EP2655680B1 - Aluminium-kupfer-lithium-legierung mit verbesserter druckfestigkeit und beständigkeit - Google Patents

Aluminium-kupfer-lithium-legierung mit verbesserter druckfestigkeit und beständigkeit Download PDF

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EP2655680B1
EP2655680B1 EP11808899.6A EP11808899A EP2655680B1 EP 2655680 B1 EP2655680 B1 EP 2655680B1 EP 11808899 A EP11808899 A EP 11808899A EP 2655680 B1 EP2655680 B1 EP 2655680B1
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mpa
weight
yield strength
thickness
toughness
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French (fr)
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EP2655680A2 (de
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Armelle Danielou
Gaëlle POUGET
Christophe Sigli
Timothy Warner
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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
    • 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
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/057—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent

Definitions

  • the invention relates to aluminum-copper-lithium alloy products, more particularly, such products, their manufacturing and use processes, intended in particular for aeronautical and aerospace construction.
  • Aluminum alloy rolled products are developed to produce high strength parts for the aerospace industry and the aerospace industry in particular.
  • Aluminum alloys containing lithium are very interesting in this respect, since lithium can reduce the density of aluminum by 3% and increase the modulus of elasticity by 6% for each weight percent of lithium added.
  • their performance compared with the other properties of use must reach that of the alloys commonly used, in particular in terms of a compromise between the static mechanical strength properties (yield strength in tension and in compression, breaking strength) and the properties of damage tolerance (toughness, fatigue crack propagation resistance), these properties being in general antinomic.
  • the yield strength in compression is an essential property.
  • These mechanical properties must also preferably be stable over time and have good thermal stability, that is to say, not be significantly modified by aging at a temperature of use.
  • 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 5,032,359 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 patent US5,455,003 discloses a process for producing Al-Cu-Li alloys which have improved mechanical strength and toughness at cryogenic temperature, particularly through proper work-hardening and tempering.
  • the patent US7,438,772 discloses alloys comprising, in weight percent, Cu: 3-5, Mg: 0.5-2, Li: 0.01-0.9 and discourage the use of higher lithium content due to degradation compromise between toughness and mechanical strength.
  • the patent US 7,229,509 discloses an alloy comprising (% by weight): (2.5-5.5) Cu, (0.1-2.5) Li, (0.2-1.0) Mg, (0.2-0, 8) Ag, (0.2-0.8) Mn, 0.4 max Zr or other grain refining agents such as Cr, Ti, Hf, Sc, V.
  • the patent application US 2009/142222 A1 discloses alloys comprising (in% by weight), 3.4 to 4.2% Cu, 0.9 to 1.4% Li, 0.3 to 0.7% Ag, 0.1 to 0, 6% Mg, 0.2 to 0.8% Zn, 0.1 to 0.6% Mn and 0.01 to 0.6% of at least one element for controlling the granular structure. This application also describes a process for manufacturing spun products.
  • Another object of the invention is an aircraft structure element, preferably an extrados wing skin, comprising a product according to the invention.
  • Yet another object of the invention is the use of a product according to the invention or a structural element according to the invention for aeronautical construction.
  • 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 tension in other words the tensile strength R m , the conventional yield stress at 0.2% elongation R p0.2 , and the elongation at break A% are determined by a tensile test according to standard NF EN ISO 6892-1, the sampling and the direction of the test being defined by the EN 485-1 standard.
  • the yield strength in compression was measured at 0.2% compression according to ASTM E9.
  • the stress intensity factor (K Q ) is determined according to ASTM E 399.
  • ASTM E 399 gives the criteria for determining if K Q is a valid value of K 1C .
  • K Q is a valid value of K 1C .
  • a curve of the stress intensity as a function of the crack extension, known as the curve R is determined according to ASTM E 561.
  • the critical stress intensity factor K C in other words the factor of intensity that makes the crack unstable, is calculated from the curve R.
  • the stress intensity factor K CO is also calculated by assigning the initial crack length to the critical load at the beginning of the monotonic 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. Unless otherwise specified, the definitions of EN 12258 apply.
  • 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 the fuselage skin, fuselage skin in English), the stiffeners or fuselage stringers, the bulkheads, circumferential frames, wings (such as upper or lower wing skin), stiffeners, ribs and longitudinal members (Spars)) and the empennage composed in particular of horizontal and vertical stabilizers (horizontal or vertical stabilizers), as well as the floor beams, the seat tracks and the doors.
  • a selected class of aluminum alloys which contain specific and critical amounts of lithium, copper, magnesium, silver and zirconium makes it possible to prepare, under certain processing conditions, rolled products having a compromise improved between toughness, tensile yield strength and yield strength in compression.
  • the present inventors have found that, surprisingly, it is possible to improve the compression elasticity limit for these alloys by choosing specific transformation process parameters, in particular during hot deformation and controlled tensile control. .
  • the copper content of the products according to the invention is between 4.2 and 4.6% by weight. In an advantageous embodiment of the invention, the copper content is at least 4.3% by weight. A maximum copper content of 4.4% by weight is preferred.
  • the lithium content of the products according to the invention is between 0.85% and 0.95% by weight. The increase in the copper content and to a lesser extent in the lithium content contributes to improving the static mechanical resistance, however, the copper having a detrimental effect especially on the density, it is preferable to limit the copper content to the maximum value preferred.
  • the increase in the lithium content has a favorable effect on the density, however the present inventors have found that for the alloys according to the invention, the lithium content of between 0.85% and 0.95% by weight allows a improvement of the compromise between mechanical strength (elastic limit in tension and in compression) and toughness and, moreover, the toughness reached for an income at or near the peak is higher.
  • the magnesium content of the products according to the invention is between 0.50% and 0.70% by weight.
  • the present inventors have found that the combination of a magnesium content of between 0.50% or preferably 0.53% and 0.70% or preferentially 0.65% by weight and a lithium content of between 0.85% and 0.95% by weight leads to a compromise between mechanical strength (elastic limit in tension and in compression) and particularly advantageous toughness, while keeping a failure rate during the acceptable conversion, and therefore a satisfactory reliability of the manufacturing process.
  • the zirconium content is between 0.05 and 0.18% by weight and preferably between 0.08 and 0.14% by weight. In an advantageous embodiment of the invention, the zirconium content is at least 0.11% by weight.
  • the manganese content is between 0.0 and 0.5% by weight. In one embodiment of the invention, the manganese content is between 0.2 and 0.4% by weight.
  • the manganese content is less than 0.1% by weight and preferably less than 0.05% by weight, which allows for the products obtained by the process according to the invention. to reduce the amount of insoluble metal phases and further improve the tolerance to damage.
  • the silver content is between 0.05% and 0.5% by weight. In an advantageous embodiment of the invention, the silver content is between 0.10 and 0.40% by weight. The addition of silver contributes to improving the compromise of mechanical properties of the products obtained by the process according to the invention.
  • the sum of the iron content and the silicon content is at most 0.20% by weight.
  • the iron and silicon contents are each at most 0.08% by weight.
  • the iron and silicon contents are at most 0.06% and 0.04% by weight, respectively.
  • a controlled and limited iron and silicon content contributes to the improvement of the compromise between mechanical resistance and damage tolerance.
  • the alloy also contains at least one element that can contribute to controlling the grain size selected from 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 content of Cr, Sc and Hf is limited to a maximum of 0.05% by weight, these elements possibly having an adverse effect. in particular on the density and being added only to further promote the obtaining of a substantially non-recrystallized structure if necessary.
  • Zinc is an undesirable impurity, especially because of its contribution to the density of the alloy.
  • the zinc content is less than 0.20% by weight, preferably Zn ⁇ 0.15% by weight and preferably Zn ⁇ 0.05% by weight.
  • the zinc content is advantageously less than 0.04% by weight. It is possible to select the content of the alloying elements to minimize the density.
  • the additive elements contributing to increase the density such as Cu, Zn, Mn and Ag are minimized and the elements contributing to decrease the density such as Li and Mg are maximized so as to reach a density lower than 2.73 g / cm 3 and preferably less than 2.70 g / cm 3 .
  • the manufacturing process of the products according to the invention comprises the steps of production, casting, homogenization, rolling with a temperature above 400 ° C, dissolution, quenching, traction between 2 and 3.0% and income.
  • a bath of liquid metal is produced so as to obtain an aluminum alloy of composition according to the invention.
  • the liquid metal bath is then cast as a rolling plate.
  • the rolling plate is then homogenized so as to reach a temperature of between 450 ° C. and 550 ° C. and preferably between 480 ° C. and 530 ° C. for a period of between 5 and 60 hours.
  • the homogenization treatment can be carried out in one or more stages.
  • the rolling plate is generally cooled to room temperature before being preheated to be hot rolled.
  • Preheating aims to achieve a temperature to maintain a temperature of at least 400 ° C and preferably at least 420 ° C during hot rolling.
  • Intermediate reheating is achieved if during hot rolling the temperature decreases excessively.
  • the hot rolling is carried out to a thickness of between 8 and 50 mm and preferably between 12 and 40 mm.
  • Significant cold deformation is typically a deformation of at least about 5% or 10%.
  • the product thus obtained is then put in solution by heat treatment to reach a temperature between 490 and 530 ° C for 15 min to 8 h, and then typically quenched with water at room temperature or preferably cold water .
  • the combination of the chosen composition, in particular the zirconium content, and the transformation range, in particular the hot deformation temperature and the absence of cold deformation before being dissolved, makes it possible to obtain a granular structure.
  • essentially non-recrystallized means a non-recrystallized granular structure content at mid-thickness greater than 70% and preferably greater than 85%.
  • the product then undergoes controlled traction with a permanent deformation of 2 to 3.0% and preferably of 2.0% to 3.0%.
  • Controlled traction with a maximum permanent deformation of about 2.5% is preferred.
  • the present inventors have found that, surprisingly, the yield stress in compression decreases with increasing permanent deformations during controlled traction while the tensile yield strength increases under these conditions. There is therefore a permanent deformation by optimal controlled traction to obtain a yield strength in high compression while maintaining a limit of elasticity in sufficient traction.
  • the permanent deformation by controlled traction is chosen so as to obtain a yield strength in compression at least equal to the yield strength limit.
  • the present inventors have also found that surprisingly the effect of the permanent deformation rate on the compressive yield strength is specific to the rolled products, tests on the spun products have shown that such an effect is not observed in this case.
  • Known steps such as rolling, planing, straightening shaping may optionally be performed after solution and quenching and before or after controlled pulling.
  • a cold rolling step of at least 7% and preferably at least 9% and at most 15% is carried out after dissolution and quenching and before controlled pulling.
  • An income is achieved in which the product reaches a temperature between 130 and 170 ° C and preferably between 150 and 160 ° C for 5 to 100 hours and preferably 10 to 70h. The income can be realized in one or more levels.
  • the yield strength increases with the duration of tempering at a given temperature up to a maximum value called the peak of hardening or "peak” then decreases with the duration of income.
  • the yield curve is defined as the evolution of the elastic limit as a function of the equivalent duration of income at 155 ° C.
  • An example of an income curve is presented on the Figure 1 .
  • it is determined whether a point N of the yield curve, of duration equivalent to 155 ° C t N and elastic limit R p0,2 (N) is close to the peak by determining the slope P N of the tangent to the income curve at point N.
  • the elastic limit of a point N of the yield curve is close to the elastic limit at the peak if the absolute value of the slope P N is at most 3 MPa / h.
  • an under-income state is a state for which P N is positive and an over-income state is a state for which P N is negative.
  • the present inventors have found that a satisfactory approximation of P N is generally obtained when the difference t N - t N-1 is between 2 and 20 hours and preferably is of the order of 3 hours.
  • the tensile or compressive yield strength can be used to determine if the income achieves a state close to the peak, however the results are not necessarily the same. In the context of the invention, it is preferred to use compression elastic limit values for the optimization of income.
  • the clearly underdeveloped states correspond to compromises between the static mechanical resistance (Rp 0.2 , R m ) and the damage tolerance (toughness, resistance to propagation cracks in fatigue) more interesting than peak and a fortiori that beyond the peak.
  • the present inventors have found that a state close to the peak makes it possible both to obtain a compromise between static mechanical resistance and damage tolerance that is of interest, but also to improve the performance in terms of corrosion resistance and thermal stability.
  • the use of a state close to the peak makes it possible to improve the robustness of the industrial process: a variation in the income conditions leads to a small variation in the properties obtained.
  • N of the compression yield curve at 155 ° C such that the tangent to the yield curve at this point has a slope P N , expressed in MPa / h, such that -1 ⁇ P N ⁇ 3 and preferably - 0 , 5 ⁇ P N ⁇ 2.3.
  • Aircraft structural elements according to the invention comprise products according to the invention.
  • a preferred aircraft structural element is an extrados wing skin.
  • the use of a structural element incorporating at least one product according to the invention or manufactured from such a product is advantageous, in particular for aeronautical construction.
  • the products according to the invention are particularly advantageous for producing extrados elements of aircraft wing.
  • Example 1 is not part of the invention but is useful for understanding the invention.
  • the plate was homogenized at about 500 ° C for about 20 hours.
  • the plate was hot rolled at a temperature above 445 ° C to obtain 25 mm thick sheets.
  • the sheets were dissolved at about 510 ° C for 5h, quenched with water at 20 ° C.
  • the sheets were then tractionned with a permanent elongation of between 2% and 6%.
  • the plates have experienced a single-stage income of 40 h at 155 ° C for 2% and 3% tractions, 30h for 4% and 20h for 6%, this income making it possible to achieve a yield strength in traction and in compression at the peak or near the peak.
  • Samples were taken at mid-thickness to measure the static mechanical tensile and compressive properties as well as the K Q toughness.
  • the structure of the sheets obtained was essentially non-recrystallized.
  • the uncrystallized granular structure level at mid-thickness was 90%.
  • Table 2 Mechanical properties obtained for the different sheets. Alloy Returned Permanent elongation during controlled traction Rp 0.2 L Traction (Mpa) Rp 0.2 L Compression (Mpa) K 1C (MPa.m 1/2 ) LT # 1 40h 155 ° C 2% 621 639 24.2 40h 155 ° C 3% 627 633 30h 155 ° C 4% 633 629 20h 155 ° C 6% 635 622 23.4
  • the figure 2 presents the evolution of the elastic limit in tension and in compression as a function of the permanent elongation during the controlled traction. For a permanent elongation during traction between 2 and 3.5% a favorable compromise is obtained between the yield strength in compression and the tensile yield strength. Thus, under these conditions, the yield strength in compression is greater than the tensile yield strength, the tensile elasticity remaining greater than 620 MPa.
  • the plates were homogenized by a two-stage treatment of 8h at 500 ° C followed by 12h at 510 ° C and then scalped. After homogenization, the plates were hot rolled to obtain sheets having a thickness of 9.4 mm with intermediate reheating in the case where the temperature decreases to minus 400 ° C. The sheets were dissolved for 5 h at approximately 510 ° C., quenched with cold water and triturated with a permanent elongation of 3%.
  • the structure of the sheets obtained was essentially non-recrystallized.
  • the uncrystallized granular structure level at mid-thickness was 90%.
  • the Figure 3 illustrates the compromise obtained between the elasticity limit in compression and the toughness K app .
  • composition according to the invention (alloy No. 3) with the process according to the invention leads, in particular for an income of 50 hours at 155 ° C., income being the most favorable from the point of view of the stability thermal, to a particularly favorable compromise between yield strength in compression, tensile yield strength and toughness.
  • the plate was homogenized at about 500 ° C for about 30 hours.
  • the plate was hot rolled at a temperature above 400 ° C to obtain 25 mm thick sheets.
  • the sheets were dissolved at about 510 ° C for 5h, quenched with water at 20 ° C.
  • the sheets were then tractionned with a permanent elongation of 2% or 3%.

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Claims (11)

  1. Verfahren zur Herstellung eines Walzerzeugnisses aus einer Legierung auf Aluminiumbasis, bei dem nacheinander
    a) ein Flüssigmetallbad auf Aluminiumbasis hergestellt wird, enthaltend 4,2 bis 4,6 Gew.-% Cu, 0,85 bis 0,95 Gew.-% Li, 0,50 bis 0,70 Gew.-% Mg, 0,05 bis 0,18 Gew.-% Zr, 0,05 bis 0,5 Gew.-% Ag, 0,0 bis 0,5 Gew.-% Mn, maximal 0,20 Gew.-% Fe + Si, weniger als 0,20 Gew.-% Zn, wenigstens ein Element ausgewählt unter Cr, Sc, Hf und Ti, wobei die Menge des Elements, falls ausgewählt, 0,05 bis 0,3 Gew.-% für Cr und für Sc, 0,05 bis 0,5 Gew.-% für Hf und 0,01 bis 0,15 Gew.-% für Ti beträgt, weitere Elemente jeweils maximal 0,05 Gew.-% und insgesamt 0,15 Gew.-%, Rest Aluminium;
    b) aus dem Flüssigmetallbad ein Walzbarren gegossen wird;
    c) der Walzbarren so homogenisiert wird, dass eine Temperatur zwischen 450 °C und 550 °C und vorzugsweise zwischen 480 °C und 530 °C für eine Dauer von 5 bis 60 Stunden erreicht wird;
    d) der Walzbarren zu einem Blech bis zu einer Dicke zwischen 8 und 50 mm warmgewalzt und dabei die Temperatur oberhalb von 400 °C und vorzugsweise oberhalb von 420 °C gehalten wird,
    e) das Blech zwischen 490 °C und 530 °C während 15 Minuten bis 8 Stunden lösungsgeglüht wird und das Erzeugnis abgeschreckt wird;
    f) das Blech kontrolliert gereckt wird, mit einer bleibenden Verformung von 2 bis 3,0 % und vorzugsweise 2,0 bis 3,0 %,
    g) eine Auslagerungsbehandlung durchgeführt wird, bei der das Blech eine Temperatur zwischen 130 und 170 °C und vorzugsweise zwischen 150 und 160 °C für 5 bis 100 Stunden und vorzugsweise 10 bis 70 Stunden erreicht,
    wobei keine signifikante Kaltumformung des Blechs, insbesondere durch Kaltwalzen, zwischen dem Warmwalzen d) und dem Lösungsglühen e) durchgeführt wird.
  2. Verfahren nach Anspruch 1, wobei der Gehalt an Cu zwischen 4,3 und 4,4 Gew.-% beträgt.
  3. Verfahren nach irgendeinem der Ansprüche 1 bis 2, wobei der Gehalt an Mg zwischen 0,53 und 0,65 Gew.-% beträgt.
  4. Verfahren nach irgendeinem der Ansprüche 1 bis 3, wobei der Gehalt an Mn weniger als 0,1 Gew.-% und vorzugsweise weniger als 0,05 Gew.-% beträgt.
  5. Verfahren nach irgendeinem der Ansprüche 1 bis 4, wobei
    die Gehalte an Fe und Si jeweils maximal 0,08 Gew.-% betragen, und/oder
    der Gehalt an Ti zwischen 0,01 und 0,10 Gew.-% und der Gehalt an Cr, Sc und Hf maximal 0,05 Gew.-% beträgt, und/oder
    der Gehalt an Zn maximal 0,15 Gew.-% und bevorzugt maximal 0,05 Gew.-% beträgt.
  6. Verfahren nach irgendeinem der Ansprüche 1 bis 5, bei dem die bleibende Verformung durch kontrolliertes Recken so gewählt wird, dass eine Druckstreckgrenze erhalten wird, die mindestens gleich der Zugstreckgrenze ist.
  7. Verfahren nach irgendeinem der Ansprüche 1 bis 6, bei dem das kontrollierte Recken unmittelbar nach dem Lösungsglühen und Abschrecken durchgeführt wird.
  8. Verfahren nach irgendeinem der Ansprüche 1 bis 7, bei dem die Auslagerungsbehandlung eine Unteralterung nahe der maximalen Druckstreckgrenze ist.
  9. Walzerzeugnis mit einer Dicke zwischen 8 und 50 mm und einer im Wesentlichen nichtrekristallisierten Kornstruktur, welches durch das Verfahren nach irgendeinem der Ansprüche 1 bis 8 herstellbar ist und auf halber Dicke mindestens eine der folgenden Eigenschaftskombinationen aufweist:
    (i) bei Dicken von 8 bis 15 mm, auf halber Dicke, eine Zugstreckgrenze Rp0,2(L) ≥ 600 MPa und vorzugsweise Rp0,2(L) ≥ 610 MPa, eine Druckstreckgrenze Rp0,2(L) ≥ 620 MPa und vorzugsweise Rp0,2(L) ≥ 630 MPa, und eine solche Zähigkeit, dass KlC(L-T) ≥ 28 MPa√m und vorzugsweise KlC(L-T) ≥ 32 MPa√m und/oder Kapp(L-T) ≥ 73 MPa√m und vorzugsweise Kapp(L-T) ≥ 79 MPa√m, für CCT-Proben von 300 mm Breite und 6,35 mm Dicke,
    (ii) bei Dicken von 8 bis 15 mm, auf halber Dicke, eine Zugstreckgrenze Rp0,2(L) ≥ 630 MPa und vorzugsweise Rp0,2(L) ≥ 640 MPa, eine Druckstreckgrenze Rp0,2(L) ≥ 640 MPa und vorzugsweise Rp0,2(L) ≥ 650 MPa, und eine solche Zähigkeit, dass KlC(L-T) ≥ 26 MPa√m und vorzugsweise KlC(L-T) ≥ 30 MPa√m und/oder Kapp(L-T) ≥ 63 MPa√m und vorzugsweise Kapp(L-T) ≥ 69 MPa√m, für CCT-Proben von 300 mm Breite und 6,35 mm Dicke,
    (iii) bei Dicken von 15 bis 50 mm, auf halber Dicke, eine Zugstreckgrenze Rp0,2(L) ≥ 610 MPa und vorzugsweise Rp0,2(L) ≥ 620 MPa, eine Druckstreckgrenze Rp0,2(L) ≥ 620 MPa und vorzugsweise Rp0,2(L) ≥ 630 MPa, und eine Zähigkeit KlC(L-T) ≥ 22 MPa√m und vorzugsweise KlC(L-T) ≥ 24 MPa√m,
    (iv) bei Dicken von 15 bis 50 mm, auf halber Dicke, eine Zugstreckgrenze Rp0,2(L) ≥ 580 MPa und vorzugsweise Rp0,2(L) ≥ 590 MPa, eine Druckstreckgrenze Rp0,2(L) ≥ 600 MPa und vorzugsweise Rp0,2(L) ≥ 610 MPa, und eine Zähigkeit KlC(L-T) ≥ 24 MPa√m und vorzugsweise KlC(L-T) ≥ 26 MPa√m.
  10. Strukturbauteil eines Flugzeugs, vorzugsweise eine Außenhaut für die Flügelsaugseite, welches ein Erzeugnis nach Anspruch 9 umfasst.
  11. Verwendung eines Erzeugnisses nach Anspruch 9 oder eines Strukturbauteils nach Anspruch 10 für den Flugzeugbau.
EP11808899.6A 2010-12-20 2011-12-16 Aluminium-kupfer-lithium-legierung mit verbesserter druckfestigkeit und beständigkeit Active EP2655680B1 (de)

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DE11808899.6T DE11808899T1 (de) 2010-12-20 2011-12-16 Aluminium-Kupfer-Lithium-Legierung mit verbesserter Druckfestigkeit und Beständigkeit

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US201061424970P 2010-12-20 2010-12-20
FR1004962A FR2969177B1 (fr) 2010-12-20 2010-12-20 Alliage aluminium cuivre lithium a resistance en compression et tenacite ameliorees
PCT/FR2011/000659 WO2012085359A2 (fr) 2010-12-20 2011-12-16 Alliage aluminium cuivre lithium à résistance en compression et ténacité améliorées

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EP2655680B1 true EP2655680B1 (de) 2019-05-22

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US (1) US20120152415A1 (de)
EP (1) EP2655680B1 (de)
CN (2) CN108048717A (de)
BR (1) BR112013015531B1 (de)
CA (1) CA2821663C (de)
DE (1) DE11808899T1 (de)
FR (1) FR2969177B1 (de)
WO (1) WO2012085359A2 (de)

Families Citing this family (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2989387B1 (fr) 2012-04-11 2014-11-07 Constellium France Alliage aluminium cuivre lithium a resistance au choc amelioree
FR2996857B1 (fr) * 2012-10-17 2015-02-27 Constellium France Elements de chambres a vide en alliage d'aluminium
FR3007423B1 (fr) * 2013-06-21 2015-06-05 Constellium France Element de structure extrados en alliage aluminium cuivre lithium
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
RU2560485C1 (ru) * 2014-06-10 2015-08-20 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") Высокопрочный сплав на основе алюминия и изделие, выполненное из него
US10253404B2 (en) * 2014-10-26 2019-04-09 Kaiser Aluminum Fabricated Products, Llc High strength, high formability, and low cost aluminum-lithium alloys
CN104313421B (zh) * 2014-11-07 2017-02-15 西南铝业（集团）有限责任公司 一种铝锂合金铸锭的制备方法
FR3044682B1 (fr) 2015-12-04 2018-01-12 Constellium Issoire Alliage aluminium cuivre lithium a resistance mecanique et tenacite ameliorees
WO2018037390A2 (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
FR3057476B1 (fr) 2016-10-17 2018-10-12 Constellium Issoire Toles minces en alliage aluminium-magnesium-scandium pour applications aerospatiales
US11072844B2 (en) 2016-10-24 2021-07-27 Shape Corp. Multi-stage aluminum alloy forming and thermal processing method for the production of vehicle components
CN106756344B (zh) * 2016-11-16 2018-07-31 重庆大学 一种基于pso-svr的高硬度铝合金及其制备方法
FR3067044B1 (fr) * 2017-06-06 2019-06-28 Constellium Issoire Alliage d'aluminium comprenant du lithium a proprietes en fatigue ameliorees
CN108570579A (zh) * 2018-04-11 2018-09-25 上海交通大学 一种含钪铸造铝锂合金及其制备方法
FR3080861B1 (fr) 2018-05-02 2021-03-19 Constellium Issoire Procede de fabrication d'un alliage aluminium cuivre lithium a resistance en compression et tenacite ameliorees
FR3080860B1 (fr) * 2018-05-02 2020-04-17 Constellium Issoire Alliage aluminium cuivre lithium a resistance en compression et tenacite ameliorees
CN108754263A (zh) * 2018-07-30 2018-11-06 东北轻合金有限责任公司 一种高强度航天用铝锂合金型材及其制备方法
WO2021101485A2 (en) * 2019-11-19 2021-05-27 Gazi Universitesi Thermo-mechanical treatment method for strengthening aa7075- t651 alloy during rra heat treatment
CN111020322A (zh) * 2019-12-10 2020-04-17 江苏豪然喷射成形合金有限公司 一种高强高韧航天用铝锂合金板材及制造方法
CN111020323A (zh) * 2019-12-31 2020-04-17 湖南恒佳新材料科技有限公司 一种超高强度铝合金板材的轧制方法
CN112588856B (zh) * 2020-12-22 2022-07-22 中北大学 一种高性能Cu-Ni-Al合金板带制备方法
CN115433888B (zh) * 2022-08-18 2023-06-13 哈尔滨工业大学（深圳） 一种铝锂合金中厚板的形变热处理方法
CN117187642B (zh) * 2023-11-03 2024-04-02 中铝材料应用研究院有限公司 一种超高强高韧Al-Cu-Li-Mg-Zn-Mn-Zr合金板材及其制备方法和应用

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
US5455003A (en) * 1988-08-18 1995-10-03 Martin Marietta Corporation Al-Cu-Li alloys with improved cryogenic fracture toughness
US5211910A (en) * 1990-01-26 1993-05-18 Martin Marietta Corporation Ultra high strength aluminum-base alloys
WO1996010099A1 (en) * 1994-09-26 1996-04-04 Ashurst Technology Corporation (Ireland) Limited High strength aluminum casting alloys for structural applications
US7438772B2 (en) 1998-06-24 2008-10-21 Alcoa Inc. Aluminum-copper-magnesium alloys having ancillary additions of lithium
WO2004106570A1 (en) * 2003-05-28 2004-12-09 Pechiney Rolled Products New al-cu-li-mg-ag-mn-zr alloy for use as stractural members requiring high strength and high fracture toughness
FR2900160B1 (fr) * 2006-04-21 2008-05-30 Alcan Rhenalu Sa Procede de fabrication d'un element de structure pour construction aeronautique comprenant un ecrouissage differentiel
CA2700250C (en) * 2007-09-21 2016-06-28 Aleris Aluminum Koblenz Gmbh Al-cu-li alloy product suitable for aerospace application
CN104674090A (zh) 2007-12-04 2015-06-03 美铝公司 改进的铝-铜-锂合金
FR2925523B1 (fr) * 2007-12-21 2010-05-21 Alcan Rhenalu Produit lamine ameliore en alliage aluminium-lithium pour applications aeronautiques

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

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FR2969177B1 (fr) 2012-12-21
CA2821663C (fr) 2018-10-30
CN108048717A (zh) 2018-05-18
BR112013015531A2 (pt) 2017-05-09
FR2969177A1 (fr) 2012-06-22
BR112013015531B1 (pt) 2018-09-18
EP2655680A2 (de) 2013-10-30
CA2821663A1 (fr) 2012-06-28
DE11808899T1 (de) 2014-01-02
WO2012085359A3 (fr) 2012-09-13
CN103370432A (zh) 2013-10-23
WO2012085359A2 (fr) 2012-06-28
US20120152415A1 (en) 2012-06-21

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