EP2569456B1 - Aluminium-kupfer-lithium-legierung für niedrigeres oberflächenelement - Google Patents

Aluminium-kupfer-lithium-legierung für niedrigeres oberflächenelement Download PDF

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EP2569456B1
EP2569456B1 EP11725129.8A EP11725129A EP2569456B1 EP 2569456 B1 EP2569456 B1 EP 2569456B1 EP 11725129 A EP11725129 A EP 11725129A EP 2569456 B1 EP2569456 B1 EP 2569456B1
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product according
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EP2569456A2 (de
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Bernard Bes
Frank Eberl
Gaëlle POUGET
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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
    • 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
    • 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
    • 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 generally relates to aluminum alloy products and, more particularly, to such products, their methods of manufacture and use, particularly in the aerospace industry.
  • Aluminum-lithium alloys 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.
  • the US Patent 5,032,359 discloses a large 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.
  • the US Patent 5,198,045 discloses a family of alloys comprising (in% by weight) (2,4-3,5) Cu, (1,35-1,8) Li, (0,25-0,65) Mg, (0.25 -0.65) Ag, (0.08-0.25) Zr. Wrought products made with these alloys combine a density of less than 2.64 g / cm 3 and a compromise between the mechanical strength and the interesting toughness.
  • the patent US 7,229,509 discloses a family of alloys comprising (in% 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, (up to 0.4) Zr or other affinants such as Cr, Ti, Hf, Sc and V.
  • the examples presented have a compromise between the mechanical strength and toughness improved but their density is greater than 2.7 g / cm 3 .
  • the patent EP 1,966,402 discloses an alloy containing no zirconium for fuselage plates of substantially 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 patent 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, Sc, Hf and Ti, wherein the Cu and Li contents are Cu + 5/3 Li ⁇ 5.2 .
  • the patent US5,455,003 discloses a process for producing aluminum-copper-lithium alloys having improved strength and toughness properties at cryogenic temperature. This method applies in particular to an alloy comprising (in% by weight) (2.0-6.5) Cu, (0.2-2.7) Li, (0-4.0) Mg, (0- 4.0) Ag, (0-3.0) Zn.
  • International demand WO 2010/055225 discloses a manufacturing method in which a bath of liquid metal comprising 2.0 to 3.5 wt.% Cu, 1.4 to 1.8 wt.% Li, 0.1 to 0.5 wt. weight of Ag, 0.1 to 1.0% by weight of Mg, 0.05 to 0.18% by weight of Zr, 0.2 to 0.6% by weight of Mn and at least one selected element among 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 from 0.01 to 0.15% by weight for Ti, the remainder being aluminum and unavoidable impurities; casting a raw form from the bath of liquid metal and homogenizing said raw form at a temperature between 515 ° C and 525 ° C so that the time equivalent to 520 ° C for homogenization is between 5 and 20 hours.
  • alloy AA2196 comprising (in% by weight) (2.5-3.3) Cu, (1.4-2.1) Li, (0.25-0.8) Mg, is known , 25-0.6) Ag, (0.04-0.18) Zr and at most 0.35 Mn.
  • Yet another object of the invention is the use of a product according to the invention as an aircraft wing-bottom element.
  • Figure 1 Shape of the profile of example 1. The dimensions are given in mm. The thickness of the sole is 26.3 mm.
  • alloys are in accordance with the regulations of The Aluminum Association, known to those skilled in the art.
  • the density depends on the composition and is determined by calculation rather than by a method of measuring weight.
  • the values are calculated in accordance with the procedure of The Aluminum Association, which is described on pages 2-12 and 2-13 of "Aluminum Standards and Data".
  • the definitions of the metallurgical states are given in the European standard EN 515.
  • the static mechanical characteristics in other words the ultimate ultimate tensile strength R m , the tensile yield strength Rp 0.2 and the elongation at break A, are determined by a tensile test. according to standard EN 10002-1 or NF EN ISO 6892-1, the location to which the parts are taken and their meaning being defined by the EN 485-1 standard.
  • the stress intensity factor (K Q ) is determined according to ASTM E 399.
  • the ASTM E 399 gives in 9.1.3 and 9.1.4 criteria to determine if K Q is a valid K 1C value .
  • K 1C is always a value K Q the reciprocal is not true.
  • the criteria of paragraphs 9.1.3 and 9.1.4 of the standard ASTM E399 are not always verified, however for a given test piece geometry, the K Q values presented are always comparable with each other, the specimen geometry making it possible to obtain a valid value of K 1C that is not always accessible. given the constraints related to the dimensions of the sheets or profiles.
  • the thickness of the selected test piece is a thickness deemed suitable by those skilled in the art to obtain a valid value of K 1C .
  • the values of the apparent tensile strength factor (K app ) and the tensile stress intensity factor (K c ) are as defined in ASTM E561.
  • the thickness of the profiles is defined according to EN 2066: 2001: the cross section is divided into elementary rectangles of dimensions A and B; A being always the largest dimension of the elementary rectangle and B can be considered as the thickness of the elementary rectangle. The sole is the elementary rectangle with the largest dimension A.
  • 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 the 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), wings (such as wing skin), stiffeners (stiffeners), ribs (ribs) and spars) and empennage including horizontal stabilizers 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 fuselage skin
  • bulkheads fuselage (circumferential frames)
  • wings such as wing skin
  • stiffeners stiffeners (stiffeners), ribs (ribs) and spars
  • empennage including horizontal stabilizers and vertical stabilizers horizontal or vertical stabilizers, as well as floor beams, seat tracks and doors.
  • the copper content of the alloy for which the surprising effect is observed is between 2.12 and 2.37% by weight, preferably between 2.12 or 2.20 and 2.37% or 2.30% by weight. weight.
  • the lithium content is between 1.3 and 1.6% or even between 1.30 and 1.60% by weight. In an advantageous embodiment, the lithium content is between 1.35 and 1.55% by weight.
  • the silver content is between 0.1 and 0.5% by weight.
  • the silver content is between 0.15 and 0.35% by weight. In one embodiment of the invention, which has the advantage of minimizing the density, the silver content is at most 0.25% by weight.
  • the magnesium content is between 0.2 and 0.6% by weight and preferably it is less than 0.4% by weight.
  • the simultaneous addition of zirconium and manganese is an essential feature of the invention. The zirconium content must be between 0.05 and 0.15% by weight and the manganese content must be between 0.1 and 0.5% by weight.
  • the alloy also contains 0.01 to 0.12 wt.% Ti to control grain size during casting.
  • the alloy according to the invention may also optionally contain at least one element selected from Cr, Sc, and Hf, the amount of the element, if it is chosen, being from 0.05 to 0.3% by weight for Cr and for Sc, 0.05 to 0.5% by weight for Hf. It is preferable to limit the content of unavoidable impurities in the alloy so as to achieve the most favorable damage tolerance properties.
  • the unavoidable impurities include iron and silicon, these elements have a content of less than 0.1% by weight each and preferably a content of less than 0.08% by weight and 0.06% by weight for iron and silicon , respectively, the other impurities have a content of less than 0.05% by weight each and 0.15% by weight in total.
  • the zinc content is preferably less than 0.04% by weight.
  • the composition is adjusted so as to obtain a density at room temperature of less than 2.65 g / cm 3, even more preferably less than 2.64 g / cm 3, in some cases even less than 2.63 g / cm 3. .
  • the alloy according to the invention can be used to manufacture spun, rolled and / or forged products.
  • the alloy according to the invention is used to manufacture sheets.
  • the products according to the invention preferably have a substantially non-recrystallized structure, having a recrystallization rate of less than 30% and preferably less than 15%.
  • the spun products and in particular the extruded profiles obtained by the process according to the invention are advantageous.
  • the thick sections that is to say the thickness of at least one elementary rectangle is greater than 8 mm, and preferably greater than 12 mm or 15 mm are the most advantageous.
  • the products according to the invention have a very high tenacity.
  • the products according to the invention are obtained by a process comprising the steps of casting, homogenization, hot deformation, dissolution, quenching, stress relief and tempering.
  • the homogenization temperature is preferably between 480 and 540 ° C for 5 to 60 hours.
  • the homogenization temperature is between 515 ° C and 525 ° C so that the equivalent time t (eq) at 520 ° C for homogenization is between 5 and 20 hours and preferably between 6 and 15 hours.
  • the formula giving t (eq) takes into account the heating and cooling phases.
  • the homogenization temperature is about 520 ° C and the duration of treatment is between 8 and 20 hours.
  • the raw form is generally cooled to room temperature before being preheated for hot deformation.
  • Preheating aims to achieve an initial deformation temperature preferably between 400 and 500 ° C and preferably of the order of 450 ° C to 480 ° C allowing the deformation of the raw form.
  • Hot deformation is typically performed by spinning, rolling and / or forging to obtain a spun, rolled and / or forged product.
  • the product thus obtained is then put in solution preferably by heat treatment between 490 and 530 ° C for 15 min to 8 h, then quenched typically with water.
  • the product then undergoes a controlled pull of 1 to 5% and preferably of at least 2%.
  • cold rolling is carried out with a reduction of between 5% and 15% before the controlled pulling step.
  • Known steps such as planing, straightening, shaping may optionally be performed before or after the controlled pull.
  • An income is produced at a temperature between 120 and 170 ° C for 5 to 100 h, preferably between 150 and 160 ° C for 20 to 60 h.
  • the preferred metallurgical states are for the plates the states T84 and T89 and for the profiles the state T8511.
  • the products according to the invention can be used as structural elements, in particular in aeronautical construction.
  • the products according to the invention are used as an aircraft wing surface element.
  • Table 1 Chemical composition (% by weight) ⁇ / u> Reference Yes Fe Cu mn mg Zn Zr Li Ag Ti AT 0.03 0.05 2.37 0.29 0.37 0.01 0.13 1.37 0.28 0.04 B 0.03 0.05 2.50 0.31 0.35 0.01 0.13 1.43 0.25 0.04 VS 0.03 0.06 2.62 0.30 0.35 0.01 0.14 1.42 0.24 0.04
  • Alloys A, B and C were cast as billets.
  • the billets were homogenized for 8 hours at 520 ° C. the equivalent time at 520 ° C. was 9.5 hours.
  • the billets were heated to 450 ° C +/- 40 ° C and then hot spun to obtain profiles according to the Figure 1 .
  • the profiles thus obtained were dissolved at 524 +/- 2 ° C, quenched with water temperature below 40 ° C, and fractionated with a permanent elongation of between 2 and 5%.
  • the profiles received an income of 30 hours at 152 ° C corresponding to the maximum value of toughness.
  • the samples were taken on the sole.
  • Alloys D, E, F, G and H were cast as plates.
  • the plates were homogenized for 8 h at 520 ° C. After homogenization, the plates were heated and then hot rolled to obtain sheets of thickness 14, 25 or 60 mm.
  • the sheets thus obtained were dissolved at 524 ⁇ 1 ° / -2 ° C., quenched with water of temperature below 40 ° C., and triturated with a permanent elongation of between 3 and 5%.
  • the sheets were tempered for 30 to 60 hours at 155 ° C. Samples were taken at medium thickness for 14 mm and 25 mm thick plates and at mid-thickness and quarter-thickness for 60 mm thick plates.
  • the specimens used for the tenacity measurements had a thickness of 12.5 mm for 14 mm thick sheets, 20 mm for 25 mm thick sheets, 25 mm for 60 mm thick sheets, measured thickness and 40 mm for 60 mm thick sheets measured at mid-thickness. R-curve measurements were also made at mid-thickness for certain income conditions.

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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)
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Claims (9)

  1. Strangpress-, Walz- und/oder Schmiedeerzeugnis, dessen Rekristallisationsgrad weniger als 30 % beträgt, aufweisend eine Legierung auf Aluminiumbasis enthaltend:
    2,12 bis 2,37 Gew.-% Cu,
    1,3 bis 1,6 Gew.-% Li,
    0,1 bis 0,5 Gew.-% Ag,
    0,2 bis 0,6 Gew.-% Mg,
    0,05 bis 0,15 Gew.-% Zr,
    0,1 bis 0,5 Gew.-% Mn,
    0,01 bis 0,12 Gew.-% Ti,
    wahlweise mindestens ein Element ausgewählt unter Cr, Sc und Hf, wobei die Menge des Elements, falls gewählt, 0,05 bis 0,3 Gew.-% für Cr und Sc, 0,05 bis 0,5 Gew.-% für Hf beträgt,
    eine Menge Fe und Si von jeweils höchstens 0,1 Gew.-% und unvermeidbare Verunreinigungen mit einem Gehalt von jeweils höchstens 0,05 Gew.-% und insgesamt 0,15 Gew.-%.
  2. Erzeugnis nach Anspruch 1, aufweisend 2,20 bis 2,30 Gew.-% Cu, 1,35 bis 1,55 Gew.-% Li, 0,15 bis 0,35 Gew.-% Ag, 0,2 bis 0,4 Gew.-% Mg.
  3. Erzeugnis nach Anspruch 1 oder Anspruch 2, dessen Rekristallisationsgrad weniger als 15 % beträgt.
  4. Erzeugnis nach irgendeinem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass es sich um ein Profil handelt, bei dem die Dicke mindestens eines Elementarrechtecks mehr als 8 mm und vorzugsweise mehr als 12 mm beträgt.
  5. Erzeugnis nach Anspruch 4, aufweisend
    eine Dehngrenze Rp0,2 in L-Richtung von mindestens 390 MPa und vorzugsweise mindestens 400 MPa und
    eine Bruchzähigkeit KQ(L-T) von mindestens 64 MPa m
    Figure imgb0021
     und vorzugsweise mindestens 65 MPa m .
    Figure imgb0022
  6. Erzeugnis nach irgendeinem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass es sich um ein gewalztes Erzeugnis handelt, dessen Dicke mindestens 14 mm und vorzugsweise mindestens 20 mm beträgt.
  7. Erzeugnis nach Anspruch 6, welches in halber Dicke im Zustand T84
    (a) bei einer Dicke zwischen 20 mm und 40 mm eine Dehngrenze Rp0,2 in L-Richtung von mindestens 410 MPa und vorzugsweise mindestens 420 MPa und eine Bruchzähigkeit KQ(L-T) von mindestens 45 MPa m
    Figure imgb0023
     und vorzugsweise mindestens 47 MPa m
    Figure imgb0024
     aufweist,
    (b) bei einer Dicke zwischen 40 mm und 80 mm eine Dehngrenze Rp0,2 in L-Richtung von mindestens 380 MPa und vorzugsweise mindestens 390 MPa und eine Bruchzähigkeit KQ(L-T) von mindestens 45 MPa m
    Figure imgb0025
     und vorzugsweise mindestens 50 MPa m
    Figure imgb0026
     aufweist.
  8. Verfahren zur Herstellung eines Erzeugnisses nach irgendeinem der Ansprüche 1 bis 7, bei dem:
    (a) eine Rohform aus einer Legierung nach einem der Ansprüche 1 bis 3 gegossen wird,
    (b) die Rohform bei 480 bis 540°C für 5 bis 60 Stunden homogenisiert wird,
    (c) die Rohform durch Strangpressen, Walzen und/oder Schmieden mit einer anfänglichen Warmumformungstemperatur von 400 bis 500°C warmumgeformt wird, um ein Walz- und/oder Schmiedeerzeugnis zu erhalten,
    (d) das Erzeugnis bei 490 bis 530°C für 15 Minuten bis 8 Stunden lösungsgeglüht wird,
    (e) das Erzeugnis abgeschreckt wird,
    (f) das Erzeugnis mit einer bleibenden Verformung von 1 bis 5 % kontrolliert gereckt wird,
    (g) das Erzeugnis durch Erwärmen auf 120 bis 170°C für 5 bis 100 Stunden ausgelagert wird.
  9. Verwendung eines Erzeugnisses nach irgendeinem der Ansprüche 1 bis 7 als Flügelunterseitenelement eines Flugzeugs.
EP11725129.8A 2010-05-12 2011-05-11 Aluminium-kupfer-lithium-legierung für niedrigeres oberflächenelement Active EP2569456B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1002033A FR2960002B1 (fr) 2010-05-12 2010-05-12 Alliage aluminium-cuivre-lithium pour element d'intrados.
US33444610P 2010-05-13 2010-05-13
PCT/FR2011/000290 WO2011141647A2 (fr) 2010-05-12 2011-05-11 Alliage aluminium-cuivre-lithium pour element d'intrados

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EP2569456A2 EP2569456A2 (de) 2013-03-20
EP2569456B1 true EP2569456B1 (de) 2017-09-06

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US (1) US20110278397A1 (de)
EP (1) EP2569456B1 (de)
CN (1) CN102985573A (de)
BR (1) BR112012028658A2 (de)
CA (1) CA2798480C (de)
FR (1) FR2960002B1 (de)
WO (1) WO2011141647A2 (de)

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FR3014448B1 (fr) * 2013-12-05 2016-04-15 Constellium France Produit en alliage aluminium-cuivre-lithium pour element d'intrados a proprietes ameliorees
FR3014904B1 (fr) 2013-12-13 2016-05-06 Constellium France Produits files pour planchers d'avion en alliage cuivre lithium
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
CN116083764A (zh) 2015-12-23 2023-05-09 诺尔斯海德公司 生产具有改善的机械性能的可热处理铝合金的方法
FR3047253B1 (fr) 2016-02-03 2018-01-12 Constellium Issoire Toles epaisses en alliage al - cu - li a proprietes en fatigue 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
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
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

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CA2798480A1 (fr) 2011-11-17
CN102985573A (zh) 2013-03-20
FR2960002B1 (fr) 2013-12-20
WO2011141647A3 (fr) 2012-11-01
FR2960002A1 (fr) 2011-11-18
WO2011141647A2 (fr) 2011-11-17
BR112012028658A2 (pt) 2016-08-09
US20110278397A1 (en) 2011-11-17
EP2569456A2 (de) 2013-03-20

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