EP1966402B1 - Blech aus einer hochfesten aluminiumlegierung mit kupfer und lithium für einen flugzeugrumpf - Google Patents

Blech aus einer hochfesten aluminiumlegierung mit kupfer und lithium für einen flugzeugrumpf Download PDF

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EP1966402B1
EP1966402B1 EP06841937A EP06841937A EP1966402B1 EP 1966402 B1 EP1966402 B1 EP 1966402B1 EP 06841937 A EP06841937 A EP 06841937A EP 06841937 A EP06841937 A EP 06841937A EP 1966402 B1 EP1966402 B1 EP 1966402B1
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zirconium
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EP1966402A1 (de
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Bernard Bes
Hervé Ribes
Christophe Sigli
Timothy Warner
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Constellium Issoire SAS
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Alcan Rhenalu SAS
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • 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
    • 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, in particular 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.
  • AlLi alloys are not yet used extensively in the aerospace industry because of the defects of the alloys developed until today, such as, for example, inadequate thermal stability, strong anisotropy and inadequate toughness.
  • AlLi alloys The history of the development of AlLi alloys is described, for example, in the chapter "Aluminum-lithium alloys”: from “Aluminum and Aluminum Alloys” (ASM Specialty Handbook, 1994) ).
  • the first aluminum-lithium alloys (Al-Zn-Cu-Li) were introduced in Germany in the 1920s, and were followed by the introduction of AA2020 alloy (Al-Cu-Li-Mn-Cd) at the end of the 1950s, and by the introduction of alloy 1420 (Al-Mg-Li) in the Soviet Union, in the mid-1960s.
  • the only industrial applications of the AA2020 alloy were the horizontal wings and stabilizers of the Vigilante RA5C aircraft.
  • the conventional composition of AA2020 alloy was (in percent by weight): Cu: 4.5, Li: 1.2, Mn: 0.5, Cd: 0.2.
  • Cu 4.5
  • Li 1.2
  • Mn 0.5
  • Cd 0.2
  • EA Starke declared (in "Metallurgical Transactions A.”, Vol. 13A, p.2267 ): “Larger Mn-rich dispersoids can also be detrimental to ductility, causing porosities". This idea of a harmful effect of Mn has been widely recognized by those skilled in the art.
  • Pickens' List of Refining Additives actually mixes elements used for foundry grain refining (such as TiB2) and elements used to control grain structure during operations transformation, such as zirconium.
  • foundry grain refining such as TiB2
  • elements used to control grain structure during operations transformation such as zirconium.
  • conventional grain refiners such as Cr, Mn, Ti, B, Hf, V, TiB 2 and mixtures thereof can be used ", it is clear from the development history of AlLi alloys that a bias related to the use of any element other than Zr for the control of the granular structure exists for the skilled person.
  • the Zr is used.
  • the document W02004 / 106570 A1 discloses the following alloy, in percent by weight: Cu: 2.5-5.5%, Li: 0.1-2.5%, Mg: 0.2-1%, Ag; 0.2-0.8%, Mn: 0.2-0.8%, Zr: up to 0.3%, Al remainder and unavoidable impurities.
  • AA2297 alloy which contains lithium, copper and manganese, optionally magnesium but no silver for which zirconium is also used for refining grain.
  • US 5,234,662 discloses a preferred composition of 1.6% by weight of Li, 3% by weight of Cu, 0.3% by weight of Mn and 0.12% by weight of Zr.
  • Alloys AA2050 and AA2297 were mainly available for thick plates, thicker than 0.5 inches (12.7 mm).
  • the alloys In order to use AlLi alloys for fuselage applications, the alloys must offer the same performance, or even better performance, in terms of mechanical strength, damage tolerance, as the alloys not containing Li currently used. In particular, resistance to crack propagation is an important issue in these applications, and this explains why alloys known for their high tolerance to damage, such as AA2524 and AA2056, are traditionally used. Other desirable properties include weldability and corrosion resistance. Due to the growing trend of reducing costly mechanical fastening operations in the aerospace industry, weldable alloys such as AA6013, AA6056 or AA6156 are being introduced for fuselage panels. High corrosion resistance is also desirable in order to replace plated products with cheaper bare products.
  • the R curve test is a widely recognized means for characterizing the toughness properties.
  • the curve R represents the evolution of the critical effective stress intensity factor for the crack propagation as a function of the effective crack extension, under increasing monotonic stress. It allows the determination of the critical load for unstable failure for any configuration relevant to cracked aircraft structures.
  • the values of the stress intensity factor and the crack extension are actual values as defined in ASTM E561.
  • the length of the curve R - namely the maximum crack extension of the curve - is an important parameter in itself for the design of the curve. fuselage, in particular for panels having fixed stiffeners.
  • a first subject of the invention is an aluminum-based alloy comprising 2.1 to 2.8% by weight of Cu, 1.1 to 1.7% by weight of Li, 0.1 to 0.8% by weight of Ag, 0.2 to 0.6% by weight of Mg, 0.2 to 0.6% by weight of Mn, an amount of Fe and Si of less than or equal to 0.1% by weight each, balance A1 and unavoidable impurities at a content less than or equal to 0.05% by weight each and 0.15% by weight in total, the alloy being substantially free of zirconium, which means that the zirconium content is less than 0.04% by weight.
  • Yet another subject of the invention is a rolled, spun or forged product comprising an alloy according to the invention.
  • Yet another object of the invention is a structural element intended for aeronautical construction comprising a product according to the invention.
  • the static mechanical characteristics in other words the ultimate ultimate tensile strength R m , the tensile yield strength R p0 , 2 and the elongation at break A, are determined by a tensile test according to EN 10002-1, the location at which the parts are taken and their meaning defined by EN 485-1.
  • the cracking rate (using the da / dN - ⁇ K test) is determined according to ASTM E 647.
  • a curve giving the effective stress intensity factor as a function of the effective crack extension, known as the R curve, is determined according to ASTM E 561.
  • the critical stress intensity factor K c in d other words the intensity factor which makes the crack unstable, is calculated from the curve R.
  • the stress intensity factor K oc is also calculated by assigning the initial crack length at the beginning of the monotonous load, at the critical load. These two values are calculated for a specimen of the required form.
  • K app represents the K CO factor corresponding to the specimen that was used to perform the R curve test.
  • K eff represents the K C factor corresponding to the specimen that was used to perform the R curve test.
  • ⁇ a eff ( max ) represents the crack extension of the last point of the curve R, valid according to the ASTM E561 standard.
  • the last point is obtained either at the time of the sudden rupture of the test piece, or possibly at the moment when the stress on the uncracked ligament exceeds on average the elastic limit of the material.
  • the crack size at the end of the pre-fatigue cracking stage is W / 3 for M (T) type specimens, where W is the specimen width as defined in ASTM E561.
  • the width of the specimen used in a toughness test may have a substantial influence on the R curve measured in the test.
  • the fuselage sheets being large panels, only the toughness results obtained on sufficiently large samples, such as samples having a width greater than or equal to 400 mm, are considered significant for the evaluation of the toughness. For this reason, only CCT760 test specimens, which had a width of 760 mm, were used for the evaluation of toughness.
  • structural element or “structural element” of a mechanical construction a mechanical part 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.
  • sheet is meant here a rolled product not exceeding 12.7 mm or 0.5 inch thick.
  • the aluminum-copper-lithium-silver-magnesium-manganese alloy according to one embodiment of the invention advantageously has the following composition: ⁇ u> Table 1: Composition ranges of alloys according to the invention (% by weight, the remainder being Al) ⁇ / u> Cu Li Ag mg mn Large 2, 1 to 2.8 1.1 to 1.7 0.1 to 0.8 0.2 to 0.6 0.2 to 0.6 favorite 2,2 to 2,6 1.2 to 1.6 0.2 to 0.6 0.3 to 0.5 0.2 to 0.5 The most preferred 2,3 to 2,5 1.3 to 1.5 0.2 to 0.4 0.3 to 0.4 0.3 to 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4
  • the alloy being substantially free of zirconium.
  • substantially free of zirconium it should be understood that the zirconium content should be less than 0.04% by weight, preferably less than 0.03% by weight, and even more preferably less than 0.01% by weight. % in weight.
  • the inventors have discovered that the low zirconium content makes it possible to improve the toughness of Al-Cu-Li-Ag-Mg-Mn alloys; in particular, the length of the curve R is significantly increased.
  • the use of manganese in place of zirconium to control the granular structure has several additional advantages such as obtaining a recrystallized structure and isotropic properties for a thickness of between 0.8 and 12.7 mm, or between 1/32 and 1/2 inch.
  • Iron and silicon generally affect toughness properties.
  • the amount of iron should be limited to 0.1% by weight (preferably 0.05% by weight) and the amount of silicon should be limited to 0.1% by weight (preferably 0.05% by weight).
  • the unavoidable impurities should be limited to 0.05% by weight each and 0.15% by weight in total. If the alloy has no other additive element, the rest is made of aluminum.
  • the inventors have discovered that if the copper content is greater than 2.8% or even 2.6% or even 2.5% by weight, the toughness properties may in some cases fall rapidly, whereas, if the copper is less than 2.1% or even 2.2% or even 2.3% by weight, the mechanical strength is too low.
  • lithium content As regards the lithium content, a lithium content greater than 1.7% or even 1.6% or even 1.5% by weight causes problems of thermal stability. A lithium content of less than 1.1% or even 1.2% or even 1.3% by weight results in inadequate mechanical strength and lower density gain.
  • the silver content is less than 0.1% or even 0.2% by weight, the obtained mechanical strength does not satisfy the desired properties.
  • the silver content must be kept below 0.8% or even 0.6% or even 0.4% by weight because a high amount of silver increases the density of the alloy and also its cost.
  • the alloy according to the invention can be used to manufacture extruded, forged or rolled products.
  • the alloy according to the invention is used to manufacture sheets.
  • the products according to the invention have a very high tenacity.
  • Zr and Mn, both of which can be used to control the granular structure exhibit a very different behavior.
  • Zr being a peritectic element is usually enriched at the grain center and depleted at the grain boundaries, while Mn, which is a eutectic element with a partition coefficient close to one, is distributed much more homogeneously.
  • the different behavior of Zr and Mn during solidification could be related to the different effect observed in terms of toughness.
  • the obtaining of a recrystallized structure, favored here by the absence of zirconium may moreover perhaps have an intrinsic beneficial effect on the tenacity.
  • the recrystallization rate of the products according to the invention is greater than 80%.
  • the homogenization temperature should preferably be between 480 and 520 ° C for 5 to 60 hours, and even more preferably between 490 and 510 ° C for 8 to 20 hours.
  • the inventors have observed that homogenization temperatures above 520 ° C tended to reduce the toughness performance in some cases. The inventors believe that there is a relationship between the technical effect of the homogenization conditions and the behavior during the solidification described above.
  • the initial hot rolling temperature is preferably 450 to 490 ° C.
  • the hot rolling is preferably carried out to obtain a thickness of between about 4 and 12.7 mm.
  • a cold rolling step may optionally be added, if necessary.
  • the sheet obtained has a thickness of between 0.8 and 12.7 mm, and the invention is more advantageous for sheets of 1.6 to 9 mm thick, and even more advantageous. for sheets 2 to 7 mm thick.
  • the product according to the invention is then dissolved, preferably by heat treatment between 480 and 520 ° C for 15 min to 4 h, and then quenched with water at room temperature.
  • the product then undergoes a controlled pull of 1 to 5% and preferably 2 to 4%. If the traction is greater than 5%, the mechanical properties may not be sufficiently improved and one may encounter industrial difficulties such as a high implementation, which would increase the cost of the product.
  • An income is produced at a temperature between 140 and 170 ° C for 5 to 80 hours and, more preferably, between 140 and 155 ° C for 20 to 80 hours. The lowest solution temperatures in this range generally favor high toughness.
  • the revenue step is divided into two steps: a pre-revenue step prior to a welding operation, and a final heat treatment of an element. welded structural.
  • the recrystallization rate of the sheets according to the invention is greater than 80%.
  • the shaping of the products according to the invention can advantageously be carried out by stretch-forming, deep-drawing, pressing, spinning, profile rolling or folding, these techniques being known to those skilled in the art.
  • all known and possible riveting, bonding and welding techniques suitable for aluminum alloys can be used, if desired.
  • the products according to the invention can be attached to stiffeners or frames, for example by riveting, gluing or welding.
  • the inventors have discovered that if welding is chosen, it may be preferable to use low temperature welding techniques, which help to ensure that the thermally affected area is as limited as possible. In this respect, laser welding and friction stir welding often give particularly satisfactory results.
  • the products according to the invention before or after shaping, can advantageously be subjected to an income to confer improved static mechanical properties. This income can also advantageously be conducted on an assembled structural element if desired.
  • the products according to the invention are preferably used for the manufacture structural elements for aeronautical construction.
  • a structural element, formed of a sheet according to the invention and stiffeners or frames, these stiffeners or frames preferably consisting of extruded profiles, can be used in particular for the manufacture of aeronautical fuselage as well as any other use where the present properties could be advantageous.
  • a fuselage panel comprising at least one sheet according to the invention.
  • the inventors have discovered that the products of the invention offer a particularly favorable compromise between the static mechanical properties, the high tenacity and the density.
  • high tensile and high yield strength sheets generally have low toughness.
  • the properties of high tenacity, and in particular the very long curve R favor the industrial application to aircraft fuselage parts.
  • the density of the products is less than about 2.69 g / cm 3 and preferably less than about 2.66 g / cm 3 .
  • the products of the invention generally do not induce any particular problem during subsequent surface treatment operations conventionally used in aeronautical construction, in particular for mechanical or chemical polishing, or treatments intended to improve the adhesion of the polymer coatings.
  • the resistance to intergranular corrosion of the products of the invention is generally high by way of example, pits are generally only detected when the metal is subjected to a corrosion test.
  • a sheet of the invention may be used without being plated on either side with an aluminum alloy lightly loaded with alloying elements.
  • Example A is a reference AA2098 alloy.
  • the chemical compositions of the various alloys tested are given in Table 2. ⁇ u> Table 2: Chemical composition (% by weight) ⁇ / u> Casting reference Yes Fe Cu mn mg Cr Zn Zr Li Ag Ti A (2098) 0.03 0.04 3.6 0.01 0.32 0.01 0.01 0.14 1.0 0.33 0.02 B 0.03 0.04 2.2 0.29 0.3 - - ⁇ 0.01 1.4 - 0.02 VS 0.03 0.03 0.03 2.4 0.29 0.3 - - ⁇ 0.01 1.4 0.34 0.02 D 0.03 0.03 1.5 0.28 0.3 - - ⁇ 0.01 1.4 - 0.03
  • the granular structure of the samples was characterized from microscopic observation of cross sections after anodic oxidation, under polarized light, or after chromatic attack.
  • a recrystallization rate was determined.
  • the recrystallization rate is defined as the surface fraction occupied by recrystallized grains.
  • the recrystallization rate was 100%.
  • the recrystallization rate was less than 20%.
  • the static mechanical properties of the samples according to the invention are comparable to those of a conventional 2XXX damage tolerant alloy, and are lower than those of high strength alloys such as 7475 or 2098 (A).
  • the resistance of the comparative alloy B is lower than that of the alloy according to the invention (C), which may be related to the absence of silver in the comparative alloy B.
  • the inventors consider that that the lower copper content and zirconium content of the sample according to the invention explain the lower strength compared to alloy 2098 (sample A).
  • the anisotropy of the sample C according to the invention is very weak as illustrated by FIG. figure 5 which represents the normalized evolution of the elastic limit as a function of the orientation.
  • the tensile strength limit at 45 ° is slightly greater than the tensile yield strength in the TL direction, the difference between these values, defined by (Rp 0.2 (TL) - Rp 0.2 ( 45 °)) / Rp 0.2 (TL) is thus -0.3%. In comparison, this difference is 13.2% for the reference sample A # 2 (AA2098).
  • sample C according to the invention has high toughness properties.
  • the curves R of the samples A # 1, B and C are provided on the Figures 1 and 2 , for the TL and LT directions, respectively.
  • the figure 1 clearly shows that the crack extension of the last valid point of the curve R (Aa eff (max) ) is much greater for the sample C of the invention than for the reference sample A # 1.
  • This parameter is at least as critical as K app values because, as explained in the description of the prior art, the length of the curve R is an important parameter for the design of the fuselage.
  • the figure 2 shows the same trend, but the difference is smaller because the LT direction inherently gives better results.
  • Table 6 summarizes the results of the toughness tests.
  • the Figures 3 and 4 show the evolution of the cracking rate in the TL and LT orientation, respectively, as the magnitude of the stress intensity factor varies.
  • the width of the sample was 400 mm (CCT 400 specimen) and

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Claims (12)

  1. Legierung auf Aluminiumbasis, bestehend aus 2,1 bis 2,8 Gew.-% Cu, 1,1 bis 1,7 Gew.-% Li, 0,1 bis 0,8 Gew.-% Ag, 0,2 bis 0,6 Gew.-% Mg, 0,2 bis 0,6 Gew.-% Mn, einer Menge an Fe und Si von jeweils max. 0,1 Gew.-%, Rest Al und unvermeidbare Verunreinigungen mit einem Anteil von jeweils max. 0,05 Gew.-% und insgesamt max. 0,15 Gew.-%, wobei die Legierung im Wesentlichen zirkoniumfrei ist, was bedeutet, dass der Gehalt an Zirkonium weniger als 0,04 Gew.-% beträgt.
  2. Aluminiumlegierung nach Anspruch 1, bestehend aus 2,2 bis 2,6 Gew.-% Cu, 1,2 bis 1,6 Gew.-% Li, 0,2 bis 0,6 Gew.-% Ag, 0,3 bis 0,5 Gew.-% Mg, 0,2 bis 0,5 Gew.-% Mn.
  3. Aluminiumlegierung nach Anspruch 1, bestehend aus 2,3 bis 2,5 Gew.-% Cu, 1,3 bis 1,5 Gew.-% Li, 0,2 bis 0,4 Gew.-% Ag, 0,3 bis 0,4 Gew.-% Mg, 0,3 bis 0,4 Gew.-% Mn.
  4. Aluminiumlegierung nach irgendeinem der Ansprüche 1 bis 3, wobei der Gehalt an Zirkonium weniger als 0,03 Gew.-% und vorzugsweise weniger als 0,01 Gew.-% beträgt.
  5. Walz-, Strangpress- oder Schmiedeerzeugnis, bestehend aus einer Legierung nach irgendeinem der Ansprüche 1 bis 4.
  6. Erzeugnis nach Anspruch 5, dessen Rekristallisationsgrad mehr als 80 % beträgt.
  7. Walzerzeugnis nach Anspruch 5 oder Anspruch 6, dessen Dicke 12,7 mm nicht übersteigt.
  8. Verfahren zur Herstellung eines Blechs aus Aluminiumlegierung mit hoher Festigkeit und hoher Bruchzähigkeit, bei dem
    (a) ein Walzbarren gegossen wird, bestehend aus 2,1 bis 2,8 Gew.-% Cu, 1,1 bis 1,7 Gew.-% Li, 0,1 bis 0,8 Gew.-% Ag, 0,2 bis 0,6 Gew.-% Mg, 0,2 bis 0,6 Gew.-% Mn, einer Menge an Fe und Si von jeweils max. 0,1 Gew.-%, Rest Aluminium und unvermeidbare Verunreinigungen mit einem Anteil von jeweils max. 0,05 Gew.-% und insgesamt max. 0,15 Gew.-%, wobei die Legierung im Wesentlichen zirkoniumfrei ist, was bedeutet, dass der Gehalt an Zirkonium weniger als 0,04 Gew.-% beträgt,
    (b) der Walzbarren bei 480 bis 520°C für 5 bis 60 Stunden homogenisiert wird,
    (c) der Walzbarren mit einer Walzanfangstemperatur von 450 bis 490°C zu einem Blech warmgewalzt und optional kaltgewalzt wird,
    (d) das Blech bei 480 bis 520°C für 15 Minuten bis 4 Stunden lösungsgeglüht wird,
    (e) das Blech abgeschreckt wird,
    (f) das Blech mit 1 bis 5 % bleibender Verformung kontrolliert gereckt wird,
    (g) das Blech durch Erwärmen auf 140 bis 170°C für 5 bis 80 Stunden warmausgelagert wird.
  9. Verfahren nach Anspruch 8, bei dem die Dicke der erhaltenen Bleche zwischen 0,8 mm und 12,7 mm und vorzugsweise zwischen 1,6 und 9 mm liegt.
  10. Blech, herstellbar durch das Verfahren des Anspruchs 8 oder des Anspruchs 9, aufweisend
    (a) eine Dehngrenze Rp0,2 in L-Richtung (Längsrichtung) von mindestens 390 MPa und vorzugsweise mindestens 400 MPa, und/oder
    (b) eine Differenz zwischen der Dehngrenze bei Zugbelastung Rp0,2 bei 45° zur Walzrichtung und der Dehngrenze bei Zugbelastung Rp0,2 in TL-Richtung (Quer-Längsrichtung), definiert durch (Rp0,2(TL) - Rp0,2(45)) /Rp0,2(TL), im Bereich zwischen +5% und -5% und vorzugsweise zwischen +3% und -3% und /oder
    (c) eine Bruchzähigkeit bei ebener Spannung Kapp, gemessen an Proben vom Typ CCT760 (2ao = 253 mm), von mindestens 100 MPa ⁢ m
    Figure imgb0013
     und vorzugsweise mindestens 120 MPa ⁢ m
    Figure imgb0014
     in TL-Richtung, und/oder
    (c) eine Rissverlängerung Δaeff(max) des letzten gültigen Messpunkts der R-Kurve in TL-Richtung von mindestens 60 mm und vorzugsweise mindestens 80 mm.
  11. Rumpfhautfeld für ein Luftfahrzeug, bestehend aus mindestens einem Blech nach Anspruch 10.
  12. Strukturelement für den Flugzeugbau, bestehend aus mindestens einem Erzeugnis nach Anspruch 6, 7 oder 10.
EP06841937A 2005-12-20 2006-12-14 Blech aus einer hochfesten aluminiumlegierung mit kupfer und lithium für einen flugzeugrumpf Active EP1966402B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0512931A FR2894985B1 (fr) 2005-12-20 2005-12-20 Tole en aluminium-cuivre-lithium a haute tenacite pour fuselage d'avion
PCT/FR2006/002733 WO2007080267A1 (fr) 2005-12-20 2006-12-14 Tole en aluminium-cuivre-lithium a haute tenacite pour fuselage d'avion

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EP1966402A1 EP1966402A1 (de) 2008-09-10
EP1966402B1 true EP1966402B1 (de) 2009-03-18

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EP (1) EP1966402B1 (de)
CN (1) CN101341267B (de)
AT (1) ATE426051T1 (de)
CA (1) CA2633420C (de)
DE (2) DE06841937T1 (de)
ES (1) ES2323902T3 (de)
FR (1) FR2894985B1 (de)
RU (1) RU2418088C2 (de)
WO (1) WO2007080267A1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019122639A1 (fr) 2017-12-20 2019-06-27 Constellium Issoire Procede de fabrication ameliore de toles en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselage d'avion
US10836464B2 (en) 2013-12-05 2020-11-17 Constellium Issoire Aluminum—copper—lithium alloy product for a lower wing skin element with improved properties

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2707311C (en) 2007-12-04 2017-09-05 Alcoa Inc. Improved aluminum-copper-lithium alloys
FR2938553B1 (fr) * 2008-11-14 2010-12-31 Alcan Rhenalu Produits en alliage aluminium-cuivre-lithium
FR2938790B1 (fr) * 2008-11-21 2012-02-17 Alcan Rhenalu Profiles creux en alliage d'aluminium
FR2960002B1 (fr) * 2010-05-12 2013-12-20 Alcan Rhenalu Alliage aluminium-cuivre-lithium pour element d'intrados.
FR2975403B1 (fr) * 2011-05-20 2018-11-02 Constellium Issoire Alliage aluminium magnesium lithium a tenacite amelioree
FR2981365B1 (fr) 2011-10-14 2018-01-12 Constellium Issoire Procede de transformation ameliore de toles en alliage al-cu-li
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.
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
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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
RU2610646C1 (ru) * 2015-12-21 2017-02-14 Сергей Алексеевич Костин Способ получения осесимметричных деталей из жаропрочных сплавов на медной основе
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FR3065012B1 (fr) 2017-04-10 2022-03-18 Constellium Issoire Produits en alliage aluminium-cuivre-lithium a faible densite
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FR3082210B1 (fr) 2018-06-08 2020-06-05 Constellium Issoire Toles minces en alliage d’aluminium-cuivre-lithium pour la fabrication de fuselages d’avion
FR3104172B1 (fr) 2019-12-06 2022-04-29 Constellium Issoire Tôles minces en alliage d’aluminium-cuivre-lithium à ténacité améliorée et procédé de fabrication
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FR3132306B1 (fr) 2022-01-28 2024-05-03 Constellium Issoire Tôle mince améliorée en alliage d’aluminium-cuivre-lithium
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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

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Publication number Priority date Publication date Assignee Title
US10836464B2 (en) 2013-12-05 2020-11-17 Constellium Issoire Aluminum—copper—lithium alloy product for a lower wing skin element with improved properties
US12116122B2 (en) 2013-12-05 2024-10-15 Constellium Issoire Aluminum-copper-lithium alloy product for a lower wing skin element with improved properties
WO2019122639A1 (fr) 2017-12-20 2019-06-27 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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WO2007080267A1 (fr) 2007-07-19
CN101341267A (zh) 2009-01-07
FR2894985B1 (fr) 2008-01-18
ES2323902T3 (es) 2009-07-27
CA2633420C (fr) 2014-12-09
RU2418088C2 (ru) 2011-05-10
CA2633420A1 (fr) 2007-07-19
RU2008129812A (ru) 2010-01-27
CN101341267B (zh) 2010-07-21
DE602006005846D1 (de) 2009-04-30
EP1966402A1 (de) 2008-09-10
ATE426051T1 (de) 2009-04-15
DE06841937T1 (de) 2009-01-15
FR2894985A1 (fr) 2007-06-22

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