EP2984195B1 - Verfahren zur umformung von blechen aus al-cu-li-legierung für verbesserte formbarkeit und korrosionsbeständigkeit - Google Patents

Verfahren zur umformung von blechen aus al-cu-li-legierung für verbesserte formbarkeit und korrosionsbeständigkeit Download PDF

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EP2984195B1
EP2984195B1 EP14721432.4A EP14721432A EP2984195B1 EP 2984195 B1 EP2984195 B1 EP 2984195B1 EP 14721432 A EP14721432 A EP 14721432A EP 2984195 B1 EP2984195 B1 EP 2984195B1
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weight
sheet
mpa
heat treatment
minutes
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EP2984195A1 (de
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Christophe Sigli
Bernard Bes
Frank Eberl
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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
    • C22C21/18—Alloys based on aluminium with copper as the next major constituent with zinc
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D7/00—Casting ingots, e.g. from ferrous metals
    • B22D7/005—Casting ingots, e.g. from ferrous metals from non-ferrous metals
    • 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
    • C22C21/14—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
    • 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.
  • 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 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.
  • the patent EP 1,966,402 just like the demand WO2007080267 discloses a non-zirconium-containing alloy for fuselage sheets of substantially recrystallized structure comprising (in% by weight) (2.1-2.8) Cu, (1.1-1.7) Li, (0 , 2-0.6) Mg, (0.1-0.8) Ag, (0.2-0.6) Mn.
  • the products obtained in the T8 state are not suitable for substantial shaping, with in particular a ratio R m / / R p0.2 of less than 1.2 in the directions L and LT.
  • This document describes an income by heating at 140 to 170 ° C for 5 to 80 hours.
  • the patent EP 1,891,247 just like the demand WO2006131627 discloses an alloy for fuselage plates comprising (in% by weight) (3.0-3.4) Cu, (0.8-1.2) Li, (0.2-0.6) Mg, (0.2-0.5) Ag and at least one of Zr, Mn, Cr, Sc, Hf and Ti, wherein the Cu and Li contents are Cu + 5/3 Li ⁇ 5, 2.
  • the products obtained in the T8 state are not suitable for substantial shaping, in particular with a ratio R m / R p0.2 of less than 1.2 in the directions L and LT.
  • the patent EP 1045043 describes the process for manufacturing parts formed from AA2024 type alloy, and in particular of highly deformed parts, by the combination of an optimized chemical composition and particular manufacturing processes, making it possible to avoid as much as possible the dissolution in solution on formed sheet.
  • state "T3” or “T4" even in the annealed state (“O” state), subject them to a solution heat treatment followed by quenching, and then to form them on fresh quenching (state "W"), before finally subjecting them to natural or artificial aging, so as to obtain the required mechanical characteristics.
  • This variant is used in particular when the targeted shaping is too important to be carried out in a single operation from a state W, but can however be performed in two passes from a state O.
  • the plates in the state O being stable in time are easier to transform.
  • the manufacture of the sheet in the O state involves a final annealing of the raw rolling sheet, and therefore generally an additional manufacturing step, and also a dissolution and quenching of the product formed which is contrary the aim of simplification aimed at by the present invention.
  • the shaping of complex structural elements in the T8 state is limited to cases of small shaping because the elongation and the ratio R m / R p0,2 are too low in this state.
  • the properties that are optimal in terms of compromise of properties must be obtained once the part has been shaped, in particular as a fuselage element, since it is the shaped part which must in particular have good performances. in damage tolerance to avoid too frequent repair of fuselage elements. It is generally accepted that the large deformations after dissolution and quenching lead to an increase in the mechanical strength but a strong degradation of the tenacity.
  • the sheets that are delivered to the aircraft manufacturer can be stored for a sometimes significant period before being shaped and to incur an income. It is therefore necessary to prevent these sheets are sensitive to corrosion, in particular to simplify the storage conditions.
  • Another subject of the invention is a laminated product that can be obtained by the process according to the invention having a yield strength R p0.2 (L) and / or R p0.2 (LT) of between 75%. and 90%, preferably between 80 and 85% and preferably between 81% and 84% of the yield strength in the same direction of a sheet of the same composition in the T4 or T3 state having undergone the same controlled traction after quenching, at least one property selected from a ratio R m / R p0.2 (L) of at least 1.40 and preferably at least 1.45 and a ratio R m / R p0.2 (LT) at least 1.45 and preferably at least 1.50 and exhibits at least one corrosion resistance property chosen from a quotation according to ASTM G34 for sheets subjected to the conditions of the ASTM G85 A2 test of P and / or EA and a poorly developed intergranular corrosion for plates subject to the conditions of ASTM G110.
  • Yet another object of the invention is the use of a product obtained by a method according to the invention for the manufacture of a structural element for an airplane, in particular an aircraft fuselage skin.
  • Corrosion resistance tests are performed according to ASTM G34, ASTM G85 A2 and ASTM G110 standards.
  • solution, quenching and optionally leveling and / or pulling is carried out at least one short heat treatment with a duration and a temperature such that the sheet reaches a temperature between 145 ° C and 175 ° C and preferably between 150 ° C and 170 ° C for 0.1 to 45 minutes, preferably from 0.2 to 20 minutes, preferably for 0.5 to 5 minutes and preferably for 1 to 3 minutes, the heating rate being between 3 and 600 ° C / min.
  • the short heat treatment is advantageously carried out after natural aging for at least 24 hours after quenching and preferably at least 48 hours after quenching.
  • the elastic limit R p0,2 is significantly lower, that is to say at least 20 MPa or even at least 40 MPa in the directions L and LT, compared to that of the same sheet in a state T3 or T4.
  • the short heat treatment is not an income with which one would obtain a T8 state but a particular heat treatment which makes it possible to obtain a non-standardized state particularly suitable for shaping.
  • a sheet in the T8 state has a yield strength greater than that of the same sheet in a T3 or T4 state while after the short heat treatment according to the invention the elastic limit is instead more weak than that of a T3 or T4 state.
  • the present inventors have found that the mechanical properties obtained at the end of the short heat treatment are stable over time, which makes it possible to use the sheets in the state obtained at the end of the short heat treatment.
  • the sheet metal place in a state O or in a state W for the shaping.
  • the present inventors have found that, surprisingly, the high heating rate during treatment Short thermal and / or short duration of the short heat treatment make it possible to obtain an improved ability to shape while maintaining a corrosion resistance of the sheet resulting from the short heat treatment, in particular to the intergranular and exfoliating corrosion, equivalent to that of a sheet in the state T3 or T4.
  • the heating rate is between 10 and 400 ° C / min and preferably between 40 and 300 ° C / min.
  • the heating rate is typically the average slope of the sheet temperature as a function of time during heating between room temperature and 145 ° C.
  • the heating rate is preferably at least 80 ° C./min.
  • the cooling rate is between 1 and 1000 ° C./min, preferably between 10 and 800 ° C./min.
  • the cooling rate is typically the average slope of the sheet temperature as a function of time during cooling between 145 ° C and 70 ° C or even between 145 ° C and 30 ° C.
  • the cooling is carried out by spraying a liquid such as for example water or by immersion in such a liquid.
  • the cooling is carried out in air with optional forced convection, the cooling rate then preferably being between 1 and 400 ° C./min, preferably between 40 and 200 ° C. / min.
  • the short heat treatment is carried out in a continuous treatment furnace.
  • a continuous treatment furnace is an oven such that the sheet is supplied in the form of a coil which is continuously unwound for heat treatment in the furnace and then cooled and wound.
  • the present inventors have found that, surprisingly, not only the short heat treatment makes it possible to simplify the manufacturing process of the products by eliminating the shaping on state O or W, but moreover that the compromise between static mechanical resistance and tolerance to damage to the tempering state is at least the same or even improved by the method of the invention, compared to a method not comprising short heat treatment.
  • the compromise obtained between static mechanical strength and toughness is improved compared to the state of the art.
  • the advantage of the process according to the invention is obtained for products having a copper content of between 2.1 and 3.9% by weight.
  • the copper content is at least 2.8% or 3% by weight.
  • a maximum copper content of 3.7 or 3.4% by weight is preferred.
  • the lithium content is between 0.6% or 0.7% and 2.0% by weight.
  • the lithium content is at least 0.70% by weight.
  • a maximum lithium content of 1.4 or even 1.1% by weight is preferred.
  • the magnesium content is between 0.1% and 1.0% by weight.
  • the magnesium content is at least 0.2% or even 0.25% by weight.
  • the maximum magnesium content is 0.6% by weight.
  • the silver content is between 0% and 0.6% by weight.
  • the silver content is between 0.1 and 0.5% by weight and preferably between 0.15 and 0.4% 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 zinc content is between 0% and 1% by weight.
  • the zinc content is less than 0.6% by weight, preferably less than 0.40% by weight.
  • Zinc is generally an undesirable impurity, especially because of its contribution to the density of the alloy, in one embodiment of the invention the zinc content is less than 0.2% by weight and preferably less than 0. , 04% by weight.
  • zinc may be used alone or in combination with silver, a minimum zinc content of 0.2% by weight is then advantageous.
  • the alloy also contains at least one element that can contribute to controlling the grain size selected from Zr, Mn, Cr, Sc, Hf and Ti, the amount of the element, if selected, being 0.05 to 0.18% by weight for Zr, 0.1 to 0.6% by weight for Mn, 0.05 to 0.3% by weight for Cr, 0.02 to 0.2% by weight for Sc, O 0.5 to 0.5% by weight for Hf and 0.01 to 0.15% by weight for Ti.
  • zirconium is at least 0.11% by weight.
  • the manganese content is between 0.2 and 0.4% by weight and the zirconium content is less than 0.04% 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 other elements have a content of at most 0.05% by weight each and 0.15% by weight in total, it is inevitable impurities, the rest is aluminum.
  • the manufacturing method according to the invention comprises the steps of production, casting, rolling, dissolution, quenching, optionally planing and / or pulling and short heat treatment.
  • 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 can then optionally be homogenized so as to reach a temperature 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 rolling plate is then hot-rolled and optionally cold-rolled into a sheet.
  • the thickness of said sheet is between 0.5 and 10 mm, advantageously between 0.8 and 8 mm and preferably between 1 and 6 mm.
  • the product thus obtained is then put in solution typically by a heat treatment making it possible to reach a temperature of between 490 and 530 ° C. for 5 min to 8 h, and then typically quenched with water at ambient temperature or, preferably, with water. Cold water. It is optionally possible to carry out a planing and / or controlled traction of the sheet thus dissolved and quenched, with a cumulative deformation of at least 0.5% and less than 3%.
  • planing the deformation performed during planing is not always known precisely but it is estimated at about 0.5%.
  • the controlled traction is implemented with a permanent deformation of between 0.5 to 2.5% and preferably between 0.5 to 1.5%.
  • the short heat treatment is carried out directly after quenching without intermediate work-hardening, but advantageously after a natural aging of at least 24 hours.
  • This embodiment without intermediate work-hardening is advantageous in particular when the steps of dissolution, quenching and short heat treatment are carried out continuously in a continuous treatment furnace.
  • the present inventors have found that in the absence of intermediate hardening between quenching and short heat treatment defects such as lines Lüders appearing after shaping could be removed in some cases.
  • the sheet obtained by the process according to the invention advantageously has, typically for at least 50 days and even for at least 200 days, after a short heat treatment, a yield strength R p 0.2 (L) and / or R p0,2 (LT) of between 75% and 90%, preferably between 80 and 85% and preferably between 81% and 84% of the yield strength in the same direction of a sheet metal of the same composition in the T4 or T3 state having undergone the same controlled pull after quenching, at least one property chosen from a ratio R m / R p0.2 (L) of at least 1.40 and preferably at least 1 , 45 and a ratio R m / R p0.2 (LT) of at least 1.45 and preferably at least 1.50 and has at least one corrosion resistance property selected from a rating according to ASTM G34 for plates subject to the conditions of the P ASTM G85 A2 test and / or EA and poorly developed intergranular corrosion for
  • the sheet obtained by the process according to the invention typically exhibits for at least 50 days and even for at least 200 days after a short heat treatment, a combination of at least one property selected from R p0.2 (L) of at least 220 MPa and preferably at least 250 MPa, R p0.2 (LT) of at least 200 MPa and preferably at least 230 MPa , R m (L) of at least 340 MPa and preferably at least 380 MPa, R m (LT) of at least 320 MPa and preferably at least 360 MPa with a property selected from A% ( L) at least 14% and preferably at least 15%, A% (LT) at least 24% and preferably at least 26%, R m / R p0.2 (L) at least 1.40 and preferably at least at least 1.45, R m / R p0.2 (LT) at least 1.45 and preferably at least 1.50 and has at least one corrosion resistance property selected from a rating according to ASTM G34 for
  • the sheet obtained by the process according to the invention has a ratio R m / R p0,2 in the direction LT of at least 1.52. or 1.53.
  • the sheet obtained by the process according to the invention has a yield strength R p0.2 (L) of less than 290 MPa and of preferably less than 280 MPa and R p0.2 (LT) less than 270 MPa and / or a rupture strength R m (L) less than 410 MPa and preferably less than 400 MPa and R p0.2 (LT) less than 390 MPa.
  • the rating according to ASTM G34 for sheets subject to the conditions of the ASTM G85 A2 test is P or P-EA.
  • the intergranular corrosion for sheets subjected to the conditions of the ASTM G110 standard is not very developed if it corresponds to the images of the Figures 1 or 2 .
  • the sheet obtained by the process according to the invention has an intercrystalline corrosion resistance at least equal to that of a sheet of the same composition in the T3 or T4 state.
  • the sheet can be stored without particular difficulties thanks to its resistance to intercrystalline corrosion.
  • the sheet resulting from the short heat treatment is ready for additional cold deformation, in particular a 3-dimensional forming operation.
  • An advantage of the invention is that this additional deformation can locally or generally reach values of 6 to 8% or even up to 10%.
  • a minimum cumulative deformation of 2% between said additional deformation and the cumulative deformation by planing and / or controlled tension optionally performed before the short heat treatment is advantageous.
  • the additional cold deformation is locally or generally at least 1%, preferably at least 4% and preferably at least 6%.
  • an income is produced in which said sheet thus shaped reaches a temperature of between 130 and 170 ° C., advantageously between 145 and 165 ° C. and preferably between 150 and 160 ° C. for 5 to 100 hours, and preferably at 70h.
  • the income can be achieved in one or more levels.
  • the cold deformation is performed by one or more forming processes such as stretching, stretch-forming, stamping, spinning or folding. In an advantageous embodiment, it is a shaping in the three dimensions of the space to obtain a piece of complex shape, preferably by stretch-forming.
  • the product obtained after the short heat treatment can be shaped as a product in a state O or a product in a state W.
  • the compromise between the static mechanical properties and the damage-tolerance properties obtained at the end of the income is advantageous compared to that obtained for a similar treatment that does not include short heat treatment.
  • the sheets were then trimmed in a controlled manner. Controlled traction was achieved with a permanent elongation of 2%. Natural aging was at least 24 hours after quenching.
  • the sheets were then subjected to a short heat treatment, the conditions of which are given in Table 2.
  • the highest heating rates, representative of the heating rates obtained in a continuous treatment furnace, were obtained by immersion in an immersion bath. oil while the lowest heating rates were obtained by controlled air treatment, representative of industrial conditions in a static furnace.
  • the cooling rate was of the order of 60 ° C./min for all the tests.
  • the corrosion resistance properties of the sheets were evaluated under the conditions of standardized intergranular corrosion tests (ASTM G110) and exfoliation corrosion tests (MASTMAASIS dry bottom ASTM G85-A2).
  • ASTM G110 test immersion time is 6 hours and the test duration of the MASTMAASIS test is 750 hours.
  • the characterizations were performed on the surface ("skin") and after machining one-tenth of the thickness ("T / 10").
  • the results of intergranular corrosion tests according to ASTM G110 are shown in Table 4. Micrographic sections representative of poorly developed intergranular corrosion and pitting are given on the Figures 1 (sample S) and 2 (sample H2). The observations were made under an optical microscope at magnifications of X200.
  • a micrographic section representative of a developed intergranular corrosion and pitting is given on the Figure 3 (sample A30).
  • a micrographic section representative of a developed intergranular corrosion is given on the Figure 4 (sample A120).
  • Table 4 Results of intergranular corrosion tests according to ASTM G110 Sample Surface tested Skin T / 10 S Less developed CI + sting Less developed CI + sting H1 Less developed CI + sting Less developed CI + sting H2 Less developed CI + sting Less developed CI + sting H4 Less developed CI + sting Less developed CI + sting H8 Less developed CI + sting Less developed CI + sting H16 Less developed CI + sting Less developed CI + sting H30 Less developed CI + sting Less developed CI + sting A30 CI developed + sting CI developed + sting A60 CI developed CI developed A120 CI developed CI developed A240 CI developed CI developed CI: intergranular corrosion
  • Sample S is a sample in the T3 state. It does not have mechanical properties to consider its shaping for the highest deformations.
  • Samples A30, A60, A120, A240 have mechanical properties which make it possible to envisage shaping for the highest deformations but exhibit a resistance to corrosion requiring particular precautions during storage.
  • Samples H1, H2, H4, H8, H16 and H30 simultaneously have mechanical properties to consider its shaping for the highest deformations and corrosion resistance to consider storage without special precautions.
  • Sample H1 however, has slightly less mechanical properties favorable, especially in terms of lengthening in the LT direction.
  • Sample H30 has slightly less favorable properties, particularly in terms of corrosion resistance.

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Claims (12)

  1. Verfahren zur Herstellung eines Walzerzeugnisses auf Basis einer Aluminiumlegierung insbesondere für die Luftfahrtindustrie, wobei nacheinander
    a) ein Flüssigmetallbad auf Basis von Aluminium hergestellt wird, enthaltend 2,1 bis 3,9 Gew.-% Cu, 0,6 bis 2,0 Gew.-% Li, 0,1 bis 1,0 Gew.-% Mg, 0 bis 0,6 Gew.-% Ag, 0 bis 1 Gew.-% Zn, höchstens 0,20 Gew.-% der Summe von Fe und Si, mindestens ein Element gewählt unter Zr, Mn, Cr, Sc, Hf und Ti, wobei die Menge dieses Elementes, falls gewählt, 0,05 bis 0,18 Gew.-% für Zr, 0,1 bis 0,6 Gew.-% für Mn, 0,05 bis 0,3 Gew.-% für Cr, 0,02 bis 0,2 Gew.-% für Sc, 0,05 bis 0,5 Gew.-% für Hf und 0,01 bis 0,15 Gew.-% für Ti beträgt, weitere Elemente jeweils ≤ 0,05 und insgesamt ≤ 0,15, Rest Aluminium;
    b) aus dem Flüssigmetallbad ein Walzbarren gegossen wird;
    c) der Walzbarren wahlweise homogenisiert wird;
    d) der Walzbarren warm- und wahlweise kaltgewalzt wird, um ein Blech mit einer Dicke zwischen 0,5 und 10 mm zu erhalten;
    e) das Blech lösungsgeglüht und abgeschreckt wird;
    f) das Blech wahlweise gerichtet und/oder kontrolliert gereckt wird, und zwar mit einer kumulativen Verformung von mindestens 0,5% und unterhalb 3%;
    g) eine kurze Wärmebehandlung durchgeführt wird, bei der das Blech eine Temperatur zwischen 145°C und 175°C und vorzugsweise zwischen 150°C und 170°C während 0,1 bis 45 Minuten und vorzugsweise während 0,5 bis 5 Minuten erreicht, wobei die Aufheizgeschwindigkeit im Bereich zwischen 3 und 600°C/min liegt, wobei die kurze Wärmebehandlung so durchgeführt wird, dass sich eine Äquivalentzeit bei 150°C von 0,5 bis 35 Minuten und vorzugsweise von 1 bis 20 Minuten ergibt, wobei die Äquivalentzeit t i bei 150°C definiert ist durch die Formel: t i = ∫ exp − 16400 / T dt exp − 16400 / T ref
    Figure imgb0004
     worin T (in Kelvin) die jeweilige Behandlungstemperatur des Metalls ist, die sich mit der Zeit t (in Minuten) verändert, und Tref eine auf 423 K festgelegte Referenztemperatur ist, ti in Minuten ausgedrückt ist, die Konstante Q/R = 16400 K aus der Aktivierungsenergie für die Diffusion von Cu abgeleitet ist, für die der Wert Q = 136100 J/mol verwendet wurde, und wobei die Abkühlgeschwindigkeit zwischen 1 und 1000°C/min beträgt.
  2. Verfahren nach Anspruch 1, wobei im Schritt g) der kurzen Wärmebehandlung die Abkühlgeschwindigkeit zwischen 10 und 800°C/min beträgt.
  3. Verfahren nach irgendeinem der Ansprüche 1 bis 2, wobei die kurze Wärmebehandlung unmittelbar nach dem Abschrecken ohne Zwischenverfestigung durchgeführt wird.
  4. Verfahren nach irgendeinem der Ansprüche 1 bis 3, wobei der Kupfergehalt mindestens 2,8 und höchstens 3,4 Gew.-% beträgt.
  5. Verfahren nach irgendeinem der Ansprüche 1 bis 4, wobei der Lithiumgehalt mindestens 0,70 und höchstens 1,1 Gew.-% beträgt.
  6. Verfahren nach irgendeinem der Ansprüche 1 bis 5, wobei der Magnesiumgehalt mindestens 0,2 und höchstens 0,6 Gew.-% beträgt.
  7. Verfahren nach irgendeinem der Ansprüche 1 bis 6, wobei die Legierung zwischen 0,08 und 0,15 Gew.-% Zirconium, zwischen 0,01 und 0,10 Gew.-% Titan enthält, und wobei der Gehalt an Mn, Cr, Sc und Hf höchstens 0,05 Gew.-% beträgt.
  8. Verfahren nach irgendeinem der Ansprüche 1 bis 7, wobei nach dem Schritt g)
    h) eine zusätzliche Kaltverformung des Blechs so durchgeführt wird, dass die zusätzliche Verformung weniger als 10 % beträgt,
    i) eine Auslagerung durchgeführt wird, bei der das Blech eine Temperatur zwischen 130 und 170°C, vorteilhaft zwischen 145 und 165°C und bevorzugt zwischen 150 und 160°C während 5 bis 100 Stunden und vorzugsweise 10 bis 70 Stunden erreicht.
  9. Walzerzeugnis erhältlich durch das Verfahren nach irgendeinem der Ansprüche 1 bis 7, mit einer Dehngrenze Rp0,2(L) und/oder Rp0,2(LT) zwischen 75 und 90%, vorzugsweise zwischen 80 und 85% und besser noch zwischen 81 und 84% der Dehngrenze in gleicher Richtung eines Blechs gleicher Zusammensetzung im Zustand T4 oder T3, das nach dem Abschrecken in gleicher Weise kontrolliert gereckt wurde, mit mindestens einer Eigenschaft ausgewählt aus einem Verhältnis Rm/Rp0,2(L) von mindestens 1,40 und vorzugsweise mindestens 1,45 und einem Verhältnis Rm/Rp0,2(LT) von mindestens 1,45 und vorzugsweise mindestens 1,50, und mit mindestens einer Korrosionseigenschaft ausgewählt aus einer Einstufung P und/oder EA nach dem ASTM G34-Standard für Bleche, die den Bedingungen der Prüfung gemäß ASTM G85 A2 unterliegen, und einer schwach ausgebildeten interkristallinen Korrosion für Bleche, die den Bedingungen der Norm ASTM G110 unterliegen.
  10. Walzerzeugnis nach Anspruch 9, aufweisend eine Kombination von wenigstens einer Eigenschaft, ausgewählt aus Rp0,2(L) von mindestens 220 MPa und vorzugsweise mindestens 250 MPa, Rp0,2(LT) von mindestens 200 MPa und vorzugsweise mindestens 230 MPa, Rm(L) von mindestens 340 MPa und vorzugsweise mindestens 380 MPa, Rm(LT) von mindestens 320 MPa und vorzugsweise mindestens 360 MPa, mit einer Eigenschaft, ausgewählt aus A%(L) von mindestens 14% und vorzugsweise mindestens 15%, A%(LT) von mindestens 24% und vorzugsweise mindestens 26%, Rm/Rp0,2(L) von mindestens 1,40 und vorzugsweise mindestens 1,45, Rm/Rp0,2(LT) von mindestens 1,45 und vorzugsweise mindestens 1,50.
  11. Walzerzeugnis nach Anspruch 9 oder Anspruch 10, welches so beschaffen ist, dass es sich bei der Einstufung nach dem ASTM G34-Standard für Bleche, die den Bedingungen der ASTM G85 A2-Prüfung unterliegen, um P oder P-EA handelt.
  12. Verwendung eines durch das Verfahren nach Anspruch 8 erhaltenen Erzeugnisses für die Herstellung eines Strukturelementes für Flugzeuge, insbesondere einer Flugzeugrumpfhaut.
EP14721432.4A 2013-04-12 2014-04-07 Verfahren zur umformung von blechen aus al-cu-li-legierung für verbesserte formbarkeit und korrosionsbeständigkeit Active EP2984195B1 (de)

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FR1300870A FR3004464B1 (fr) 2013-04-12 2013-04-12 Procede de transformation de toles en alliage al-cu-li ameliorant la formabilite et la resistance a la corrosion
PCT/FR2014/000076 WO2014167191A1 (fr) 2013-04-12 2014-04-07 Procédé de transformation de tôles en alliage al-cu-li améliorant la formabilité et la résistance à la corrosion

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US10400313B2 (en) 2019-09-03
CA2908454C (fr) 2021-05-18
CA2908454A1 (fr) 2014-10-16
WO2014167191A1 (fr) 2014-10-16
US20160304995A1 (en) 2016-10-20
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