Pechiney Rhenalu

Alcan Rhenalu

Constellium Issoire

Other

Constellium France

Constellium Rolled Products Ravenswood, LLC

Alcan Rolled Products - Ravenswood, LLC

Alcan Rhenalu/constellium France

Alean Rolled Products Ravenswood LLC

Alean Rhenalu

Timothy Warner

Philippe Jarry

Bernard Bes

Jean-Christophe Ehrstrom

Christophe Sigli

Armelle Danielou

Philippe Lequeu

Fabrice Heymes

Herve Ribes

Ronan Dif

Vic Dangerfield

Philippe Lassince

Julien Boselli

Alex Cho

David Godard

Bernard Bès

Frank Eberl

Pierre Sainfort

Gaelle Pouget

Jean-Louis Achard

Sjoerd Van Der Veen

Raphaël Muzzolini

Sylvie Arsene

David Dumont

Denis Bechet

Cedric Gasqueres

Marine Ledoux

Diana Koschel

Erembert Nizery

Bernard Bés

Ricky Whelchel

Hervé Ribes

Kenneth Paul Smith

Gaëlle Pouget

Julien Laye

Fabio Taina

Maria Belen Davo Gutierrez

Mircea Cablea

Mathieu Marquette

Jerome Pignatel

Pierre-Yves Menet

Jean Domeyne

Cédric Gasqueres

Marc Bertherat

Raphael Muzzolini

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.

Al—Zn—Cu—Mg alloys with high strength and method of fabrication

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.

Process for manufacturing a bimetallic part using a dilation-causing thermal treatment

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.

AlMgMn alloy product with improved corrosion resistance

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&#x2264;0.20; Zn&#x2264;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 &#x2264;0.05 each and &#x2264;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.

Aluminum-copper-lithium alloy with improved mechanical strength and toughness

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.

Method for manufacturing a structural element having a variable thickness for aircraft production

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.

Aluminum-copper-lithium alloy with improved impact resistance

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.

High fracture toughness aluminum-copper-lithium sheet or light-gauge plates suitable for fuselage panels

A rolled or forged Al&#x2014;Zn&#x2014;Cu&#x2014;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 &#x2266;0.05 each. Alloys per se and aircraft and aerospace uses, as well as methods of making products are also disclosed.

Al-Zn-Cu-Mg aluminum base alloys and methods of manufacture and use

The invention relates to a work-hardened product, particularly a rolled, extruded or forged product, made of an alloy with the following composition (% by weight): Cu 3.8-4.3; Mg 1.25-1.45; Mn 0.2-0.5; Zn 0.4-1.3; Fe&#x3c;0.15; Si&#x3c;0.15; Zr&#x2266;0.05; Ag&#x3c;0.01, other elements &#x3c;0.05 each and &#x3c;0.15 total, remainder Al, treated by dissolution, quenching and cold strain-hardening, with a permanent deformation of between 0.5% and 15%, and preferably between 1.5% and 3.5%. Cold strain-hardening can be achieved by controlled tension and/or cold transformation, for example rolling, die forging or drawing. This cladded metal plate type product is a suitable element to be used as aircraft fuselage skin.

Aircraft structural member made of an Al-Cu-Mg alloy

The present invention includes a process for manufacturing metal sheets or plates and a machined metal part as well as machined products, structural components and their uses in various applications. Manufacture of a metal sheet or plate by a process of the present invention comprises casting of a rolling ingot, optionally followed by homogenisation, one or more hot or cold rolling operations, optionally separated by one or more re-heating operations, to obtain a sheet, or plate and optionally one or more sheet or plate cutting or finishing operations. The sheet is pre-machined on one or both sides so as to obtain a pre-machined stock, and subjected to solution heat treatment, quenching treatment, and optionally, one or more of the following steps: controlled stretching, aging treatment, and/or cutting.

Process for manufacturing structural components by machining plates

The present invention includes a process for manufacturing metal sheets or plates and a machined metal part as well as machined products, structural components and their uses in various applications. Manufacture of a metal sheet or plate by a process of the present invention comprises casting of a rolling ingot, optionally followed by homogenization, one or more hot or cold rolling operations, optionally separated by one or more re-heating operations, to obtain a sheet, or plate and optionally one or more sheet or plate cutting or finishing operations. The sheet is pre-machined on one or both sides so as to obtain a pre-machined stock, and subjected to solution heat treatment, quenching treatment, and optionally, one or more of the following steps: controlled stretching, aging treatment, and/or cutting.

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. %)&#x3c;5.2.

High fracture toughness aluminum-copper-lithium sheet or light-gauge plate suitable for use in a fuselage panel

An aluminum alloy having improved strength and ductility, comprising:

Al-Cu-Mg-Ag-Mn alloy for structural applications requiring high strength and high ductility

The invention relates to alloys and associated products which are laminated, extruded or forged in Al&#x2014;Zn&#x2014;Mg&#x2014;Cu alloy. Alloys of the invention generally comprise (in mass percentage):

Al-Zn-Mg-Cu alloys and products with improved ratio of static mechanical characteristics to damage tolerance

A method for manufacturing aluminium alloy parts with precipitation hardening including friction stir welding of at least two elements made from the same alloy or different alloys, solution heat treatment, and quenching of welded parts, in which the elements are subjected to heat treatment before welding at temperature T for at least 2t, tbeing defined as the minimum treatment duration at temperature T leading to a specific melting peak energy defined by AED equal to less than 1 J/g. A method according to the invention substantially avoids an increase in the grain size following solution heat treatment after welding. The invention further relates to novel aluminum materials as well as uses therefor.

Manufacturing method for friction welded aluminum alloy parts

Growing community of inventors

Voreppe, France

Timothy Warner