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    ALUMINUM ALLOY COMPRISING LITHIUM WITH IMPROVED FATIGUE PROPERTIES
    3.
    发明申请
    ALUMINUM ALLOY COMPRISING LITHIUM WITH IMPROVED FATIGUE PROPERTIES 审中-公开

    公开(公告)号：US20200165707A1

    公开(公告)日：2020-05-28

    申请号：US16619419

    申请日：2018-06-05

    Applicant: CONSTELLIUM ISSOIRE

    Inventor： Ricky WHELCHEL ,  Mathieu REVIL-BAUDARD ,  Philippe JARRY ,  Bernard BES ,  Fanny MAS

    IPC: C22C21/18 ,  C22C21/16 ,  C22F1/057

    Abstract: 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.

    TRANSFORMATION PROCESS OF AL-CU-LI ALLOY SHEETS
    8.
    发明申请
    TRANSFORMATION PROCESS OF AL-CU-LI ALLOY SHEETS 审中-公开

    公开(公告)号：US20190071753A1

    公开(公告)日：2019-03-07

    申请号：US16184046

    申请日：2018-11-08

    Applicant: CONSTELLIUM ISSOIRE

    Inventor： Frank EBERL ,  Bernard BES

    IPC: C22C21/12 ,  C22F1/057 ,  C22C21/16

    Abstract: The invention concerns a process to manufacture a flat-rolled product, notably for the aeronautic industry containing aluminum alloy comprising 2.1% to 3.9% Cu by weight, 0.7% to 2.0% Li by weight, 0.1% to 1,0% Mg by weight, 0% to 0.6% Ag by weight, 0% to 1% Zn by weight, at least 0.20% Fe +Si by weight, at least one element chosen from Zr, Mn, Cr, Sc, Hf and Ti, the quantity of said element, if chosen, being 0.05% to 0.18% by weight for Zn, 0.1% to 0.6% by weight for Mn, 0.05% to 0.3% by weight for Cr, 0.02% to 0.2% by weight for Sc, 0.05% to 0.5% by weight for Hf and 0.01% to 0.15% by weight for Ti, the other elements at most 0.05% by weight each and 0.15% by weight in total, the rest being aluminum, 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.

    ALUMINIUM-COPPER-LITHIUM ALLOY SHEETS FOR PRODUCING AEROPLANE FUSELAGES
    10.
    发明申请
    ALUMINIUM-COPPER-LITHIUM ALLOY SHEETS FOR PRODUCING AEROPLANE FUSELAGES 审中-公开
    用于生产机场FUSEL的铝合金 - 锂合金板

    公开(公告)号：US20160060741A1

    公开(公告)日：2016-03-03

    申请号：US14781097

    申请日：2014-04-01

    Applicant: CONSTELLIUM ISSOIRE

    Inventor： Juliette CHEVY ,  Bernard BES ,  Frank EBERL ,  Jean-Christophe EHRSTROM

    IPC: C22F1/057 ,  C22C21/14 ,  B22D21/00 ,  C22C21/16

    CPC classification number: C22F1/057 ,  B22D21/007 ,  C22C21/14 ,  C22C21/16

    Abstract: The invention concerns a sheet 0.5 to 8 mm thick made from aluminium alloy. The sheet can be obtained by a method comprising casting, homogenising, hot rolling and optionally cold rolling, solution heat treatment, quenching and tempering, the composition and the tempering being combined in such a way that the elasticity limit in the longitudinal direction Rp0.2(L) is between 395 and 435 MPa. A sheet according to the invention is particularly advantageous for producing aircraft fuselage panels.

    Abstract translation: 本发明涉及一种0.5至8毫米厚的由铝合金制成的片材。 该片材可以通过铸造，均质，热轧和任选的冷轧，固溶热处理，淬火和回火的方法获得，组合物和回火组合，使得纵向R弹性极限Rp0.2 （L）在395和435MPa之间。 根据本发明的片材对于生产飞机机身面板是特别有利的。

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