EP2766503B2 - Verbessertes verfahren zum bearbeiten von metallblechen aus einer al-cu-li-legierung - Google Patents

Verbessertes verfahren zum bearbeiten von metallblechen aus einer al-cu-li-legierung Download PDF

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EP2766503B2
EP2766503B2 EP12788613.3A EP12788613A EP2766503B2 EP 2766503 B2 EP2766503 B2 EP 2766503B2 EP 12788613 A EP12788613 A EP 12788613A EP 2766503 B2 EP2766503 B2 EP 2766503B2
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weight
mpa
heat treatment
sheet
short heat
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EP2766503B1 (de
EP2766503A1 (de
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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
    • 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
    • C22F1/002—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
    • 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 products made of aluminum-copper-lithium alloys, more particularly, to such products, their methods of manufacture and use, intended in particular for aeronautical and aerospace construction.
  • Lithium-containing aluminum alloys are very interesting in this respect, because lithium can reduce the density of aluminum by 3% and increase the modulus of elasticity by 6% for each percent by weight of lithium added.
  • their performance relative to other use properties must reach that of commonly used alloys, particularly in terms of the trade-off between static strength properties (yield strength, fracture toughness) and damage tolerance properties (toughness, resistance to fatigue crack propagation), which are generally contradictory. Improving the trade-off between strength and damage tolerance is a constant pursuit.
  • Al-Cu-Li alloy sheets are used in particular to manufacture aircraft fuselage elements or rocket elements that have a complex overall 3-dimensional shape.
  • aircraft manufacturers seek to minimize the number of sheet forming steps, and to use sheets that can be manufactured inexpensively using short processing ranges, i.e. comprising as few individual steps as possible.
  • a current practice of aircraft manufacturers generally consists of supplying hot-rolled or cold-rolled sheets according to the required thickness, in the as-manufactured state (state “F” according to the standard EN 515) in the quenched matured state (state “T3” or “T4"), or in the annealed state (state “O"), to subject them to a solution heat treatment followed by quenching, then to shape them on fresh quenching (state "W”), before finally subjecting them to natural or artificial ageing, so as to obtain the required mechanical characteristics.
  • the sheets after solution treatment and quenching, the sheets are in a state characterized by good formability, but this state is unstable (state "W"), and the shaping must take place on fresh quenching, that is to say within a short time after quenching, of the order of a few tens of minutes to a few hours. If this is not possible for production management reasons, the sheet must be stored in a cold room at a sufficiently low temperature and for a sufficiently short period of time so as to avoid natural maturation. In some cases, it is found that for too short durations after solution treatment, Lüders lines appear after forming, which imposes an additional constraint with a minimum waiting time.
  • this solution heat treatment requires large furnaces, which makes the operation inconvenient, even compared to the same operation carried out on flat sheet metal.
  • the possible need for a cold room adds to the costs and disadvantages of the state of the art.
  • the sheet metal can be deformed and pose problems related to this deformation, for example when it comes to positioning it in the jaws of the drawing-forming tool.
  • this operation may have to be repeated if the material does not have, in its metallurgical state, sufficient formability to achieve the desired shape in a single operation.
  • the patent US 5,455,003 describes a process for manufacturing Al-Cu-Li alloys which exhibit improved mechanical strength and toughness at cryogenic temperatures, in particular through appropriate work hardening and tempering.
  • the patent US 7,229,509 describes an alloy comprising (wt%): (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 describes alloys comprising (in wt %), 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 grain structure. This application also describes a method of manufacturing extruded products.
  • the patent EP 1,966,402 describes an alloy not containing zirconium intended for fuselage sheets of essentially 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 forming, with in particular a ratio R m/ / R p0.2 less than 1.2 in the L and LT directions.
  • the patent EP 1,891,247 describes an alloy for fuselage sheets comprising (in wt%) (3.0-3.4) Cu, (0.8-1.2) Li, (0.2-0.6) Mg, (0.2-0.5) Ag and at least one element from Zr, Mn, Cr, Sc, Hf and Ti, in which the Cu and Li contents meet the condition Cu + 5/3 Li ⁇ 5.2.
  • the products obtained in the T8 state are not suitable for forming, with in particular a ratio R m/ / R p0.2 less than 1.2 in the L and LT directions. It has also been found that the overall energy at fracture measured by Kahn test which is related to toughness decreases with deformation and more abruptly for a deformation of 6%, which poses the problem of obtaining high toughness whatever the local deformation rate during forming.
  • the patent EP 1045043 describes the manufacturing process for formed parts in AA2024 type alloy, and in particular for highly deformed parts, by combining an optimized chemical composition and specific manufacturing processes, making it possible to avoid as much as possible solution treatment on formed sheet metal.
  • WO2006/131627 discloses a method of manufacturing an aluminum alloy-based sheet for the aerospace industry and suitable for use in fuselage applications, the sheet having superior toughness and mechanical strength high, in which: a) a liquid metal bath is prepared comprising 2.7 to 3.4% by weight of Cu, 0.8 to 1.4% by weight of Li, 0.1 to 0.8% by weight of weight of Ag, 0.2 to 0.6% by weight of Mg and at least one element selected from Zr, Mn, Cr, Sc, Hf and Ti, the amount of said element, if selected, being 0 ,05 to 0.13 wt% for Zr, 0.05 to 0.8 wt% for Mn, 0.05 to 0.3 wt% for Cr and for Sc, 0.05 to 0.5 wt% weight for Hf and 0.05 to 0.15 wt.% for Ti, the remainder being aluminium and unavoidable impurities, with the additional condition that the amount of Cu and Li is such that Cu (wt.%) ) + 5/3 Li (% by weight) ⁇ 5.2;
  • a second subject of the invention is a rolled product obtainable by a process according to the invention, having between 0 and 50 days after short heat treatment, a combination of at least one property chosen from R p,2 (L) of 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 380 MPa, R m (LT) of at least 320 MPa and preferably at least 360 MPa with a property chosen from A% (L) 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 1.45, R m /R p0,2 (LT) at least 1.45 and preferably at least 1.50.
  • Another subject of the invention is a product capable of being obtained by a process according to the invention, having a tensile yield strength R p0.2 (L) at least substantially equal and a toughness K R greater, preferably by at least 5%, than those obtained by a similar process not comprising short heat treatment.
  • Yet another object of the invention is the use of a product capable of being obtained by a process according to the invention for the manufacture of an aircraft fuselage skin.
  • the plane stress toughness is determined by a stress intensity factor versus crack extension plot, known as the R-curve, according to ASTM E 561.
  • the critical stress intensity factor K C in other words the stress intensity factor that makes the crack unstable, is calculated from the R-curve.
  • the stress intensity factor K CO is also calculated by assigning the initial crack length to the critical load at the beginning of the monotonic loading. Both values are calculated for a specimen of the required shape.
  • K app is the K CO factor corresponding to the specimen that was used to perform the R-curve test.
  • K eff is the K C factor corresponding to the specimen that was used to perform the R-curve test.
  • ⁇ a eff(max) is the crack extension of the last valid point on the R-curve.
  • a "structural element” or “structural element” of a mechanical construction is 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 carried out.
  • These are typically elements whose failure is likely to endanger the safety of said construction, its users, its users or others.
  • these structural elements include in particular the elements that make up the fuselage (such as the fuselage skin), the stringers, the bulkheads, the circumferential frames, the wings (such as the upper or lower wing skin, the stringers, the ribs and spars) and the empennage composed in particular of horizontal and vertical stabilisers, as well as the floor beams, the seat tracks and the doors.
  • At least one short heat treatment is carried out with a duration and temperature such that the sheet reaches a temperature of between 130 and 170°C and preferably between 150 and 160°C for 0.1 to 13 hours, preferably 0.5 to 9 hours and more preferably 1 to 5 hours.
  • the yield strength R p0.2 decreases by at least 20 MPa or even more, while the elongation A% is increased, i.e. it is multiplied by a factor of at least 1.1, or even at least 1.2 or even at least 1.3 compared to the state obtained without short heat treatment, typically T3 or T4.
  • the short heat treatment is therefore not an income with which a T8 state would be obtained but a particular heat treatment which makes it possible to obtain a non-standardized state which is particularly suitable to the shaping.
  • a sheet in the T8 state has a higher elastic limit than that of a T3 or T4 state whereas after the short heat treatment according to the invention the elastic limit is on the contrary lower than that of a T3 or T4 state.
  • the short heat treatment is carried out so as to obtain a time equivalent to 150 °C of 0.5 h to 6 h and preferably of 1 h to 4 h and more preferably of 1 h to 3 h
  • T (in Kelvin) is the instantaneous metal processing temperature, which changes with time t (in hours)
  • T ref is a reference temperature set at 423 K.
  • t i is expressed in hours
  • the present inventors have found that the mechanical properties obtained after the short heat treatment are stable over time, which makes it possible to use the sheets in the state obtained after the short heat treatment instead of sheets in the O or W state for forming.
  • the present inventors have found that, surprisingly, not only does the short heat treatment make it possible to simplify the manufacturing process of the products by eliminating the shaping in the O or W state, but also that the compromise between static mechanical strength and damage tolerance is at least identical or even improved thanks to the process of the invention, in the tempered state compared to a process not comprising a 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 3.5% by weight is preferred.
  • the lithium content is between 0.7% or 0.8% and 2.0% by weight.
  • the lithium content is at least 0.85% by weight.
  • a maximum lithium content of 1.6 or even 1.2% by weight is preferred.
  • the magnesium content is between 0.1% and 1.0% by weight. Preferably, the magnesium content is at least 0.2% or even 0.25% by weight. In one embodiment of the invention, the maximum magnesium content is 0.6% by weight.
  • the silver content is between 0% and 0.6% by weight. In an advantageous embodiment of the invention, 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.
  • Zinc is generally an undesirable impurity, particularly due to its contribution to the density of the alloy, however in some cases zinc may be used alone or in combination with silver.
  • the zinc content is less than 0.40 % by weight, preferably less than 0.2% by weight In one embodiment of the invention the zinc content is less than 0.04% by weight.
  • the zirconium content is at least equal to 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 improving the compromise between mechanical strength and damage tolerance.
  • the other elements have a content of at most 0.05% by weight each and 0.15% by weight in total, these are unavoidable impurities, the remainder is aluminum.
  • the manufacturing method according to the invention comprises the steps of preparation, casting, homogenization, rolling, solution treatment, quenching, planing and/or traction and short heat treatment.
  • a bath of liquid metal is prepared so as to obtain an aluminum alloy of composition according to the invention.
  • the bath of liquid metal is then cast in the form of a rolling plate.
  • the rolling plate is then homogenized so as to reach a temperature of between 450°C and 550° and preferably between 480°C and 530°C for a period of between 5 and 60 hours.
  • the homogenization treatment can be carried out in one or more stages.
  • the rolling plate is then hot rolled and optionally cold rolled into a sheet.
  • the thickness of said sheet is between 0.5 and 15 mm and preferably between 1 and 8 mm.
  • the product thus obtained is then put into solution typically by a heat treatment allowing a temperature of between 490 and 530°C to be reached for 15 min to 8 h, then quenched typically with water at room temperature or preferably cold water.
  • a planishing and/or traction is carried out in a controlled manner on said sheet metal with a cumulative deformation of at least 0.5% and less than 3%.
  • the deformation made during the planishing is not always known precisely but it is estimated at approximately 0.5%.
  • the traction controlled is implemented with a permanent deformation of between 0.5 to 2.5% and preferably between 0.5 to 1.5%. The combination of controlled traction with a preferred permanent deformation and a short heat treatment makes it possible to achieve optimum results in terms of formability and mechanical properties, especially when additional forming and tempering are carried out.
  • the sheet obtained by the method according to the invention preferably has, between 0 and 50 days and preferably between 0 and 200 days after short heat treatment, a combination of at least one property chosen from R p0.2 (L) of 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 380 MPa, R m (LT) of at least 320 MPa and preferably at least 360 MPa with a property chosen from A% (L) 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 1.45, R m /R p0.2 (LT) at least 1.45 and preferably at least 1.50. minus 1.50.
  • the sheet obtained by the process according to the invention has a ratio R m /R p0.2 in the LT direction of at least 1.52 or 1.53.
  • the sheet obtained by the process according to the invention has an elastic limit R p0.2 (L) of less than 290 MPa and preferably less than 280 MPa and R p0.2 (LT) of less than 270 MPa and preferably less than 260 MPa.
  • the sheet is therefore ready for additional cold deformation, in particular a 3-dimensional shaping 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 planishing and/or controlled traction carried out 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 carried out in which the said sheet reaches a temperature between 130 and 170°C and preferably between 150 and 160°C for 5 to 100 hours and preferably from 10 to 70 hours.
  • the income can be carried out in one or more stages.
  • the cold deformation is carried out by one or more shaping processes such as drawing, drawing-forming, stamping, flow forming or bending. In an advantageous embodiment, this involves shaping in the three dimensions of space to obtain a part of complex shape, preferably by drawing-forming.
  • the product obtained at the end of the short heat treatment can be shaped as a product in state O or a product in state W.
  • the short heat treatment can be carried out at the sheet metal manufacturer and the shaping at the aeronautical structure manufacturer, directly on the delivered product.
  • the method according to the invention makes it possible to carry out the 3-dimensional shaping of a sheet metal at the end of the short heat treatment without the sheet metal being in a T8 state, an O state or a W state before this 3-dimensional shaping.
  • a rolling plate made of AA2198 alloy was homogenized and then hot rolled to a thickness of 4 mm.
  • the sheets thus obtained were solution-treated for 30 min at 505 °C and then quenched in water.
  • the sheets were then pulled in a controlled manner.
  • the controlled traction was achieved with a permanent elongation of 2.2%.
  • the sheets then underwent a short heat treatment of 2 hours at 150°C.
  • a rolling plate made of AA2198 alloy was homogenized and then hot rolled to a thickness of 4 mm.
  • the sheets thus obtained were solution-treated for 30 min at 505 °C and then quenched in water.
  • the sheets then underwent a short heat treatment of 2 hours at 150°C.
  • the sheets thus obtained then underwent additional cold deformation by controlled traction with a permanent elongation of 2.5%, 4% or 8%.
  • the sheets did not present any prohibitive Lüders lines after deformation.
  • the sheets were finally tempered for 12 hours at 155 °C to obtain a T8 state.
  • a sheet underwent a controlled 2% traction directly after quenching followed by tempering for 14 hours at 155 °C to the T8 state, without any intermediate short heat treatment.
  • the R curves were measured in the TL direction according to the E561-05 standard on CCT760 test specimens, which had a width of 760 mm.
  • the obtained R curves are shown in the figure 1 .
  • the sheets were then planed and tensioned in a controlled manner.
  • the controlled tension was carried out with a permanent elongation of 1%.
  • the sheets were aged sufficiently to reach a stabilized T3 state.
  • the sheets were then subjected to a short heat treatment at 145 °C, 150 °C or 155 °C.
  • the equivalent time at 150 °C was calculated taking into account a temperature rise rate of 20 °C/h.
  • the static mechanical characteristics of the sheets were characterized after the short heat treatment in the TL direction.
  • the R curves were measured according to E561-05 on CCT760 test specimens, which had a width of 760 mm in the T-L direction and in the L-T direction.

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Claims (16)

  1. Verfahren zur Herstellung eines Walzerzeugnisses aus Aluminiumlegierung insbesondere für die Luftfahrtindustrie, bei dem nacheinander
    a) ein Flüssigmetallbad auf Aluminiumbasis hergestellt wird, enthaltend 2,1 bis 3,9 Gew.-% Cu, 0,7 bis 2,0 Gew.-% Li, 0,1 bis 1,0 Gew.-% Mg, 0 bis 0,6 Gew.-% Ag, 0 bis 1 Gew.-% Zn, maximal 0,20 Gew.-% Fe + Si, wenigstens ein Element ausgewählt unter Zr, Mn, Cr, Sc, Hf und Ti, wobei die Menge des Elements, falls es gewählt wird, 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 maximal 0,05 Gew.-% und insgesamt 0,15 Gew.-%, Rest Aluminium;
    b) aus dem Flüssigmetallbad ein Walzbarren gegossen wird;
    c) der Walzbarren homogenisiert wird um eine Temperatur von 450°C bis 550°C während einer Zeitspanne von 5 bis 60 Stunden zu erreichen;
    d) der Walzbarren zu einem Blech warm- und wahlweise kaltgewalzt wird;
    e) das Blech lösungsgeglüht und abgeschreckt wird;
    f) das Blech gerichtet und/oder kontrolliert gezogen wird, mit einer Gesamtverformung von mindestens 0,5 % und weniger als 3,0 %,
    g) eine kurze Wärmebehandlung durchgeführt wird, bei der das Blech eine Temperatur zwischen 130 und 170°C und vorzugsweise zwischen 150 und 160°C während 0,1 bis 13 Stunden und vorzugsweise 1 bis 5 Stunden erreicht, wobei die kurze Wärmebehandlung eine Erniedrigung der Streckgrenze Rp0,2 um mindestens 20 MPa und eine Erhöhung der Dehnung A% induziert, so dass A% mindestens um einen Faktor 1,1 höher ist als in dem ohne kurze Wärmebehandlung erhaltenen Zustand.
  2. Verfahren nach Anspruch 1, bei dem die kurze Wärmebehandlung so durchgeführt wird, dass eine Äquivalentzeit bei 150°C von 0,5 bis 6 Stunden und vorzugsweise 1 Stunde bis 4 Stunden erhalten wird, wobei die Äquivalentzeit t i bei 150°C definiert ist durch die Formel t i = ∫ exp − 16400 / T dt exp − 16400 / T ref
    Figure imgb0011
     worin T (in Kelvin) die momentane, mit der Zeit t (in Stunden) sich ändernde Metallbehandlungstemperatur ist und Tref eine auf 423 K festgelegte Referenztemperatur ist, t i in Stunden ausgedrückt ist, die Konstante Q/R = 16400 K von der Aktivierungsenergie für die Diffusion von Cu abgeleitet ist, für die der Wert Q=136000J/mol verwendet wurde.
  3. Verfahren nach Anspruch 1 oder Anspruch 2, bei dem die Dicke des Blechs zwischen 0,5 und 15 mm und vorzugsweise zwischen 1 und 8 m beträgt.
  4. Verfahren nach irgendeinem der Ansprüche 1 bis 3, bei dem im Schritt f) ein kontrolliertes Ziehen mit einer bleibenden Verformung von 0,5 bis 1,5 % durchgeführt wird.
  5. Verfahren nach irgendeinem der Ansprüche 1 bis 4, bei dem der Kupfergehalt mindestens 3 und höchstens 3,5 Gew.-% beträgt.
  6. Verfahren nach irgendeinem der Ansprüche 1 bis 5, bei dem der Lithiumgehalt mindestens 0,85 und höchstens 1,2 Gew.-% beträgt.
  7. Verfahren nach irgendeinem der Ansprüche 1 bis 6, bei dem der Magnesiumgehalt mindestens 0,2 und höchstens 0,6 Gew.-% beträgt.
  8. Verfahren nach irgendeinem der Ansprüche 1 bis 7, bei dem der Silbergehalt zwischen 0,1 und 0,5 Gew.-% und vorzugsweise zwischen 0,15 und 0,4 Gew.-% beträgt und/oder der Zinkgehalt kleiner als 0,4 Gew.-% und vorzugsweise kleiner als 0,2 Gew.-% ist.
  9. Verfahren nach irgendeinem der Ansprüche 1 bis 8, bei dem die Legierung zwischen 0,08 und 0,15 Gew.-% Zirconium, zwischen 0,01 und 0,10 Gew.-% Titan enthält und bei dem der Gehalt an Mn, Cr, Sc und Hf höchstens 0,05 Gew.-% beträgt.
  10. Verfahren nach irgendeinem der Ansprüche 1 bis 9, bei dem nach dem Schritt g)
    h) eine weitere Kaltverformung des Blechs so durchgeführt wird, dass diese weitere Verformung weniger als 10 % beträgt,
    i) eine Auslagerungsbehandlung durchgeführt wird, bei der das Blech eine Temperatur zwischen 130 und 170°C und vorzugsweise zwischen 150 und 160°C während 5 bis 100 Stunden und vorzugsweise 10 bis 70 Stunden erreicht.
  11. Verfahren nach Anspruch 10, bei dem die weitere Kaltverformung örtlich oder allgemein mindestens 1 %, vorzugsweise mindestens 4 % und bevorzugt mindestens 6 % beträgt.
  12. Verfahren nach Anspruch 10 oder Anspruch 11, bei dem die Kaltverformung mittels einem oder mehreren Formgebungsverfahren durchgeführt wird, wie z.B. Ziehen, Ziehformen, Tiefziehen, Drückwalzen oder Biegen.
  13. Walzerzeugnis, erhältlich durch das Verfahren nach irgendeinem der Ansprüche 1 bis 9, das 0 bis 5 Tage nach der kurzen Wärmebehandlung eine Eigenschaftskombination aufweist, bestehend aus mindestens einer Eigenschaft ausgewählt unter Rp0,2(L) von mindestens 250 MPa, Rp0,2(LT) von mindestens 200 MPa und vorzugsweise mindestens 230 MPa, Rm(L) von mindestens 380 MPa, Rm(LT) von mindestens 320 MPa und vorzugsweise mindestens 360 MPa, und einer Eigenschaft ausgewählt unter A%(L) von 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.
  14. Walzerzeugnis, erhältlich durch das Verfahren nach irgendeinem der Ansprüche 10 bis 12, das eine zumindest im Wesentlichen gleiche Streckgrenze unter Zugbeanspruchung Rp0,2(L) und eine vorzugsweise um mindestens 5% höhere Zähigkeit im Vergleich zur Zähigkeit aufweist, die durch ein ähnliches Verfahren ohne kurze Wärmebehandlung erhalten wird.
  15. Walzerzeugnis, erhältlich durch das Verfahren nach irgendeinem der Ansprüche 10 bis 12, dadurch gekennzeichnet, dass es sich um ein Blech aus der Legierung AA2198 mit einer Dicke von 0,5 bis 15 mm und vorzugsweise 1 bis 8 mm handelt, das nach Warmauslagerung im Zustand T8 eine Eigenschaftskombination aufweist, bestehend aus mindestens einer statischen Festigkeitseigenschaft ausgewählt unter Rp0,2(L) von mindestens 500 MPa und vorzugsweise mindestens 510 MPa und/oder Rp0,2(LT) von mindestens 480 MPa und vorzugsweise mindestens 490 MPa, und mindestens einer, an Proben vom Typ CCT760 (mit 2ao = 253 mm) gemessenen Zähigkeitseigenschaft ausgewählt unter Kapp in TL-Richtung von mindestens 160 MPa√m und vorzugsweise mindestens 170 MPa√m und/oder Keff in TL-Richtung von mindestens 200 MPa√m und vorzugsweise mindestens 220 MPa√m und/oder Δeff(max) in TL-Richtung von mindestens 40 mm und vorzugsweise mindestens 50 mm.
  16. Verwendung eines durch das Verfahren nach irgendeinem der Ansprüche 10 bis 12 erhältlichen Walzerzeugnisses für die Herstellung eines Flugzeugstrukturelementes, insbesondere einer Rumpfhaut eines Flugzeugs.
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EP2766503B1 (de) 2016-12-07
EP2766503A1 (de) 2014-08-20
CA2851592A1 (fr) 2013-04-18
CN106222504A (zh) 2016-12-14
CN106222504B (zh) 2019-10-18
US10968501B2 (en) 2021-04-06
BR112014008685B1 (pt) 2019-04-24
BR112014008685A2 (pt) 2017-04-25
CA2851592C (fr) 2020-01-07
CN103874775A (zh) 2014-06-18
FR2981365B1 (fr) 2018-01-12
FR2981365A1 (fr) 2013-04-19
US20190071753A1 (en) 2019-03-07
US11667994B2 (en) 2023-06-06
US20130092294A1 (en) 2013-04-18
CN103874775B (zh) 2016-07-06
WO2013054013A1 (fr) 2013-04-18

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