EP3635146B2 - Aluminiumlegierung mit lithium mit verbesserten ermüdungseigenschaften - Google Patents

Aluminiumlegierung mit lithium mit verbesserten ermüdungseigenschaften

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Publication number
EP3635146B2
EP3635146B2 EP18748959.6A EP18748959A EP3635146B2 EP 3635146 B2 EP3635146 B2 EP 3635146B2 EP 18748959 A EP18748959 A EP 18748959A EP 3635146 B2 EP3635146 B2 EP 3635146B2
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Prior art keywords
weight
alloy
product according
product
thickness
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French (fr)
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EP3635146B1 (de
EP3635146A1 (de
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Ricky WHELCHEL
Mathieu REVIL-BAUDARD
Philippe Jarry
Bernard Bes
Fanny MAS
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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
    • 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
    • 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 2XXX alloy products based on aluminum comprising lithium, more particularly such products, and their use, intended in particular for aeronautical and space construction.
  • Aluminium alloy products are developed to produce structural elements intended in particular for the aeronautical and space industries.
  • Aluminum-lithium alloys are particularly promising for manufacturing this type of product.
  • the specifications imposed by the aerospace industry for fatigue resistance are high and particularly difficult to meet for thick products. Indeed, given the possible thicknesses of cast plates, the thickness reduction through hot deformation is quite small, and consequently, the casting-related sites where fatigue cracks initiate only slightly reduce in size during hot deformation.
  • Al-Li alloys generally offer better compromises in properties than conventional alloys, particularly in terms of the trade-off between fatigue resistance, damage tolerance, and mechanical strength. This allows, in particular, for a reduction in the thickness of wrought Al-Li alloy products, thus further maximizing the weight reduction they offer. However, this also increases the prevailing stresses, leading to a higher risk of fatigue crack initiation. Therefore, improving the fatigue resistance of Al-Li alloy products is of interest.
  • WO 2012/110717 To improve the properties, particularly fatigue resistance, of aluminum alloys containing at least 0.1% Mg and/or 0.1% Li, it is proposed to perform an ultrasonic treatment during casting. However, this type of treatment requires a substantial modification of the casting furnace and remains difficult to implement for the quantities needed to manufacture thick sheets.
  • alloys may include 3.4-4.2 wt% of Cu, 0.9-1.4 wt% of Li, 0.3-0.7 wt% of Ag, 0.1-0.6 wt% of Mg, 0.2-0.8 wt% of Zn, 0.1-0.6 wt% of Mn and 0.01-0.6 wt% of at least one element controlling the granular structure, the remainder being aluminum, incident elements and impurities.
  • the demand WO 2015/086921 describes alloys comprising, in % by weight, Cu: 2.0 - 6.0; Li: 0.5 - 2.0; Mg: 0- 1.0; Ag: 0 - 0.7; Zn 0 - 1.0; and at least one element chosen from Zr, Mn, Cr, Sc, Hf and Ti, the quantity of said element, if chosen, being 0.05 to 0.20 % by weight for Zr, 0.05 to 0.8 % by weight for Mn, 0.05 to 0.3 % by weight for Cr and for Sc, 0.05 to 0.5 % by weight for Hf and 0.01 to 0.15 % by weight for Ti, the remainder being aluminium, incident elements and impurities.
  • Al-Cu-Li alloys are known from the "International Alloy Designations and Chemical Composition Limits for Wrought Aluminium and Alloys" published by The Aluminium Association.
  • AA2050, AA2055, AA2098, and AA2099 alloys are known.
  • none of these known alloys incorporates 0.005 to 0.045% by weight of Cr and/or V.
  • the invention relates to a rolled, extruded and/or forged product according to claim 1.
  • the said wrought product does not substantially contain V and/or Cr dispersoids.
  • the invention relates to an aircraft structural element, preferably an intrados or extrados element whose skin and stiffeners come from the same starting product, a spar or a rib, comprising a rolled, spun and/or forged product as described above.
  • alloys are expressed as a percentage by weight based on the total weight of the alloy.
  • the expression 1.4 Cu means that the copper content expressed as a percentage by weight is multiplied by 1.4.
  • the designation of alloys is in accordance with the regulations of The Aluminium Association, which are known to those skilled in the art. When the concentration is expressed in ppm (parts per million), this also refers to a mass concentration.
  • the thickness of the profiles is defined according to EN 2066:2001: the cross-section is divided into elementary rectangles of dimensions A and B; A is always the largest dimension of the elementary rectangle and B can be considered as the thickness of the elementary rectangle.
  • the static mechanical tensile characteristics in other words the tensile strength Rm , the conventional yield strength at 0.2% elongation Rp0.2 , 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).
  • the stress intensity factor (K 1C ) is determined according to ASTM E 399 (2012).
  • the Walker equation was used to determine a maximum stress value representing 50% non-failure at 240,000 cycles.
  • the IQF corresponding to the median, i.e., 50% failure for 240,000 cycles, is reported.
  • the numerical analysis of the image consists of an iterative closure of the image with an increasing step size.
  • the step size i that closes the image C ⁇ sub>i ⁇ /sub> is defined by i successive dilations of the image of the same object (a dilation consisting of replacing each pixel of an image with the maximum value of its neighbors) followed by i successive erosions of the image of the same object (an erosion consisting of replacing each pixel of an image with the minimum value of its neighbors) of the image d (note that the erosion and dilation operations are not commutative).
  • the area ratio A which represents the surface fraction of the objects, is plotted as a function of the number of closure steps i .
  • the parameter p * represents the average distance between particles present in the matrix.
  • s * ⁇ ⁇ A max ⁇ A min 4
  • 1/s * is proportional to the standard deviation of the first-neighbor distance distribution between particles.
  • the parameter s * is therefore a measure of the regularity of the phase distribution in the matrix.
  • the semi-quantitative evaluation is performed using micrographs of samples taken from a quarter or half the thickness of the casting slabs after anodic oxidation (diluted HBF4 solution, open-circuit voltage of 30V, etching time between 60 and 180 s).
  • Example 1 (Table 3, Figures 1 And 2 ) illustrates in detail the correspondence between a score of 0, 1, or 2 as described previously and the micrographs.
  • Figures 1a and 2a are representative of a score of 0, the figures 1c And 2c of a score of 1 and the figures 1b And 2b with a score of 2.
  • the microstructure of wrought sheets is characterized at half thickness (t/2) and at a quarter thickness (t/4) by scanning electron microscopy to determine the dispersion and size of intermetallic phases at the micrometer scale.
  • Intermetallic phases also known as “constituent particles,” are insoluble phases formed during solidification, for example, Al6 (FeMn), Cu2FeAl7 , or FeAl3 phases.
  • Their size is greater than 1 ⁇ m, typically ranging from 2 to 50 ⁇ m.
  • a sheet is a rolled product with a rectangular cross-section and a uniform thickness of at least 6 mm and not exceeding 1/10th of its width.
  • a "structural element" of a mechanical construction refers to a mechanical part whose static and/or dynamic mechanical properties are particularly important for the structure's performance, and for which a structural calculation is usually prescribed or performed. These are typically elements whose failure could jeopardize the safety of the construction, its users, its visitors, or others.
  • these structural elements include in particular the elements that make up the fuselage (such as the fuselage skin, the stringers, the bulkheads, the circumferential frames, the wings (such as the wing skin, the stringers, the ribs and the spars) and the empennage composed in particular of horizontal and vertical stabilizers, as well as the floor beams, the seat tracks and the doors.
  • the present inventors have found that, surprisingly, 2xxx alloy sheets based on aluminium, i.e. Al-Cu alloy, or according to the definition of The Aluminium Association, aluminium alloys whose major addition element is copper and whose content of addition element is greater than 1% by weight, including lithium, exhibiting improved fatigue performance while having advantageous toughness and static mechanical strength properties by selecting specific and critical amounts of chromium and/or vanadium in said alloy, more particularly by specifically adding 0.025 to 0.045% by weight of Cr and/or V.
  • the alloy contains 0.035 to 0.043 wt% of chromium and/or vanadium.
  • Vanadium and/or chromium are generally added to aluminum alloys as grain-refining or grain-structure-controlling elements, similar to zirconium, scandium, hafnium, manganese, or rare earth elements.
  • Grain-refining elements are typically added in quantities of 0.05 to 0.5 wt% to form dispersoids during homogenization and heating.
  • Dispersives primarily serve to prevent grain boundary migration and dislocations during subsequent processing steps. This, in particular, prevents recrystallization during steps such as solution heating. Dispersives are fine precipitates that form during high-temperature thermal operations. For example ZrAl 3 , Al 12 (FeMn) 3 Si and Al 12 Mg 2 Cr. Their size is less than 1 ⁇ m typically from 0.01 to 0.5 ⁇ m.
  • substantially no Cr and/or V dispersoids means a Cr and/or V dispersoid density of less than 0.1 dispersoid per ⁇ m2 , preferably less than 0.05 per ⁇ m2 .
  • the critical amount of Li and V and/or Cr contained in the 2XXX alloy according to the invention affects the microstructure of the as-cast product as well as that of the final wrought product, and the inventors have demonstrated improved properties of the products according to the invention compared to those of known products, particularly in terms of fatigue properties.
  • the inventors For products with thicknesses from 12 to 175 mm according to the invention, preferably from 30 to 140 mm, the inventors have demonstrated an improvement in fatigue resistance and also in toughness and static mechanical strength of the products compared to those of known products having a similar composition, with the exception of the critical V and Cr content.
  • the lithium content of the products according to the invention is from 0.05 to 1.9% by weight.
  • the lithium content is from 0.5 to 1.5% by weight, more preferably from 0.7 to 1.2% by weight and, even more preferably from 0.80 to 0.95% by weight.
  • the alloy of the products according to the invention is a 2XXX alloy comprising 3.2 to 4.0% by weight of Cu.
  • the alloy of the products according to the invention further comprises magnesium.
  • the magnesium content of the products according to the invention is advantageously between 0.15 and 0.7% by weight, and preferably between 0.2 and 0.6% by weight.
  • the magnesium content is at least 0.30% by weight, preferably at least 0.35% by weight, and preferably at least 0.38% by weight.
  • the magnesium content is between 0.30 and 0.40% by weight.
  • the alloy of the products according to the invention comprises less than 0.8% by weight of Zn, preferably less than 0.7% by weight of Zn.
  • the zinc content is between 0.45 and 0.65% by weight, which can contribute to achieving an excellent compromise between toughness and mechanical strength.
  • the alloy according to the invention advantageously comprises less than 0.15% by weight of Ag, preferably less than 0.1% by weight, and even more preferably less than 0.05% by weight.
  • the alloy according to the invention comprises less than 0.05% by weight of Zn.
  • the alloy according to the invention advantageously comprises more than 0.2% by weight of Silver, preferably between 0.3 and 0.5% by weight of Ag and more preferably between 0.3 and 0.4% by weight of Ag.
  • the alloy of the products according to the invention further comprises 0.07 to 0.15% by weight of Zr, preferably 0.07 to 0.11% by weight of Zr and, more preferably still, 0.08 to 0.10% by weight of Zr.
  • the manganese content of the products according to the invention is between 0.1 and 0.6% by weight, preferably 0.2 and 0.4% by weight, which makes it possible to improve toughness without compromising mechanical strength.
  • the sum of the iron and silicon content is at most 0.20% by weight.
  • the iron and silicon contents are each at most 0.08% by weight.
  • the iron and silicon contents are at most 0.06% and 0.04% by weight, respectively.
  • the alloy also contains at least one element that can contribute to grain size control, chosen from Hf, Ti, and Sc or other rare earth elements.
  • the amount of the element, if chosen, is 0.02 to 0.10% by weight for Sc and other rare earth elements; 0.02 to 0.5% by weight for Hf; and 0.01 to 0.15% by weight for Ti.
  • the product is an aluminum-based alloy comprising, in % by weight, in addition to the aforementioned critical content of Cr and/or V, Cu: 3.2 - 4.0; Li: 0.80 - 0.95; Zn: 0.45 - 0.70; Mg: 0.15 - 0.7; Zr: 0.07 - 0.15; Mn: 0.1 - 0.6; Ag: ⁇ 0.15; Fe + Si ⁇ 0.20; at least one element among Ti: 0.01 - 0.15; Sc: 0.02 - 0.1; Hf: 0.02 - 0.5; other elements ⁇ 0.05 each and ⁇ 0.15 in total, remainder aluminum.
  • the product according to the invention is made from AA2050 alloy comprising the aforementioned critical content of Cr and/or V.
  • the manufacturing process for the products according to the invention includes the steps of preparing a bath of liquid metal; casting; homogenization; rolling, forging and/or extrusion; solution heating; quenching; stress relieving and optionally tempering.
  • a liquid metal bath is prepared in an aluminum-based 2XXX alloy comprising 0.05 to 1.9% by weight of Li and 0.025 to 0.045% by weight of Cr and/or V.
  • the liquid metal bath is then cast in a raw form typically a rolling plate, a forging blank or a sprue.
  • the microstructure of the product according to claim 1 differs from that of prior art products from the casting stage onwards.
  • the as-cast product has more dendritic grains compared to those of an as-cast alloy product of the same composition, with the exception of its specific and critical V and Cr content.
  • the raw casting product is then advantageously homogenized at a temperature between 450°C and 550°C and preferably between 480°C and 530°C for a period of between 5 and 60 hours.
  • the as-cast product is generally cooled to room temperature before being reheated for hot forming.
  • the reheating aims to reach a temperature advantageously between 400 and 550 °C, and preferably around 500 °C, enabling the deformation of the as-cast shape.
  • Hot forming can be carried out by rolling, forging, and/or extrusion.
  • hot forming is carried out by rolling and/or forging to obtain a rolled and/or forged product with a thickness of preferably at least 12 mm, more preferably at least 30 mm, and even more preferably at least 40 mm.
  • the rolled and/or forged product also has a preferred thickness of not more than 175 mm, more preferably not more than 140 mm, and even more preferably not more than 110 mm.
  • the resulting wrought product is then solution-treated, preferably at 490 to 550 °C for 15 minutes to 8 hours, and then typically quenched with water at room temperature.
  • the product then undergoes controlled stress relieving, preferably by tension and/or compression, with a permanent strain of 1 to 7%, and preferably at least 2%.
  • Rolled products preferably undergo controlled tension with a permanent strain of at least 3.5%.
  • the preferred metallurgical conditions are T84 and T86, preferably T84.
  • Known steps such as rolling, planishing, straightening, and shaping may optionally be carried out after solution heating and quenching, and before or after controlled tension.
  • An income is optionally generated including heating at a temperature between 130 and 170°C for 5 to 100 hours and preferably from 10 to 50 hours.
  • the rolled and/or forged product has a thickness of between 30 and 140 mm, preferably still between 40 and 110 mm and even more preferably between 40 and 75 mm.
  • the alloy according to the invention is particularly intended for the manufacture of rolled and/or forged products and, more particularly, of rolled products.
  • the products according to the invention can advantageously be used in structural elements, in particular aircraft structural elements.
  • the use of a structural element incorporating at least one product according to the invention is advantageous, particularly for aircraft construction.
  • the products according to the invention are especially advantageous for the production of machined parts, such as, in particular, upper and lower wing surfaces whose skin and stiffeners are derived from the same starting material, longerons and ribs, as well as any other application where these properties could be advantageous.
  • Table 1 Composition in % by weight of Al-Cu-Li alloys cast in plate form. Alloy If Fe Cu Mn Mg Zn Ti Zr Li Ag V Cr HAS 0.02 0.03 3.60 0.38 0.34 - 0.03 0.08 0.92 0.36 0.04 - B 0.02 0.04 3.60 0.35 0.34 - 0.03 0.08 0.93 0.37 - 0.04 C (2050) 0.03 0.04 3.60 0.38 0.33 - 0.03 0.09 0.90 0.35 - - D (2050) 0.03 0.04 3.50 0.35 0.33 - 0.04 0.08 0.92 0.35 - - -
  • Samples were taken from half-thickness (t/2) and a quarter-thickness (t/4) of selected casting slabs to measure the casting grain size and the parameters p * and s *, which characterize the fineness and uniformity of microsegregation.
  • the parameter s * is more significant for describing the regularity of the particle distribution, while the parameter p * is more significant for describing the fineness of their spatial distribution.
  • Table 2 Grain size and parameters s ⁇ sup>* ⁇ /sup> and p ⁇ sup>* ⁇ /sup> evaluated at half thickness (t/2) and quarter thickness (t/4) of Al-Cu-Li alloy casting plates.
  • score 0 predominantly globular grains
  • score 1 weakly dendritic grains
  • score 2 strongly dendritic grains.
  • the semi-quantitative evaluation was performed using micrographs of the samples after anodic oxidation (diluted HBF4 solution, open-circuit voltage of 30V, etching time between 60 and 180 s).
  • Table 3 summarizes the scores assigned to the different samples.
  • Figures 1 And 2 present micrographs obtained for samples taken at mid-thickness ( Fig. 3 ) and quarter-thickness ( Fig. 4 ) casting plates in alloy A (Fig. 3b and 4b), B (Fig. 3c and 4c) and C (Fig. 3a and 4a).
  • Plates A and B exhibit larger and more dendritic casting grains compared to those of plate C.
  • Example 1 Some of the casting slabs from Example 1 were homogenized at 505 °C for approximately 12 hours and then scalped. The slabs were hot-rolled to obtain sheets 60 mm thick. They were solution-treated at 527 °C and quenched with cold water. The sheets were then tensile-tested with a permanent elongation of 3.7%.
  • the sheets underwent tempering at 155°C for approximately 20 hours.
  • Sheets A and B generally exhibit an improved compromise of mechanical resistance Rp0.2 / toughness K1C properties compared to that of sheets C and D in alloy 2050 according to the prior art.
  • Alloy sheets A and B exhibit improved fatigue properties compared to sheet D.
  • Table 7 Composition in % by weight of Al-Cu-Li cast in plate form. Alloy If Fe Cu Mn Mg Zn Ti Zr Li Ag V Cr E 0.03 0.04 3.57 0.34 0.44 0.52 0.03 0.10 0.87 0.026 0.041 - F 0.03 0.05 3.58 0.34 0.43 0.60 0.03 0.11 0.86 0.002 0.040 - G 0.02 0.04 3.61 0.34 0.43 0.61 0.03 0.11 0.85 0.010 0.042 - H 0.03 0.04 3.45 0.33 0.34 0.56 0.03 0.10 0.86 0.079 0.038 - I 0.02 0.05 3.55 0.34 0.33 0.60 0.03 0.10 0.93 0.110 0.039 - J 0.02 0.04 3.55 0.34 0.33 0.60 0.03 0.11 0.87 0.090 0.039 -
  • the plates were homogenized at 505 °C for 12 hours and then scalped. They were hot-rolled to a final thickness of 20 and 50 mm (E and J alloy sheets), or 102 and 130 mm (G alloy sheet), or 150 mm (sheets of alloys F and I) were then solution-treated at 527 °C and quenched with cold water. The sheets were then tensile-tested with a permanent elongation of 6% and tempered at 150 °C for approximately 20 hours.
  • the G alloy from Example 2 was processed as previously described (102 mm thickness) except for the final tempering step.
  • a tempering kinetics analysis was performed for this example, and the results are compared to those obtained for the K alloy (detailed composition in Table 8 below) processed under the same conditions.
  • Table 8 Composition in % by weight of Al-Cu-Li cast in plate form. Alloy If Fe Cu Mn Mg Zn Ti Zr Li Ag V Cr K 0.02 0.04 3.62 0.36 0.43 0.56 0.031 0.10 0.90 0.01 - -
  • tempering conditions studied were as follows: 150°C for 20, 25 or 30h (alloy G) and 20, 30, 40 and 50h (alloy K).
  • microstructure at half thickness (t/2) and quarter thickness (t/4) of sheets from examples 1 and 3 was studied by scanning electron microscopy in order to determine the density of intermetallic phases at the micrometer scale.
  • the density (number of phases per mm2 ) of the intermetallic phases is detailed in Table 9.
  • Table 9 Density (number per mm2) of intermetallic phases Alloy Intermetallic phases (number per mm2 ) t/4 t/2 Average density through thickness HAS 130.8 127.6 129.2 B 124.3 120.7 122.5 C 161.0 154.6 157.8 E 144.6 145.1 144.8 F 148.5 159.3 153.9 G 159.9 144.9 152.4
  • Table 10 Composition in % by weight of Al-Cu-Li cast in plate form. Alloy If Fe Cu Mn Mg Zn Ti Zr Li Ag V Cr L 0.03 0.05 3.48 0.38 0.35 0.62 0.031 0.08 0.89 0.10 - - M 0.03 0.04 3.53 0.38 0.37 0.61 0.032 0.08 0.91 0.12 0.040 - N 0.03 0.04 3.52 0.36 0.35 0.58 0.031 0.09 0.88 0.10 0.040 -
  • the plates were homogenized for 12 hours at 505 °C and then for 12 hours at 525 °C before being scalped.
  • the plates were hot-rolled to obtain sheets 130 mm thick. They were solution-treated at 517 °C and quenched with cold water. The sheets were then tensile-tested to a permanent elongation of 3.7%.
  • the sheets underwent tempering at 155°C for approximately 20 hours.
  • Table 11 Static mechanical properties obtained for the different sheets.
  • the M and N sheets generally present an improved compromise of mechanical resistance Rp0.2 / toughness K1C properties compared to that of the L sheet.

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Claims (12)

  1. Walzprodukt, stranggepresst und/oder geschmiedet, aus einer 2XXX-Legierung auf Basis von Aluminium, dessen Dicke 12 bis 175 mm, in Gewichtsprozenten umfassend,
    Li 0,05 - 1,9 %;
    Cu 1,0 - 6,0 %;
    Cr und/oder V: 0,025-0,044 %;
    Mg 0,1 - 1,0 %;
    Zr 0 - 0,15 %;
    Mn 0 - 0,6 %;
    Zn < 0,8 %;
    Ag 0 - 0,5;
    Fe+Si < 0,2;
    mindestens ein Element, das zur Kontrolle der Korngröße beitragen kann, aus Hf, Ti und Sc oder einer anderen seltenen Erde, wie 0,02 bis 0,1 % für Sc und eine andere seltene Erde, 0,02 bis 0,5 % für Hf und 0,01 bis 0,15 % für Ti;
    sonstige Elemente jeweils ≤ 0,05 und ≤ 0,15 insgesamt, der Rest Aluminium;
    und derart, dass die Dichte der Cr- und/oder V-Dispersoide geringer als 0,1 Dispersoid je µm2 ist.
  2. Produkt nach Anspruch 1, das eine mittlere Dichte d an intermetallischen Phasen, ausgedrückt in Anzahl an Phasen je mm2 aufweist, sodass: d < − 0 , 0023 e 2 + 0 , 0329 e + 160 , 91 mit e = Produktdicke in mm.
  3. Produkt nach einem der Ansprüche 1 bis 2, umfassend 0,5 bis 1,5 Gew.-% an Li, vorzugsweise 0,7 bis 1,2 Gew.-% an Li und, noch bevorzugter 0,80 bis 0,95 Gew.-% an Li.
  4. Produkt nach einem der vorstehenden Ansprüche, mindestens 0,7 Gew.-% an Zn umfassend.
  5. Produkt nach einem der vorstehenden Ansprüche, weiter 0,07 bis 0,15 Gew.-% an Zr, vorzugsweise 0,07 bis 0,11 Gew.-% an Zr, und noch bevorzugter 0,08 bis 0,10 Gew.-% an Zr umfassend.
  6. Produkt nach einem der Ansprüche, 0,035 bis 0,043 Gew.-% an Cr und/oder an V umfassend.
  7. Produkt nach Anspruch 1, sodass die Legierung auf Basis von Aluminium in Gewichts-% umfasst,
    Cu: 3,2 - 4,0;
    Li: 0,80 - 0,95;
    Cr und/oder V: 0,025-0,044 %;
    Zn: 0,45 - 0,70;
    Mg: 0,15 - 0,7;
    Zr: 0,07 - 0,15;
    Mn: 0,1 - 0,6;
    Ag: < 0,15;
    Fe + Si ≤ 0,20;
    mindestens ein Element aus
    Ti: 0,01 - 0,15;
    Sc: 0,02 - 0,1;
    Hf: 0,02 - 0,5;
    sonstige Elemente jeweils ≤ 0,05 und ≤ 0,15 insgesamt, der Rest Aluminium.
  8. Produkt nach den Ansprüchen 1 bis 4, sodass die Legierung auf Basis von Aluminium eine AA2050-Legierung ist.
  9. Produkt nach einem der vorstehenden Ansprüche, dessen Dicke 30 bis 140 mm noch bevorzugter 40 bis 110 mm und ganz besonders bevorzugt 40 bis 75 mm beträgt.
  10. Produkt nach einem der vorstehenden Ansprüche in einem gewalzten Zustand, in Lösung gebracht, getempert, vorzugsweise durch Ziehen spannungsarmgeglüht, und angelassen, welches für Dicken zwischen 12 und 175 mm eine Ermüdungsfestigkeit, IQF, bei 240.000 Zyklen, ausgedrückt in MPa, wie folgt aufweist: IQF > − 0 , 0886 e + 177 mit e = Dicke des Produkts in mm.
  11. Produkt nach einem der vorstehenden Ansprüche in einem gewalzten Zustand, in Lösung gebracht, getempert, vorzugsweise durch Ziehen spannungsarmgeglüht, und angelassen, welches mindestens einen, vorzugsweise mindestens zwei der folgenden Eigenschaftskompromisse aufweist, die in Bezug auf ein Produkt aus einer Legierung mit einer selben Zusammensetzung, mit Ausnahme seines Cr- und V-Gehaltes, verbessert sind:
    - Rp0,2 (L) und K1C (L-T),
    - Rp0,2 (TL) und K1C (T-L)
    - Rp0,2 (TC) und K1C (TC-L).
  12. Flugzeugstrukturelement, vorzugsweise inneres oder äußeres Wölbungselement, dessen Haut und Verstrebungen aus einem selben Ausgangsprodukt stammen, ein Längsträger oder eine Rippe, umfassend ein Produkt nach einem der Ansprüche 1 bis 11.
EP18748959.6A 2017-06-06 2018-06-05 Aluminiumlegierung mit lithium mit verbesserten ermüdungseigenschaften Active EP3635146B2 (de)

Applications Claiming Priority (2)

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FR1755031A FR3067044B1 (fr) 2017-06-06 2017-06-06 Alliage d'aluminium comprenant du lithium a proprietes en fatigue ameliorees
PCT/FR2018/051298 WO2018224767A1 (fr) 2017-06-06 2018-06-05 Alliage d'aluminium comprenant du lithium a proprietes en fatigue ameliorees

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CN (1) CN110741103B (de)
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WO2020097169A1 (en) 2018-11-07 2020-05-14 Arconic Inc. 2xxx aluminum lithium alloys
EP3947761A4 (de) * 2019-04-05 2022-11-30 Arconic Technologies LLC Verfahren zur kaltumformung von aluminium-lithium-legierungen
CN114318089A (zh) * 2022-01-05 2022-04-12 成都阳光铝制品有限公司 一种用于制造汽车配件的铝合金及其制备方法
CN114737233B (zh) * 2022-02-27 2024-04-02 陕西良鼎瑞金属新材料有限公司 一种铝材产品
FR3147815A1 (fr) * 2023-04-13 2024-10-18 Constellium Issoire Produit épais en alliages aluminium cuivre lithium avec une ténacité améliorée et procédé d’obtention

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EP3635146B1 (de) 2022-11-16
EP3635146A1 (de) 2020-04-15
US12601036B2 (en) 2026-04-14
FR3067044A1 (fr) 2018-12-07
CN110741103A (zh) 2020-01-31
CN110741103B (zh) 2022-03-25
CA3064802A1 (fr) 2018-12-13
FR3067044B1 (fr) 2019-06-28
BR112019025517A2 (pt) 2020-06-23
US20200165707A1 (en) 2020-05-28
BR112019025517B1 (pt) 2023-04-25
WO2018224767A1 (fr) 2018-12-13

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