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    THICK PLATES MADE OF AL-CU-LI ALLOY WITH IMPROVED FATIGUE PROPERTIES
    81.
    发明申请
    THICK PLATES MADE OF AL-CU-LI ALLOY WITH IMPROVED FATIGUE PROPERTIES 审中-公开

    公开(公告)号：US20190040508A1

    公开(公告)日：2019-02-07

    申请号：US16074661

    申请日：2017-02-03

    Applicant: CONSTELLIUM ISSOIRE

    Inventor： Jean-Christophe EHRSTROM ,  Carla DA FONSECA BARBATTI

    IPC: C22F1/057 ,  C22C21/16 ,  C22C21/18 ,  C22C21/14

    Abstract: 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.

    TOOLING FOR PRODUCING A METAL PRODUCT BY FEED CASTING
    82.
    发明申请
    TOOLING FOR PRODUCING A METAL PRODUCT BY FEED CASTING 审中-公开

    公开(公告)号：US20190022744A1

    公开(公告)日：2019-01-24

    申请号：US16069224

    申请日：2017-01-27

    Applicant: CONSTELLIUM ISSOIRE

    Inventor： Bernard VALENTIN ,  Arnaud BALLU ,  Soizic BLAIS

    IPC: B22D11/04 ,  B22D11/041 ,  B22D11/103

    Abstract: A tooling for producing a metal product by feed casting, comprising a mold comprising 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 so as to vary between an inactive state in which the holding mechanism exerts said holding force (F2) on the clamping ring (12) such that the clamping ring (12) exerts said 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.

    ISOTROPIC PLATES MADE FROM ALUMINUM-COPPER-LITHIUM ALLOY FOR MANUFACTURING AIRCRAFT FUSELAGES
    85.
    发明申请
    ISOTROPIC PLATES MADE FROM ALUMINUM-COPPER-LITHIUM ALLOY FOR MANUFACTURING AIRCRAFT FUSELAGES 审中-公开

    公开(公告)号：US20170306454A1

    公开(公告)日：2017-10-26

    申请号：US15515891

    申请日：2015-10-01

    Applicant: CONSTELLIUM ISSOIRE

    Inventor： JULIETTE CHEVY ,  BERNARD BES ,  FRANK EBERL

    IPC: C22C21/16 ,  C22F1/057

    CPC classification number: C22C21/16 ,  C22F1/057

    Abstract: 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.

    EXTRADOS STRUCTURAL ELEMENT MADE FROM AN ALUMINIUM COPPER LITHIUM ALLOY
    87.
    发明申请
    EXTRADOS STRUCTURAL ELEMENT MADE FROM AN ALUMINIUM COPPER LITHIUM ALLOY 审中-公开
    来自铝合金锂合金的外部结构元件

    公开(公告)号：US20160144946A1

    公开(公告)日：2016-05-26

    申请号：US14899743

    申请日：2014-06-18

    Applicant: CONSTELLIUM ISSOIRE

    Inventor： Armelle DANIELOU ,  Gaelle POUGET ,  Christophe SIGLI

    IPC: B64C3/26 ,  C22C21/14 ,  C22C1/02 ,  C21D1/30 ,  C21D8/00 ,  B22D21/00 ,  C22F1/057 ,  C22C21/16

    CPC classification number: B64C3/26 ,  B22D21/007 ,  C21D1/30 ,  C21D8/00 ,  C22C1/026 ,  C22C21/12 ,  C22C21/14 ,  C22C21/16 ,  C22F1/057

    Abstract: The invention relates to an extrados structural element made from an aluminum, copper and lithium alloy and a method for manufacturing same. In the method according to the invention, an alloy with composition (in wt %) 4.2 to 5.2 Cu, 0.9 to 1.2 Li, 0.1 to 0.3 Ag, 0.1 to 0.25 Mg, 0.08 to 0.18 Zr, 0.01 to 0.15 Ti, optionally up to 0.2 Zn, optionally up to 0.6 Mn, an Fe and Si content level less than or equal to 0.1% each, and other element with a content level less than or equal to 0.05% each and 0.15% in total, the aluminum is poured, homogenized, deformed hot and optionally cold, placed in a solution at a temperature of at least 515° C., pulled from 0.5 to 5% and annealed. The combination in particular of the magnesium, copper and manganese content with the temperature in solution can reach a very advantageous elasticity under compression limit. Thus, the products according to the invention having a thickness of at least 12 mm have an elasticity under compression limit in the longitudinal direction of at least 645 MPa and an elongation in the longitudinal direction of at least 7%.

    Abstract translation: 本发明涉及由铝，铜和锂合金制成的外部结构元件及其制造方法。 在根据本发明的方法中，组合物（重量％）为4.2〜5.2的Cu，0.9〜1.2的Li，0.1〜0.3的Ag，0.1〜0.25的Mg，0.08〜0.18的Zr，0.01〜0.15的Ti， 0.2 Zn，任选高达0.6Mn，Fe和Si含量各自小于或等于0.1％，其他元素的含量均小于或等于0.05％，总共为0.15％，将铝倒入， 均质化，变形的热和任选冷的，在至少515℃的温度下放置在溶液中，从0.5至5％拉伸并退火。 特别是镁，铜和锰含量与溶液中的温度的组合在压缩极限下可以达到非常有利的弹性。 因此，根据本发明的具有至少12mm厚度的产品在纵向的压缩极限下具有至少645MPa的弹性，并且在纵向上的伸长率至少为7％。

    ALUMINIUM-COPPER-LITHIUM ALLOY SHEETS FOR PRODUCING AEROPLANE FUSELAGES
    88.
    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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