Constellium Issoire

Constellium France

Constellium Neuf-brisach

Alcan Rhenalu

Armelle Danielou

Philippe Lequeu

Timothy Warner

Olivier Ribaud

Philippe Jarry

Christophe Sigli

Soizic Blais

Bernard Valentin

Gaelle Pouget

Christine Henon

Jean-Christophe Ehrstrom

Bechir Chehab

Fabrice Heymes

Pablo Lorenzino

David Dumont

Cedric Gasqueres

Lionel Peguet

Gaëlle Pouget

Isabelle Bordesoules

Jean Christophe Ehrstrom

Isabelle Bordesoules-Eberl

Benoit Commet

Jerome Pignatel

Mathieu Marquette

David Barbier

Benoît Commet

Andrew David Howells

Guenther Hoellrigl

Florence Lauret

Cédric Gasqueres

Samuel Juge

Fanny Mas

A strip intended for the manufacture of brazed heat exchangers, having a core made of an alloy with the composition (weight %):

Strip of aluminium alloy for manufacturing brazed heat exchangers

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&#xb0; 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%.

Extrados structural element made from an aluminium copper lithium alloy

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 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&#x2264;0.1; Fe&#x2264;0.1; others &#x2264;0.05 each and &#x2264;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.

Aluminium-copper-lithium alloy products with improved fatigue properties

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 () is lower than 0.4 ml/100 g, the oxygen content above the liquid surface () is less than 0.5% by volume.

Method for manufacturing products made of aluminum-copper-lithium alloy with improved fatigue properties, and distributor for this method

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

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.

Method of making a structural element for aeronautical construction comprising differential work-hardening

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

A welded assembly of aluminum alloy part, in which

Method for assembling aluminum alloy parts by welding

The present disclosure concerns a method for assembling aluminum alloy parts, in which (i) at least a first aluminum alloy part is procured in a solution heat treated, quenched, optionally cold worked, and naturally aged at ambient temperature or pre-aged temper, and at least a second aluminum alloy part, (ii) said parts are welded to obtain a welded assembly having a welded zone, (iii) cold working the entire welded zone between 0.3% and 5% is performed, (iv) the welded assembly thus cold worked undergoes post-weld aging to obtain a final metallurgical temper.

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 &#x398; of at least 20&#xb0; under a maximum equivalent stress intensity factor Keff max of 10 MPa &#x221a;m for a S-L cracked test sample under a mixed mode I and mode II loading wherein the angle &#x3a8; between a plane perpendicular to the initial crack direction and the load direction is 75&#xb0;.

Al-Li rolled product for aerospace applications

A vertical casting process for an intermediate product, including the steps of (a) preparation of at least two aluminum based alloys, particularly a first alloy with composition P and a second alloy with composition T, (b) casting of the first alloy with composition P to a required height H, and (c) casting of an additional required height Hof the alloy with composition T. The object of this invention is the manufacture of monolithic structural elements with working properties that are variable in at least one direction, and particularly bi-functional or multi-functional structural elements capable of performing at least two functions that are traditionally performed by two different parts.

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Les Echelles, France

Armelle Danielou