EP3610047B1 - Aluminium-kupfer-lithium-legierungsprodukte - Google Patents

Aluminium-kupfer-lithium-legierungsprodukte Download PDF

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EP3610047B1
EP3610047B1 EP18724941.2A EP18724941A EP3610047B1 EP 3610047 B1 EP3610047 B1 EP 3610047B1 EP 18724941 A EP18724941 A EP 18724941A EP 3610047 B1 EP3610047 B1 EP 3610047B1
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weight
product
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aluminium
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EP3610047A1 (de
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Juliette CHEVY
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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
    • 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
    • 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
    • C22C21/16—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
    • 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

Definitions

  • the invention relates in general to wrought products in aluminium-copper-lithium alloys, and more particularly to such products in the form of sections intended to produce stiffeners in aeronautical construction.
  • Aluminum alloys containing lithium are very attractive in this regard, as 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 must match that of commonly used alloys, particularly in terms of the trade-off between static strength properties (yield strength, fracture toughness) and damage tolerance properties ( toughness, resistance to the propagation of fatigue cracks), these properties generally being contradictory.
  • These alloys must also have sufficient corrosion resistance, be able to be shaped according to the usual methods and have low residual stresses so that they can be machined integrally.
  • the patent US 5,198,045 describes a family of Weldalite TM alloys comprising (wt%) (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. THE Wrought products made with these alloys combine a density of less than 2.64 g/cm 3 and an interesting compromise between mechanical strength and toughness.
  • the patent US 7,229,509 describes a family of Weldalite TM alloys comprising (wt%) (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 elements such as Cr, Ti, Hf, Sc and V.
  • the examples shown have a compromise between mechanical strength and improved toughness but their density is greater than 2.7 g/cm 3 .
  • the patent application WO2007/080267 discloses a zirconium-free Weldalite TM alloy for use in fuselage sheets comprising (wt%) (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 AA2196 alloy is also known, comprising (in % by weight) (2.5-3.3) Cu, (1.4-2.1) Li, (0.25-0.8) Mg, (0 .25-0.6) Ag, (0.04-0.18) Zr and at most 0.35 Mn.
  • Yet another object of the invention is a structural element incorporating at least one product according to the invention.
  • the static mechanical characteristics in other words the breaking strength R m , the conventional yield strength at 0.2% elongation R p0.2 ("yield strength") and l elongation at break A, are determined by a tensile test according to standard EN 10002-1 (2001), the sampling and direction of the test being defined by standard EN 485-1 (2016).
  • K Q The stress intensity factor
  • the thickness of the sections is defined according to standard EN 2066:2001: the cross section is divided into elementary rectangles of dimensions A and B; A always being the largest dimension of the elementary rectangle and B being able to be considered as the thickness of the elementary rectangle.
  • structural element or "structural element” of a mechanical construction is used here to mean 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 performed. These are typically elements whose failure is likely to endanger the safety of the said construction, of the users, of the users or of others.
  • these elements of structure include in particular the elements that make up the fuselage (such as the fuselage skin), the fuselage stiffeners or stringers, the bulkheads (bulkheads), the fuselage frames (circumferential frames), the wings (such as the wing skin), the stiffeners (stringers or stiffeners), the ribs (ribs) and spars (spars) and the empennage composed in particular of horizontal and vertical stabilizers (horizontal or vertical stabilizers), as well as floor beams, seat tracks and doors.
  • a selected class of aluminum alloys containing specific and critical contents of copper, lithium, magnesium, zinc, manganese and zirconium but containing essentially no silver makes it possible to prepare products wrought having in particular an improved compromise between toughness and mechanical strength compared to that of products containing essentially no silver.
  • the present inventors have found that, surprisingly, it is possible for products to obtain a compromise that is at least equivalent between the properties of static mechanical strength and the properties of tolerance to damage than that obtained with an aluminum-copper-lithium alloy containing silver, such as in particular the AA2196 alloy, by making a narrow selection of the quantities of lithium, copper, magnesium, manganese, zinc and zirconium.
  • the copper content of the products according to the invention is between 2.5 and 3.4% by weight. In an advantageous embodiment of the invention, the copper content is at least 2.8 or preferably at least 2.9% by weight and/or at most 3.2 and preferably at most 3.1% by weight. weight.
  • the lithium content of the products according to the invention is between 1.6 and 2.2% by weight.
  • the lithium content is between 1.65% and 1.8% by weight.
  • the lithium content is at most 1.75% by weight.
  • the magnesium content of the products according to the invention is between 0.4 and 0.9% by weight and preferably it is at least 0.5% by weight and, more preferably still greater than 0.6% in weight.
  • the magnesium content is at plus 0.8% by weight.
  • the present inventors have found that when the magnesium content is less than 0.30% by weight the advantageous compromise between mechanical strength and damage tolerance is not obtained.
  • the manganese content of the products according to the invention is between 0.2 and 0.6% by weight and, preferably, it is at least 0.3% by weight and, even more preferably at least 0.33% by weight and more preferably at least 0.4% by weight. In another embodiment, the manganese content is between 0.2 and 0.4% by weight, preferably between 0.25 and 0.35% by weight.
  • the present inventors have found that when the manganese content is less than 0.2% by weight, the tenacity KQ (L-T), in the L-T direction, advantageous according to the invention is not obtained.
  • the zirconium content of the products according to the invention is between 0.08 and 0.18% by weight and, preferably, it is from 0.12 to 0.16% by weight and, even more preferably, 0 .14 to 0.15% by weight. In another embodiment, the zirconium content is advantageously between 0.09 and 0.12% by weight, preferably between 0.09 and 0.11% by weight, or even between 0.09 and 0.10% in weight.
  • the zinc content is less than 0.4% by weight, preferably it is 0.05 and 0.35% by weight.
  • the zinc content is 0.2 to 0.3% by weight, which can contribute to achieving the desired compromise between toughness and mechanical strength.
  • the silver content is less than 0.15% by weight, preferably less than 0.10% by weight and, more preferably still, less than 0.05% by weight.
  • the present inventors have found that the advantageous compromise between strength and damage tolerance known for alloys typically containing 0.2 to 0.4% by weight silver can be obtained for alloys containing essentially no silver. with the composition selection made.
  • 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.
  • the alloy also contains at least one element which can contribute to the control of the grain size chosen from among Ti, Sc, Cr, Hf and V, the content of the element, if chosen, being from 0.01 to 0 .15% by weight, preferably 0.01 to 0.05% by weight for Ti; from 0.01 to 0.15% by weight, preferably 0.02 to 0.1% by weight for Sc; 0.01 to 0.5% by weight, preferably 0.02 to 0.1% by weight for Hf and 0.01 to 0.3% by weight, preferably 0.02 to 0.1% by weight for Cr and from 0.01 to 0.3% by weight, preferably 0.01 to 0.05% by weight for V.
  • the alloy according to the invention is particularly intended for the manufacture of rolled, extruded and/or forged products and, even more particularly, extruded products.
  • the products according to the invention have a particularly advantageous compromise between mechanical strength and toughness.
  • the products according to the invention have, in a spun, solution-treated, tempered, drawn and tempered state, in particular for thicknesses up to 50 mm or even between 8 and 50 mm, or even between 15 and 35 mm, a yield strength measured at 0.2% elongation in the L direction, Rp0.2 (L), of at least 510 MPa and a toughness KQ (LT), in the LT direction, of at least 21 MPa ⁇ m and such that KQ (LT) > - 0.2667*Rp0.2 (L) + 169.
  • the specimens used for the KQ measurements are of the CT type with a thickness of 20 mm and a width of 50 mm.
  • the process for manufacturing the products according to the invention comprises steps of production, casting, rolling, extrusion and/or forging, solution treatment, quenching, stress relieving and tempering.
  • a bath of liquid metal is prepared so as to obtain an aluminum alloy of composition according to the invention.
  • the liquid metal bath is then cast in a raw form, typically a rolling plate, an extrusion billet or a forging blank.
  • the raw form is then homogenized at a temperature of between 450° C. and 550° and preferably between 520° C. and 530° C. for a period of between 6 and 15 hours.
  • the raw form is optionally cooled down to room temperature before being preheated with a view to being hot deformed.
  • the hot deformation is carried out by rolling, extrusion and/or forging so as to obtain a rolled, extruded and/or forged product, preferably an extruded product.
  • the product thus obtained is then placed in solution by heat treatment between 490 and 550° C. for 15 min to 8 h, then quenched typically with water at room temperature.
  • the product then undergoes controlled stress relief, preferably by traction, with a permanent deformation of 1 to 15% and preferably of 2 to 4%.
  • the extruded product has, at the end of the process steps detailed above, a thickness ranging up to 50 mm or even between 8 and 50 mm, or even between 15 and 35 mm.
  • Tempering is carried out comprising heating at a temperature of between 140 and 170°C for 5 to 70 hours so that said product has a conventional yield strength measured at 0.2% elongation in the L direction, R p0.2 (L), of at least 510 MPa and a toughness K Q (LT), in the LT direction, of at least 21 MPa m and such that K Q (LT) > -0.2667 ⁇ R p0.2 (L) + 169.
  • the extruded product with a conventional yield strength measured at 0.2% elongation in the L direction, Rp0.2 (L), of at least 525 MPa and a tenacity KQ ( L-T), in the L-T direction, of at least 23 MPa ⁇ m and such that KQ (L-T) > -0.2667*Rp0.2 (L) + 171.
  • the spun product advantageously has a thickness, up to 50 mm or between 8 and 50 mm, or even between 15 and 35 mm.
  • an object of the invention is a structural element incorporating at least one product according to the invention or a product manufactured using a process according to the invention.
  • a structural element incorporating at least one product according to the invention or made from such a product is advantageous, in particular for aeronautical construction.
  • the products according to the invention are particularly advantageous for the production of structural elements such as stiffeners or frames for the manufacture of intrados or extrados elements of an aircraft wing, preferably stiffeners, spars and ribs, or also floor beams and seat rails.
  • the alloy billets 67, 74 a and b, 66, 68 and 69 were then homogenized for 8 to 10 hours at 524°C.
  • the billet in alloy 2 was homogenized for 8 hours at 500°C then 24 hours at 527°C while that in alloy 5 was homogenized for 8 hours at 520°C.
  • the billets were reheated to 450°C +/- 40°C then hot-spinned to obtain W profiles according to the figure 1 for alloy 2, 67, 74 a and b, 66, 68 and 69 and Z according to picture 2 for alloys 5.
  • the profiles thus obtained were put in solution at 524°C, quenched and stretched with a permanent elongation of between 2 and 5%.
  • Samples taken from the end of the section were tested to determine their static mechanical properties as well as their toughness (K Q ).
  • the location of the samples is indicated in dotted lines on the figure 1 And 2 .
  • the test pieces used for measuring the static properties were 10 mm in diameter and taken so that the direction of the axis of the test piece corresponded to the direction of spinning (direction L).

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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)
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Claims (11)

  1. Produkt aus einer Legierung auf Aluminiumbasis aufweisend, in Gew.-%,
    Cu: 2,5-3,4; bevorzugt 2,8-3,2;
    Li: 1,6-2,2; bevorzugt 1,65-1,8;
    Mg: 0,4-0,9; bevorzugt 0,5-0,8;
    Mn: 0,2-0,6; bevorzugt 0,3-0,6;
    Zr: 0,08-0,18; bevorzugt 0,12-0,16;
    Zn: < 0,4 bevorzugt 0,05-0,4; bevorzugter 0,2-0,4;
    Ag: < 0,15; bevorzugter < 0,1; noch bevorzugter < 0,05;
    Fe + Si ≤ 0,20;
    mindestens ein Element ausgewählt aus Ti, Sc, Cr, Hf und V, wobei der Gehalt des Elements, falls ausgewählt:
    Ti: 0,01-0,15; bevorzugt 0,01-0,05;
    Sc: 0,01-0,15, bevorzugt 0,02-0,1;
    Cr: 0,01-0,3, bevorzugt 0,02-0,1;
    Hf: 0,01-0,5, bevorzugt 0,02 - 0,1;
    V: 0,01-0,3, bevorzugt 0,01-0,05 beträgt;
    weitere Elemente jeweils ≤ 0,05 und insgesamt ≤ 0,15, Rest Aluminium.
  2. Produkt nach Anspruch 1, wobei der Kupfergehalt 2,9 bis 3,1 Gew.-% beträgt.
  3. Produkt nach irgendeinem der Ansprüche 1 bis 2, wobei der Lithiumgehalt 1,65 bis 1,75 Gew.-% beträgt.
  4. Produkt nach irgendeinem der Ansprüche 1 bis 3, wobei der Mangangehalt 0,4 bis 0,6 Gew.-% beträgt.
  5. Produkt nach irgendeinem der Ansprüche 1 bis 3, wobei der Zirkoniumgehalt 0,14 bis 0,15 Gew.-% beträgt.
  6. Verfahren zur Herstellung eines Strangpress-, Walz- und/oder Schmiedeprodukts auf Basis einer Aluminiumlegierung mit folgenden Schritten:
    a) Herstellen eines Flüssigmetallbades aufweisend, in Gewichtsprozent, Cu: 2,5-3,4; Li: 1,6-2,2; Mg: 0,4-0,9; Mn: 0,2-0,6; Zr: 0,08-0,18; Zn: < 0,4; Ag : < 0,15; Fe + Si ≤ 0,20; mindestens ein Element ausgewählt aus Ti, Sc, Cr, Hf und V, wobei der Gehalt dieses Elements, falls ausgewählt, Ti: 0,01 - 0,15; Sc: 0,01 - 0,15; Cr: 0,01 - 0,3; Hf: 0,01 - 0,5; V: 0,01 - 0,3 beträgt; weitere Elemente jeweils ≤ 0,05 und insgesamt ≤ 0,15, Rest Aluminium
    b) Gießen einer Rohform aus dem Flüssigmetallbad;
    c) Homogenisieren der Rohform;
    d) Warm- und optional Kaltverformen der Rohform zu einem Strangpress-, Walz- und/oder Schmiedeprodukt;
    e) Lösungsglühen und Abschrecken des Produkts;
    f) kontrolliertes Ziehen des Produkts mit einer bleibenden Verformung von 1 bis 15%, bevorzugt 2 bis 4%;
    g) Auslagern des Produkts durch Erwärmen auf 140 bis 170°C für 5 bis 70 Stunden, so dass das Produkt eine Dehngrenze, gemessen bei 0,2% Dehnung in L-Richtung, Rp0,2 (L), von mindestens 510 MPa aufweist und eine Zähigkeit KQ (L-T) in L-T-Richtung von mindestens 21 MPaVm und die so ist, dass KQ (L-T) > -0,2667∗Rp0,2 (L) + 169.
  7. Verfahren nach Anspruch 6, wobei die Homogenisierungstemperatur zwischen 520°C und 530°C und die Behandlungszeit zwischen 6 und 15 Stunden beträgt.
  8. Verfahren nach irgendeinem der Ansprüche 6 bis 7, bei dem das Auslagern bei einer Temperatur zwischen 150 und 165°C für eine Äquivalentzeit ti bei 160°C von 15 bis 28 Stunden, bevorzugt von 20 bis 27 Stunden, durchgeführt wird, wobei ti definiert ist durch die Formel: t i = ∫ exp − 16400 / T dt exp − 16400 / T ref
    Figure imgb0006
     worin T (in Kelvin) die momentane Behandlungstemperatur des Metalls ist, die sich mit der Zeit t (in Stunden) ändert, und Tref eine Referenztemperatur ist, die auf 433 K festgelegt ist.
  9. Produkt, erhalten nach irgendeinem der Ansprüche 6 bis 8, dadurch gekennzeichnet, dass es eine Dehngrenze, gemessen bei 0,2% Dehnung in L-Richtung, Rp0,2 (L), von mindestens 525 MPa aufweist und eine Zähigkeit KQ (L-T) in L-T-Richtung von mindestens 23 MPa√m und die so ist, dass KQ (L-T) > -0,2667∗Rp0,2 (L) + 171.
  10. Strukturelement, enthaltend mindestens ein Produkt nach irgendeinem der Ansprüche 1 bis 5 oder hergestellt aus einem Produkt, das nach einem der Ansprüche 6 bis 8 erhalten wird.
  11. Verwendung eines Strukturelements nach Anspruch 10 als Versteifung oder Rahmen von Unter- oder Oberseitenelementen von Flugzeugflügeln, oder als Bodenbalken oder Sitzschiene.
EP18724941.2A 2017-04-10 2018-04-09 Aluminium-kupfer-lithium-legierungsprodukte Active EP3610047B1 (de)

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FR1753133A FR3065011B1 (fr) 2017-04-10 2017-04-10 Produits en alliage aluminium-cuivre-lithium
PCT/FR2018/050886 WO2018189471A1 (fr) 2017-04-10 2018-04-09 Produits en alliage aluminium-cuivre-lithium

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EP3610047B1 true EP3610047B1 (de) 2023-08-23

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EP (1) EP3610047B1 (de)
CN (1) CN110536972B (de)
BR (1) BR112019021170B1 (de)
CA (1) CA3058021A1 (de)
DE (1) DE18724941T1 (de)
FR (1) FR3065011B1 (de)
WO (1) WO2018189471A1 (de)

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CN113249665A (zh) * 2021-07-02 2021-08-13 中国航发北京航空材料研究院 一种铝合金构件的成形方法

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5032359A (en) 1987-08-10 1991-07-16 Martin Marietta Corporation Ultra high strength weldable aluminum-lithium alloys
US5198045A (en) 1991-05-14 1993-03-30 Reynolds Metals Company Low density high strength al-li alloy
DE04753337T1 (de) 2003-05-28 2007-11-08 Alcan Rolled Products Ravenswood LLC, Ravenswood Neue al-cu-li-mg-ag-mn-zr-legierung für bauanwendungen, die hohe festigkeit und hohe bruchzähigkeit erfordern
FR2894985B1 (fr) * 2005-12-20 2008-01-18 Alcan Rhenalu Sa Tole en aluminium-cuivre-lithium a haute tenacite pour fuselage d'avion
FR2938553B1 (fr) * 2008-11-14 2010-12-31 Alcan Rhenalu Produits en alliage aluminium-cuivre-lithium
FR3004464B1 (fr) * 2013-04-12 2015-03-27 Constellium France Procede de transformation de toles en alliage al-cu-li ameliorant la formabilite et la resistance a la corrosion
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
FR3014905B1 (fr) * 2013-12-13 2015-12-11 Constellium France Produits en alliage d'aluminium-cuivre-lithium a proprietes en fatigue ameliorees
CN106521270B (zh) * 2016-12-07 2018-08-03 中国航空工业集团公司北京航空材料研究院 一种改善铝锂合金耐腐蚀性能的热处理工艺

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FR3065011B1 (fr) 2019-04-12
US20210087665A1 (en) 2021-03-25
BR112019021170A2 (pt) 2020-04-28
EP3610047A1 (de) 2020-02-19
DE18724941T1 (de) 2020-06-04
FR3065011A1 (fr) 2018-10-12
BR112019021170B1 (pt) 2023-05-09
CA3058021A1 (fr) 2018-10-18
WO2018189471A1 (fr) 2018-10-18
CN110536972B (zh) 2022-01-25

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