EP2766503A1 - Verbessertes verfahren zum bearbeiten von metallblechen aus einer al-cu-li-legierung - Google Patents

Verbessertes verfahren zum bearbeiten von metallblechen aus einer al-cu-li-legierung

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Publication number
EP2766503A1
EP2766503A1 EP12788613.3A EP12788613A EP2766503A1 EP 2766503 A1 EP2766503 A1 EP 2766503A1 EP 12788613 A EP12788613 A EP 12788613A EP 2766503 A1 EP2766503 A1 EP 2766503A1
Authority
EP
European Patent Office
Prior art keywords
weight
mpa
heat treatment
sheet
process according
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP12788613.3A
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English (en)
French (fr)
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EP2766503B1 (de
Inventor
Bernard Bes
Frank Eberl
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Constellium Issoire SAS
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Constellium France SAS
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Classifications

    • 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
    • C22C21/18—Alloys based on aluminium with copper as the next major constituent with zinc
    • 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
    • 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
    • C22F1/002—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working by rapid cooling or quenching; cooling agents used therefor
    • 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 invention relates to aluminum-copper-lithium alloy products, more particularly, such products, their manufacturing and use processes, intended in particular for aeronautical and aerospace construction.
  • Aluminum alloy rolled products are developed to produce high strength parts for the aerospace industry and the aerospace industry in particular.
  • Aluminum alloys containing lithium are very interesting in this respect, since lithium can reduce the density of aluminum by 3% and increase the modulus of elasticity by 6% for each weight percent of lithium added.
  • their performance compared to other properties of use must reach that of commonly used alloys, in particular in terms of a compromise between the static mechanical strength properties (yield strength, resistance to rupture) and the properties of damage tolerance (toughness, resistance to the propagation of fatigue cracks), these properties being in general antinomic. The improvement of the compromise between mechanical resistance and damage tolerance is constantly sought.
  • the sheet must be stored in a cold room at a sufficiently low temperature and for a sufficiently short duration so as to avoid natural ripening.
  • this solution heat treatment requires large furnaces, which makes the operation inconvenient, including with respect to the same operation performed on flat sheet.
  • the possible need for a cold room adds to the costs and disadvantages of the state of the art.
  • the sheet may be deformed and cause problems related to this deformation, for example when it comes to the position in the jaws of the drawing-forming tool.
  • this operation must possibly be repeated, if the material does not present, in the metallurgical state in which it is, sufficient formability to achieve the desired form in a single operation.
  • This variant is used in particular when the targeted shaping is too important to be carried out in a single operation from a state W, but can however be carried out in two passes from the state O.
  • the plates in the state O being stable in time are easier to transform.
  • the manufacture of the sheet in the O state involves a final annealing of the raw rolling sheet, and therefore generally an additional manufacturing step, and also a dissolution and quenching of the product formed which is contrary the aim of simplification aimed at by the present invention.
  • the shaping of complex structural elements in the T8 state is limited to mild shaping cases because the elongation and the ratio R m / R p0 , 2 are too low in this state. It should be noted that the properties that are optimal in terms of compromise of properties must be obtained once the part has been shaped, in particular as a fuselage element, since it is the shaped part which must in particular have good performances. in damage tolerance to avoid too frequent repair of fuselage elements. And 'generally accepted that high strains after solution hardening and lead to an increase in strength but a sharp deterioration in toughness.
  • No. 5,032,359 discloses a broad family of aluminum-copper-lithium alloys in which the addition of magnesium and silver, in particular between 0.3 and 0.5 percent by weight, makes it possible to increase the mechanical strength.
  • No. 5,455,003 discloses a process for manufacturing Al-Cu-Li alloys which have improved mechanical strength and toughness at cryogenic temperature, in particular through proper work-hardening and tempering.
  • US Pat. No. 7,438,772 describes alloys comprising, in percentage by weight, Cu: 3-5, Mg: 0.5-2, Li: 0.01-0.9 and discourages the use of higher lithium content because of degradation of the compromise between toughness and mechanical strength.
  • US Pat. No. 7,229,509 describes an alloy comprising (% by weight): (2.5-5.5) Cu, (0.1-2.5) Li, (0.2-1.0) Mg, (0, 2-0.8) Ag, (0.2-0.8) Mn, 0.4 max Zr or other grain refining agents such as Cr, Ti, Hf, Se, V.
  • US Patent Application 2009 / 142222 A1 discloses alloys comprising (in% by weight), 3.4 to 4.2% Cu, 0.9 to 1.4% Li, 0.3 to 0.7% Ag, 0.1 at 0.6% Mg, 0.2 to 0.8% Zn, 0.1 to 0.6% Mn and 0.01 to 0.6% of at least one element for structure control granular. This application also describes a process for manufacturing spun products.
  • Patent EP 1,966,402 describes a non-zirconium-containing alloy for fuselage sheets of essentially recrystallized structure comprising (in% by weight) (2.1 - 2.8) Cu, (1.1-1.7) Li (0.2-0.6) Mg, (0.1-0.8) Ag, (0.2-0.6) Mn.
  • the products obtained in the T8 state are not suitable for shaping, with in particular a ratio R m / R p0 .2 of less than 1.2 in the directions L and LT.
  • EP 1,891,247 discloses an alloy for fuselage plates comprising (in% by weight) (3.0-3.4) Cu, (0.8-1.2) Li, (0.2-0.6 ) Mg, (0.2-0.5) Ag and at least one of Zr, Mn, Cr, Se, Hf and Ti, wherein the Cu and Li contents are Cu + 5/3 Li ⁇ 5.2.
  • the products obtained in the T8 state are not suitable for shaping, with in particular a ratio R m / / R p o. 2 less than 1, 2 in directions L and LT.
  • Patent EP 1045043 describes the process for manufacturing parts made of alloy AA2024 type, and in particular highly deformed parts, by the combination of an optimized chemical composition and particular manufacturing processes, to avoid as much as possible the solution in solution on formed sheet.
  • a first object of the invention is a process for manufacturing a laminated product based on aluminum alloy, in particular for the aeronautical industry in which, successively,
  • an aluminum-based liquid metal bath comprising 2.1 to 3.9% by weight Cu, 0.7 to 2.0% by weight Li, 0.1 to 1.0% by weight of Mg, 0 to 0.6% by weight of Ag, 0 to 1% by weight of Zn, at most 0.20% by weight of Fe + Si, at least one 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,
  • planing is carried out and / or the sheet is controlledly tensile with a cumulative deformation of at least 0.5% and less than 3%
  • a short heat treatment is carried out in which said sheet reaches a temperature between 130 and 170 ° C and preferably between 150 and 160 ° C for 0.1 to 13 hours and preferably 1 to 5 hours.
  • a second object of the invention is a laminated product obtainable by a process according to the invention, having between 0 and 50 days after short heat treatment, a combination of at least one property selected from R p o, 2 (L) of at least 220 MPa and preferably at least 250 MPa, R p o, 2 (LT) of at least 200 MPa and preferably at least 230 MPa, R ra (L) of at least 340 MPa and preferably at least 380 MPa, R m (LT) of at least 320 MPa and preferably at least 360 MPa with a property selected from A% (L) of at least 14% and preferably at least 15%, A% (LT) at least 24% and preferably at least 26%, R m / R p o, 2 (L) at least 1, 40 and preferably at least 1.45, R m / Rp0, 2 (LT) at least 1, 45 and preferably at least 1, 50.
  • Another subject of the invention is a product that can be obtained by a process according to the invention, having a tensile yield strength R p oj2 (L) at least substantially equal and a toughness K R greater than preferably at least 5%, to those obtained by a similar process not including short heat treatment.
  • Yet another object of the invention is the use of a product that can be obtained by a method according to the invention for the manufacture of an aircraft fuselage skin.
  • the static mechanical characteristics in tension in other words the tensile strength R m , the conventional yield stress at 0.2% elongation R p o, 2, and the elongation at break A%, are determined by a tensile test according to standard NF EN ISO 6892-1, the sampling and the direction of the test being defined by the EN 485-1 standard.
  • the plane stress toughness is determined by a curve of the stress intensity factor as a function of the crack extension, known as the R curve, according to ASTM E 561.
  • the critical stress intensity factor Kc in other words the intensity factor which makes the crack unstable, is calculated from the curve R.
  • the stress intensity factor ⁇ ⁇ > is also calculated by assigning the initial crack length to the critical load , at the beginning of the monotonous charge.
  • K app represents the Kco factor corresponding to the specimen that was used to perform the R curve test.
  • K e ff represents the Kc factor corresponding to the specimen that was used to perform the R curve test.
  • e ff ( m ax) represents the crack extension of the last valid point of the R curve.
  • a "structural element” or “structural element” of a mechanical construction is called a mechanical part for which the static and / or dynamic mechanical properties are particularly important for the performance of the structure, and for which a structural calculation is usually prescribed or realized. These are typically elements whose failure is likely to endanger the safety of said construction, its users, its users or others.
  • these structural elements include the elements that make up the fuselage (such as fuselage skin, fuselage skin in English), stiffeners or stringers, bulkheads, fuselage (circumferential frames), the wings (such as upper or lower wing skin, stringers or stiffeners), ribs and spars) and the composite empennage including horizontal and vertical stabilizers (horizontal or vertical stabilizers), as well as floor beams, seat tracks and doors.
  • fuselage such as fuselage skin, fuselage skin in English
  • stiffeners or stringers such as upper or lower wing skin, stringers or stiffeners
  • ribs and spars the composite empennage including horizontal and vertical stabilizers (horizontal or vertical stabilizers), as well as floor beams, seat tracks and doors.
  • solution, quenching and leveling and / or pulling is carried out at least one short heat treatment with a duration and a temperature such that the sheet reaches a temperature of between 130 and 170 ° C.
  • the yield strength R p o, 2 decreases significantly, that is to say at least 20 MPa or more, while the elongation A% is increased. that is, it is multiplied by a factor of at least 1.1, or even at least 1.2, or at least 1.3, relative to the state obtained without short heat treatment, typically T3 or T4.
  • the short heat treatment is therefore not an income with which one would obtain a state T8 but a particular heat treatment which makes it possible to obtain a non-standardized state particularly suitable for shaping.
  • a sheet in the T8 state has a yield strength greater than that of a T3 or T4 state while after the short heat treatment according to the invention the elastic limit is on the contrary lower than that of a T3 or T4 state.
  • the short heat treatment is carried out so as to obtain a time equivalent to 150 ° C. from 0.5 h to 6 h and preferably from 1 h to 4 h and preferably from 1 h to 3 h, the equivalent time t to 150 h. ° C is defined by the formula:
  • T in Kelvin
  • T ref is a reference temperature set at 423 K.
  • the present inventors have found that the mechanical properties obtained at the end of the short heat treatment are stable over time, which makes it possible to use the sheets in the state obtained at the end of the short heat treatment.
  • the sheet metal place in the state O or the state W for the shaping.
  • the present inventors have found that, surprisingly, not only the short heat treatment makes it possible to simplify the manufacturing process of the products by eliminating the shaping on state O or W, but moreover that the compromise between static mechanical resistance and tolerance to damage is at least the same or even improved by the method of the invention in the returned state compared to a method not comprising short heat treatment.
  • the compromise obtained between static mechanical strength and toughness is improved compared with the state of the art.
  • the advantage of the process according to the invention is obtained for products having a copper content of between 2.1 and 3.9% by weight.
  • the copper content is at least 2.8% or 3% by weight.
  • a maximum copper content of 3.7 or 3.5% by weight is preferred.
  • the lithium content is between 0.7% or 0.8% and 2.0% by weight.
  • the lithium content is at least 0.85% by weight.
  • a maximum lithium content of 1.6 or even 1.2% by weight is preferred.
  • the magnesium content is between 0.1% and 1.0% by weight.
  • the magnesium content is at least 0.2% or even 0.25% by weight. In one embodiment of the invention, the maximum magnesium content is 0.6% by weight.
  • the silver content is between 0% and 0.6% by weight. In an advantageous embodiment of the invention, the silver content is between 0.1 and 0.5% by weight and preferably between 0.15 and 0.4% by weight.
  • the addition of silver contributes to improving the compromise of mechanical properties of the products obtained by the process according to the invention.
  • the zinc content is between 0% and 1% by weight.
  • Zinc is generally an undesirable impurity, especially because of its contribution to the density of the alloy, however in some cases zinc may be used alone or in combination with silver.
  • the zinc content is less than 0.40% by weight, preferably less than 0.2% by weight. In one embodiment of the invention, the zinc content is less than 0.04% by weight. .
  • the alloy also contains at least one element that can contribute to controlling the grain size selected from Zr, Mn, Cr, Se, Hf and Ti, the amount of the 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 0.5 to 0.5% by weight for Hf and 0.01 to 0.15% by weight for Ti.
  • the zirconium content is at least 0.11% by weight.
  • the manganese content is between 0.2 and 0.4% by weight and the zirconium content is less than 0.04% by weight.
  • the sum of the iron content and the silicon content is at most 0.20% by weight.
  • the iron and silicon contents are each at most 0.08% by weight.
  • the iron and silicon contents are at most 0.06% and 0.04% by weight, respectively.
  • a controlled and limited iron and silicon content contributes to the improvement of the compromise between mechanical resistance and damage tolerance.
  • the other elements have a content of at most 0.05% by weight each and 0.15% by weight in total, it is inevitable impurities, the rest is aluminum.
  • the manufacturing method according to the invention comprises the stages of production, casting, rolling, dissolution, quenching, planing and / or pulling and short heat treatment.
  • a bath of liquid metal is produced so as to obtain an aluminum alloy of composition according to the invention.
  • the liquid metal bath is then cast as a rolling plate.
  • the rolling plate can then optionally be homogenized so as to reach a temperature between 450 ° C and 550 ° and preferably between 480 ° C and 530 ° C for a period of between 5 and 60 hours.
  • the homogenization treatment can be carried out in one or more stages.
  • the rolling plate is then hot-rolled and optionally cold-rolled into a sheet.
  • the thickness of said sheet is between 0.5 and 15 mm and preferably between 1 and 8 mm.
  • the product thus obtained is then put in solution typically by a heat treatment making it possible to reach a temperature of between 490 and 530 ° C. for 15 minutes to 8 hours, and then typically quenched with water at room temperature or, preferably, with water. Cold water.
  • planing is carried out and / or controlled traction said sheet with a cumulative deformation of at least 0.5% and less than 3%.
  • the deformation performed during planing is not always known precisely but it is estimated at about 0.5%.
  • the controlled traction is implemented with a permanent deformation of between 0.5 to 2.5% and preferably between 0.5 to 1.5%.
  • the sheet obtained by the process according to the invention preferably has, between 0 and 50 days and preferably between 0 and 200 days after short heat treatment, a combination of at least one property.
  • the sheet obtained by the process according to the invention has a ratio R m / R p o , 2 in the direction LT of at least 1, 52 or 1.53.
  • the sheet obtained by the process according to the invention has a yield strength R p o, 2 (L) less than 290 MPa and preferably less than 280 MPa and R p o, 2 (LT) less than 270 MPa and preferably less than 260 MPa.
  • the sheet is thus ready for additional cold deformation, in particular a 3-dimensional shaping operation.
  • An advantage of the invention is that this additional deformation can locally or generally reach values of 6 to 8% or even up to 10%.
  • a minimum cumulative deformation of 2% between said additional deformation and cumulative deformation by planing and / or controlled traction performed before the short heat treatment is advantageous.
  • the additional cold deformation is locally or generally at least 1%, preferably at least 4% and preferably at least 6%.
  • an income is produced in which said sheet reaches a temperature between 130 and 170 ° C and preferably between 150 and 160 ° C for 5 to 100 hours and preferably 10 to 70h. The income can be achieved in one or more levels.
  • the cold deformation is carried out by one or more shaping processes such as stretching, stretching-forming, stamping, spinning or folding.
  • it is a shaping in the three dimensions of the space to obtain a piece of complex shape, preferably by stretch-forming.
  • the product obtained after the short heat treatment can be shaped as a product in the state O or a product in the state W.
  • a simple income treatment is sufficient.
  • the product also has the advantage in general of not generating lines of Luders crippling during formatting.
  • the method according to the invention makes it possible to carry out the 3-dimensional shaping of a sheet at the end of the short heat treatment without the sheet being in a state T8, a state O or a state W before this setting shaped in 3 dimensions.
  • the compromise between the static mechanical properties and the damage-tolerance properties obtained at the end of the income is advantageous compared to that obtained for a similar treatment that does not include short heat treatment.
  • the mechanical strength in particular the tensile yield strength R P0 , 2 (L) is high and increases with the additional deformation, but that, contrary to their expectation, the tenacity measured by the curve R ( values of K) does not decrease significantly, especially up to a crack extension value of 60 mm when increasing the additional deformation, even up to a generalized deformation of 8%.
  • the product that can be obtained by the process comprising the additional deformation and tempering steps has a tensile yield strength R p o, 2 (L) that is at least substantially equal and a higher toughness K R , preferably greater than at least 5%, to that obtained by a similar process not including short heat treatment.
  • the tensile yield strength R p o, 2 (L) is at least 90% or preferably 95% of that obtained by a similar method not comprising short heat treatment.
  • the process according to the invention makes it possible to obtain, in particular, an alloy sheet AA2198 whose thickness is between 0.5 and 15 mm and preferably between 1 and 8 mm having, after thermal treatment of tempering in the T8 state, a combination of at least one static strength property selected from R p o, 2 (L) of at least 500 MPa and preferably at least 510 MPa and / or R p o, 2 (LT) of at least minus 480 MPa and preferably at least 490 MPa, and at least one toughness property measured on specimens of the CCT760 type
  • Example 1 An AA2198 alloy rolling plate was homogenized and then hot rolled to a thickness of 4 mm. The sheets thus obtained were dissolved for 30 minutes at 505 ° C. and then quenched with water.
  • the sheets then underwent a short heat treatment of 2 hours at 150 ° C.
  • An AA2198 alloy rolling plate was homogenized and then hot rolled to a thickness of 4 mm.
  • the sheets thus obtained were dissolved for 30 minutes at 505 ° C. and then quenched with water.
  • the sheets then underwent a short heat treatment of 2 hours at 150 ° C.
  • the sheets thus obtained then underwent additional cold deformation by controlled traction with a permanent elongation of 2.5%, 4% or 8%.
  • the sheets did not show after deformation of lines of Luders crippling.
  • the sheets finally received an income of 12h at 55 ° C to obtain a T8 state.
  • a sheet was subjected directly after quenching to a controlled pull of 2% followed by an income of 14h at 155 ° C. in the T8 state, without intermediate short heat treatment.
  • the sheets were then glided and controlled in a controlled manner. Controlled traction was achieved with a permanent elongation of 1%. The sheets have been aged sufficiently to reach a stabilized T3 state.
  • the sheets then underwent a short heat treatment at 145 ° C, 150 ° C or 155 ° C.
  • the equivalent time at 150 ° C was calculated taking into account a temperature rise rate of 20 ° C / h.
  • the static mechanical characteristics of the sheets were characterized after the short heat treatment in the TL direction.
  • the sheets then had an income of 14h at 155 ° C until the T8 state.
  • the static mechanical properties were characterized at the end of the income presented in Table 5 below.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Metal Rolling (AREA)
  • Heat Treatment Of Steel (AREA)
  • Laminated Bodies (AREA)
EP12788613.3A 2011-10-14 2012-10-12 Verbessertes verfahren zum bearbeiten von metallblechen aus einer al-cu-li-legierung Active EP2766503B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE12788613.3T DE12788613T1 (de) 2011-10-14 2012-10-12 Verbessertes Verfahren zum Bearbeiten von Metallblechen aus einer AL-CU-LI-Legierung

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US201161547289P 2011-10-14 2011-10-14
FR1103155A FR2981365B1 (fr) 2011-10-14 2011-10-14 Procede de transformation ameliore de toles en alliage al-cu-li
PCT/FR2012/000414 WO2013054013A1 (fr) 2011-10-14 2012-10-12 Procédé de transformation amélioré de tôles en alliage al-cu-li

Publications (2)

Publication Number Publication Date
EP2766503A1 true EP2766503A1 (de) 2014-08-20
EP2766503B1 EP2766503B1 (de) 2016-12-07

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Country Status (8)

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US (2) US10968501B2 (de)
EP (1) EP2766503B1 (de)
CN (2) CN106222504B (de)
BR (1) BR112014008685B1 (de)
CA (1) CA2851592C (de)
DE (1) DE12788613T1 (de)
FR (1) FR2981365B1 (de)
WO (1) WO2013054013A1 (de)

Cited By (2)

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Publication number Priority date Publication date Assignee Title
WO2021111069A1 (fr) 2019-12-06 2021-06-10 Constellium Issoire Tôles minces en alliage d'aluminium-cuivre-lithium à tenacite ameliorée et procédé de fabrication d'une tôle mince en alliage d'aluminium-cuivre-lithium
WO2023144492A1 (fr) 2022-01-28 2023-08-03 Constellium Issoire Tole mince amelioree en alliage d'aluminium-cuivre-lithium

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Publication number Priority date Publication date Assignee Title
FR3004197B1 (fr) 2013-04-03 2015-03-27 Constellium France Toles minces en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselages d'avion.
CN103484738A (zh) * 2013-08-12 2014-01-01 安徽盛达前亮铝业有限公司 一种高耐损伤铝合金板材的生产工艺
FR3014448B1 (fr) * 2013-12-05 2016-04-15 Constellium France Produit en alliage aluminium-cuivre-lithium pour element d'intrados a proprietes ameliorees
RU2560481C1 (ru) * 2014-07-01 2015-08-20 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") СПЛАВ НА ОСНОВЕ СИСТЕМЫ Al-Cu-Li И ИЗДЕЛИЕ, ВЫПОЛНЕННОЕ ИЗ НЕГО
FR3026747B1 (fr) 2014-10-03 2016-11-04 Constellium France Toles isotropes en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselages d'avion
US10253404B2 (en) * 2014-10-26 2019-04-09 Kaiser Aluminum Fabricated Products, Llc High strength, high formability, and low cost aluminum-lithium alloys
US9419580B2 (en) 2014-10-31 2016-08-16 Raytheon Company Output matching network having a single combined series and shunt capacitor component
WO2017060697A1 (en) * 2015-10-06 2017-04-13 Bae Systems Plc Metal object production
EP3153600A1 (de) * 2015-10-06 2017-04-12 BAE Systems PLC Metallobjektherstellung
EP3153601A1 (de) * 2015-10-06 2017-04-12 BAE Systems PLC Metallobjektherstellung
FR3044682B1 (fr) * 2015-12-04 2018-01-12 Constellium Issoire Alliage aluminium cuivre lithium a resistance mecanique et tenacite ameliorees
CA3032261A1 (en) 2016-08-26 2018-03-01 Shape Corp. Warm forming process and apparatus for transverse bending of an extruded aluminum beam to warm form a vehicle structural component
CN106244874B (zh) * 2016-08-27 2019-05-07 来安县科来兴实业有限责任公司 一种高速动车组齿轮箱箱体专用耐热铝合金及其制备方法
FR3057476B1 (fr) 2016-10-17 2018-10-12 Constellium Issoire Toles minces en alliage aluminium-magnesium-scandium pour applications aerospatiales
WO2018078527A1 (en) 2016-10-24 2018-05-03 Shape Corp. Multi-stage aluminum alloy forming and thermal processing method for the production of vehicle components
FR3065012B1 (fr) * 2017-04-10 2022-03-18 Constellium Issoire Produits en alliage aluminium-cuivre-lithium a faible densite
FR3067620B1 (fr) 2017-06-19 2019-08-02 Constellium Issoire Toles minces en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselage d'avion
FR3075078B1 (fr) 2017-12-20 2020-11-13 Constellium Issoire Procede de fabrication ameliore de toles en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselage d'avion
US20190233921A1 (en) * 2018-02-01 2019-08-01 Kaiser Aluminum Fabricated Products, Llc Low Cost, Low Density, Substantially Ag-Free and Zn-Free Aluminum-Lithium Plate Alloy for Aerospace Application
FR3080861B1 (fr) * 2018-05-02 2021-03-19 Constellium Issoire Procede de fabrication d'un alliage aluminium cuivre lithium a resistance en compression et tenacite ameliorees
CN108823519B (zh) * 2018-07-02 2021-10-01 鼎镁新材料科技股份有限公司 一种高Mg含量中强高延变形铝锂合金及其热处理方法
CN108754263A (zh) * 2018-07-30 2018-11-06 东北轻合金有限责任公司 一种高强度航天用铝锂合金型材及其制备方法
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
CN110512125B (zh) * 2019-08-30 2020-09-22 中国航发北京航空材料研究院 一种用于增材制造的直径铝锂合金丝材的制备方法
CN112281035B (zh) * 2019-11-25 2021-07-27 重庆文理学院 一种综合性能优异的金属合金的制备方法
CN114622108A (zh) * 2022-02-10 2022-06-14 山东南山铝业股份有限公司 一种绿色循环保级6系高强度汽车板生产方法

Family Cites Families (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2083576A (en) * 1935-09-20 1937-06-15 Aluminum Co Of America Heat treatment of aluminum alloys
US3706606A (en) * 1970-02-10 1972-12-19 L Esercizio Dell Inst Sperimen Thermomechanical treatment process for heat treatable aluminium alloys
US3947297A (en) * 1973-04-18 1976-03-30 The United States Of America As Represented By The Secretary Of The Air Force Treatment of aluminum alloys
US5116572A (en) * 1983-12-30 1992-05-26 The Boeing Company Aluminum-lithium alloy
US4806174A (en) * 1984-03-29 1989-02-21 Aluminum Company Of America Aluminum-lithium alloys and method of making the same
US4648913A (en) * 1984-03-29 1987-03-10 Aluminum Company Of America Aluminum-lithium alloys and method
US4812178A (en) * 1986-12-05 1989-03-14 Bruno Dubost Method of heat treatment of Al-based alloys containing Li and the product obtained by the method
US5032359A (en) 1987-08-10 1991-07-16 Martin Marietta Corporation Ultra high strength weldable aluminum-lithium alloys
US5066342A (en) * 1988-01-28 1991-11-19 Aluminum Company Of America Aluminum-lithium alloys and method of making the same
US4869870A (en) * 1988-03-24 1989-09-26 Aluminum Company Of America Aluminum-lithium alloys with hafnium
US5455003A (en) * 1988-08-18 1995-10-03 Martin Marietta Corporation Al-Cu-Li alloys with improved cryogenic fracture toughness
US5259897A (en) * 1988-08-18 1993-11-09 Martin Marietta Corporation Ultrahigh strength Al-Cu-Li-Mg alloys
US5076859A (en) * 1989-12-26 1991-12-31 Aluminum Company Of America Heat treatment of aluminum-lithium alloys
US5234662A (en) * 1991-02-15 1993-08-10 Reynolds Metals Company Low density aluminum lithium alloy
US7438772B2 (en) * 1998-06-24 2008-10-21 Alcoa Inc. Aluminum-copper-magnesium alloys having ancillary additions of lithium
FR2792001B1 (fr) * 1999-04-12 2001-05-18 Pechiney Rhenalu Procede de fabrication de pieces de forme en alliage d'aluminium type 2024
US6869490B2 (en) * 2000-10-20 2005-03-22 Pechiney Rolled Products, L.L.C. High strength aluminum alloy
US7229509B2 (en) * 2003-05-28 2007-06-12 Alcan Rolled Products Ravenswood, Llc Al-Cu-Li-Mg-Ag-Mn-Zr alloy for use as structural members requiring high strength and high fracture toughness
CN101189353A (zh) * 2005-06-06 2008-05-28 爱尔康何纳吕公司 用于飞机机身的高韧度的铝-铜-锂合金板材
BRPI0610937B1 (pt) * 2005-06-06 2015-12-08 Alcan Rhenalu processo de fabricação de uma chapa em liga de alumínio e chapa em liga de alumínio produzida pelo processo
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
US8118950B2 (en) * 2007-12-04 2012-02-21 Alcoa Inc. Aluminum-copper-lithium alloys
FR2945464B1 (fr) * 2009-05-13 2012-03-23 Alcan Rhenalu Procede d'assemblage par soudage de pieces en alliage d'aluminium.
FR2947282B1 (fr) * 2009-06-25 2011-08-05 Alcan Rhenalu Alliage aluminium cuivre lithium a resistance mecanique et tenacite ameliorees
US9359660B2 (en) 2010-09-08 2016-06-07 Alcoa Inc. 6XXX aluminum alloys, and methods for producing the same
CN101967588B (zh) * 2010-10-27 2012-08-29 中国航空工业集团公司北京航空材料研究院 一种耐损伤铝锂合金及其制备方法

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2013054013A1 *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2021111069A1 (fr) 2019-12-06 2021-06-10 Constellium Issoire Tôles minces en alliage d'aluminium-cuivre-lithium à tenacite ameliorée et procédé de fabrication d'une tôle mince en alliage d'aluminium-cuivre-lithium
FR3104172A1 (fr) 2019-12-06 2021-06-11 Constellium Issoire Tôles minces en alliage d’aluminium-cuivre-lithium à ténacité améliorée et procédé de fabrication
WO2023144492A1 (fr) 2022-01-28 2023-08-03 Constellium Issoire Tole mince amelioree en alliage d'aluminium-cuivre-lithium
FR3132306A1 (fr) 2022-01-28 2023-08-04 Constellium Issoire Tôle mince améliorée en alliage d’aluminium-cuivre-lithium

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DE12788613T1 (de) 2015-02-19
US20190071753A1 (en) 2019-03-07
BR112014008685A2 (pt) 2017-04-25
EP2766503B1 (de) 2016-12-07
CA2851592A1 (fr) 2013-04-18
WO2013054013A1 (fr) 2013-04-18
CN103874775B (zh) 2016-07-06
US10968501B2 (en) 2021-04-06
CN103874775A (zh) 2014-06-18
BR112014008685B1 (pt) 2019-04-24
CA2851592C (fr) 2020-01-07
FR2981365B1 (fr) 2018-01-12
FR2981365A1 (fr) 2013-04-19
US20130092294A1 (en) 2013-04-18
US11667994B2 (en) 2023-06-06
CN106222504B (zh) 2019-10-18

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