EP2364378B1 - Produits en alliage aluminium-cuivre-lithium - Google Patents

Produits en alliage aluminium-cuivre-lithium Download PDF

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EP2364378B1
EP2364378B1 EP09764268.0A EP09764268A EP2364378B1 EP 2364378 B1 EP2364378 B1 EP 2364378B1 EP 09764268 A EP09764268 A EP 09764268A EP 2364378 B1 EP2364378 B1 EP 2364378B1
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Prior art keywords
mpa
weight
expressed
product
fracture toughness
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German (de)
English (en)
French (fr)
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EP2364378A1 (fr
Inventor
Fabrice Heymes
Frank Eberl
Gaëlle POUGET
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Constellium Issoire SAS
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Constellium France 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
    • 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

Definitions

  • the invention generally relates to wrought products of aluminum-copper-lithium alloys, and more particularly to such products in the form of profiles intended to produce stiffeners in aeronautical construction.
  • 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 must reach that of commonly used alloys, in particular in terms of a compromise between the static mechanical strength properties (elastic limit, breaking strength) and the properties of damage tolerance ( toughness, resistance to the propagation of fatigue cracks), these properties being in general antinomic.
  • 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 discloses a family of Weldalite TM 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.
  • the wrought products made with these alloys combine a density of less than 2.64 g / cm 3 and a compromise between strength and toughness of interest.
  • the patent US 7,229,509 discloses a family of Weldalite TM 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 mechanical strength and improved toughness but their density is greater than 2.7 g / cm 3 .
  • the patent application WO2007 / 080267 discloses a non-zirconium-containing Weldalite TM alloy for fuselage plates 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 EP1891247 discloses a Weldalite TM alloy which is lightly loaded with alloying elements and is also intended for the manufacture of fuselage sheets comprising (in% by weight) (2.7-3.4) Cu, (0.8-1.4) Li (0.2-0.6) Mg, (0.1-0.8) Ag and at least one member selected from Zr, Mn, Cr, Sc, Hf, Ti.
  • the patent application WO2006 / 131627 discloses an alloy for fuselage plates comprising (in% by weight) (2.7-3.4) Cu, (0.8-1.4) Li, (0.2-0.6) Mg, ( 0.1-0.8) 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 mechanical 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.
  • 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.
  • the invention also relates to a product spun, rolled and / or forged aluminum alloy with a density of less than 2.67 g / cm 3 obtainable by the process according to the invention.
  • Yet another object of the invention is a structural element incorporating at least one product according to the invention.
  • 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 tensile strength R m , the conventional yield stress at 0.2% elongation R p0.2 ("yield strength") and the elongation at break A, are determined by a tensile test according to EN 10002-1, the sampling and the direction of the test 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 standard provides in 9.1.3 and 9.1.4 criteria for determining whether K Q is a valid K 1C value .
  • a value K 1C is always a value K Q the reciprocal is not true.
  • the MASTMAASIS Modified ASTM Acetic Acid Salt Intermittent Spray
  • ASTM G85 ASTM G85.
  • EN 12258 the definitions of EN 12258 apply.
  • 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 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 present inventors have found that, surprisingly, for certain low density Al-Cu-Li alloys containing at the same time an addition of silver, magnesium, zirconium and manganese, the choice of specific homogenization conditions makes it possible to significantly improve the compromise between mechanical resistance and damage tolerance.
  • the method according to the invention allows the manufacture of a product spun, rolled and / or forged.
  • a bath of liquid metal is produced so as to obtain an aluminum alloy of defined composition.
  • the copper content of the alloy for which the surprising effect related to the choice of homogenization conditions is observed is between 2.0 and 3.5% by weight, preferably between 2.45 or 2.5 and 3.3% by weight.
  • the copper content is between 2.7 and 3.1% by weight.
  • the lithium content is between 1.4 and 1.8%.
  • the lithium content is between 1.42 and 1.77% by weight.
  • the silver content is between 0.1 and 0.5% by weight.
  • the present inventors have found that a significant amount of silver is not needed to achieve the desired improvement in the trade-off between strength and damage tolerance.
  • the silver content is between 0.15 and 0.35% by weight.
  • the silver content is at most 0.25% by weight.
  • the magnesium content is between 0.1 and 1.0% by weight and preferably it is less than 0.4% by weight. The combination of specific homogenization conditions and the simultaneous addition of zirconium and manganese is an essential feature of the invention.
  • the zirconium content must be between 0.05 and 0.18% by weight and the manganese content must be between 0.2 and 0.6% by weight. Preferably, the manganese content is at most 0.35% by weight.
  • the alloy also contains at least one element that can contribute to the control of the grain size selected from Cr, Sc, Hf and Ti, the quantity of the element, if it is chosen, being 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. 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 impurities preferably have a content of less than 0.08% by weight and 0.06% by weight for iron and silicon, respectively, the other impurities preferably have a lower content to 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 2.67 g / cm 3 , even more preferably less than 2.66 g / cm 3, in some cases even less than 2.65 g / cm 3 or even 2.64 g / cm 3 .
  • the decrease in density is generally associated with a degradation of the properties.
  • the liquid metal bath is then cast in a raw form, such as a billet, a rolling plate or a forging blank.
  • the crude form is then homogenized at a temperature of 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 20 hours. and 15 hours.
  • T (in Kelvin) is the instantaneous treatment temperature, which changes with time t (in hours)
  • T ref is a reference temperature set at 793 K.
  • t (eq) is expressed in hours.
  • the formula giving t (eq) takes into account the heating and cooling phases.
  • the homogenization temperature is about 520 ° C and the treatment time is between 8 and 20 hours. For homogenization, the times indicated correspond to times for which the metal is actually at the desired temperature.
  • a toughness K Q (LT) of at least MPa m with a yield strength R p0.2 (L) of at least 520 MPa a copper content of between 2.65 and 2.85% by weight is associated with a lithium content of between 1.5 and 1 , 7% by weight.
  • the density of the spun products according to the invention is less than 2.66 g / cm 3 , even more preferably less than 2.65 g / cm 3, in some cases even less than 2.64 g / cm 3. 3 .
  • an income is obtained which makes it possible to obtain a conventional yield strength measured at 0.2% elongation greater than 520 MPa, for example from 30 h to 152 ° C.
  • the resistance at break in the LR m (L) direction, expressed in MPa and the K Q toughness (LT), in the LT direction expressed in MPa m are then such R m (L)> 550 and K Q (LT)> 50.
  • the process according to the invention also makes it possible to obtain advantageous rolled products.
  • the sheets whose thickness is at least 10 mm and preferably at least 15 mm and / or at most 100 mm and preferably at most 50 mm are advantageous.
  • An aluminum alloy laminated product according to the invention has a density of less than 2.67 g / cm 3 , is obtainable by the method according to the invention, and is advantageously characterized in that its tenacity K Q (LT), in the LT direction is at least 23 MPa m and preferably at least 25 MPa m , its conventional yield strength measured at 0.2% elongation in the LR p0.2 (L) direction is at least 560 MPa and preferably at least 570 MPa and / or its breaking strength in the direction LR m (L) is at least 585 MPa and preferably at least equal to 595 MPa.
  • LT tenacity K Q
  • the density of the rolled products according to the invention is less than 2.66 g / cm 3 , even more preferably less than 2.65 g / cm 3, in some cases even less than 2.64 g / cm 3. 3 .
  • the products according to the invention can advantageously be used in structural elements, in particular aircraft.
  • 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.
  • a structural element, formed of at least one product according to the invention, in particular a spun product according to the invention used as stiffener or frame, can be advantageously used for the manufacture of fuselage panels or airplane wing as well as any other use where the present properties could be advantageous.
  • the plates were homogenized according to the prior art for 8 h at 500 ° C. and then 24h at 527 ° C. Bills were taken from the plates. The billets were heated to 450 ° C +/- 40 ° C and then hot spun to obtain W profiles according to Figure 1 . The profiles thus obtained were dissolved at 524 ° C, quenched with water temperature below 40 ° C, and tractionned with a permanent elongation of between 2 and 5%. The income was made for 48 hours at 152 ° C.
  • the billets were homogenized either 8h at 500 ° C and then 24h at 527 ° C (reference A) or 8h at 520 ° C (reference B) or 8h at 500 ° C (reference C).
  • the rate of rise in temperature was 15 ° C / h for the homogenization and the equivalent time was 37.5 hours for homogenization of reference A, 9.5 hours for homogenization of reference B, and 4
  • the billets were heated to 450 ° C. +/- 40 ° C. and then hot-spun to obtain X-profiles according to FIG. Figure 2 or Y according to the Figure 3 .
  • the profiles thus obtained were dissolved at 524 +/- 2 ° C, quenched with water temperature below 40 ° C, and tractionned with a permanent elongation of between 2 and 5%.
  • Example 2 two of the homogenization conditions of Example 2 were compared for another type of profile, obtained from billets taken from a plate whose composition is given in Table 6 below: Table 6.
  • Table 6 Composition in% by weight of Al-Cu-Li alloys used Alloy Yes Fe Cu mn mg Zn Ti Zr Li Ag Density (g / cm 3 ) 4 0.03 0.05 3.05 0.01 0.39 0.01 0.03 0.12 1.70 0.35 2,631 5 0.03 0.04 2.90 0.31 0.40 0.01 0.03 0.1 1.67 0.38 2,635
  • the alloy billets 4 were homogenized for 8 hours at 500 ° C. and then 24h at 527 ° C. (ie the reference homogenization A) while the alloy billets 5 were homogenized for 8 hours at 520 ° C. (reference B). After homogenization, the billets were heated to 450 ° C +/- 40 ° C and then hot spun to obtain Z profiles according to the Figure 7 . The profiles thus obtained were dissolved at 524 +/- 2 ° C, quenched with water temperature below 40 ° C, and tractionned with a permanent elongation of between 2 and 5%. The profiles finally had an income of 48h at 152 ° C.
  • the alloy billets 6 were homogenized for 8 hours at 520 ° C. (ie reference homogenization B). After homogenization, the billets were heated to 450 ° C. +/- 40 ° C. and then hot-spun to obtain P profiles according to Figure 8 . The profiles thus obtained were dissolved, quenched with water of temperature below 40 ° C, and tractionned with a permanent elongation of between 2 and 5%. The profiles finally had an income of 48h at 152 ° C. Samples taken at the end of the section were tested for their static mechanical properties (elastic limit R p0,2 , the tensile strength R m , and the elongation at break A).
  • the alloy billets 7 were homogenized for 8 hours at 520 ° C. (ie reference homogenization B). After homogenization, the billets were heated to 450 ° C +/- 40 ° C and then hot spun to obtain Q profiles according to the Figure 9 . The profiles thus obtained were dissolved, quenched with water of temperature below 40 ° C, and tractionned with a permanent elongation of between 2 and 5%. The profiles finally had an income of 48h at 152 ° C. Samples taken at the end of the section were tested for their static mechanical properties (elastic limit R p0,2 , the tensile strength R m , and the elongation at break A).
  • Table 14 Composition in% by weight and density of the Al-Cu-Li alloy used. Alloy Yes Fe Cu mn mg Zn Ti Zr Li Ag Density (g / cm 3 ) 8 0.03 0.06 3.1 0.3 0.4 0.01 0.03 0.11 1.77 0.36 2,631
  • the plate was scalped and then homogenized at 520 +/- 5 ° C for 8 h (the reference homogenization B). After homogenization, the plate was hot rolled to obtain sheets having a thickness of 25 mm. The sheets were put in solution at 524 +/- 2 ° C, quenched with cold water and triturated with a permanent elongation between 2 and 5%. Samples with a diameter of 10 mm taken from some of these sheets were then subjected to an income of between 20 h and 50 h at 155 ° C.
  • the homogenization conditions according to the invention were used for two types of profiles, obtained from billets made of two different alloys whose composition is given in Table 17 below.
  • Table 17 Composition in% by weight and density of the Al-Cu-Li alloy used. Alloy Yes Fe Cu mn mg Zn Ti Zr Li Ag Density (g / cm 3 ) 9 0.03 0.05 2.49 0.31 0.35 0.01 0.04 0.13 1.43 0.25 2,645 10 0.03 0.06 2.62 0.30 0.35 0.01 0.04 0.14 1.42 0.25 2,648
  • the billets were homogenized for 8 hours at 520 ° C. (reference B). The temperature rise rate was 15 ° C./h for homogenization and the equivalent time was 9.5 hours.
  • the billets were reheated to 450 ° C. ° C +/- 40 ° C then hot spun to obtain X profiles according to the Figure 2 or Y according to the Figure 3 .
  • the profiles thus obtained were dissolved at 524 +/- 2 ° C, quenched with water of temperature below 40 ° C, and tractionned with a permanent elongation of between 2 and 5%. Different income conditions have been implemented.
  • the compromise between toughness and mechanical strength obtained with alloys 9 and 10 is particularly advantageous, in particular to obtain very high toughness values, with K Q (LT) greater than 50 MPa m , and even greater than 55 MPa m .

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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)
  • Extrusion Of Metal (AREA)
  • Heat Treatment Of Steel (AREA)
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EP09764268.0A 2008-11-14 2009-11-10 Produits en alliage aluminium-cuivre-lithium Active EP2364378B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE9764268T DE09764268T1 (de) 2008-11-14 2009-11-10 Produkte aus einer aluminium-kupfer-lithium-legierung

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US11449308P 2008-11-14 2008-11-14
FR0806339A FR2938553B1 (fr) 2008-11-14 2008-11-14 Produits en alliage aluminium-cuivre-lithium
PCT/FR2009/001299 WO2010055225A1 (fr) 2008-11-14 2009-11-10 Produits en alliage aluminium-cuivre-lithium

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EP2364378A1 EP2364378A1 (fr) 2011-09-14
EP2364378B1 true EP2364378B1 (fr) 2014-01-08

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US (3) US8366839B2 (zh)
EP (1) EP2364378B1 (zh)
CN (1) CN102224267B (zh)
BR (1) BRPI0921819B1 (zh)
CA (1) CA2743353C (zh)
DE (1) DE09764268T1 (zh)
ES (1) ES2457221T3 (zh)
FR (1) FR2938553B1 (zh)
WO (1) WO2010055225A1 (zh)

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CN102834502A (zh) 2010-04-12 2012-12-19 美铝公司 具有低的强度差异的2xxx系列铝锂合金
FR2960002B1 (fr) * 2010-05-12 2013-12-20 Alcan Rhenalu Alliage aluminium-cuivre-lithium pour element d'intrados.
US20120247623A1 (en) * 2011-04-04 2012-10-04 Matuska Robert A Optimization and Control of Metallurgical Properties During Homogenization of an Alloy
FR3007423B1 (fr) * 2013-06-21 2015-06-05 Constellium France Element de structure extrados en alliage aluminium cuivre lithium
FR3014448B1 (fr) * 2013-12-05 2016-04-15 Constellium France Produit en alliage aluminium-cuivre-lithium pour element d'intrados a proprietes ameliorees
FR3014905B1 (fr) * 2013-12-13 2015-12-11 Constellium France Produits en alliage d'aluminium-cuivre-lithium a proprietes en fatigue ameliorees
FR3014904B1 (fr) * 2013-12-13 2016-05-06 Constellium France Produits files pour planchers d'avion en alliage cuivre lithium
KR20200110707A (ko) * 2014-07-30 2020-09-24 생-고뱅 퍼포먼스 플라스틱스 코포레이션 조향 서포트 요크
EP3577246A1 (en) 2017-01-31 2019-12-11 Universal Alloy Corporation Low density aluminum-copper-lithium alloy extrusions
FR3065011B1 (fr) * 2017-04-10 2019-04-12 Constellium Issoire Produits en alliage aluminium-cuivre-lithium
FR3065012B1 (fr) 2017-04-10 2022-03-18 Constellium Issoire Produits en alliage aluminium-cuivre-lithium a faible densite
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
CN109182807B (zh) * 2018-09-20 2020-06-30 北京新立机械有限责任公司 一种高强度铝锂合金及其制备方法
PT3683327T (pt) * 2019-01-17 2021-06-01 Aleris Rolled Prod Germany Gmbh Método de fabrico de um produto em liga de série almgsc
CN114540679B (zh) * 2022-04-26 2022-08-02 北京理工大学 一种微量元素复合强化高强度铝锂合金及制备方法

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FR2938553A1 (fr) 2010-05-21
US8366839B2 (en) 2013-02-05
BRPI0921819B1 (pt) 2022-05-17
US10190200B2 (en) 2019-01-29
US20130255839A1 (en) 2013-10-03
CA2743353C (fr) 2017-04-11
FR2938553B1 (fr) 2010-12-31
DE09764268T1 (de) 2011-12-01
EP2364378A1 (fr) 2011-09-14
US20190136356A1 (en) 2019-05-09
ES2457221T3 (es) 2014-04-25
CN102224267B (zh) 2013-09-25
BRPI0921819A2 (pt) 2018-02-14
WO2010055225A1 (fr) 2010-05-20
CN102224267A (zh) 2011-10-19
US20100126637A1 (en) 2010-05-27
CA2743353A1 (fr) 2010-05-20

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