Pechiney Rhenalu

Constellium Issoire

Alcan Rhenalu

Constellium France

Philippe Lequeu

Armelle Danielou

Timothy Warner

Philippe Lassince

Fabrice Heymes

Christine Henon

Guy-Michel Raynaud

Olivier Ribaud

David Dumont

Isabelle Bordesoules

Isabelle Bordesoules-Eberl

Benoit Commet

Benoît Commet

Julien Boselli

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

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.

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.

Manufacturing process for semi-finished products containing two aluminum-based alloys

A process for forming a structure element, particularly an lower wing element of an aircraft, manufactured from a rolled, extruded or forged product made of an alloy of composition (% by weight) Cu&equals;4.6-5.3, Mg&equals;0.10-0.50, Mn&equals;0.15-0.45, Si<0.10, Fe<0.15, Zn<0.20, Cr<0.10, other elements <0.05 each and <0.15 total, remainder Al. The product is treated by solution heat treating, quenching, controlled tension to more than 1.5% permanent deformation and aging.

Aircraft structure element made of an Al-Cu-Mg- alloy

Rolled product for use in the manufacture of aircraft structural elements, made of an AlCuMg alloy processed by solution heat treatment, quenching and cold stretching. The product has a composition consisting essentially of, in % by weight: Fe<0.15; Si<0.15; Cu:3.8-4.4; Mg:1-1.5; Mn:0.5-0.8; Zr:0.08-0.15; other elements: <0.05 each and <0.15 total. This product has a thickness of between 6 and 60 mm, with an ultimate tensile strength R in the quenched and stretched temper >475 MPa and yield stress R (L)>370 MPa, with a ratio R /R (L)>1.25.

Product made of an AlCuMg alloy for aircraft structural elements

Aircraft structure element made of an Al-Cu-Mg alloy

A metal sheet with a total thickness &gt;0.5 mm comprising an AlCuMg aluminum alloy consisting essentially of Al and, in percent by weight:

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Issoire, France

Philippe Lequeu