EP3788178B1 - Aluminium-kupfer-lithium-legierung mit verbesserter kompressionsfestigkeit und erhöhter beständigkeit - Google Patents

Aluminium-kupfer-lithium-legierung mit verbesserter kompressionsfestigkeit und erhöhter beständigkeit Download PDF

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EP3788178B1
EP3788178B1 EP19726060.7A EP19726060A EP3788178B1 EP 3788178 B1 EP3788178 B1 EP 3788178B1 EP 19726060 A EP19726060 A EP 19726060A EP 3788178 B1 EP3788178 B1 EP 3788178B1
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mpa
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aluminum alloy
comprised
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EP3788178A1 (de
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Fanny MAS
David BARBIER
Samuel JUGE
Armelle Danielou
Gaëlle POUGET
Nicolas BAYONA-CARRILLO
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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
    • 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
    • C22C21/14—Alloys based on aluminium with copper as the next major constituent with silicon
    • 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 to aluminum-copper-lithium alloy products, more particularly, such products intended for aeronautical and aerospace construction.
  • Aluminum alloy products are developed to produce high-strength parts intended in particular for the aeronautical and aerospace industries.
  • 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 with respect to other usage properties must reach that of commonly used alloys, in particular in terms of compromise between static mechanical strength properties (tensile and compression, breaking strength) and damage tolerance properties (toughness, resistance to the propagation of fatigue cracks), these properties generally being contradictory.
  • the elastic limit in compression is an essential property.
  • 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. Finally, they must be obtainable by robust manufacturing processes, in particular, the properties must be able to be obtained on industrial tools for which it is difficult to guarantee temperature homogeneity within a few degrees for large parts.
  • the patent US 5,455,003 describes a process for the manufacture of Al-Cu-Li alloys which exhibit improved mechanical strength and toughness at cryogenic temperature, in particular thanks to suitable work hardening and tempering.
  • the patent US 7,229,509 describes 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 refiners such as Cr, Ti, Hf, Sc, V.
  • the patent application WO2009/036953 relates to an aluminum alloy product for structural elements having a chemical composition comprising, by weight Cu from 3.4 to 5.0, Li from 0.9 to 1.7, Mg from 0.2 to 0.8, Ag from about 0.1 to 0.8, Mn from 0.1 to 0.9, Zn up to 1.5, and one or more elements selected from the group consisting of: (Zr from about 0.05 to 0 ,3, Cr 0.05 to 0.3, Ti about 0.03 to 0.3, Sc about 0.05 to 0.4, Hf about 0.05 to 0.4), Fe ⁇ 0.15, Si ⁇ 0, 5, the normal and unavoidable impurities.
  • the W0 patent application 2012/085359 A2 relates to a process for the manufacture of aluminum alloy rolled products comprising 4.2 to 4.6% by weight of Cu, 0.8 to 1.30% by weight of Li, 0.3 to 0.8% by weight of Mg, 0.05 to 0.18% by weight of Zr, 0.05 to 0.4% by weight of Ag, 0.0 to 0.5% by weight of Mn, at most 0.20 % by weight of Fe + Si, less than 0.20 % by weight of Zn, at least one element chosen from Cr, Se, Hf and Ti, the amount of said element, if chosen, being from 0.05 to 0.3% by weight for Cr and for Se, 0.05 to 0.5% by weight for Hf and 0.01 to 0.15% by weight for Ti, the other elements at most 0.05% by weight each and 0.15% by weight in total, the balance aluminium, comprising the steps of production, casting, homogenization, rolling with a temperature above 400°C, solution treatment, quenching, traction between 2 and 3.5% and returned.
  • the patent application US2012/0225271Al concerns wrought products with a thickness of at least 12.7 mm containing 3.00 to 3.80 wt.% Cu, 0.05 to 0.35 wt.% Mg, 0.975 to 1.385 wt.% of Li, in which -0.3 Mg - 0.15Cu +1.65 ⁇ Li ⁇ -0.3 Mg-0.15Cu +1.85, from 0.05 to 0.50 by weight.
  • the grain structure controlling element is selected from the group consisting of Zr, Sc, Cr, V, Hf, other earth elements rare, and combinations thereof, up to 1.0 wt% Zn, up to 1.0 wt% Mn, up to 0.12 wt% Si, up to 0 .15 wt% Fe, up to 0.15 wt% Ti, up to 0.10 wt. % of other elements with a total not exceeding 0.35 by weight %.
  • Requirement WO 2013/169901 describes alloys comprising, by weight percent, 3.5 to 4.4% Cu, 0.65 to 1.15% Li, 0.1 to 1.0% Ag, 0.45 to 0, 75% Mg, 0.45 to 0.75% Zn and 0.05 to 0.50% of at least one element for grain structure control.
  • the alloys advantageously have a Zn to Mg ratio of between 0.60 and 1.67.
  • the patent application FR 3 007 423 A1 relates to an extrados structural element in aluminum, copper and lithium alloy and its method of manufacture.
  • Alloys comprising (in % by weight) 4.2 to 5.2 Cu, 0.9 to 1.2 Li, 0.1 to 0.3 Ag, 0.1 to 0.25 Mg, 0.11 to 0 .18 Zr, 0.01 to 0.15 Ti, optionally up to 0.2 Zn, optionally up to 0.6 Mn, a Fe and Si content less than or equal to 0.1, and other elements at a lower or equal content at 0.05 each and 0.15 in total, remains Al.
  • a first object of the invention is a product based on an aluminum alloy comprising, in percentage by weight, 4.0 to 4.6% by weight of Cu, 0.7 to 1.2% by weight of Li , 0.5 to 0.65 wt% Mg, 0.10 to 0.20 wt% Zr, 0.15 to 0.30 wt% Ag, 0.25 to 0.45 wt% weight of Zn, 0.05 to 0.35% by weight of Mn, at most 0.20% by weight of Fe + Si, at least one element chosen from among Cr, Sc, Hf, V and Ti, the amount of said element , if chosen, being 0.05 to 0.3% by weight for Cr and for Sc, 0.05 to 0.5% by weight for Hf and for V and 0.01 to 0.15% by weight for Ti, other elements not more than 0.05% by weight each and 0.15% by weight in total and remainder aluminum.
  • Yet another object is an aircraft structural element, preferably an aircraft wing upper surface element.
  • the static mechanical characteristics in tension in other words the breaking strength R m , the conventional yield strength 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 (2016), the sampling and direction of the test being defined by standard EN 485 (2016).
  • R p0.2 (L) means R p0.2 measured in the longitudinal direction.
  • the compressive yield strength Rc p0.2 was measured at 0.2% compression according to ASTM E9-09 (2016).
  • Rc p0.2 (L) means Rc p0.2 measured in the longitudinal direction.
  • the stress intensity factor (K 1C ) is determined according to standard ASTM E 399 (2012).
  • the stress intensity factor (KQ) is determined according to ASTM E 399 (2012).
  • the ASTM E 399 (2012) standard gives the criteria for determining whether K Q is a valid value of K 1C . For a given specimen geometry, the values of K Q obtained for different materials are comparable with each other provided that the elastic limits of the materials are of the same order of magnitude.
  • the critical stress intensity factor Kc in other words the intensity factor that makes the crack unstable, is calculated from the R-curve.
  • the stress intensity factor KCO is also calculated by assigning the initial crack length at the beginning of the monotonic load, at the critical load. These two values are calculated for a specimen of the required shape.
  • K app represents the K CO factor corresponding to the specimen that was used to perform the R-curve test.
  • K eff represents the Kc factor corresponding to the specimen that was used to perform the R-curve test.
  • 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 said construction, its users, its users or others.
  • these structural elements include in particular the elements that make up the fuselage (such as the fuselage skin), the fuselage stiffeners or stringers, the bulkheads, the fuselage (circumferential frames), wings (such as upper or lower wing skin), stiffeners (stringers or stiffeners), ribs and spars) and compound empennage including horizontal and vertical stabilizers (horizontal or vertical stabilizers), as well as floor beams (floor beams), seat tracks (seat tracks) and doors.
  • the fuselage such as the fuselage skin
  • the fuselage stiffeners or stringers such as upper or lower wing skin
  • stiffeners stringers or stiffeners
  • compound empennage including horizontal and vertical stabilizers (horizontal or vertical stabilizers), as well as floor beams (floor beams), seat tracks (seat tracks) and doors.
  • a selected class of aluminum alloys containing in particular specific and critical quantities of lithium, copper, magnesium, silver, manganese and zinc makes it possible to prepare structural elements, in particular wing upper surface plates , having a high elastic limit in compression Rc p0,2 (L), a small difference between elastic limit in compression Rc p0,2 (L) and elastic limit in tensile R p0.2 (L) and a particularly improved apparent stress intensity factor at break K app .
  • the selected alloy composition of the invention also makes it possible to obtain all or part of the aforementioned advantages for a wide range of tempering times (in particular a range of at least 5 hours at a given tempering temperature). Such a composition thus makes it possible to guarantee the robustness of the manufacturing process and therefore to guarantee the final properties of the product during industrial production.
  • the product based on an aluminum alloy according to the invention comprises, in percentage by weight, 4.0 to 4.6% by weight of Cu; 0.7 to 1.2% by weight of Li; 0.5 to 0.65% by weight of Mg; 0.10 to 0.20% by weight of Zr; 0.15 to 0.30% by weight of Ag; 0.25 to 0.45% by weight of Zn; 0.05 to 0.35% by weight of Mn; at most 0.20% by weight of Fe+Si; at least one element selected from Cr, Sc, Hf, V and Ti; other elements not more than 0.05% by weight each and 0.15% by weight in total and remainder aluminium.
  • the copper content of the products according to the invention is between 4.0 and 4.6% by weight, preferably between 4.2 and 4.5% by weight and more preferably between 4.2 and 4.4% by weight. .
  • the minimum copper content is 4.25% by weight.
  • the lithium content of the products according to the invention is between 0.7 and 1.2% by weight.
  • the lithium content is between 0.8 and 1.0% by weight; preferably between 0.85 and 0.95% by weight.
  • the copper content and to a lesser extent the lithium content contributes to improving the static mechanical resistance, however, copper having a detrimental effect in particular on the density, it is preferable to limit the copper content to the preferred maximum value of 4.4% by weight.
  • Increasing 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 preferred lithium content of between 0.85% and 0.95% by weight allows an improvement in the compromise between mechanical strength (yield point in tension and compression) and toughness.
  • a high lithium content, in particular beyond the preferred maximum value of 0.95% by weight can lead to a degradation of toughness.
  • the magnesium content of the products according to the invention is between 0.5% and 0.65% by weight.
  • the magnesium content is at least 0.50% or even at least 0.55% by weight, which simultaneously improves static mechanical strength and toughness.
  • a magnesium content greater than 0.65% by weight can induce a deterioration in toughness.
  • the zinc and silver contents are respectively between 0.25 and 0.45% by weight and 0.15 and 0.30% by weight. Such zinc and silver contents are necessary to guarantee an elastic limit in compression having a value close to that of the elastic limit in tension.
  • the products according to the invention have a difference between the elastic limit in tension R p0.2 (L) and the elastic limit in compression Rc p0.2 (L) less than or equal to 10 MPa, preferably less than or equal to 5 MPa.
  • the presence of silver and zinc makes it possible to obtain a good compromise between the different properties sought.
  • the presence of silver makes it possible to obtain a product in a reliable and robust manner, that is to say that the desired compromise of properties is achieved for a wide range of tempering times, in particular a range of times greater than at 5 a.m., which is compatible with the variability inherent in an industrial manufacturing process.
  • a minimum content of 0.20% by weight of silver is advantageous.
  • a maximum content of 0.27% by weight of silver is advantageous.
  • a minimum content of 0.30% by weight of zinc is advantageous.
  • a maximum content of 0.40% by weight of zinc is advantageous.
  • the Zn content is between 0.30 and 0.40% by weight.
  • the sum of the Zn, Mg and Ag contents comprised between 0.95 and 1.35% by weight, preferentially between 1.00 and 1.30% by weight, more preferentially still between 1.15 and 1.25% in weight.
  • the present inventors have observed that the optimum compromise of properties sought, in particular for wing upper surface structural elements, was only achieved for specific and critical values of the sum of Zn, Mg and Ag.
  • the manganese content is between 0.05 and 0.35% by weight.
  • the Mn content between 0.10 and 0.35% by weight.
  • the manganese content is between 0.2 and 0.35% by weight and preferably between 0.25 and 0.35% by weight.
  • the manganese content is between 0.1 and 0.2% by weight and preferably between 0.10 and 0.20% by weight.
  • the addition of Mn in particular makes it possible to obtain a high tenacity. However, if the Mn content is more than 0.35% by weight, the fatigue life may be significantly reduced.
  • the Zr content of the alloy is between 0.10 and 0.20% by weight. In an advantageous embodiment, the Zr content is between 0.10 and 0.15% by weight, preferably between 0.11 and 0.14% by weight.
  • 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 which can contribute to the control of the grain size chosen from Cr, Sc, Hf, V and Ti, the amount of said element, if chosen, being from 0.05 to 0.3 % by weight for Cr and for Sc, 0.05 to 0.5 % by weight for Hf and for V and 0.01 to 0.15 % by weight for Ti. In an advantageous embodiment, it is chosen to add between 0.01 and 0.15% by weight of titanium. In a preferred embodiment, the Ti content is between 0.01 and 0.08% by weight, preferably between 0.02 and 0.06% by weight.
  • the content of Cr, Sc, V and Hf is limited to a maximum content of 0.05% by weight, these elements possibly having an unfavorable effect, in particular on the density and being added only to further promote obtaining a substantially non-recrystallized structure if necessary.
  • the Ti is present in particular in the form of TiC particles.
  • AlTiC refining the presence of TiC particles in the refining wire during casting (AlTiC refining), makes it possible to obtain a product having an optimized compromise of properties. .
  • the refining agent has the formula AlTi x C y which is also written AT x C y where x and y are the contents of Ti and C in % by weight for 1% by weight of Al, and x/y > 4
  • the AlTiC refining in the alloy of the present invention allows an improvement in the compromise between the toughness K app LT and the elastic limit in compression R c p0.2 L.
  • the content of the alloying elements prefferably, the addition elements contributing to increase the density such as Cu, Zn, Mn and Ag are minimized and the elements contributing to decreasing the density such as Li and Mg are maximized so as to reach a density less than or equal to 2.73 g/cm 3 and preferably less than or equal to 2.72 g/cm 3 .
  • the content of the other elements is at most 0.05% by weight each and 0.15% by weight in total.
  • the other elements are typically unavoidable impurities.
  • the process for manufacturing the products according to the invention comprises the steps of preparation, casting, homogenization, hot deformation, solution treatment and quenching, traction between 2 and 16% 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 the form of a raw form, preferably in the form of a rolling plate or an extruded billet.
  • the raw form is then homogenized so as to reach a temperature of between 450° C. and 550° 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 raw form is generally cooled to ambient temperature before being preheated in order to be hot deformed.
  • the hot deformation can in particular be an extrusion or a hot rolling.
  • this is a hot rolling step. Hot rolling is carried out to a thickness preferably between 8 and 50 mm and preferably between 15 and 40 mm.
  • the product thus obtained is then placed in solution by heat treatment making it possible to reach a temperature of between 490 and 530° C. for 15 min to 8 h, then typically quenched with water at room temperature.
  • the product then undergoes cold deformation with a deformation of 2 to 16%. It may be a controlled tensile with a permanent set of 2 to 5%, preferably 2.0% to 4.0%.
  • the cold deformation is carried out in two stages: the product is first cold rolled with a thickness reduction rate of between 8 to 12% then subsequently pulled in a controlled manner with a permanent deformation between 0.5 and 4%.
  • the product is then subjected to a tempering step carried out by heating at a temperature of between 130 and 170° C. and preferably between 140 and 160° C. for 5 to 100 hours and preferably from 10 to 70 hours.
  • the present inventors have found that, surprisingly, the specific and critical contents of the alloy of the present invention make it possible to achieve excellent properties, in particular a compromise between the elastic limit in compression Rc p0.2 (L ) and particularly improved Kapp plane stress toughness.
  • these properties can be obtained, for the alloys of the invention, regardless of the tempering time between 15 h and 25 h at 155° C., which guarantees robustness of the manufacturing process.
  • the granular structure of the products obtained is mostly non-recrystallized.
  • the rate of non-recrystallized granular structure at mid-thickness is preferably at least 70% and preferentially at least 80%.
  • characteristics i) and ii) are obtained for a wide range of tempering times, in particular a range of at least 5 h at a given tempering temperature.
  • Such a composition thus makes it possible to guarantee the robustness of the manufacturing process and therefore to guarantee the final properties of the product during industrial production.
  • the alloy products according to the invention allow in particular the manufacture of structural elements, in particular aircraft structural elements.
  • the preferred aircraft structural element is an aircraft wing upper surface element.
  • the plate was homogenized with a first level of 15 h at 500°C, followed by a second level of 20 h at 510°C.
  • the plate was hot rolled at a temperature above 440°C to obtain sheets with a thickness of 25 mm for alloys 2 to 8 and 28 mm for alloy 1.
  • the sheets were put in solution at approximately 510° C for 3h, quenched with water at 20°C.
  • the sheets were then stretched with a permanent elongation of between 2% and 6%.
  • the plates underwent single-stage tempering as indicated in Table 2. Samples were taken at mid-thickness to measure the static mechanical characteristics in tension and compression in the longitudinal direction. The plane stress toughness was also measured at mid-thickness during R-curve tests with CCT specimens 406 mm wide and 6.35 mm thick in the LT direction. The results are presented in Table 2 and in figure 1 .
  • Plates were homogenized at approximately 510°C and then scalped. After homogenization, the plates were hot rolled to obtain sheets having a thickness of 25 mm. The sheets were put in solution for 3 hours at approximately 510° C., quenched in cold water and stretched with a permanent elongation of 3%.
  • the structure of the sheets obtained was mostly non-recrystallized.
  • the rate of non-recrystallized granular structure at mid-thickness was 90%.
  • Plates were homogenized at approximately 510°C and then scalped. After homogenization, the plates were hot rolled to obtain plates having a thickness of 25mm. The sheets were put in solution for 3 hours at approximately 510° C., quenched in cold water and stretched with a permanent elongation of 3%.

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Claims (12)

  1. Produkt auf Aluminiumlegierungsbasis umfassend in Gewichtsprozent 4,0 bis 4,6 Gew.-% Cu,
    0,7 bis 1,2 Gew.-% Li,
    0,5 bis 0,65 Gew.-% Mg,
    0,10 bis 0,20 Gew.-% Zr,
    0,15 bis 0,30 Gew.-% Ag,
    0,25 bis 0,45 Gew.-% Zn,
    0,05 bis 0,35 Gew.-% Mn,
    höchstens 0,20 Gew.-% Fe + Si,
    mindestens ein Element ausgewählt aus Cr, Sc, Hf, V 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 für V und 0,01 bis 0,15 Gew.-% für Ti beträgt,
    weitere Elemente jeweils höchstens 0,05 Gew.-% und höchstens 0,15 Gew.-% insgesamt, Rest Aluminium.
  2. Produkt auf Aluminiumlegierungsbasis nach Anspruch 1, bei dem der Cu-Gehalt zwischen 4,2 und 4,5 Gew.-%, vorzugsweise zwischen 4,2 und 4,4 Gew.-% liegt.
  3. Produkt auf Aluminiumlegierungsbasis nach Anspruch 1 oder 2, bei dem der Li-Gehalt zwischen 0,8 und 1,0 Gew.-%, vorzugsweise zwischen 0,85 und 0,95 Gew.-% liegt.
  4. Produkt auf Aluminiumlegierungsbasis nach irgendeinem der Ansprüche 1 bis 3, bei dem der Zn-Gehalt zwischen 0,30 und 0,40 Gew.-% liegt.
  5. Produkt auf Aluminiumlegierungsbasis nach irgendeinem der Ansprüche 1 bis 4, bei dem der Mn-Gehalt zwischen 0,10 und 0,35 Gew.-% liegt.
  6. Produkt auf Aluminiumlegierungsbasis nach irgendeinem der Ansprüche 1 bis 5, bei dem die Summe der Gehalte an Zn, Mg und Ag zwischen 0,95 und 1,35 Gew.-%, bevorzugt zwischen 1,00 und 1,30 Gew.-%, noch bevorzugter zwischen 1,15 und 1,25 Gew.-% liegt.
  7. Produkt auf Aluminiumlegierungsbasis nach irgendeinem der Ansprüche 1 bis 6, bei dem der Zr-Gehalt 0,10 bis 0,15 Gew.-%, vorzugsweise 0,11 bis 0,14 Gew.-%, beträgt.
  8. Produkt auf Aluminiumlegierungsbasis nach irgendeinem der Ansprüche 1 bis 7, bei dem der Ti-Gehalt zwischen 0,01 und 0,15 Gew.-% für Ti, bevorzugt zwischen 0,01 und 0,08 Gew.-%, noch bevorzugter zwischen 0,02 und 0,06 Gew.-% liegt.
  9. Produkt auf Aluminiumlegierungsbasis nach Anspruch 8, bei dem Ti insbesondere in Form von TiC-Partikeln vorliegt.
  10. Verfahren zur Herstellung eines Produkts auf Aluminiumlegierungsbasis, bei dem nacheinander
    a) ein Flüssigmetallbad auf Aluminiumbasis hergestellt wird, umfassend 4,0 bis 4,6 Gew.-% Cu; 0,7 bis 1,2 Gew.-% Li; 0,5 bis 0,65 Gew.-% Mg; 0,10 bis 0,20 Gew.-% Zr; 0,15 bis 0,30 Gew.-% Ag; 0,25 bis 0,45 Gew.-% Zn; 0,05 bis 0,35 Gew.-% Mn; höchstens 0,20 Gew.-% Fe + Si; mindestens ein Element, ausgewählt aus Cr, Sc, Hf, V und Ti, wobei die Menge des Elements, falls ausgewählt, 0,05 bis 0,3 Gew.-% für Cr und Sc, 0,05 bis 0,5 Gew.-% für Hf und V und 0,01 bis 0,15 Gew.-% für Ti beträgt; weitere Elemente jeweils höchstens 0,05 Gew.-% und höchstens 0,15 Gew.-% insgesamt und Rest Aluminium;
    b) aus dem Flüssigmetallbad eine Rohform gegossen wird;
    c) die Rohform bei einer Temperatur zwischen 450°C und 550°C, vorzugsweise zwischen 480°C und 530°C, für eine Dauer zwischen 5 und 60 Stunden homogenisiert wird;
    d) die homogenisierte Rohform warm umgeformt wird, vorzugsweise durch Walzen;
    e) das warm umgeformte Produkt bei 490 bis 530°C für 15 min bis 8 h lösungsgeglüht wird und das lösungsgeglühte Produkt abgeschreckt wird;
    f) das Produkt mit einer Verformung von 2 bis 16 % kalt umgeformt wird;
    g) eine Auslagerungsbehandlung durchgeführt wird, bei der das Produkt eine Temperatur zwischen 130 und 170°C und vorzugsweise zwischen 140 und 160°C während 5 bis 100 Stunden und vorzugsweise 10 bis 70 Stunden erreicht.
  11. Produkt nach irgendeinem der Ansprüche 1 bis 9 oder erhältlich durch das Verfahren nach Anspruch 10, mit einer Dicke zwischen 8 und 50 mm, aufweisend bei halber Dicke:
    i) eine Dehngrenze unter Druckbelastung Rcp0,2(L) ≥ 590 MPa, vorzugsweise Rcp0,2(L) ≥ 595 MPa;
    ii) eine Zähigkeit Kapp (L-T) ≥ 60 MPa√m, vorzugsweise Kapp (L-T) ≥ 75 MPa√m, wobei Kapp (L-T) der Wert des scheinbaren Spannungsintensitätsfaktors beim Bruch ist, definiert gemäß ASTM E561 (2015), gemessen an CCT-Proben mit der Breite W=406 mm und der Dicke B = 6,35 mm;
    iii) eine Differenz zwischen der Dehngrenze unter Zugbelastung Rp0,2(L) und der Dehngrenze unter Druckbelastung Rcp0,2(L), Rp0,2(L) - Rcp0,2(L), von 10 MPa oder weniger, vorzugsweise ≤ 5 MPa.
  12. Flugzeugstrukturelement, vorzugsweise ein Flugzeugflügeloberseitenelement, umfassend ein Produkt nach irgendeinem der Ansprüche 1 bis 9 oder nach Anspruch 11.
EP19726060.7A 2018-05-02 2019-04-24 Aluminium-kupfer-lithium-legierung mit verbesserter kompressionsfestigkeit und erhöhter beständigkeit Active EP3788178B1 (de)

Applications Claiming Priority (2)

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FR1853798A FR3080860B1 (fr) 2018-05-02 2018-05-02 Alliage aluminium cuivre lithium a resistance en compression et tenacite ameliorees
PCT/FR2019/050965 WO2019211547A1 (fr) 2018-05-02 2019-04-24 Alliage aluminium cuivre lithium a resistance en compression et tenacite ameliorees

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EP3788178B1 true EP3788178B1 (de) 2022-08-17

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CA (1) CA3096776A1 (de)
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CN111647786A (zh) * 2020-06-22 2020-09-11 安徽德科科技有限公司 一种铝铜合金材料及其铸造、热处理工艺
CN114438382B (zh) * 2021-11-17 2022-10-11 江阴沐祥精工科技有限公司 一种轨道铝型材

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CN103509984A (zh) 2013-09-28 2014-01-15 中南大学 一种超高强铝锂合金及其制备方法

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WO2013169901A1 (en) 2012-05-09 2013-11-14 Alcoa Inc. 2xxx series aluminum lithium alloys
CN103509984A (zh) 2013-09-28 2014-01-15 中南大学 一种超高强铝锂合金及其制备方法

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CN112041473A (zh) 2020-12-04
BR112020021796B1 (pt) 2024-01-09
CA3096776A1 (fr) 2019-11-07
BR112020021796A2 (pt) 2021-03-23
US20210310108A1 (en) 2021-10-07
WO2019211547A1 (fr) 2019-11-07
FR3080860B1 (fr) 2020-04-17
FR3080860A1 (fr) 2019-11-08
EP3788178A1 (de) 2021-03-10

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