EP3201371B1 - Verfahren zur herstellung eines knetproduktes aus einer aluminium-magnesium-lithium legierung, knetprodukt und vervendung des knetproduktes - Google Patents

Verfahren zur herstellung eines knetproduktes aus einer aluminium-magnesium-lithium legierung, knetprodukt und vervendung des knetproduktes Download PDF

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EP3201371B1
EP3201371B1 EP15785160.1A EP15785160A EP3201371B1 EP 3201371 B1 EP3201371 B1 EP 3201371B1 EP 15785160 A EP15785160 A EP 15785160A EP 3201371 B1 EP3201371 B1 EP 3201371B1
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product
mpa
alloy
process according
weight
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EP3201371A1 (de
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Gaëlle POUGET
Bernard Bes
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Constellium Issoire SAS
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Constellium Issoire SAS
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Priority claimed from FR1402186A external-priority patent/FR3026411B1/fr
Priority claimed from FR1402187A external-priority patent/FR3026410B1/fr
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/047—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 magnesium 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
    • C22C21/06—Alloys based on aluminium with magnesium 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
    • C22C21/06—Alloys based on aluminium with magnesium as the next major constituent
    • C22C21/08—Alloys based on aluminium with magnesium as the next major constituent with silicon
    • 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
    • C22F1/002—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working by rapid cooling or quenching; cooling agents used therefor

Definitions

  • the invention relates to a process for manufacturing a wrought aluminum-magnesium-lithium alloy product, more particularly to a process for manufacturing such a product exhibiting an improved compromise in properties, in particular an improved compromise between tensile yield strength. and toughness of said products.
  • the subject of the invention is also a product capable of being obtained by said manufacturing process and its use, said product being intended in particular for aeronautical and aerospace construction.
  • Wrought aluminum alloy products are developed to produce high strength parts intended in particular for the aeronautical industry and the aerospace industry.
  • Aluminum alloys containing lithium are of great interest 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 lithium added.
  • aluminum alloys simultaneously containing magnesium and lithium make it possible to achieve particularly low densities and have therefore been extensively studied.
  • the patent GB 1,172,736 teaches an alloy containing, in weight percent, 4-7% Mg, 1.5 - 2.6% Li, 0.2 - 1% Mn and / or 0.05 - 0.3% Zr, remains aluminum. This alloy is useful for producing products with high mechanical strength, good corrosion resistance, low density and high modulus of elasticity. Said products are obtained by a process comprising optional quenching followed by tempering. By way of example, the products resulting from the process according to GB 1,172,736 present a tensile strength ranging from about 440 MPa to about 490 MPa, a tensile yield strength ranging from about 270 MPa to about 340 MPa and an elongation at break of the order of 5-8%.
  • This document also discloses a process for obtaining said alloy comprising the steps: a) casting an ingot of the composition described above, b) removing the residual stresses from said ingot by heat treatment, c) homogenizing by heating and maintaining temperature then cooling the ingot, d) hot rolling said ingot to its final thickness, e) dissolving and then quenching the product thus rolled, f) pulling the product and g) tempering said product by heating and maintaining temperature .
  • the patent US 5,431,876 teaches a group of ternary alloys of lithium aluminum and magnesium or copper, including at least one additive such as zirconium, chromium and / or manganese.
  • the alloy is prepared according to methods known to those skilled in the art comprising, by way of example, an extrusion, a solution, a quenching, a traction of the product of 2 to 7% then an annealing.
  • the patent US 6,551,424 describes a process for manufacturing aluminum-magnesium-lithium alloy rolled products of composition (in% by weight) Mg: 3.0 - 6.0; Li: 0.4 - 3.0; Zn up to 2.0; Mn up to 1.0; Ag up to 0.5; Fe up to 0.3; Si up to 0.3; Cu up to 0.3; 0.02 - 0.5 of a member selected from the group consisting of Sc, Hf, Ti, V, Nd, Zr, Cr, Y, Be, said process including cold rolling lengthwise and in the direction of the width.
  • the patent US 6,461,566 describes an alloy of composition (in% by weight) Li: 1.5 - 1.9; Mg: 4.1 - 6.0; Zn 0.1 - 1.5; Zr 0.05 - 0.3; Mn 0.01 - 0.8; H 0.9 x 10 -5 -4.5 x 10 -5 and at least one element selected from the group Be 0.001 - 0.2; Y 0.001 - 0.5 and Sc 0.01 - 0.3.
  • the patent application WO 2012/16072 describes a wrought aluminum alloy product of composition in% by weight, Mg: 4.0 - 5.0; Li: 1.0 - 1.6; Zr: 0.05 - 0.15; Ti: 0.01 - 0.15; Fe: 0.02 - 0.2; Si: 0.02 - 0.2; Mn: ⁇ 0.5; Cr ⁇ 0.5; Ag: ⁇ 0.5; Cu ⁇ 0.5; Zn ⁇ 0.5; Sc ⁇ 0.01; other elements ⁇ 0.05; remains aluminum.
  • Said product is in particular obtained according to a manufacturing process comprising in particular successively the casting of the alloy in raw form, its hot and optionally cold deformation, the solution and then the quenching of the product thus deformed, optionally the cold deformation.
  • the metallurgical state obtained for the rolled products is advantageously a T6 or T6X or T8 or T8X state and for the extruded products advantageously a T5 or T5X state in the case of quenching on a press or a T6 or T6X or T8 or T8X state.
  • FR 1 519 021 A discloses an alloy, which contains 4-7% Mg, 1.5-2.6% Li, 0.05-0.3% Zr, 0.2-1.0 Mn, the remainder being aluminum.
  • SU 1 367 517 A1 discloses an aluminum base alloy.
  • EP 0 273 600 A2 discloses an aluminum alloy containing 1.0-2.8 Li%, 2.5-7.0% Mg and ⁇ 1% at least one of the additive elements including Zr.
  • CHEN ZG ET AL "The effect of small additions of silver on aging behavior of Al-Mg-Li alloys", ALUMUMUM ALLOYS: THEIR PHYSICAL AND MECHANICAL PROPERTIES, PAPERS PRESENTED AT THE INTERNATIONAL CONFERENCE, 4TH, ATLANTA, SEPT.
  • Wrought aluminum-magnesium-lithium alloy products have a low density and are therefore particularly advantageous in the extremely demanding field of aeronautics.
  • their performance must be significantly improved compared to that of existing products, in particular their performance in terms of compromise between the properties of static mechanical resistance (in particular tensile yield strength and compression, tensile strength) and damage tolerance properties (toughness, fatigue crack propagation resistance), these properties being generally contradictory.
  • These alloys must also have sufficient corrosion resistance, be able to be shaped according to the usual methods and have low residual stresses so as to be able to be machined without substantial distortion during said machining.
  • Another subject of the invention is a wrought product capable of being obtained according to the method of the invention as well as the use of said wrought product to produce an aircraft structural element.
  • alloys are expressed as a percentage by weight based on the total weight of the alloy.
  • expression 1.4 Cu means that the copper content expressed in% by weight is multiplied by 1.4.
  • the designation of the alloys is made in accordance with the regulations of The Aluminum Association, known to those skilled in the art. Density depends on composition and is determined by calculation rather than by a weight measurement method. 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 metallurgical states are given in European standard EN 515.
  • the static mechanical properties in tension are determined by a tensile test according to standard NF EN ISO 6892-1, the sampling and direction of the test being defined by standard EN 485-1.
  • the increased stress on the product during the K1c toughness test according to ASTM E399 may be indicative of the product's propensity to delamination.
  • delamination is meant here (“crack delamination” and / or “crack divider” in English) a cracking in planes orthogonal to the front of the main crack. The orientation of these planes corresponds to that of the grain boundaries not recrystallized after deformation by wrought.
  • a low delamination is the sign of less fragility of the planes concerned and minimizes the risks of deviation of crack towards the longitudinal direction during propagation in fatigue or under monotonic stress.
  • structural element or “structural element” of a mechanical construction 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 the failure of which 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 stiffeners or runners of the fuselage (stringers), the watertight bulkheads, the frames of the fuselage (circumferential frames), the wings (such as the upper or lower wing skin), the stiffeners (stringers or stiffeners), the ribs, the spars (spars), the floor (floor beams) and seat tracks (seat tracks)) and the tail unit composed in particular of horizontal and vertical stabilizers (horizontal or vertical stabilizers), as well as the doors.
  • the process for manufacturing the products according to the invention comprises the successive stages of producing a bath of liquid metal so as to obtain an Al-Mg-Li alloy of particular composition, the casting of said alloy in crude form, optionally the homogenization of said raw form thus cast, hot deformation of said raw form to obtain a hot-deformed product, separate solution of the product thus hot-deformed, quenching of said hot-deformed product, optionally dressing / leveling of the deformed and tempered product, the tempering of said deformed and tempered product and the cold deformation of the tempered product in a controlled manner to obtain a permanent cold deformation of 1 to 10%, preferably 2 to 6%, more preferably still of 3 at 5% and more preferably still from 4 to 5%.
  • the manufacturing process therefore consists first of all in the casting of a crude form of Al-Mg-Li alloy of composition, in% by weight: Mg: 4.0 - 5.0; Li: 1.0 -1.8; Zr: 0.05 - 0.15; Mn: ⁇ 0.6; Ag: ⁇ 0.5; Fe: ⁇ 0.1; Ti: ⁇ 0.15; Si: ⁇ 0.05; other elements ⁇ 0.05 each and ⁇ 0.15 in combination; remains aluminum.
  • a bath of liquid metal is therefore produced and then cast in raw form, typically a rolling plate, a spinning billet or a forge blank.
  • the Al-Mg-Li alloy has an Mn content, in% by weight, of 0.2 to 0.6%, preferably from 0.35 to 0.5%, more preferably of 0.35 to 0.45% and more preferably still from 0.35 to 0.40%.
  • the alloy products as described above and having the advantageous Mn content exhibit in particular improved static mechanical properties as well as a low propensity for delamination.
  • the raw aluminum alloy form has a silver content of less than or equal to 0.25% by weight, more preferably a silver content of 0.05% to 0.1% by weight.
  • This element contributes in particular to the static mechanical properties.
  • the raw aluminum alloy form has a total Ag and Cu content of less than 0.15% by weight, preferably less than or equal to 0.12%. The control of the maximum content of these two elements in combination makes it possible in particular to improve the resistance to intergranular corrosion of the wrought product.
  • the crude form has a zinc content, in% by weight, of less than 0.04%, preferably less than or equal to 0.03%.
  • a zinc content in% by weight, of less than 0.04%, preferably less than or equal to 0.03%.
  • Such limitation of zinc content in the particular alloy described above has given excellent results in terms of density and corrosion resistance of the alloy.
  • the raw aluminum alloy form has an Fe content, in% by weight, less than 0.08%, preferably less than or equal to 0.07%, more preferably still less than or equal to 0.06%.
  • the present inventors believe that a minimum content of Fe, as well as possibly that of Si, can contribute to improving the mechanical properties and in particular the fatigue properties of the alloy. Excellent results have in particular been obtained for an Fe content of 0.02 to 0.06% by weight and / or an Si content of 0.02 to 0.05% by weight.
  • the lithium content of the products according to the invention is between 1.0 and 1.8% by weight.
  • the raw aluminum alloy form has a Li content, in% by weight, less than 1.6%, preferably less than or equal to 1.5%, more preferably less than or equal to 1 , 4%.
  • a minimum lithium content of 1.1% by weight and preferably 1.2% by weight is advantageous.
  • the present inventors have observed that a limited lithium content, in the presence of certain addition elements, makes it possible to very significantly improve the toughness, which largely compensates for the slight increase in density and the decrease in static mechanical properties.
  • the raw aluminum alloy form has a Zr content, in% by weight, of 0.10 to 0.15%.
  • the inventors have in fact observed that such a Zr content makes it possible to obtain an alloy having a favorable fiber structure for improved static mechanical properties.
  • the raw aluminum alloy form has an Mg content, in% by weight, of 4.5 to 4.9%. Excellent results have been obtained for alloys according to this embodiment, in particular as regards the static mechanical properties.
  • the Cr content of the products according to the invention is less than 0.05% by weight, preferably less than 0.01% by weight.
  • Such a limited Cr content in combination with the other elements of the alloy according to the invention makes it possible in particular to limit the formation of primary phases during casting.
  • the Ti content of the products according to the invention is less than 0.15% by weight, preferably between 0.01 and 0.05% by weight.
  • the Ti content is limited in the particular alloy of the present invention, in particular to prevent the formation of primary phases during casting.
  • the manufacturing process optionally comprises a step of homogenizing the raw form so as to reach a temperature between 450 ° C and 550 ° C and, preferably, between 480 ° C and 520 ° C for a period of between 5 and 60 hours.
  • the homogenization treatment can be carried out in one or more stages.
  • the hot deformation is carried out directly following a simple reheating without carrying out homogenization.
  • the raw shape is then hot deformed, typically by extrusion, rolling and / or forging, to obtain a deformed product.
  • This hot deformation is carried out from preferably at an inlet temperature above 400 ° C and, advantageously, from 420 ° C to 450 ° C.
  • the hot deformation is a deformation by extrusion of the raw form.
  • the hot and optionally cold deformed product is optionally subjected to separate solution at a temperature of 360 ° C to 460 ° C, preferably 380 ° C to 420 ° C, for 15 minutes to 8 hours.
  • the hot-deformed product is dissolved and then quenched.
  • the quenching is carried out with water and / or air. It is advantageous to carry out the quenching in air because the intergranular corrosion properties are improved.
  • a press or quenching on extrusion heat
  • it is advantageous to carry out the quenching on a press (or quenching on extrusion heat), preferably quenching on an air press, such quenching making it possible in particular to improve the static mechanical properties.
  • it can also be quenching on a water press. In the case of quenching on a press, the product is dissolved over extrusion heat.
  • the hot-deformed and tempered product may optionally be subjected to a dressing or leveling step depending on whether it is a section or a sheet.
  • dressing or leveling is understood here to mean a cold deformation step without permanent deformation or with a permanent deformation of less than 1%.
  • the hot-deformed, quenched and optionally dressed / planed product then undergoes a tempering step.
  • the tempering is carried out by heating, in one or more stages, at a temperature below 150 ° C, preferably at a temperature of 70 ° C to 140 ° C, for 5 to 100 hours.
  • the hot-deformed product thus tempered is cold-deformed in a controlled manner to obtain a permanent cold deformation of 1 to 10%, preferably 2 to 6%, more preferably still from 3 to 5% and, more preferably still. from 4 to 5%.
  • the permanent cold deformation is 2 to 4%.
  • the cold deformation can in particular be carried out by traction, compression and / or rolling.
  • the cold deformation is carried out by traction.
  • the metallurgical state obtained for the wrought products corresponds in particular to a T9 state according to standard EN515.
  • the process for manufacturing a wrought product does not include any cold deformation step inducing a permanent deformation of at least 1% between the hot deformation step or, if this step is present, solution and the income stage.
  • composition chosen in particular the content of Mg, Li and Mn if the latter is present, and the processing parameters, in particular the order of the steps of the manufacturing process, advantageously makes it possible to obtain wrought products. having a very particular improved property compromise, in particular the compromise between mechanical strength and damage tolerance, while exhibiting low density and good corrosion performance.
  • the wrought products according to the invention are preferably extruded products such as profiles, rolled products such as sheets or thick sheets and / or forged products.
  • a subject of the invention is also wrought products capable of being obtained according to the method described above, advantageously such products cold-deformed with a permanent cold-deformation of greater than 4%. Indeed, such products have quite new and particular characteristics.
  • the wrought products that can be obtained by the process according to the invention have, for a thickness of between 0.5 and 15 mm, at mid-thickness at least two mechanical strength properties static selected from properties (i) to (iii) and at least one damage tolerance property selected from properties (iv) to (v).
  • the products spun according to the invention exhibit particularly advantageous characteristics.
  • the spun products have a thickness of between 0.5mm and 15mm, but according to the disclosure of products with a thickness greater than 15mm, up to 50mm or even 100mm or more can also have advantageous properties.
  • the thickness of extruded products is defined according to standard EN 2066: 2001: the cross section is divided into elementary rectangles of dimensions A and B; A being always the largest dimension of the elementary rectangle and B being able to be considered as the thickness of the elementary rectangle. The sole is the elementary rectangle with the largest dimension A.
  • the wrought products according to the invention are advantageously used to produce structural elements of an aircraft, in particular of airplanes.
  • Preferred aircraft structural elements are in particular a fuselage skin, a fuselage frame, a stiffener or a fuselage stringer or else a wing skin, a wing stiffener, a rib or a spar.
  • Alloys A and B both have a composition suitable for carrying out the process according to the invention.
  • the density of alloys A and B calculated in accordance with the procedure of The Aluminum Association described on pages 2-12 and 2-13 of “Aluminum Standards and Data” , is 2.55.
  • Table 1 Composition in% by weight and density of Al-Mg-Li alloys used Alloy Ag Li Yes Fe Cu Ti Mn Mg Zn Zr Na (ppm) Ca (ppm) Density AT 0.10 1.39 0.04 0.05 0.01 0.03 0.14 4.56 0.03 0.12 8 22 2.55 B 0.11 1.39 0.03 0.06 0.01 0.03 0.41 4.57 0.03 0.11 8 15 2.55
  • the mechanical properties, in particular the maximum stress tolerable by the product or tensile strength, Rm, and the elastic limit Rp0.2 (stress value for a plastic deformation of 0.2%) of the products in the T9 are globally significantly higher than those of products in T8 or T6 states. Furthermore, the mechanical properties, in particular Rp0.2, increase with the increase in controlled traction (T6 ⁇ T8-3% ⁇ T8-5% ⁇ T9-3% ⁇ T9-5%).
  • An Mn content of the Al-Mg-Li alloy of about 0.4% by weight significantly improves the mechanical strength (Rp0.2 and Rm), in particular in the L direction, of the alloy relative to that of an alloy having an Mn content of about 0.14% by weight (alloy A).
  • the yield strength (stress value for a plastic deformation of 0.2%, Rp0.2) of the products in the T9 state is significantly higher than those of the products in the T8 or T6 states. Moreover, Rp0.2 increases with the increase in the controlled tensile stress (T6 ⁇ T8-3% ⁇ T8-5% ⁇ T9-3% ⁇ T9-5%).
  • alloy B An Mn content of the Al-Mg-Li alloy of about 0.4% by weight significantly improves the mechanical strength of the alloy (Rp0.2 and Rm) compared to that of a alloy having an Mn content of about 0.14% by weight (alloy A).
  • the products according to the invention exhibit satisfactory toughness whatever the Mn content of the alloy.
  • the figure 2 illustrates the yield strength, Rp0.2, of the products of this example as a function of the toughness, K Q (all values of K Q are invalid due to the criterion P max / P Q ⁇ 1.10).
  • the figure 3 illustrates the yield strength, Rp0.2, of the products of this example as a function of the stress intensity factor corresponding to the maximum stress, K max .
  • T9 products present an excellent compromise between their static properties, in particular Rp0.2, and their toughness, K Q , or their stress intensity factor corresponding to the maximum force, K max .
  • Alloy B products have lower delamination than Alloy A products.

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Claims (12)

  1. Verfahren zur Herstellung eines Knetprodukts im Zustand T9 nach der Norm EN515 mit den aufeinanderfolgenden Schritten:
    (a) Gießen einer Rohform aus einer Aluminiumlegierung folgender Zusammensetzung, in Gewichtsprozent: Mg: 4,0 - 5,0 ; Li: 1,0 - 1,8 ; Zr: 0,05 - 0,15 ; Mn: ≤ 0,6; Ag: ≤ 0,5 ; Fe: ≤ 0,1 ; Ti: < 0,15 ; Si: ≤ 0,05; weitere Elemente jeweils ≤ 0,05 und zusammen ≤ 0,15 ; Rest Aluminium;
    (b) Wahlweises Homogenisieren der Rohform;
    (c) Warmumformen der Rohform, um ein warmumgeformtes Produkt zu erhalten;
    (d) Lösungsglühen des warmumgeformten Produkts bei einer Temperatur von 360°C bis 460°C, vorzugsweise 380-420°C, für 15 Minuten bis 8 Stunden;
    (e) Abschrecken des warmumgeformten Produkts;
    (f) wahlweises Richten oder Dressieren des umgeformten und abgeschreckten Produkts;
    (g) Warmauslagern des umgeformten und abgeschreckten Produkts;
    (h) Kontrolliertes Kaltumformen des warmausgelagerten umgeformten Produkts zur Erzielung einer bleibenden Kaltverformung unter Zugbelastung von 1 bis 10%, bevorzugt von 2 bis 6%, weiter bevorzugt von 3 bis 5%, um ein Knetprodukt im Zustand T9 nach der Norm EN515 zu erhalten.
  2. Verfahren nach Anspruch 1, wobei das Warmumformen aus Schritt c) ein Umformen der Rohform durch Strangpressen ist.
  3. Verfahren nach Anspruch 1 oder 2, wobei das Warmumformen aus Schritt c) bei einer Anfangstemperatur oberhalb von 400°C, vorzugsweise im Bereich von 420°C bis 450°C durchgeführt wird.
  4. Verfahren nach irgendeinem der Ansprüche 1 bis 3, wobei das Abschrecken aus Schritt (e) ein Presshärten ist.
  5. Verfahren nach irgendeinem der Ansprüche 1 bis 4, wobei das Abschrecken aus Schritt (e) mit Luft erfolgt.
  6. Verfahren nach irgendeinem der Ansprüche 1 bis 5, wobei die Warmauslagerungsbehandlung des warmumgeformten und abgeschreckten Produkts aus Schritt (g) durch Erhitzen in einer oder mehreren Stufen bei einer Temperatur unterhalb von 150°C, vorzugsweise bei einer Temperatur von 70°C bis 140°C, für 5 bis 100 Stunden durchgeführt wird.
  7. Verfahren nach Anspruch 1, wobei die Rohform aus Aluminiumlegierung einen Mn-Gehalt, in Gewichtsprozent, von 0,2 bis 0,6, bevorzugt von 0,35 bis 0,5 aufweist.
  8. Verfahren nach Anspruch 1, wobei die Rohform aus Aluminiumlegierung einen Zn-Gehalt, in Gewichtsprozent, kleiner 0,04%, bevorzugt kleiner oder gleich 0,03% aufweist.
  9. Verfahren nach Anspruch 1, wobei die Rohform aus Aluminiumlegierung einen Fe-Gehalt, in Gewichtsprozent, kleiner 0,08%, bevorzugt kleiner oder gleich 0,07%, weiter bevorzugt kleiner oder gleich 0,06% aufweist.
  10. Verfahren nach Anspruch 1, wobei die Rohform aus Aluminiumlegierung einen Li-Gehalt, in Gewichtsprozent, kleiner 1,6%, bevorzugt kleiner oder gleich 1,5%, weiter bevorzugt kleiner oder gleich 1,4% aufweist.
  11. Knetprodukt erhältlich nach irgendeinem der Verfahren der Ansprüche 1 bis 10, das in halber Dicke, bei einer Dicke zwischen 0,5 und 15 mm, wobei die Dicke der Strangpressprodukte nach der Norm EN 2066:2001 definiert ist, mindestens eine statische Festigkeitseigenschaft der Eigenschaften (i) bis (ii) und mindestens eine Schadenstoleranzeigenschaft der Eigenschaften (iii) bis (iv) aufweist:
    (i) eine Streckgrenze unter Zugbelastung Rp0,2 in L-Richtung ≥ 360 MPa und vorzugsweise Rp0,2 in L-Richtung ≥ 380 MPa und weiter bevorzugt Rp0,2 in L-Richtung ≥ 400 MPa;
    (ii) eine Streckgrenze unter Zugbelastung Rp0,2 in TL-Richtung ≥ 330 MPa und vorzugsweise Rp0,2 in TL-Richtung ≥ 340 MPa und weiter bevorzugt Rp0,2 in TL-Richtung ≥ 370 MPa;
    (iii) eine Bruchzähigkeit, gemessen nach ASTM E399 mit CT8-Proben mit Breite W = 16 mm und 8 mm Dicke, KQ in L-T-Richtung ≥ 20 MPa√m, vorzugsweise KQ in L-T-Richtung ≥ 22 MPa√m;
    (iv) einen der maximalen Kraft Pmax entsprechenden Spannungsintensitätsfaktor, gemessen nach ASTM E399 mit CT8-Proben mit Breite W = 16 mm und 8 mm Dicke, Kmax in L-T-Richtung ≥ 20 MPa√m, vorzugsweise Kmax in L-T-Richtung ≥ 25 MPa√m.
  12. Verwendung eines Kneterzeugnisses nach Anspruch 11 zur Herstellung eines Strukturbauteils eines Luftfahrzeugs, vorzugsweise einer Rumpfhaut, eines Rumpfrahmens, einer Rumpfversteifung, einer Rippe oder eines Holms.
EP15785160.1A 2014-09-29 2015-09-29 Verfahren zur herstellung eines knetproduktes aus einer aluminium-magnesium-lithium legierung, knetprodukt und vervendung des knetproduktes Active EP3201371B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1402186A FR3026411B1 (fr) 2014-09-29 2014-09-29 Procede de fabrication de produits en alliage aluminium magnesium lithium
FR1402187A FR3026410B1 (fr) 2014-09-29 2014-09-29 Produit corroye en alliage aluminium magnesium lithium
PCT/FR2015/052581 WO2016051061A1 (fr) 2014-09-29 2015-09-29 Procédé de fabrication de produits en alliage aluminium, magnésium, lithium

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MX2019001802A (es) 2016-08-26 2019-07-04 Shape Corp Proceso de modelacion en caliente y aparato para flexion transversal de una viga de aluminio extrudida para modelar en caliente un componente estructural del vehiculo.
FR3057476B1 (fr) * 2016-10-17 2018-10-12 Constellium Issoire Toles minces en alliage aluminium-magnesium-scandium pour applications aerospatiales
EP3529394A4 (de) 2016-10-24 2020-06-24 Shape Corp. Mehrstufiges formen von aluminiumlegierungen und thermisches behandlungsverfahren zur herstellung von fahrzeugkomponenten
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
EP3947761A4 (de) * 2019-04-05 2022-11-30 Arconic Technologies LLC Verfahren zur kaltumformung von aluminium-lithium-legierungen
MX2022007165A (es) * 2019-12-17 2022-07-12 Novelis Inc Supresion de agrietamiento por corrosion bajo tension en aleaciones de alto contenido de magnesio mediante la adicion de calcio.
CN112226656A (zh) * 2020-09-25 2021-01-15 西南铝业（集团）有限责任公司 一种Al-Mg-Mn-Er系铝合金挤压制品的生产工艺
CN112410691B (zh) * 2020-11-10 2021-12-24 中国航发北京航空材料研究院 一种铝锂合金材料退火工艺
CN114054531B (zh) * 2021-11-18 2024-09-20 西南铝业（集团）有限责任公司 一种高均匀性2196铝锂合金型材的挤压方法

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US20170218493A1 (en) 2017-08-03
CA2960942A1 (fr) 2016-04-07
BR112017006273B1 (pt) 2021-06-08
EP3201370B1 (de) 2020-04-15
WO2016051061A1 (fr) 2016-04-07
US20170292180A1 (en) 2017-10-12
BR112017006131A2 (pt) 2017-12-19
BR112017006273A2 (pt) 2017-12-12
EP3201371A1 (de) 2017-08-09
WO2016051060A1 (fr) 2016-04-07
CN107075623A (zh) 2017-08-18
EP3201370A1 (de) 2017-08-09
KR20170067810A (ko) 2017-06-16
CN106715735A (zh) 2017-05-24
JP2017532456A (ja) 2017-11-02
CA2960947A1 (fr) 2016-04-07

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