EP3728667B1 - Procede de fabrication ameliore de tôles en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselage d'avion et tôle correspondante - Google Patents

Procede de fabrication ameliore de tôles en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselage d'avion et tôle correspondante Download PDF

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EP3728667B1
EP3728667B1 EP18833951.9A EP18833951A EP3728667B1 EP 3728667 B1 EP3728667 B1 EP 3728667B1 EP 18833951 A EP18833951 A EP 18833951A EP 3728667 B1 EP3728667 B1 EP 3728667B1
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manufacturing process
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EP3728667A1 (fr
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Pablo LORENZINO
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Constellium Issoire SAS
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Constellium Issoire SAS
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D8/00—Modifying the physical properties by deformation combined with, or followed by, heat treatment
    • C21D8/02—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips
    • C21D8/0221—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips characterised by the working steps
    • C21D8/0226—Hot rolling
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D8/00—Modifying the physical properties by deformation combined with, or followed by, heat treatment
    • C21D8/02—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips
    • C21D8/0221—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips characterised by the working steps
    • C21D8/0236—Cold rolling
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D8/00—Modifying the physical properties by deformation combined with, or followed by, heat treatment
    • C21D8/02—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips
    • C21D8/0247—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips characterised by the heat treatment
    • C21D8/0273—Final recrystallisation annealing
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C22C21/14—Alloys based on aluminium with copper as the next major constituent with silicon
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C22C21/16—Alloys based on aluminium with copper as the next major constituent with magnesium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/057—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent

Definitions

  • the present invention relates in general to processes for the manufacture of aluminum-based 2XXX alloy sheets comprising lithium, in particular such improved processes particularly suited to the constraints of the aeronautical and space industry.
  • the methods according to the invention are especially suitable for the manufacture of fuselage sheets.
  • Al-Cu-Li alloys are of particular interest in the manufacture of rolled aluminum alloy products, in particular fuselage elements, as they offer generally higher compromises in properties than conventional alloys, particularly in terms of the compromise between fatigue , damage tolerance and mechanical strength. This makes it possible in particular to reduce the thickness of wrought Al-Cu-Li alloy products, thus further maximizing the weight reduction they provide. On the other hand, during the manufacture of such products, it is important to take into account the constraints of the aeronautical industry where any time saving in the manufacture of semi-finished products constitutes a significant competitive advantage.
  • the document EP 1 966 402 B2 discloses in particular fuselage laminations with particularly advantageous properties, these laminations being produced using an alloy comprising in particular, in percentage by weight, Cu: 2.1 to 2.8; Li: 1.1 to 1.7; Ag: 0.1 to 0.8; Mg: 0.2 to 0.6; Mn: 0.2 to 0.6; Zr ⁇ 0.04; Fe and Si ⁇ 0.1 each; unavoidable impurities ⁇ 0.05 each and 0.15 in total; remains aluminum.
  • such a product cannot however be subjected to a manufacturing process optimized in terms of duration of tempering without a deterioration of its properties, in particular of its compromise between mechanical resistance and tenacity.
  • the patent application WO2011/141647 describes an aluminum-based alloy comprising, in% by weight, 2.1 to 2.4% Cu, 1.3 to 1.6% Li, 0.1 to 0.51 Ag, 0.2 to 0.6% Mg, 0.05 to 0.15% Zr, 0.1 to 0.5% Mn, 0.01 to 0.12% Ti, optionally at least one element chosen from Cr, Se, and Hf, the amount of the element, if chosen, being 0.05 to 0.3% for Cr and for Se, 0.05 to 0.5% for Hf, an amount of Fe and of Si less than or equal to 0.1 each, and unavoidable impurities at a content less than or equal to 0.05 each and 0.15 in total.
  • the alloy allows the production of extruded, rolled and/or forged products particularly suited to the manufacture of elements for the lower surfaces of aircraft wing.
  • the temperature used for tempering in the examples is 155°C.
  • the patent application WO2013/054013 relates to the process for manufacturing a rolled product, in particular for the aeronautical industry, based on an aluminum alloy with a composition of 2.1 to 3.9% by weight of Cu, 0.7 to 2.0% by weight of Li, 0.1 to 1.0 wt% Mg, 0 to 0.6 wt% Ag, 0 to 1% wt% Zn, at most 0.20 wt% Fe + Si, at least an element selected from Zr, Mn, Cr, Se, Hf and Ti, the amount of said element, if selected, being 0.05 to 0.18% by weight for Zr, 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 Se, 0.05 to 0.5% by weight for Hf and from 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 remainder aluminum, in which, in particular, leveling and/or traction is carried out with cumulative deformation of at least
  • the patent application WO2010/055225 relates to a process for the manufacture of an extruded, rolled and/or forged product based on an aluminum alloy, in which: a bath of liquid metal is produced comprising 2.0 to 3.5% by weight of Cu, 1, 4 to 1.8 wt% Li, 0.1 to 0.5 wt% Ag, 0.1 to 1.0 wt% Mg, 0.05 to 0.18 wt% Zr , 0.2 to 0.6% by weight of Mn and at least one element selected from Cr, Sc, Hf and Ti, the amount of the element, if selected, being from 0.05 to 0.3 % by weight for Cr and for Sc, 0.05 to 0.5 % by weight for Hf and 0.01 to 0.15 % by weight for Ti, the remainder being aluminum and unavoidable impurities; a raw shape is cast from the liquid metal bath and said raw shape is homogenized at a temperature between 515°C and 525°C so that the equivalent time at 520°C for homogenization is between 5 and 20 hours
  • WO2015082779 discloses a process for manufacturing a rolled or forged product whose thickness is between 14 and 100 mm, in aluminum alloy of composition, in% by weight, Cu: 1.8 - 2.6; Li: 1.3 - 1.8; Mg: 0.1 - 0.5; Mn: 0.1 - 0.5 and Zr ⁇ 0.05 or Mn ⁇ 0.05 and Zr 0.10 - 0.16; Ag: 0 - 0.5; Zn ⁇ 0.20; Ti: 0.01 - 0.15; Fe: ⁇ 0.1; Si: ⁇ 0.1; other elements ⁇ 0.05 each and ⁇ 0.15 in total, rest aluminum whose density is less than 2.670 g/cm3 including homogenization, hot deformation whose conditions are such when the manganese content is 0.1 than 0.5% by weight and the zirconium content is less than 0.05% by weight the final heat deformation temperature is at least 400°C and when the manganese content is less than 0.05% by weight and the zirconium content is between 0.10 and
  • the products according to the invention are distinguished by their thickness intended for fuselage sheets whereas those disclosed in WO2015082779 are intended for the manufacture of aircraft wing underside elements and have a thickness greater than 14 mm.
  • the temperature used for tempering in the examples is between 140°C and 155°C.
  • US2007/0181229 discloses an aluminum alloy comprising 2.1 to 2.8 by weight. % Cu, 1.1 to 1.7 by weight. % Li, 0.1 to 0.8 by weight. % Ag, 0.2 to 0.6 by weight. % Mg, 0.2 to 0.6 by weight. % Mn, a Fe and Si content less than or equal to 0.1 by weight. % each, and a content of unavoidable impurities less than or equal to 0.05 by weight. % each and 0.15 by weight. % total, and the alloy being substantially free of zirconium.
  • the subject of the invention is a process for manufacturing a wrought aluminum alloy product 2. according to claim 1.
  • Another subject of the invention is a product capable of being obtained by the process according to the invention according to claim 11.
  • the static mechanical characteristics in tension in other words the breaking strength R m , the conventional yield strength at 0.2% elongation R p0.2 , and the elongation at break A%, are determined by a tensile test according to standard NF EN ISO 6892-1 / ASTM E8 -E8M-13, the sampling and direction of the test being defined by standard EN 485-1.
  • a curve giving the effective stress intensity factor as a function of the effective crack extension, known as the R-curve, is determined according to E561-10 (2010).
  • the critical stress intensity factor Kc in other words the intensity factor that makes the crack unstable, is calculated from the R-curve.
  • the stress intensity factor KCO is also calculated by assigning the initial crack length at the beginning of the monotonic load, at the critical load. These two values are calculated for a specimen of the required shape.
  • K app represents the K CO factor corresponding to the specimen which was used to perform the R curve test.
  • K eff represents the K C factor corresponding to the specimen which was used to perform the R curve test.
  • ⁇ a eff(max) represents the crack extension of the last valid point of the R-curve.
  • the length of the R-curve - i.e. the maximum crack extension of the curve - is an important parameter in itself, in particular for fuselage design.
  • Kr60 represents the effective stress intensity factor for an effective crack extension ⁇ a eff of 60 mm.
  • the method according to the invention comprises in particular a step of tempering the stretched sheet by heating to a temperature of at least 160° C. for a maximum duration of 30 hours.
  • the product of particular composition has a tenacity equal to or different from less than 8%, preferably less than 5%, more preferably still less than 4% or even 2%, from that of the same product manufactured according to a conventional process of the prior art, in particular a process identical to that of the invention with the exception of tempering which would typically be tempering by heating at approximately 152° C. for approximately 48 hours.
  • the product of particular composition advantageously has a conventional limit of elasticity Rp0.2 (TL) equal to or different from less than 8%, preferentially less than 5%, more preferentially still from less of 4% or even 2%, of that of the same product manufactured according to a conventional process of the prior art, in particular a process identical to that of the invention with the exception of tempering which would typically be tempering by heating to approximately 152° C for about 48 hours.
  • TL conventional limit of elasticity
  • the process for manufacturing a wrought aluminum alloy product according to the invention firstly comprises a step of casting a plate of a particular alloy.
  • the alloy comprises, in percentage by weight, Cu: 2.1 to 2.8; Li: 1.1 to 1.7; Mg: 0.2 to 0.9; Mn: 0.2 to 0.6; Ti 0.01 to 0.2; Ag ⁇ 0.1; Zr ⁇ 0.08; Fe and Si ⁇ 0.1 each; unavoidable impurities ⁇ 0.05 each and 0.15 in total; remains aluminum.
  • the aluminum alloy plate comprises from 2.2 to 2.6% by weight of Cu, preferably from 2.3 to 2.5% by weight.
  • the inventors have discovered that if the copper content is greater than 2.8% or even 2.6% or even even 2.5% by weight, the toughness properties can in certain cases drop rapidly, whereas, if the copper content is less than 2.1% or even 2.2% or even 2.3% by weight, the mechanical strength may be too low.
  • the aluminum alloy plate includes 1.1 to 1.7 wt% lithium. Preferably, it comprises from 1.2 to 1.6% by weight of Li, or else from 1.25 to 1.55% by weight. A lithium content above 1.7% or even 1.6% or even 1.55% by weight can lead to thermal stability problems. A lithium content of less than 1.1% or even 1.2% or even 1.25% by weight may result in inadequate mechanical strength and lower density gain.
  • the aluminum alloy plate includes 0.2 to 0.9 wt% magnesium. According to an advantageous mode, the aluminum alloy plate comprises from 0.25 to 0.75% by weight of Mg.
  • the aluminum alloy plate comprises 0.01 to 0.2% by weight of titanium.
  • the addition of titanium in different forms, Ti, TiB or TiC makes it possible in particular to control the granular structure during the cast plate.
  • the aluminum alloy plate comprises from 0.01 to 0.10% by weight of Ti.
  • the plate further comprises less than 0.1% by weight of silver.
  • the aluminum alloy plate comprises less than 0.05% by weight of Ag, preferably less than 0.04% by weight.
  • the aluminum alloy plate includes 0.2 to 0.6 wt% manganese. Preferably, it comprises from 0.25 to 0.45% by weight of Mn.
  • the aluminum alloy plate comprises less than 0.08% by weight of zirconium. In an even more preferred mode, it comprises less than 0.05% by weight of Zr, preferably less than 0.04% by weight and, even more preferably, less than 0.03% or even 0.01% by weight .
  • a low zirconium content makes it possible to improve the toughness of the Al-Cu-Li-Ag-Mg-Mn alloys according to the invention; in particular, the length of the R curve is significantly increased.
  • the use of manganese instead of zirconium in order to control the granular structure has several additional advantages such as obtaining a recrystallized structure and isotropic properties in particular for a thickness of 0.8 to 12.7 mm.
  • the recrystallization rate of the products according to the invention is greater than 80%, preferably greater than 90%.
  • Iron and silicon generally affect toughness properties.
  • the amount of iron should be limited to 0.1% by weight (preferably 0.05% by weight) and the amount of silicon should be limited to 0.1% by weight (preferably 0.05% by weight ).
  • Unavoidable impurities should be limited to 0.05% by weight each and 0.15% by weight in total.
  • the manufacturing process according to the invention further comprises a step of homogenizing the casting plate at a temperature of 480 to 520° C. for 5 to 60 hours and, preferably, this step is carried out between 490 and 510° C. for 8 to 20 hours. Homogenization temperatures higher than 520° C. indeed tend to reduce the toughness performance in certain cases.
  • the homogenized plate is then hot and optionally cold rolled into a sheet.
  • the hot rolling is carried out at an initial temperature of 420 to 490°C, preferably 440 to 470°C.
  • the hot rolling is preferably carried out to obtain a thickness between approximately 4 and 12.7 mm.
  • a cold rolling step can optionally be added, if required.
  • the sheet obtained has a thickness of between 0.8 and 12.7 mm, and the invention is more advantageous for sheets 1.6 to 9 mm thick, and even more advantageous for sheets 2 to 7 mm thick.
  • the rolled product is then brought into solution by heat treatment at a temperature of 470 to 520° C. for 15 min to 4 hours, then quenched typically with water at ambient temperature.
  • the product placed in solution is then subjected to a tensile step in a controlled manner with a permanent deformation of 1 to 6%.
  • the traction in a controlled manner is carried out with a permanent deformation of between 2.5 and 5%.
  • the alloy product according to the invention can be manufactured using an optimized process, the tempering step of said process being able to be carried out at particularly high temperatures, in particular above 160 °C and even more so that the duration of the tempering can be, consequently, greatly reduced.
  • this process optimization can be achieved without deterioration of the properties of the product, in particular without affect the compromise yield strength Rp0.2 (LT) - toughness Kapp (TL).
  • the pulled product is subjected to a tempering step by special heating to a temperature of at least 160° C. for a maximum duration of 30 hours.
  • the tempering can even be carried out at a temperature of at least 162° C., preferably of at least 165° C. and, even more preferably, of at least 170° C. for a maximum duration of 30 hours, advantageously 28 hours. even 25h or 20h.
  • the tempering step is carried out at a temperature of at most 200°C and preferably of at most 190°C and preferably of at most 180°C.
  • tempering is carried out at an equivalent time t i at 165° C. of between 15 and 35 hours, preferably between 20 and 30 hours.
  • the present inventors have found that the products obtained by the process according to the invention do not contain, among the phases containing lithium, not the ⁇ ' phase (Al 3 Li) but only the T1 phase (Al 2 CuLi) which is advantageous in particular as regards the thermal stability of the product obtained.
  • the product of particular composition has a Kapp tenacity (TL) equal to or different from less than 8%, preferably less than 5%, more preferably still from less than 4 or even 2%, from that of the same product manufactured according to a conventional process of the prior art, in particular a process identical to that of the invention with the exception of tempering which would typically be tempering by heating at approximately 152° C. for approximately 48 hours.
  • TL Kapp tenacity
  • the product of particular composition also advantageously has a conventional limit of elasticity Rp0.2 (LT) equal to or different from less than 8%, preferentially less than 5%, more preferentially still from less than 4 or even 2%, of that of the same product manufactured according to a conventional process of the prior art, in particular a process identical to that of the invention with the exception of tempering which would typically be tempering by heating at approximately 152° C. for approximately 48 hours.
  • Rp0.2 conventional limit of elasticity
  • the method according to the invention makes it possible to obtain a product having very good thermal stability.
  • the product obtained directly at the end of the process according to the invention that is to say at the end of tempering by heating to a temperature of at least 160° C. for a maximum duration of 30 hours , and after a heat treatment of 1000h at 85°C, exhibits a plane stress toughness, Kapp (TL), and/or an effective stress intensity factor for an effective crack extension ⁇ a eff of 60 mm, Kr60 (TL), which differs not more than 7%, preferably not more than 5% and, even more preferably not more than 4% or even 2%.
  • the product according to the invention is a sheet and more preferably a thin sheet, more preferably still a thin fuselage sheet.
  • the product according to the invention can therefore advantageously be used in a fuselage panel for an aircraft.
  • Alloy A with the composition shown in Table 1 is an alloy according to the invention.
  • Table 1- Chemical composition (% by weight) Casting reference Whether Fe Cu min mg Zr Li Ag You HAS 0.01 0.03 2.3 0.3 0.3 ⁇ 0.01 1.4 ⁇ 0.01 0.03 Analysis on solid SOES (spark optical emission spectrometry). Average over three samples.
  • the process used for the manufacture of the alloy A sheet was as follows: a plate approximately 400 mm thick in alloy A was cast, homogenized at 508° C. for approximately 12 hours and then scalped. The plate was hot rolled to obtain a sheet having a thickness of 4 mm. It was placed in solution at approximately 500° C. then quenched in cold water. The sheet was then stretched with a permanent elongation of 3 to 4%. The following tempers were carried out on different samples of the sheet: 48h-152°C, 40h-155°C, 30h-160°C and 25h-165°C.
  • part of the sheets was subjected to a thermal stability test of 1000 hours at 85°C.
  • Samples were taken at full thickness to measure static tensile mechanical characteristics and toughness in the T-L direction.
  • the specimens used for the toughness measurement were specimens of CCT760 geometry: 760 mm (L) ⁇ 1250 mm (TL).
  • Alloy B of composition shown in Table 4 is a reference alloy known in particular from document EP 1 966 402 B2 .
  • Table 4 Chemical composition (% by weight) Casting reference Whether Fe Cu min mg Zr Li Ag You B 0.03 0.03 2.4 0.3 0.3 ⁇ 0.01 1.4 0.34 0.02 Analysis on solid SOES (spark optical emission spectrometry). Average over three samples.
  • the process used for the manufacture of the sheet in alloy B was as follows: a plate approximately 400 mm thick in alloy B was cast, homogenized at 500° C. for approximately 12 hours and then scalped. The plate was hot rolled to obtain a sheet having a thickness of 5 mm. It was placed in solution at approximately 500° C. then quenched in cold water. The sheet was then stretched with a permanent elongation of 1 to 5%. The following tempers were carried out on different samples of the sheet: 48h-152°C, and 25h-165°C.
  • test pieces were test pieces with CCT760 geometry: 760mm (L) x 1250 mm (TL)

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EP18833951.9A 2017-12-20 2018-12-17 Procede de fabrication ameliore de tôles en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselage d'avion et tôle correspondante Active EP3728667B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1762674A FR3075078B1 (fr) 2017-12-20 2017-12-20 Procede de fabrication ameliore de toles en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselage d'avion
PCT/FR2018/053316 WO2019122639A1 (fr) 2017-12-20 2018-12-17 Procede de fabrication ameliore de toles en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselage d'avion

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EP3728667A1 EP3728667A1 (fr) 2020-10-28
EP3728667B1 true EP3728667B1 (fr) 2022-06-22

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US (1) US11732333B2 (zh)
EP (1) EP3728667B1 (zh)
JP (1) JP2021508357A (zh)
CN (1) CN111492074A (zh)
CA (1) CA3085811A1 (zh)
FR (1) FR3075078B1 (zh)
WO (1) WO2019122639A1 (zh)

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CN110423926B (zh) * 2019-07-29 2020-12-29 中国航发北京航空材料研究院 一种耐热铝锂合金及其制备方法
FR3104172B1 (fr) * 2019-12-06 2022-04-29 Constellium Issoire Tôles minces en alliage d’aluminium-cuivre-lithium à ténacité améliorée et procédé de fabrication
CN111945084A (zh) * 2020-08-01 2020-11-17 安徽家园铝业有限公司 一种铝合金型材的热处理工艺
CN113388760B (zh) * 2021-06-17 2022-05-06 上海华峰铝业股份有限公司 一种Al-Cu-Mn-Zr系铝合金、铝合金复合板材及其制备方法和用途

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ES2314929T3 (es) * 2005-06-06 2009-03-16 Alcan Rhenalu Chapa de aluminio-cobre-litio con alta tenacidad para fuselaje de avion.
FR2894985B1 (fr) 2005-12-20 2008-01-18 Alcan Rhenalu Sa Tole en aluminium-cuivre-lithium a haute tenacite pour fuselage d'avion
US8771441B2 (en) 2005-12-20 2014-07-08 Bernard Bes High fracture toughness aluminum-copper-lithium sheet or light-gauge plates suitable for fuselage panels
FR2925523B1 (fr) * 2007-12-21 2010-05-21 Alcan Rhenalu Produit lamine ameliore en alliage aluminium-lithium pour applications aeronautiques
FR2938553B1 (fr) * 2008-11-14 2010-12-31 Alcan Rhenalu Produits en alliage aluminium-cuivre-lithium
FR2960002B1 (fr) * 2010-05-12 2013-12-20 Alcan Rhenalu Alliage aluminium-cuivre-lithium pour element d'intrados.
FR2981365B1 (fr) * 2011-10-14 2018-01-12 Constellium Issoire Procede de transformation ameliore de toles en alliage al-cu-li
FR3014448B1 (fr) * 2013-12-05 2016-04-15 Constellium France Produit en alliage aluminium-cuivre-lithium pour element d'intrados a proprietes ameliorees

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EP3728667A1 (fr) 2020-10-28
FR3075078B1 (fr) 2020-11-13
CA3085811A1 (fr) 2019-06-27
CN111492074A (zh) 2020-08-04
US11732333B2 (en) 2023-08-22
JP2021508357A (ja) 2021-03-04
US20210071285A1 (en) 2021-03-11
WO2019122639A1 (fr) 2019-06-27
FR3075078A1 (fr) 2019-06-21

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