copper as the next major constituent with zinc
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
The invention relates to a product made of an aluminium-based alloy comprising, by wt. %, Cu: 2.5-3.4; Li: 1.6-2.2; Mg: 0.4-0.9; Mn: 0.2-0.6, Zr: 0.08-0.18; Zn: < 0.4; Ag: < 0.15; Fe + Si = 0.20; at least one element selected from Ti, Se, Cr, Hf and V, the content of the element, if selected, being: Ti: 0.01-0.15; Se: 0.01-0.15; Cr: 0.01-0.3; Hf: 0.01-0.5; V: 0.01-0.3; other elements = 0.05 each and = 0.15 in total; the remainder being aluminium. The invention also relates to a method for manufacturing an aluminum alloy-based, extruded, rolled and/or forged product, and a structural element incorporating at least one product as described above.
C22C 21/12 - Alloys based on aluminium with copper as the next major constituent
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22C 21/18 - Alloys based on aluminium with copper as the next major constituent with zinc
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
20.
METHOD FOR IMPROVING THE WETTING OF A SURFACE OF A SOLID SUBSTRATE BY A LIQUID METAL
The invention relates to a method for treating a solid substrate, performed with a first material, of the metal or ceramic type, the method comprising bringing the substrate into contact with a liquid metal, while the substrate is exposed to an ultrasound wave called a power ultrasound wave. On a surface of the substrate, the power flux density is higher than a cavitation threshold of the liquid metal. Such an exposition improves the wettability of the surface of the substrate by the liquid metal.
B01J 19/10 - Processes employing the direct application of electric or wave energy, or particle radiationApparatus therefor employing sonic or ultrasonic vibrations
21.
METHOD FOR THE HYBRID PRODUCTION OF A STRUCTURAL ELEMENT COMPRISING ONE OR MORE STIFFENERS
The invention relates to a method for the production of a metal structural element from a workpiece, said metal structural element comprising a skin having stiffeners extending therefrom. According to the invention, one portion of the stiffeners is produced by machining, while the other portion is produced by adding material. The material can be added using an additive manufacturing process.
B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
B22F 7/04 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite layers with one or more layers not made from powder, e.g. made from solid metal
B22F 7/08 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite workpieces or articles from parts, e.g. to form tipped tools with one or more parts not made from powder
B23K 26/34 - Laser welding for purposes other than joining
22.
THIN SHEETS MADE OF AN ALUMINIUM-MAGNESIUM-SCANDIUM ALLOY FOR AEROSPACE APPLICATIONS
The invention relates to a method for producing a hot-worked product made of an aluminium alloy composed, in wt%, of Mg: 3.8-4.2; Mn: 0.3-0.8 and preferably 0.5-0.7, Sc: 0.1-0.3; Zn: 0.1-0.4; Ti: 0.01-0.05; Zr: 0.07-0.15; Cr: <0.01; Fe: <0.15; Si <0.1; wherein the homogenisation is carried out at a temperature of between 370°C and 450°C, for between 2 and 50 hours, such that the equivalent time at 400°C is between 5 and 100 hours, and the hot deformation is carried out at an initial temperature of between 350°C and 450°C. The invention also relates to hot-worked products obtained by the method according to the invention, in particular sheets with a thickness of less than 12mm. The products according to the invention are advantageous as they offer a better compromise in terms of mechanical strength, toughness and hot-formability.
C22C 21/06 - Alloys based on aluminium with magnesium as the next major constituent
C22F 1/047 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with magnesium as the next major constituent
23.
SYSTEM AND METHOD FOR CONTROLLING THE CASTING OF A PRODUCT
A system (100) for controlling the progress of the manufacture of at least one product by vertical semi-continuous direct chill casting, in particular from aluminium alloy, in a respective fixed mould (41), said control system (100) comprising: - at least one respective dummy bottom (4) configured to form a movable lower bottom of the respective fixed mould and to carry the product during casting; - at least one weighing cell (3), on which the respective dummy bottom (4) is arranged to rest, the weighing cell (3) being configured to take measurements representative of the mass of the product carried by the respective dummy bottom (4) during casting; and - a support (2) of the dummy bottom, to which the weighing cell (3) is linked, configured to lower the/each false bottom (4) relative to the respective fixed mould (41), substantially in a vertical direction, during casting; - at least one processing unit (21) connected to the/each weighing cell (3), and configured to process the measurements, and calculate the variation in the mass of the product over time.
The invention relates to a rolled product having a thickness of at least 50 mm made of aluminium alloy comprising, in % by weight, 2.2% to 3.9% of Cu, 0.7% to 1.8% of Li, 0.1% to 0.8% of Mg, 0.1% to 0.6% of Mn; 0.01% to 0.15% of Ti, at least one element chosen from Zn and Ag, the amount of said element, if it is chosen, being 0.2% to 0.8% for Zn and 0.1% to 0.5% for Ag, optionally at least one element chosen from Zr, Cr, Sc, Hf, and V, the amount of said element, if it is chosen, being 0.04% to 0.18% for Zr, 0.05% to 0.3% for Cr and for Sc, 0.05% to 0.5% for Hf and for V, less than 0.1% of Fe, less than 0.1% of Si, the remainder being aluminium and inevitable impurities, having a content of less than 0.05% each and 0.15% in total; characterized in that its granular structure is predominantly recrystallised between ¼ and ½ thickness. The invention also relates to the process for manufacturing such a product. The products according to the invention are advantageously used in aircraft construction, in particular for the production of an aircraft wing spar or rib.
The invention is a rolled and/or forged product, made of an aluminium-based alloy comprising, in % by weight, Cu: 3.2 - 4.0; Li: 0.80 - 0.95; Zn: 0.45 - 0.70; Mg: 0.15 - 0.7; Zr: 0.07 - 0.15; Mn: 0.1 - 0.6; Ag : < 0.15; Fe + Si = 0.20; at least one element from Ti: 0.01-0.15; Se: 0.02 - 0.1; Cr: 0.02 - 0.1; Hf: 0.02 - 0.5; V: 0.02 - 0.1; other elements = 0.05 each and = 0.15 in total, remainder aluminium. In the process for manufacturing the products according to the invention a bath of liquid metal based on aluminium as alloy according to the invention is melted, an unwrought product is cast from said bath of liquid metal; said unwrought product is homogenized at a temperature between 450°C and 550°C; said unwrought product is hot worked and optionally cold worked preferably to a thickness of at least 15 mm: said product is solution treated between 490°C and 530°C for 15 min to 8 h and quenched; said product is drawn in a controlled manner with a permanent deformation of 1% to 7% and a tempering of said product is carried out. The product is advantageous for the manufacture of an aircraft structural component.
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22C 21/18 - Alloys based on aluminium with copper as the next major constituent with zinc
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
26.
THIN SHEETS MADE FROM ALUMINIUM-MAGNESIUM-ZIRCONIUM ALLOYS FOR AEROSPACE APPLICATIONS
The invention relates to a wrought aluminium alloy product having composition, in percent by weight, Mg: 4.0-5.5; Li: 0.4-0.7; Mn: 0.5-0.9; Zr: 0.08-0.15; Si: = 0.2; Fe: = 0.25; Zn: = 0.4; Sc: = 0.4; Ti: = 0.15; Er, Yb, Gd, Y, Hf and/or Nb: = 0.2; other elements = 0.05 each and = 0.15 in association; the remainder being aluminium. The invention also relates to a method for producing said wrought aluminium alloy product, comprising the successive steps of: casting a crude shape in aluminium alloy; optionally, homogenising; hot deforming of the crude shape at a deformation end temperature greater than 250 °C; heat treatment or thermomechanical treatment at a temperature between 250 and 350°C, as well as the use of said wrought product for producing aluminium structural elements of aircraft, having undergone a heat treatment or a thermomechanical treatment at a temperature between 250 and 350 °C and having, at mid-thickness, for a thickness of 0.5 to 30 mm, an essentially non-recrystallised microstructure.
C22C 21/06 - Alloys based on aluminium with magnesium as the next major constituent
C22F 1/047 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with magnesium as the next major constituent
27.
EXTRUDED PRODUCT MADE FROM AL-CU-MG ALLOY WITH IMPROVED COMPROMISE BETWEEN MECHANICAL RESISTANCE AND TOUGHNESS
The invention relates to an extruded product made from an alloy of composition (% by weight): Cu: 5.05-5.35; Mg: 0.20-0.40; Mn: 0.20-0.40; Zr: 0.08-0.1; Ti: 0.01-0.15; Zn: 0-0.15; Si < 0.10; Fe < 0.15 and other elements < 0.05 each and < 0.15 in total, the remainder being Al, treated by dissolving, at a temperature between 525 and 540 °C, quenching, controlled traction during quenching until a permanent deformation of at least 1.5% is achieved, and returning to a temperature of between 160 and 190 °C. The products according to the invention are particularly well suited to use as pistons in an internal combustion engine of a vehicle and in particular of a racing car.
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
Process for using a wetted tubular sonotrode. The process comprises the following steps: a) providing a tubular sonotrode (1) formed from a material that is substantially inert to liquid aluminium, such as a ceramic, for example a silicon oxynitride, the sonotrode comprising a first end region (2) that is open and a second end region (3) that is preferably closed, b) at least partly immersing the open end region (2) of the tubular sonotrode (1) in the liquid aluminium alloy, and c) applying powerful ultrasonic waves to the liquid aluminium alloy by means of the tubular sonotrode (1).
The invention relates to a method which comprises the following steps: a) providing a sonotrode (1) made of a material that is essentially inert in the liquid metal, such as a ceramic, and preferably a silicon nitride or a silicon oxynitride, such as SIALON, or a metal that is essentially inert in said liquid metal; b) at least partially dipping the sonotrode (1) into a bath of said metal; c) applying powerful ultrasounds to the sonotrode (1), in particular ultrasounds with a power of more than 10 watts, such as to obtain the wetting of said sonotrode by said metal; d) continuously applying measurement ultrasounds to the sonotrode (1), also referred to as inspection ultrasounds, in particular ultrasounds with a frequency of 1 to 25 MHz; e) intermittently applying powerful ultrasounds to the sonotrode (1), in particular ultrasounds with a power of more than 10 watts, in order to maintain said wetting.
G01N 29/036 - Analysing fluids by measuring frequency or resonance of acoustic waves
G01N 29/28 - Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic wavesVisualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object Details providing acoustic coupling
G01S 15/88 - Sonar systems specially adapted for specific applications
The invention relates to a method which comprises the following steps: a) providing a first bath of a liquid metal (1) comprising aluminium with a content X and magnesium with a content Y, the content Y of magnesium being other than zero; b) at least partially dipping a sonotrode (3), made of a material that is inert in liquid aluminium, into the first bath of liquid metal (1); and c) applying powerful ultrasounds to the sonotrode (3) so as to energise the liquid metal (1) until the wetting (5) of the sonotrode (3) by the liquid metal (1) is achieved; d) cooling the first liquid metal (1) of the first bath until the first liquid metal (1) solidifies around the sonotrode (3), generating an intimate bond (6) between the sonotrode (3) and the first solidified liquid metal (1), said bond having a bond strength substantially equal to that of brazing between two metals; and e) machining the solidified first metal (1) in the shape of a clamp (7) configured for attaching a mechanical amplifier and/or a transducer (4).
G01N 29/28 - Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic wavesVisualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object Details providing acoustic coupling
The invention concerns a sheet 0.5 to 9 mm thick, having an essentially recrystallised granular structure made from an aluminium alloy comprising 2.8 to 3.2 % by weight of Cu, 0.5 to 0.8 % by weight of Li, 0.1 to 0.3 % by weight of Ag, 0.2 to 0.7 % by weight of Mg, 0.2 to 0.6 % by weight of Mn, 0.01 to 0.15 % by weight of Ti, a quantity of Zn of less than 0.2 % by weight, a quantity of Fe and of Si of less than 0.1 % each by weight, and inevitable impurities in a content less than or equal to 0.05% each by weight and 0.15% in total by weight, said sheet being obtained by a method comprising pouring, soaking, hot rolling and optionally cold rolling, solution annealing, quenching and tempering. The sheets according to the invention are particularly advantageous for producing aircraft fuselage panels.
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
32.
METHOD FOR RECYCLING SCRAP OF 2XXX OR 7XXX SERIES ALLOYS
The invention relates to a method for manufacturing an ingot made of an aluminium alloy using scrap of series 2xxx or 7xxx aluminium alloys, which includes the steps of: (i) provisioning the scrap of series 2xxx or 7xxx aluminium alloys; (ii) optionally separating the oil found on the scrap; (iii) performing a first operation of treating said scrap with a first liquid at a temperature of at least 10 °C, said first liquid being an aqueous solution having a pH of 1 to 5 or of 8 to 13; (iv) separating the first liquid and the scrap thus treated; (v) performing at least one second operation of treating said scrap using a second liquid; (vi) separating the second liquid and the scrap thus treated; (vii) melting down said scrap thus obtained; (viii) optionally performing a first solidification to an intermediate unwrought product; and (viii) casting an ingot of aluminium alloy of the series of the scrap used. The invention also relates to a method for manufacturing, after rolling, extruding and/or forging, an aeronautical structural element including, in addition to the steps of the preceding method, at least one step of rolling, extruding and/or forging said ingot of aluminium alloy of the series of the scrap used.
The invention relates in particular to an unprocessed extruded product for manufacturing a machined extruded product for the aeronautical industry, made of an Al-Cu-Li alloy with the following composition, as weight percentages: Cu: 2.0 - 6.0; Li: 0.5 - 2.0; Mg: 0 - 1.0; Ag: 0 - 0.7; Zn 0 - 1.0; and at least one element selected among Zr, Mn, Cr, Se, Hf and Ti, the amount of said element, if chosen, being 0.05 to 0.20 wt % for Zr, 0.05 to 0.8 wt % for Mn, 0.05 to 0.3 wt % for Cr and for Se, 0.05 to 0.5 wt % for Hf and 0.01 to 0.15 wt % for Ti, Si = 0.1; Fe = 0.1; others = 0.05 each and = 0.15 in total, the balance being aluminium, having an unprocessed core (21) with an aspect ratio of at least 5 and at least one unprocessed flank (22) with an aspect ratio of less than 4 and in which the length direction is substantially perpendicular to the lengthwise direction of the core, characterised in that a portion of the unprocessed flank (22) connecting the unprocessed flank to the unprocessed core has decreasing thickness and in that the ratio of the thickness of said unprocessed flank (22) at the end of said unprocessed flank connected to the web (E221) to that at the end thereof opposite the core (E222) i.e. E221/E222 is less than 0.8, thus defining two substantially symmetrical concave areas. The invention also relates to the method for manufacturing a machined extruded product and to the corresponding machined extruded product. The products according to the invention are useful in particular for manufacturing floor beams and girders.
C22C 21/12 - Alloys based on aluminium with copper as the next major constituent
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
34.
PRODUCTS MADE OF ALUMINIUM-COPPER-LITHIUM ALLOY WITH IMPROVED FATIGUE PROPERTIES
The invention relates to a metal sheet with a thickness of at least 80 mm made of an aluminium alloy including, as weight percentages: Cu: 2.0 - 6.0; Li: 0.5 - 2.0; Mg: 0 - 1.0; Ag: 0 - 0.7; Zn 0 - 1.0; and at least one element selected among Zr, Mn, Cr, Se, Hf and Ti, the amount of said element, if chosen, being 0.05 to 0.20 wt % for Zr, 0.05 to 0.8 wt % for Mn, 0.05 to 0.3 wt % for Cr and for Se, 0.05 to 0.5 wt % for Hf and 0.01 to 0.15 wt % for Ti, Si = 0.1; Fe = 0.1; others = 0.05 each and = 0.15 in total, characterised in that in the tempered state the logarithmic mean of the fatigue thereof, as measured at mid-thickness in the TL direction on smooth test pieces with a maximum amplitude constraint of 242 MPa, a frequency of 50 Hz and a stress ratio of R = 0.1, is at least 250,000 cycles. The product according to the invention is obtained by a method which, in particular, has specific casting conditions. The use of a metal sheet according to an invention is advantageous for manufacturing an aeroplane structural element, preferably a spar, ribs or a frame.
The invention relates to a method for manufacturing an aluminium alloy product including the steps of: creating a bath of liquid metal in an aluminium - copper - lithium alloy, casting said alloy by vertical semi-continuous casting so as to obtain a plate with thickness T and width W such that, during solidification, the hydrogen content of said liquid metal bath (1) is lower than 0.4 ml/100 g, the oxygen content above the liquid surface (14, 15) is less than 0.5 % by volume, the distributor used (7) for casting is made of a fabric including essentially carbon, including a lower surface (76), an upper surface defining the opening through which the liquid metal is inserted (71) and a wall with a substantially rectangular section, the wall containing two longitudinal portions parallel to the width W (720, 721) and two transverse portions parallel to the thickness T (730, 731) said transverse and longitudinal portions being formed by at least two fabrics, a first substantially sealing and semi-rigid fabric (77) ensuring that the distributor keeps its shape during casting, and a second non-sealing fabric (78) allowing the passage and filtration of the liquid, said first and second fabrics being connected to one another with no overlap and no gaps separating same, said first fabric continuously covering at least 30 % of the surface of said wall portions (720, 721, 730, 731) and being positioned such that the liquid surface is in contact with same over the entire section.
The invention relates to a method for manufacturing a laminated or forged material, the thickness of which is 14 to 100 mm. Said material is made of an aluminum alloy composed, in wt%, of: 1.8-2.6 Cu; 1.3-1.8 Li; 0.1-0.5 Mg; 0.1-0.5 Mn and Zr <0.05, or Mn <0.05 and 0.10-0.16 Zr; Ag 0-0.5 Ag; Zn <0.20; 0.01-0.15 Ti; Fe <0.1; Si <0.1; other elements <0.05 each and <0.15 total; and aluminum residue, the density of which is lower than 2.670 g/cm3. Said method includes: homogenizing; hot working under conditions such that, when the manganese content is 0.1 to 0.5 wt% and the zirconium content is lower than 0.05 wt%, the final hot working temperature is at least 400°C, and when manganese content is lower than 0.05 wt% and zirconium content is 0.1 to 0.16 wt%, the final hot working temperature is at most 400°C; placement in solution; quenching; controlled stretching; and tempering. The materials obtainable according to the invention have: a thickness of 20 mm to 50 mm; an elastic limit of at least 390 MPa at mid-thickness Rpo,2(L); a rigidity KappL-T (W=406 mm) of at least 105 MPAvm, even after aging of 3,000 hours at 85°C; and at least 250,000 cycles under the condition 6.5 MPavm < ?K < 16.6 MPavm for a fatigue test, carried out according to ASTM standard E647, in CCT test tubes having a width of 160 mm, with samples taken in the L-T direction at ¼ thickness. The materials according to the invention are particularly suitable for manufacturing airplane underwing elements.
B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
37.
UNDERWING SHEET METAL WITH IMPROVED DAMAGE TOLERANCE PROPERTIES
The invention relates to a rolled product with state T351, having thickness of between 15 and 50 mm, made from aluminium alloy having the following composition, in % by weight, Cu: 3.85 - 4.15; Mg: 0.95 - 1.25; Mn: 0.45 - 0.57; Zr: 0.09 - 0.16; Ti: 0.005 - 0.1; Fe: < 0.070; Si: < 0.060; with Cu + Mg = 5.15; other lesser elements 0.05 each and less than 0.15 in total, the remainder being aluminium. In the manufacturing method for a rolled product according to the invention, an alloy according to the invention is prepared and poured by adding a refiner of type A1TiB or A1TiC to obtain a rolling plate, optionally, said rolling plate is homogenised at a temperature between 480 °C and 510 °C, said optionally homogenised rolling plate being hot rolled to obtain a sheet of thickness e, between 15 and 50 mm, said sheet is solution heat-treated at a temperature between 480 and 505 °C for a period t, expressed in hours, such that t = e / 7, said sheet metal solution heat-treated in this way is then quenched, said sheet metal is cold drawn and thus hardened with a deformation of between 1.5 and 3% and aged at room temperature. The metal sheets according to the invention present, in particular, an advantageous compromise between static mechanical strength, toughness and the propagation of fatigue cracks under inspection and are advantageous for the manufacture of underwing elements of an aircraft wing.
C22C 21/12 - Alloys based on aluminium with copper as the next major constituent
C22C 21/14 - Alloys based on aluminium with copper as the next major constituent with silicon
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22F 1/04 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
38.
EXTRADOS STRUCTURAL ELEMENT MADE FROM AN ALUMINIUM COPPER LITHIUM ALLOY
The invention relates to an extrados structural element made from an aluminium, copper and lithium alloy and a method for manfacturing same. In the method according to the invention, an alloy with composition (in wt%) 4.2 to 5.2 Cu, 0.9 to 1.2 Li, 0.1 to 0.3 Ag, 0.1 to 0.25 Mg, 0.08 to 0.18 Zr, 0.01 to 0.15 Ti, optionally upt o 0.2 Zn, optionally up to 0.6 Mn, an Fe and Si content level less than or equal to 0.1% each, and other element with a content level less than or equal to 0.05% each and 0.15% in total, the aluminium is poured, homogenised, deformed hot and optionally cold, placed in a solution at a temperature of at least 515°C, pulled from 0.5 to 5% and annealed. The combination in particular of the magnesium, copper and manganese content with the temperature in solution can reach a very advantageous elasticity under compression limit. Thus, the products according to the invention having a thickness of at least 12 mm have an elasticity under compression limit in the longitudinal direction of at least 645 MPa and an elongation in the longitudinal direction of at least 7%.
C22C 21/12 - Alloys based on aluminium with copper as the next major constituent
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
39.
METHOD FOR TRANSFORMING AL-CU-LI ALLOY SHEETS IMPROVING FORMABILITY AND CORROSION RESISTANCE
The invention concerns the method for producing a rolled product 0.5 to 10 mm thick made from an aluminium alloy comprising, in particular, copper and lithium, in which, after solution annealing and quenching, a short heat treatment is carried out in which the sheet reaches a temperature of between 145°C and 175°C for 0.1 to 45 minutes, the speed of heating being between 3 and 600 °C/min. The sheet obtained at the end of the method according to the invention has high corrosion resistance and is capable of being shaped for producing a structural element for an aircraft, in particular an aircraft fuselage skin.
C22C 21/12 - Alloys based on aluminium with copper as the next major constituent
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
40.
ALUMINIUM-COPPER-LITHIUM ALLOY SHEETS FOR PRODUCING AEROPLANE FUSELAGES
The invention concerns a sheet 0.5 to 8 mm thick made from aluminium alloy comprising 2.6 to 3.0% by weight of Cu, 0.5 to 0.8% by weight of Li, 0.1 to 0.4% by weight of Ag, 0.2 to 0.7% by weight of Mg, 0.06 to 0.20% by weight of Zr, 0.01 to 0.15% by weight of Ti, optionally at least one element chosen from Mn, V, Cr, Se, and Hf, the quantity of the element, if chosen, being 0.01 to 0.8% by weight for Mn, 0.05 to 0.2% by weight for V, 0.05 to 0.3% by weight for Cr, 0.02 to 0.3% by weight for Se, 0.05 to 0.5% by weight for Hf, a quantity of Zn less than 0.2% by weight, a quantity of Fe and Si less than or equal to 0.1% by weight each, and inevitable impurities at a concentration less than or equal to 0.05% by weight each and 0.15% by weight in total, said sheet being obtained by a method comprising casting, homogenising, hot rolling and optionally cold rolling, solution heat treatment, quenching and tempering, the composition and the tempering being combined in such a way that the elasticity limit in the longitudinal direction Rp0.2(L) is between 395 and 435 MPa. The sheet according to the invention is particularly advantageous for producing aircraft fuselage panels.
B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
41.
THIN SHEETS MADE OF AN ALUMINIUM-COPPER-LITHIUM ALLOY FOR PRODUCING AIRPLANE FUSELAGES
The invention relates to a method for manufacturing a thin sheet having a thickness of 0.5 to 3.3 mm and an essentially non-recrystallized structure made of aluminium-based alloy which comprises, in sequence, the following steps: a) creating a liquid metal bath including 2.6 to 3.4 wt % of Cu, 0.5 to 1.1 wt % of Li, 0.1 to 0.4 wt % of Ag, 0.2 to 0.8 wt % of Mg, 0.11 to 0.20 wt % of Zr, 0.01 to 0.15 wt % of Ti, optionally at least one element selected from Mn, V, Cr, Se and Hf, the amount of the element, if selected, being 0.01 to 0.8 wt % for Mn, 0.05 to 0.2 wt % for V, 0.05 to 0.3 wt % for Cr, 0.02 to 0.3 wt % for Se, 0.05 to 0.5 wt % for Hf, an amount of Zn that is lower than 0.6 wt %, an amount of Fe and Si that is no higher than 0.1 wt % each, and inevitable impurities having a content that is no higher than 0.05 wt % each and 0.15 wt % in total; b) casting a plate from said liquid metal bath; c) homogenising said plate at a temperature of 450 °C to 515 °C; d) rolling said plate by hot rolling into a sheet having a thickness of 4 to 12 mm; e) rolling said sheet, by means of cold rolling, into a thin sheet having a final thickness of 0.5 to 3.3 mm, the thickness reduction achieved by cold rolling being between 1 and 3.5 mm; f) performing a thermal treatment during which the sheet reaches, for at least thirty minutes, a temperature of 300 °C to 450 °C; g) solution heat treating said thin sheet at a temperature of 450 °C to 515 °C and quenching same; h) tensioning said sheet in a controlled manner with a permanent deformation of 0.5 to 5 %, the cold deformation after a solution heat treatment being less than 15 %; and i) performing a tempering step which includes heating to a temperature of 130 °C to 170 °C, preferably 150 °C to 160 °C, during 5 to 100 hours, preferably 10 to 40 hours.
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
42.
ALUMINIUM COPPER LITHIUM ALLOY WITH IMPROVED IMPACT STRENGTH
The invention relates to an extruded product made of an aluminium-based alloy comprising 4.2% to 4.8% by weight of Cu, 0.9% to 1.1% by weight of Li, 0.15% to 0.25% by weight of Ag, 0.2% to 0.6% by weight of Mg, 0.07% to 0.15% by weight of Zr, 0.2% to 0.6% by weight of Mn, 0.01% to 0.15% by weight of Ti, an amount of Zn of less than 0.2% by weight, an amount of Fe and of Si of less than or equal to 0.1% by weight each, and inevitable impurities at a content of less than or equal to 0.05% by weight each and 0.15% by weight in total. The sections according to the invention are particularly useful as fuselage stringer or stiffener, fuselage frame, wing stiffener, floor beam or section or seat track, especially due to their improved properties compared to those of known products, in particular in terms of energy absorption during an impact; static mechanical strength and corrosion resistance properties, and their low density.
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
43.
DOUBLE-JET COOLING DEVICE FOR SEMICONTINUOUS VERTICAL CASTING MOULD
The subject of the invention is a direct cooling device for a mould for the semicontinuous vertical casting of slabs for rolling or ingots for extruding (3) that are progressively quenched with a double jet (jets 4 and 5), the first one at substantially 32° and the second substantially 22°, simultaneously, each jet delivering substantially the same flow rate and flow velocity from a single chamber (2) of liquid. Another subject of the invention is a method implementing said device, with or without a graphite insert (1) on the working faces and in combination with various configurations of false bottom.
B22D 11/049 - Continuous casting of metals, i.e. casting in indefinite lengths into open-ended moulds for direct chill casting, e.g. electromagnetic casting
B22D 11/20 - Controlling or regulating processes or operations for removing cast stock
44.
IMPROVED METHOD FOR PROCESSING SHEET METAL MADE OF AN AL-CU-LI ALLOY
The invention relates to a method for manufacturing a rolled product, in particular for the aeronautical industry, containing an aluminum alloy having a composition of 2.1 to 3.9 wt % of Cu, 0.7 to 2.0 wt % of Li, 0.1 to 1.0 wt % of Mg, 0 to 0.6 wt % of Ag, 0 to 1 wt % of Zn, at most 0.20 wt % of Fe + Si, at least one element selected from Zr, Mn, Cr, Se, Hf and Ti, the quantity of said element, if selected, being 0.5 to 0.18 wt % for Zr, 0.1 to 0.6 wt % for Mn, 0.05 to 0.3 wt % for Cr, 0.02 to 0.2 wt % for Se, 0.05 to 0.5 wt % for Hf, and 0.01 to 0.15 wt % for Ti, the other elements constituting at most 0.05 wt % each and 0.15 wt % total, the remainder being aluminum, said method involving flattening and/or pulling with a total deformation of at least 0.5% and less than 3%, and a short heat treatment in which the sheet metal reaches a temperature of between 130 and 170ºC for 0.1 to 13 hours. The invention makes it possible, in particular, to simplify the process for shaping sheet metal for fuselages, and to improve the trade-off between static mechanical strength and damage tolerance properties.
C22C 21/12 - Alloys based on aluminium with copper as the next major constituent
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
45.
ALUMINUM MAGNESIUM LITHIUM ALLOY HAVING IMPROVED TOUGHNESS
The invention relates to a welded product made of an aluminum alloy having the composition, in wt %, of Mg: 4.0 - 5.0; Li: 1.0 - 1.6; Zr: 0.05 - 0.15; Ti: 0.01 - 0.15; Fe: 0.02 - 0.2; Si: 0.02 - 0,2; Mn: = 0.5; Cr = 0.5; Ag: = 0.5; Cu = 0.5; Zn = 0.5; Se < 0.01; other elements: < 0.05; wherein the remainder is aluminum and the method for manufacturing same involves, consecutively: producing a molten metal bath so as to produce an aluminum alloy having the composition according to the invention, casting said alloy in crude form, optionally homogenizing the resulting cast product, heat deformation and optional cold deformation, an optional heat treatment at a temperature of between 300 and 420ºC in one or more stages, a solution heat treatment of the resulting deformed product, and tempering, optional cold deformation of the resulting solution heat treated and tempered product, and return to a temperature of less than 150ºC. The products according to the invention have improved toughness and are useful in manufacturing aircraft structural elements, preferably a fuselage skin, a fuselage frame or a rib.
C22C 21/06 - Alloys based on aluminium with magnesium as the next major constituent
C22F 1/047 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with magnesium as the next major constituent
46.
ALUMINIUM-COPPER-MAGNESIUM ALLOYS THAT PERFORM WELL AT HIGH TEMPERATURE
The invention relates to wrought products made of an Al-Cu-Mg aluminium alloy of composition, in % by weight, Cucorr: 2.6 - 3.7; Mgcorr: 1.5 - 2.6; Mn: 0.2 - 0.5; Zr = 0.16; Ti: 0.01 - 015; Cr = 0.25; Si = 0.2; Fe = 0.2; other elements < 0.05 and the remainder aluminium; with Cucorr = 0.9(Mgcorr) + 4.3 and Cucorr = 0.9(Mgcorr) + 5.0; where Cucorr = Cu - 0.74(Mn - 0.2) - 2.28 Fe and Mgcorr = Mg - 1.73(Si - 0.05) for Si = 0.05 and Mgcorr = Mg for Si < 0.05 and their manufacturing process. These alloys are particularly of use for applications in which the products are maintained at temperatures of 100°C to 200°C, typically at around 150°C. Thus, the products according to the invention are of use for fastenings intended to be used in an engine for a motor vehicle, such as screws or bolts or rivets or for manufacturing parts of the nacelle and/or attachment masts of aircraft, aircraft wing leading edges and the fuselage of supersonic aircraft.
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
47.
ALUMINIUM-COPPER-LITHIUM ALLOY WITH IMPROVED COMPRESSIVE STRENGTH AND TOUGHNESS
The invention relates to a process for manufacturing rolled products made of an aluminium-based alloy comprising 4.2 to 4.6% by weight of Cu, 0.8 to 1.30% by weight of Li, 0.3 to 0.8% by weight of Mg, 0.05 to 0.18% by weight of Zr, 0.05 to 0.4% by weight of Ag, 0.0 to 0.5% by weight of Mn, at most 0.20% by weight of Fe + Si, less than 0.20% by weight of Zn, at least one element chosen from Cr, Se, Hf and Ti, the amount of said element, if it is chosen, being from 0.05 to 0.3% by weight for Cr and for Se, 0.05 to 0.5% by weight for Hf and 0.01 to 0.15% by weight for Ti, the other elements being at most 0.05% by weight each and 0.15% by weight in total, the remainder being aluminium, comprising the steps of smelting, casting, homogenization, rolling with a temperature greater than 400°C, solution heat treating, quenching, tensioning between 2 and 3.5% and tempering. The invention also relates to the rolled products obtained by this process, which have a favourable compromise of properties between mechanical strength in compression and in tension and toughness. The products according to the invention are especially of use for the manufacture of upper wing skin.
B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
C22C 21/12 - Alloys based on aluminium with copper as the next major constituent
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22C 21/18 - Alloys based on aluminium with copper as the next major constituent with zinc
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
48.
ALUMINUM-COPPER-LITHIUM ALLOY FOR LOWER SURFACE ELEMENT
The invention relates to an aluminum-based alloy comprising, in % by weight, 2.1 to 2.4% of Cu, 1.3 to 1.6% of Li, 0.1 to 0.51% 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 Cr, Se, and Hf, the amount of the element, if it is chosen, being from 0.05 to 0.3% for Cr and for Se, and 0.05 to 0.5% for Hf, an amount of Fe and of Si less than or equal to 0.1% each, and inevitable impurities in a content less than or equal to 0.05% each and 0.15% in total. The alloy makes it possible to produce extruded, rolled and/or forged products that are in particular suitable for the manufacture of aircraft wing lower surface elements.
C22C 21/12 - Alloys based on aluminium with copper as the next major constituent
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22F 1/04 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
49.
ALUMINIUM-COPPER-LITHIUM ALLOY HAVING IMPROVED MECHANICAL STRENGTH AND IMPROVED TOUGHNESS
The invention relates to a wrought product such as an extruded, rolled and/or forged product, made of an alloy based on aluminium comprising, in % by weight, Cu: 3.0 - 3.9; Li: 0.8 - 1.3; Mg: 0.6 - 1.0; Zr: 0.05 - 0.18; Ag: 0.0 - 0.5; Mn: 0.0 - 0.5; Fe + Si = 0.20; Zn = 0.15; at least one element from Ti: 0.01-0.15; Sc: 0.05 - 0.3; Cr: 0.05 - 0.3; Hf: 0.05 - 0.5; other elements = 0.05 each and = 0.15 in total, the remainder being aluminium. The invention also relates to the process for manufacturing this product. The products according to the invention are particularly useful for producing thick products made of aluminium intended to produce structural components for the aeronautical industry.
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22F 1/04 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
50.
METHOD FOR ASSEMBLING PARTS MADE OF AN ALUMINUM ALLOY BY WELDING, COMPRISING COLD DEFORMATION FOLLOWED BY THE POST-WELDING TEMPERING OF THE ENTIRE WELDED AREA
The invention relates to a method for assembling parts (14a, 14b) made of an aluminum alloy, comprising: (I) providing at least one first part (14a) made of an aluminum alloy and which has been put in a solution, tempered, optionally hammer-hardened, and naturally aged at ambient temperature or previously tempered, and at least one second part (14b) made of aluminum alloy; (II) welding said parts (14a, 14b) in order to obtain a welded assembly having a welded area (16, 19, 18, 21); (III) carrying out a cold deformation of 0.3 to 5% of the entire welded area (16, 18, 19, 21); (IV) carrying out a post-welding tempering of the thus-deformed welded assembly in order to obtain a final metallurgical state. The welded assemblies obtained by the method of the invention have welded seams with improved properties, in particular in terms of mechanical strength, corrosion resistance, and the microstructure of the welded area.
B23K 20/12 - Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by frictionFriction welding
B23K 31/00 - Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by any single one of main groups
C21D 9/50 - Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articlesFurnaces therefor for welded joints
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
51.
PRODUCTS MADE OF AN ALUMINIUM-COPPER-LITHIUM ALLOY
The invention relates to a process for manufacturing an extruded, rolled and/or forged product based on an aluminium alloy in which: a bath of liquid metal is produced that comprises 2.0 to 3.5 wt% Cu, 1.4 to 1.8 wt% Li, 0.1 to 0.5 wt% Ag, 0.1 to 1.0 wt% Mg, 0.05 to 0.18 wt% Zr, 0.2 to 0.6 wt% Mn and at least one element chosen from Cr, Sc, Hf and Ti, the amount of said element, if it is chosen, being 0.05 to 0.3 wt% in the case of Cr and Sc, 0.05 to 0.5 wt% in the case of Hf and 0.01 to 0.15 wt% in the case of Ti, the balance being aluminium and inevitable impurities; an unwrought product is cast from the liquid metal bath and said unwrought product is homogenized at a temperature between 515°C and 525°C so that the time equivalent to 520°C for the homogenization is between 5 and 20 hours. The products obtained by the process according to the invention represent a particularly advantageous compromise between static mechanical strength and damage tolerance and are useful in particular in the aeronautical construction field.
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
The invention relates to a method for the friction stir welding of at least one first part, made of a metal alloy A, to at least one second part, made of a different metal alloy B, wherein: - said first and second parts are adjoined; - said first and second parts are joined together by means of a rotatable tool moving at a rate referred to as a feed rate; and is characterized in that said feed rate of the tool has at least two steady state alternating modes: a first mode in which a first mean feed rate V1 is used, and a second mode in which a second mean feed rate V2 is used, the rates V1 and V2 being significantly different, typically by at least 30% of the highest feed rate, wherein the lowest feed rate can be zero. The welded assemblies according to the invention are particularly advantageous for producing panels or profiled sections used for manufacturing transport vehicles.
B23K 20/12 - Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by frictionFriction welding
53.
SHEET MADE OF HIGH-TOUGHNESS ALUMINIUM ALLOY CONTAINING COPPER AND LITHIUM FOR AN AIRCRAFT FUSELAGE
A low-density aluminium alloy useful in an aircraft structure, in particular for fuselage sheet applications, which has a high strength, a high toughness and a high corrosion resistance, comprising: 2.1 to 2.8% Cu by weight; 1.1 to 1.7% Li by weight;, 0.1 to 0.8% Ag by weight; 0.2 to 0.6% Mg by weight; 0.2 to 0.6% Mn by weight, an amount of Fe and of Si not exceeding 0.1% by weight in each case, and inevitable impurities with a content not exceeding 0.05% by weight in each case and 0.15% by weight in total, the alloy containing substantially no zirconium.
The invention relates to an aluminum-based alloy having a low density that is useful in an aircraft structure for fuselage sheet metal applications that have a high mechanical resistance, a high level of strength and a high resistance to corrosion, containing in % by weight, 2.7 to 3.4 of Cu, 0.8 to 1.4 of Li, 0.1 to 0.8 of Ag, 0.2 to 0.6 of Mg and an element such as Zr, Mn, Cr, Sc, Hf, Ti or a combination thereof, of which the quantity, in % by weight, is 0.05 to 0.13 for Zr, 0.05 to 0.8 for Mn, 0.05 to 0.3 for Cr and Sc, 0.05 to 0.5 for Hf and 0.05 to 0.15 for Ti. The quantity of Cu and of Li is determined according to the formula Cu ( % by weight) + 5/3 Li ( % by weight) < 5.2.
C22C 21/12 - Alloys based on aluminium with copper as the next major constituent
C22F 1/057 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
55.
AL-ZN-CU-MG ALUMINUM BASE ALLOYS AND METHODS OF MANUFACTURE AND USE
A rolled or forged Al-Zn-Cu-Mg aluminum-based alloy wrought product having a thickness from 2 to 10 inches. The product has been treated by solution heat-treatment, quenching and aging, and the product comprises (in weight-%) :Zn 6.2 - 7.2, Mg 1.5 - 2.4, Cu 1.7 - 2.1. Fe 0 - 0.13, Si 0 - 0.10, Ti 0 - 0.06, Zr 0.06 - 0.13, Cr 0 - 0.04, Mn 0 - 0.04, impurities and other incidental elements <= 0.05 each. Alloys per se and aircraft and aerospace uses, as well as methods of making products are also disclosed.
C22C 21/10 - Alloys based on aluminium with zinc as the next major constituent
C22F 1/053 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with zinc as the next major constituent
56.
PRODUCTS MADE FROM AL/ZN/MG/CU ALLOYS WITH IMPROVED COMPROMISE BETWEEN STATIC MECHANICAL PROPERTIES AND TOLERANCE TO DAMAGE
The invention relates to a drawn, laminated or forged aluminium alloy product, characterised in comprising (in mass %): Zn 6.7 7.5 %, Cu 2.0 2.8 %, Mg 1.6 2.2 one or several elements selected from the group Zr 0.08 0.20 % ,Cr 0.05 0.25 %, Sc 0.01 0.50%, Hf 0.05 0.20 %, V 0.02 0.20%, Fe +Si < 0.20%, other elements = 0.05 % each and = 0.15 % in total, the residue being aluminium. Said product has an improved compromise between static mechanical resistance and tolerance to damage.
C22C 21/10 - Alloys based on aluminium with zinc as the next major constituent
C22F 1/053 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with zinc as the next major constituent
57.
AL-CU-MG-AG-MN ALLOY FOR STRUCTURAL APPLICATIONS REQUIRING HIGH STRENGTH AND HIGH DUCTILITY
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.
patents
