The invention relates to a thin sheet, the thickness of which is less than 12.7 mm, having an essentially recrystallized granular structure, made from an aluminum-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 aluminum.
C22C 21/18 - Alloys based on aluminium with copper as the next major constituent with zinc
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 1/057 - 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.
ALUMINUM COPPER LITHIUM ALLOY WITH IMPROVED MECHANICAL STRENGTH AND TOUGHNESS
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.
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
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 1/00 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
3.
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 a method for re-melting coated aluminum alloy scrap comprising a step of supplying shredded coated aluminum alloy scrap, consisting of individual entities; a decoating step, a step of preparing a heel, a step of loading and melting the decoated scrap on the heel. The invention is characterized in that the scrap has a specific geometry wherein at least 50% of the individual entities of the shredded coated scrap has a fold ratio (R) of less than or equal to 0.6, wherein the fold ratio (R) of an individual entity is defined by: fold ratio=R=(unfolded area−folded area)/(unfolded area), wherein the folded area is the maximum area of the orthogonal projection of the individual entity onto a plane and the unfolded area is the total area of the same individual entity after it has been unfolded.
The invention relates to a method for melting an aluminum load, comprising: supplying an aluminum load (11, 12, 13) of which at least 15% by weight is in the form of a sow of essentially cylindrical shape (11) of height h and maximum diameter d; loading said load into a cylindrical induction furnace (10) of height H and maximum internal diameter D in which the height direction of said sow is substantially parallel to the height direction of the furnace; melting said load by induction to obtain a liquid metal bath (2); optionally adjusting content of said liquid metal in which d is in the range from 0.7 D to 0.97 D and preferably in the range from 0.84 D to 0.92 D.
C22B 7/00 - Working-up raw materials other than ores, e.g. scrap, to produce non-ferrous metals or compounds thereof
C22B 9/00 - General processes of refining or remelting of metalsApparatus for electroslag or arc remelting of metals
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
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: S 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: S 0.05 each and: S 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.
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
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
The invention relates to a method for preheating at least one working roll for rolling, involving phases of:
determining a target thermal expansion profile,
determining an effective mean temperature profile of longitudinal segments of the working roll and for determining a target mean temperature profile,
activating a plurality of inductors distributed along the working roll in order to reduce a difference between the effective mean temperature and the target mean temperature.
B21B 27/10 - Lubricating, cooling, or heating rolls externally
B21B 37/32 - Control of flatness or profile during rolling of strip, sheets or plates using roll camber control by cooling, heating or lubricating the rolls
8.
WROUGHT PRODUCTS MADE OF 2XXX ALLOY HAVING AN OPTIMIZED CORROSION RESISTANCE, AND METHOD FOR OBTAINING SAME
A method for thermomechanical treatment of wrought products made of a 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 total; remainder aluminum, enabling an improvement in the resistance to corrosion under stress. It includes a tempering consisting of two sequences. The first sequence is defined by a maximum temperature T1max comprised between 130° C. and 180° C. and by a hold time at a temperature comprised between 130° C. and 180° C. which equates to an equivalent duration t1eq160+ C. calculated at 160° C. comprised between 10 h and 80 h. The second sequence is defined by a temperature T2° C.(t) lower than T1max and a hold time t2 at a temperature comprised between 100° C. and 130° C., which equates to an equivalent time t2eq160° C. calculated at 160° C. such that t2eq160° comprised between 0.3% and 15% of the equivalent duration t1eq160° calculated for the first sequence.
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
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 1/00 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
9.
THICK PLATES MADE OF AL-CU-LI ALLOY WITH IMPROVED FATIGUE PROPERTIES
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.
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
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
C22C 21/18 - Alloys based on aluminium with copper as the next major constituent with zinc
10.
Sheet metal plate with raised areas for creating industrial flooring with improved adhesive properties
The invention relates to a sheet metal plate (10) for creating flooring (30), in particular for industrial vehicles, having on its upper surface (11) a plurality or raised patterns, each raised pattern comprising one or more protruding portions (20), the raised patterns being arranged periodically, discreetly and in orderly fashion, the height h of the raised patterns being between 0.3 and 3 mm, characterized in that the plate has, on its lower surface (12), which is intended to be bonded to a support member, a rough surface the roughness Rmax of which is between 10 μm and 250 μm. The invention also relates to the method of producing said plate and the use of said sheet metal plate for creating flooring for industrial vehicles, preferably flooring for refrigerated vehicles.
B21B 1/22 - Metal rolling methods or mills for making semi-finished products of solid or profiled cross-sectionSequence of operations in milling trainsLayout of rolling-mill plant, e.g. grouping of standsSuccession of passes or of sectional pass alternations for rolling bands or sheets of indefinite length
B21B 3/00 - Rolling materials of special alloys so far as the composition of the alloy requires or permits special rolling methods or sequences
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.
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
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
12.
USE OF PRODUCTS MADE FROM ALUMINIUM COPPER MAGNESIUM ALLOY THAT PERFORM WELL AT HIGH TEMPERATURE
The invention relates to the use of a wrought aluminum alloy in a T8 temper 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 aluminum, 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.
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
C22C 21/18 - Alloys based on aluminium with copper as the next major constituent with zinc
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22C 21/14 - Alloys based on aluminium with copper as the next major constituent with silicon
13.
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; If ≤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.
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
The present invention relates to plates with a thickness of between 8 and 50 mm and made from aluminum alloy with a composition, as % by weight, Si: 0.7-1.3; Mg: 0.6-1.2; Mn: 0.65-1.0; Fe: 0.05-0.35; at least one element selected from Cr: 0.1-0.3 and Zr: 0.06-0.15; Ti<0.15; Cu<0.4; Zn<0.1; other elements <0.05 each and <0.15 in total, the remainder aluminum, and the method for manufacturing same. The plates according to the invention are particularly useful as precision plates, in particular for producing elements of machines, for example assembly or inspection equipment. The plates according to the invention have improved dimensional stability in particular during the machining steps, while having sufficient static mechanical properties, and excellent suitability for anodizing.
C22F 1/043 - 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 silicon as the next major constituent
C22C 21/02 - Alloys based on aluminium with silicon as the next major constituent
15.
Thick products made of 7XXX alloy and manufacturing process
(d) tempering said solution heat treated and cooled block by heating to 120 to 170° C. for 4 to 48 hours,
In this process, said block is not subjected to any significant deformation by working between the casting and the tempering. The alloy and the method according to the invention are particularly useful for the manufacture of molds for injection-molding plastics.
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.
ALUMINUM-COPPER-LITHIUM ALLOY THIN SHEETS WITH IMPROVED TOUGHNESS, AND PROCESS FOR MANUFACTURING AN ALUMINUM-COPPER-LITHIUM ALLOY THIN SHEET
The invention relates to a method for manufacturing a thin sheet made from aluminum-based alloy comprising, as % 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, a quantity of Zn of less than 0.3, a quantity of Fe and of Si of less than or equal to 0.1% each, and unavoidable impurities with a content of less than or equal to 0.05% by weight each and 0.15% by weight in total, the remainder aluminum, wherein optionally the hot-rolling input temperature being between 400° C. and 460° C. and the hot-rolling output temperature being less than 300° C. and the mean heating speed during the solution heat treatment is at least approximately 17° C./min between 300° C. and 400° C., aging conditions such that the yield strength in the long-transverse direction Rp0.2 is between 350 and 380 MPa.
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
C22C 21/18 - Alloys based on aluminium with copper as the next major constituent with zinc
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22C 21/14 - Alloys based on aluminium with copper as the next major constituent with silicon
B21B 3/00 - Rolling materials of special alloys so far as the composition of the alloy requires or permits special rolling methods or sequences
d) Purifying the circulating gas enriched with dihydrogen in a purification chamber comprising a getter material configured to trap dihydrogen from 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
C21D 9/46 - Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articlesFurnaces therefor for sheet metals
19.
AlMgMn alloy product with improved corrosion resistance
The invention relates to a method for manufacturing an aluminum alloy sheet, wherein an aluminum alloy is prepared with the following composition, in wt %: Mg: 4.0-5.2, Mn: 0.40-1.0, Zn: 0.15-0.40, at least one element selected from Ti, Cr, Cu and Zr, the content of the element, if selected, being 0.01-0.15 for Ti, 0.05-0.25 for Cr, 0.02-0.25 for Cu, 0.05-0.25 for Zr, Fe: <0.40, Si: <0.40, other elements or impurities <0.05 each and <0.15 in total, the remainder being aluminum. A rolling plate is cast by vertical semi-continuous casting, and said optionally homogenised plate is hot-rolled in two successive stages to obtain a sheet. The sheets obtained by the method according to the invention are advantageous, in particular for shipbuilding, since they demonstrate, after being exposed for 7 days to a temperature of 100° C., a weight loss of less than 15 mg/cm2 during a corrosion test according to the ASTM G67 standard.
B32B 15/01 - Layered products essentially comprising metal all layers being exclusively metallic
C22C 21/08 - Alloys based on aluminium with magnesium as the next major constituent with silicon
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
20.
Method for testing a damage tolerance property of a part made of an aluminium alloy
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 0.5-0.8; Mn 0.1-0.7; 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 21/18 - Alloys based on aluminium with copper as the next major constituent with zinc
C22F 1/05 - 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 of the Al-Si-Mg type, i.e. containing silicon and magnesium in approximately equal proportions
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
22.
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 percent 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.
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
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
23.
ALUMINUM-COPPER-LITHIUM ALLOY HAVING IMPROVED COMPRESSIVE STRENGTH AND IMPROVED TOUGHNESS
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.
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
C22C 21/18 - Alloys based on aluminium with copper as the next major constituent with zinc
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22C 21/14 - Alloys based on aluminium with copper as the next major constituent with silicon
24.
Process for manufacturing a bimetallic part using a dilation-causing thermal treatment
A process for manufacturing a bimetallic part by means of a first component formed by a first aluminum alloy and a second component formed by a second aluminum alloy, said process involving: assembling the first component and the second component to obtain an assembled part; applying a thermal treatment to the assembled part at a temperature of 100 to 250° C., the thermal treatment causing the assembled part to deform, in particular as a result of a metallurgical deformation by a precipitation of hardening phases of the first component and/or the second component; cooling the part to ambient temperature, upon which the part remains deformed. The process involves, prior to the assembling step, an estimation of the degree of deformation that the assembled part will undergo under the effect of the thermal treatment.
C21D 9/50 - Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articlesFurnaces therefor for welded joints
B23K 20/233 - Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating taking account of the properties of the materials to be welded without ferrous layer
G16C 60/00 - Computational materials science, i.e. ICT specially adapted for investigating the physical or chemical properties of materials or phenomena associated with their design, synthesis, processing, characterisation or utilisation
B23K 101/00 - Articles made by soldering, welding or cutting
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.
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
C22C 21/18 - Alloys based on aluminium with copper as the next major constituent with zinc
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22C 21/14 - Alloys based on aluminium with copper as the next major constituent with silicon
B21B 3/00 - Rolling materials of special alloys so far as the composition of the alloy requires or permits special rolling methods or sequences
26.
Aluminium alloy vacuum chamber elements stable at high temperature
, measured in plane L/TC according to standard ASTM E112, is at least equal to 350 μm between surface and ½ thickness. The invention also relates to the method of manufacturing of such a vacuum chamber element. The products according to the invention are particularly advantageous, particularly in terms of resistance to creep deformation at high temperature, while having high properties of corrosion resistance, homogeneity of properties in thickness and machinability.
C22C 21/08 - Alloys based on aluminium with magnesium as the next major constituent with silicon
C22C 21/02 - Alloys based on aluminium with silicon as the next major constituent
C22F 1/043 - 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 silicon as the next major constituent
C22F 1/05 - 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 of the Al-Si-Mg type, i.e. containing silicon and magnesium in approximately equal proportions
C25D 11/08 - Anodisation of aluminium or alloys based thereon characterised by the electrolytes used containing inorganic acids
C25D 11/10 - Anodisation of aluminium or alloys based thereon characterised by the electrolytes used containing organic acids
27.
Method for improving the wetting of a surface of a solid substrate by a liquid metal
The invention is a method for treating a solid substrate, made from a first material, of metal or ceramic type, the method comprising placing the substrate in contact with a liquid metal, while the substrate is exposed to an ultrasonic wave called a power wave. At the level of a surface of the substrate, the power density is greater than a cavitation threshold of the liquid metal. Such exposure improves the wettability of the substrate surface by the liquid metal.
C23C 2/32 - Hot-dipping or immersion processes for applying the coating material in the molten state without affecting the shapeApparatus therefor using vibratory energy applied to the bath or substrate
The subject of the invention is a process for manufacturing a wrought product made of aluminum 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: 0.01-0.2; Ag<0.1; Zr<0.08; Fe and Si #0.1 each; unavoidable impurities #0.05% each and 0.15% in total; remainder aluminum; 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
C21D 8/02 - Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips
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
29.
Aluminum-copper-lithium alloy product for a lower wing skin element with improved properties
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.
B64C 3/26 - Construction, shape, or attachment of separate skins, e.g. panels
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
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
30.
ALUMINUM 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.
C22C 21/18 - Alloys based on aluminium with copper as the next major constituent with zinc
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
31.
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 1.50-1.80; 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 ≤0.05 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.
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
C22C 21/10 - Alloys based on aluminium with zinc as the next major constituent
32.
THIN SHEETS MADE OF ALUMINIUM-COPPER-LITHIUM ALLOY FOR AIRCRAFT FUSELAGE MANUFACTURE
A method for manufacturing a brushed rolled product made from Al—Cu—Li alloy with a thickness of less than 12 mm, including the steps of producing a rolled product, solution heat treatment and quenching, stress relieving, optionally tempering, and brushing, wherein 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.
B24B 29/00 - Machines or devices for polishing surfaces on work by means of tools made of soft or flexible material with or without the application of solid or liquid polishing agents
B24B 39/00 - Burnishing machines or devices, i.e. requiring pressure members for compacting the surface zoneAccessories therefor
B24B 39/06 - Burnishing machines or devices, i.e. requiring pressure members for compacting the surface zoneAccessories therefor designed for working plane surfaces
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
B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
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
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
C22C 21/18 - Alloys based on aluminium with copper as the next major constituent with zinc
34.
System and method for controlling the casting of a product
A system 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 fixed mold, the control system includes a dummy bottom configured to form a movable lower bottom of the fixed mold and to carry the product during casting; a weighing cell, on which the dummy bottom is arranged to rest, the weighing cell being configured to take measurements representative of the mass of the product carried by the dummy bottom during casting; and a support of the dummy bottom, to which the weighing cell is linked, configured to lower the false bottom relative to the fixed mold, substantially in a vertical direction, during casting; and a processing unit connected to each weighing cell, and configured to process the measurements, and calculate the variation in the mass of the product over time.
The invention concerns a process to manufacture a flat-rolled product, notably for the aeronautic industry containing aluminum alloy, in which, notably a flattening and/or stretching is performed with a cumulated deformation of at least 0.5% and less than 3%, and a short heat-treatment is performed in which the sheet reaches a temperature between 130° C. and 170° C. for a period of 0.1 to 13 hours. The invention notably makes it possible to simplify the forming process of fuselage skins and to improve the balance between static mechanical strength properties 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
36.
Enclosure having a sealing device for a casting installation
An enclosure having a sealing device, for a casting installation, having a first body and a second body that is removably joined to the first body along a bearing axis, the first and second bodies together delimiting an internal chamber. The sealing device comprises: at least one compression member, at least one seal having a lateral contact face extending substantially parallel to the bearing axis; the compression member and the seal being arranged with respect to one another such that the compression member is in contact with the lateral contact face of the seal and exerts a compression force thereon that is oriented orthogonally to the bearing axis.
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 11/14 - Plants for continuous casting, e.g. for upwardly drawing the strand
B22D 11/00 - Continuous casting of metals, i.e. casting in indefinite lengths
A tooling for producing a metal product by feed casting, including a mold having a preheater, an ingot mold (10), a movable bottom that moves in a main direction X and a transition ring interposed between the preheater and the ingot mold (10). The tooling has a clamping ring (12) transmitting a clamping force (F1) to the transition ring (11) oriented towards the ingot mold (10), a holding mechanism that positively locks the clamping ring (12), and an axial relief mechanism configured to vary between an inactive state in which the holding mechanism exerts a holding force (F2) on the clamping ring (12) such that the clamping ring (12) exerts the clamping force (F1) on the transition ring (11) and an active state in which the axial relief mechanism resists the action applied by the holding mechanism on the clamping ring in the inactive state.
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.
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
C22F 1/00 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
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
e) Applying intermittently to the sonotrode (1) power ultrasounds, particularly ultrasounds having a power greater than 10 watts, to maintain said wetting.
G01N 29/032 - Analysing fluids by measuring attenuation of acoustic waves
G01N 29/22 - 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
41.
Isotropic plates made from aluminum-copper-lithium alloy for manufacturing aircraft fuselages
The invention relates to a plate with a thickness of 0.5 to 9 mm with an essentially recrystallized granular structure, made from an alloy based on aluminum, comprising 2.8 to 3.2% by weight Cu, 0.5 to 0.8% by weight Li, 0.1 to 0.3% by weight Ag, 0.2 to 0.7% by weight Mg, 0.2 to 0.6% by weight Mn, 0.01 to 0.15% by weight Ti, a quantity of Zn below 0.2% by weight, a quantity of Fe and Si of less than or equal to 0.1% by weight each, and unavoidable impurities to a proportion of less than or equal to 0.05% by weight each and 0.15% by weight in total, said plate being obtained by a method comprising casting, homogenization, hot rolling and optionally cold rolling, solution heat treatment, quenching and aging. The plates according to the invention are advantageous in particular for the manufacture of 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
e) Machining the solidified first metal (1) in the form of a flange (7) configured for the attachment of a mechanical amplifier and/or of a transducer (4).
G01N 29/032 - Analysing fluids by measuring attenuation of acoustic waves
G01N 29/22 - 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
A method of manufacturing an aluminum alloy ingot using scrap aluminum alloy in the 2xxx or 7xxx series, and a fabrication method after rolling, extrusion and/or forging of an aeronautical structure comprising the steps in the above method, and then at least one rolling, extrusion and/or forging step of the aluminum alloy ingot in the series of scrap used.
C22B 7/00 - Working-up raw materials other than ores, e.g. scrap, to produce non-ferrous metals or compounds thereof
B08B 3/12 - Cleaning involving contact with liquid with additional treatment of the liquid or of the object being cleaned, e.g. by heat, by electricity or by vibration by sonic or ultrasonic vibrations
B08B 3/08 - Cleaning involving contact with liquid the liquid having chemical or dissolving effect
44.
Structural elements obtained by linear friction welding
The invention concerns a method for forming by welding along a flat surface an article. The method according to the invention is particularly useful to improve strength and elongation of welded joints obtained by linear friction welding. Structural articles of aircrafts obtained with the method of the invention are advantageous, in particular aircraft structural members.
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 20/233 - Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating taking account of the properties of the materials to be welded without ferrous layer
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.
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
B64C 3/26 - Construction, shape, or attachment of separate skins, e.g. panels
B21B 3/00 - Rolling materials of special alloys so far as the composition of the alloy requires or permits special rolling methods or sequences
The invention relates to a method for manufacturing an aluminum alloy product including the steps of: creating a bath of liquid metal in an aluminum-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.
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
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22C 21/14 - Alloys based on aluminium with copper as the next major constituent with silicon
B22D 11/04 - Continuous casting of metals, i.e. casting in indefinite lengths into open-ended moulds
B22D 21/00 - Casting non-ferrous metals or metallic compounds so far as their metallurgical properties are of importance for the casting procedureSelection of compositions therefor
B21B 1/22 - Metal rolling methods or mills for making semi-finished products of solid or profiled cross-sectionSequence of operations in milling trainsLayout of rolling-mill plant, e.g. grouping of standsSuccession of passes or of sectional pass alternations for rolling bands or sheets of indefinite length
B21C 23/21 - Presses specially adapted for extruding metal
C22C 21/18 - Alloys based on aluminium with copper as the next major constituent with zinc
B22D 11/041 - Continuous casting of metals, i.e. casting in indefinite lengths into open-ended moulds for vertical casting
C22C 21/12 - Alloys based on aluminium with copper as the next major constituent
B21B 3/00 - Rolling materials of special alloys so far as the composition of the alloy requires or permits special rolling methods or sequences
47.
Method for transforming Al—Cu—Li alloy sheets improving formability and corrosion resistance
A method for producing a rolled product 0.5 to 10 mm thick made from an aluminum 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 21/18 - Alloys based on aluminium with copper as the next major constituent with zinc
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
The disclosure provides for plate having a thickness of at least 80 mm comprising aluminium alloy as a percentage by weight %: 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 from Zr, Mn, Cr, Sc, Hf and Ti, the amount of said element, if selected, being 0.05 to 0.20 wt % for Zr, 0.05 to 0.8% wt % t for Mn, 0.05 to 0.3 wt % for Cr and for Sc, 0.05 to 0.5 wt % 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, wherein the aged state logarithmic fatigue mean measured at mid-thickness in the LT direction on smooth specimens with a maximum stress amplitude of 242 MPa, a frequency of 50 Hz, a stress ratio of R=0.1 of at least 250,000 cycles.
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
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
B22D 11/00 - Continuous casting of metals, i.e. casting in indefinite lengths
B22D 11/041 - Continuous casting of metals, i.e. casting in indefinite lengths into open-ended moulds for vertical casting
B21B 1/22 - Metal rolling methods or mills for making semi-finished products of solid or profiled cross-sectionSequence of operations in milling trainsLayout of rolling-mill plant, e.g. grouping of standsSuccession of passes or of sectional pass alternations for rolling bands or sheets of indefinite length
B21C 23/21 - Presses specially adapted for extruding metal
B21J 5/00 - Methods for forging, hammering, or pressingSpecial equipment or accessories therefor
B22D 11/04 - Continuous casting of metals, i.e. casting in indefinite lengths into open-ended moulds
B22D 21/00 - Casting non-ferrous metals or metallic compounds so far as their metallurgical properties are of importance for the casting procedureSelection of compositions therefor
The invention relates to a rolled product with state T351, having thickness of between 15 and 50 mm, made from aluminum 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 aluminum.
C22C 21/14 - Alloys based on aluminium with copper as the next major constituent with silicon
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
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22C 21/12 - Alloys based on aluminium with copper as the next major constituent
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
B64C 3/26 - Construction, shape, or attachment of separate skins, e.g. panels
B22D 21/00 - Casting non-ferrous metals or metallic compounds so far as their metallurgical properties are of importance for the casting procedureSelection of compositions therefor
B22D 27/20 - Measures not previously mentioned for influencing the grain structure or textureSelection of compositions therefor
50.
Extrados structural element made from an aluminium copper lithium alloy
Extrados structural element made from an aluminum, copper and lithium alloy and method for manufacturing same. An alloy with composition (in wt %) 4.2-5.2 Cu, 0.9-1.2 Li, 0.1-0.3 Ag, 0.1-0.25 Mg, 0.08-0.18 Zr, 0.01-0.15 Ti, an Fe and Si content level less than or equal to 0.1% each, and other element with content level less than or equal to 0.05% each and 0.15% in total, is poured, homogenized, deformed hot, placed in a solution at a temperature of at least 515° C., pulled from 0.5 to 5% and annealed. The combination of magnesium, copper and manganese content with the temperature in solution can reach an advantageous elasticity under compression limit. Products having a thickness of at least 12 mm have, in the longitudinal direction, an elasticity under compression limit of at least 645 MPa and an elongation of at least 7%.
B64C 3/26 - Construction, shape, or attachment of separate skins, e.g. panels
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
C22C 21/12 - Alloys based on aluminium with copper as the next major constituent
B22D 21/00 - Casting non-ferrous metals or metallic compounds so far as their metallurgical properties are of importance for the casting procedureSelection of compositions therefor
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 aluminum-based alloy.
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
C22C 21/16 - Alloys based on aluminium with copper as the next major constituent with magnesium
C22C 21/14 - Alloys based on aluminium with copper as the next major constituent with silicon
C22F 1/00 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
52.
Method for manufacturing a structural element having a variable thickness for aircraft production
The invention relates to the method for manufacturing a rolled product of variable thickness made of heat-treatable aluminum alloy in which hot rolling is performed to achieve a variation in thickness of at least 10% lengthwise between the thickest part and the thinnest part; the rolled product of variable thickness obtained undergoes solution heat-treatment and quenching with permanent set of at least 1% in the thickest part before natural or artificial ageing. The products obtained according to the invention exhibit improved mechanical strength of at least 5% in the thinnest part and improved fracture toughness of at least 15% in the thickest part. The products according to the invention are notably useful in the fabrication of aircraft upper or lower wing skins the “buy to fly” ratio and the properties are simultaneously improved.
B32B 3/00 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form
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
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
The subject matter of the invention is a device for the direct cooling of a mould for the vertical semicontinuous casting of rolling ingots or extrusion billets (3) with gradual quenching by double jet (4 and 5), the first at substantially 32° and second at substantially 22°, simultaneously and delivering substantially the same flow rates and speeds from a single liquid chamber (2).
Another subject of the invention is a method using said device, with or without graphite insert (1) on the working faces and in association with various bottom block configurations.
B22D 11/124 - Accessories for subsequent treating or working cast stock in situ for cooling
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
B22D 30/00 - Cooling castings, not restricted to casting processes covered by a single main group
B22D 11/14 - Plants for continuous casting, e.g. for upwardly drawing the strand
54.
Thick products made of 7XXX alloy and manufacturing process
(d) tempering said solution heat treated and cooled block by heating to 120 to 170° C. for 4 to 48 hours,
In this process, said block is not subjected to any significant deformation by working between the casting and the tempering. The alloy and the method according to the invention are particularly useful for the manufacture of molds for injection-molding plastics.
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
C22C 21/10 - Alloys based on aluminium with zinc as the next major constituent
An extruded product made of an alloy containing aluminum comprising 4.2 wt % to 4.8 wt % of Cu, 0.9 wt % to 1.1 wt % of Li, 0.15 wt % to 0.25 wt % of Ag, 0.2 wt % to 0.6 wt % of Mg, 0.07 wt % to 0.15 wt % of Zr, 0.2 wt % to 0.6 wt % of Mn, 0.01 wt % to 0.15 wt % of Ti, a quantity of Zn less than 0.2 wt %, a quantity of Fe and Si less than or equal to 0.1 wt % each, and unavoidable impurities with a content less than or equal to 0.05 wt % each and 0.15 wt % in total is disclosed. The profiles according to the invention are particularly useful as fuselage stiffeners or stringers, circumferential frames, wing stiffeners, floor beams or profiles, or seat tracks, notably owing to their improved properties in relation 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.
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 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 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 an advantageous compromise between static mechanical strength and damage tolerance and are useful in aeronautical design.
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
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
57.
Method for assembling aluminum alloy parts by welding
B23K 37/00 - Auxiliary devices or processes, not specially adapted for a procedure covered by only one of the other main groups of this subclass
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
C22C 21/12 - Alloys based on aluminium with copper as the next major constituent
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
58.
Aircraft wing and fiber metal laminate forming part of such an aircraft wing
Fiber metal laminate (4) and an aircraft wing (1) having a longitudinal direction, comprising metal layers (5) and fiber reinforced plastic layers (6, 7, 6′, 7′; 6″, 7″) in between said metal layers (5), wherein the metal layers (5) and the fiber reinforced plastic layers (6, 7, 6′, 7′; 6″, 7″) are bonded together, and wherein the fibers of at least some of the fiber reinforced plastic layers (6, 7, 6′, 7′; 6″, 7″) are arranged in a first group in a first plastic layer (6) and in a second group in a second plastic layer (7) whereby the fibers of the first group are at an angle with respect to the fibers of the second group, wherein said laminate (4) exhibits fibers of a first type and fibers of a second type, wherein the fibers of the first type being arranged in the said longitudinal direction of the laminate (4) in one or more of its fiber reinforced plastic layers (6′, 7′; 6″, 7″), and that it has adjacent fiber reinforced plastic layers (6, 7) at or near a symmetry-plane of the laminate (4) that are provided with the fibers of the second type.
B32B 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 5/28 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer impregnated with or embedded in a plastic substance
B32B 15/08 - Layered products essentially comprising metal comprising metal as the main or only constituent of a layer, next to another layer of a specific substance of synthetic resin
B32B 15/14 - Layered products essentially comprising metal next to a fibrous or filamentary layer
B64C 3/26 - Construction, shape, or attachment of separate skins, e.g. panels
59.
Sheet metal plate with reliefs for creating industrial flooring over which trucks are to run, engraved cylinder for obtaining such sheet metal plates by rolling
Sheet metal plate for creating flooring, particularly of industrial vehicles, over which trucks are to run, having a plurality of patterns, the maximum height of said reliefs ranging between 0.2 and 1.5 mm, said reliefs having a friction surface which has a mean width of at least 1 mm, in which said reliefs are arranged in a plurality of aligned groups of reliefs all of the same shape, the same orientation, and with their centers of gravity substantially aligned in one and the same given direction (D), the minimum distance, measured in said direction (D), between two adjacent reliefs of one and the same aligned group being less than 6 mm. The direction (D) in which the aligned groups are aligned advantageously coincides with the direction (De) in which the trucks run.
E04F 15/06 - Flooring or floor layers composed of a number of similar elements of metal, whether or not in combination with other material
B21B 1/22 - Metal rolling methods or mills for making semi-finished products of solid or profiled cross-sectionSequence of operations in milling trainsLayout of rolling-mill plant, e.g. grouping of standsSuccession of passes or of sectional pass alternations for rolling bands or sheets of indefinite length
B21B 27/00 - RollsLubricating, cooling or heating rolls while in use
B60R 13/01 - Liners for load platforms or load compartments
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
C22C 21/12 - Alloys based on aluminium with copper as the next major constituent
61.
Manufacturing method of making aluminum alloy semi-finished product with improved microporosity
The invention relates to a manufacturing method for making an unwrought semi-finished product having at mid thickness a density of micropores of size greater than 90 μm less than 50% and preferably less than 20% of the density of micropores of size greater than 90 μm obtained by a method according to prior art. The method according to the invention comprises in particular an ultrasound treatment step for the molten metal bath in a furnace and/or a vessel using an immersed device comprising at least one ultrasound transmitter. The semi-finished products obtained according to the method of the invention are particularly advantageous for manufacturing by rolling sheets designed for the aircraft industry to produce spars, ribs, upper and lower wing skins and for manufacturing by extrusion sections designed for the aircraft industry to produce stiffeners.
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
A casting process for an aluminum alloy containing at least about 0.1% of Mg and/or at least about 0.1% of Li in which a liquid surface of the alloy is put into contact with a dried gas including at least about 2% of oxygen by volume and with a water partial pressure lower than about 150 Pa throughout most of the solidification process is described. The process makes it possible to cast most oxidable aluminum alloys, in particular aluminum alloys containing magnesium and/or lithium, without using additives such as beryllium and/or calcium and without using expensive devices and/or gases, to obtain cast ingots generally free from surface defects and pollution, in complete safety.
The invention relates to a wrought product such as an extruded, rolled and/or forged aluminum alloy-based product, comprising, in 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 among: 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 total, remainder aluminum. The invention also relates to the process for producing said product. The products according to the invention are particularly useful in the production of thick aluminum products intended for producing structural elements in the aeronautical industry.
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
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
The present invention is directed to a substantially unrecrystallized rolled aluminum alloy product, obtained from a plate with a thickness of at least 30 mm, comprising 2.2 to 3.9 wt. % Cu, 0.7 to 2.1 wt. % Li, 0.2 to 0.8 wt. % Mg, 0.2 to 0.5 wt. % Mn, 0.04 to 0.18 wt. % Zr, less than 0.05 wt. % Zn, and optionally 0.1 to 0.5 wt. % Ag, remainder aluminum and unavoidable impurities having a low propensity to crack branching during L-S a fatigue test. A product of the invention has a crack deviation angle Θ of at least 20° under a maximum equivalent stress intensity factor Keff max of 10 MPa √m for a S-L cracked test sample under a mixed mode I and mode II loading wherein the angle Ψ between a plane perpendicular to the initial crack direction and the load direction is 75°.
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.
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
A process for friction stir welding at least a first part made of metal alloy A with at least a second part made of a dissimilar metal alloy B, in which the first and second parts are placed side by side, and a joint is made between the first and second parts using a rotating tool moving at a speed referred to as the travel speed. The tool travel speed has at least two alternated modes in continuous service, a first mode wherein a first average travel speed S1 and a second mode wherein a second average travel speed S2 is used, the speeds S1 and S2 being significantly different, typically at least 30% of the highest travel speeds, with the slowest advance speed being zero. The assemblies welded according to the invention are particularly advantageous for the fabrication of panels or structural sections used in the manufacture of 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
67.
Process for recycling aluminum alloy scrap coming from the aeronautical industry
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.
The present invention relates to a stringer for an aircraft wing and a method of forming such a stringer in which the stringer is formed from a single piece of material and then machined to optimise the dimensions and weight of the stringer.
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.
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
70.
Method of making a structural element for aeronautical construction comprising differential work-hardening
A process for fabricating a worked product or a monolithic multi-functional structural element comprising aluminium alloy includes a hot working step and at least one transformation step by cold plastic deformation after the hot transformation step. At least two zones of the structural element have imposed generalized average plastic deformations and the imposed deformations are different by at least 2%. Structural elements can be fabricated, particularly for aeronautical construction, with properties that are variable while their geometric characteristics are identical to those of existing components. The process is economic and controllable, and properties can be varied for parts not requiring any artificial ageing.
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
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 1/04 - 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
71.
High fracture toughness aluminum-copper-lithium sheet or light-gauge plates suitable for fuselage panels
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.
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
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, 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.
The invention relates to a bi-functional extruded structural element, particularly a stringer for aeronautical construction, comprising a base that can be fixed on a surface, and a body, wherein the base comprises a first aluminum-based alloy, and further wherein the body comprises a second heat treatable aluminum-based alloy, having properties that are different from the properties of the first aluminum based alloy.
Process for manufacturing aluminum alloy products, with high toughness and fatigue resistance comprising: (a) preparing an aluminum alloy bath, (b) adding a refining agent containing particles of AlTiC type phases into the bath, (c) casting an as-cast form such as an extrusion ingot, a forging ingot or a rolling ingot, (d) hot transforming the as-cast form, possibly after scalping, to form a blank or a product with final thickness, (e) optionally cold transforming the blank to a final thickness, (f) applying a solution heat treatment and quenching the product output from (d) or (e), followed by relaxation by controlled stretching with permanent elongation between 0.5 and 5%, and optionally annealing, wherein the quantity of refining agent is chosen such that the average casting grain size of the as-cast form is more than 500 μm. The present invention may be used, for example, to manufacture fuselage sheet or light-gauge plates made with 6056 alloy.
C22F 1/05 - 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 of the Al-Si-Mg type, i.e. containing silicon and magnesium in approximately equal proportions
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
75.
Recrystallized Al-Zn-Cu-Mg plate with low zirconium
The present invention is directed to optimization of recrystallization rates on the fatigue crack growth resistance, in the particular case of a Al—Zn—Cu—Mg plate products, and especially on the evolution of da/dN.
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
patents
