EP2766503B1 - 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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EP2766503B1
EP2766503B1 EP12788613.3A EP12788613A EP2766503B1 EP 2766503 B1 EP2766503 B1 EP 2766503B1 EP 12788613 A EP12788613 A EP 12788613A EP 2766503 B1 EP2766503 B1 EP 2766503B1
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weight
mpa
heat treatment
sheet
short heat
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French (fr)
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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 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.
  • their performance compared to other properties of use must reach that of commonly used alloys, in particular in terms of a compromise between the static mechanical strength properties (yield strength, resistance to rupture) and the properties of damage tolerance (toughness, resistance to the propagation of fatigue cracks), these properties being in general antinomic. The improvement of the compromise between mechanical resistance and damage tolerance is constantly sought.
  • the sheet must be stored in a cold room at a sufficiently low temperature and for a sufficiently short duration so as to avoid natural ripening.
  • this solution heat treatment requires large furnaces, which makes the operation inconvenient, including with respect to the same operation performed on flat sheet.
  • the possible need for a cold room adds to the costs and disadvantages of the state of the art.
  • the sheet may be deformed and cause problems related to this deformation, for example when it comes to the position in the jaws of the drawing-forming tool.
  • this operation must possibly be repeated, if the material does not present, in the metallurgical state in which it is, sufficient formability to achieve the desired form in a single operation.
  • 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 carried out in two passes from the 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 mild shaping cases because the elongation and the ratio R m / R p0 , 2 are too low in this state. It should be noted that 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 US Patent 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 US Patent 5,455,003 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 US Patent 7,438,772 discloses alloys comprising, in weight percent, Cu: 3-5, Mg: 0.5-2, Li: 0.01-0.9 and discourage the use of higher lithium content due to degradation compromise between toughness and mechanical strength.
  • the US Patent 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 EP Patent 1,966,402 discloses an alloy containing no zirconium for fuselage plates 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 shaping, with in particular a ratio R m / / R p0.2 of less than 1.2 in the directions L and LT.
  • the EP Patent 1,891,247 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 shaping, in particular with a ratio R m / / R p0.2 of less than 1.2 in the directions L and LT.
  • the EP Patent 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.
  • WO2006 / 131627 discloses a method of manufacturing an aluminum alloy sheet for the aerospace industry and suitable for use in fuselage applications, the sheet having a high toughness and mechanical strength, wherein: a) produces a bath of liquid metal 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 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 it is chosen, being from 0.05 to 0.13% by weight; weight for Zr, 0.05 to 0.8% by weight for Mn, 0.05 to 0.3% by weight for Cr and for Sc, 0.05 to 0.5% by weight for Hf and 0.05 at 0.15% by weight for Ti, the remainder being aluminum and unavoidable impurities, with the additional condition that the amount of Cu and Li is such that Cu (% by weight) + 5/3 Li (% by weight) ⁇ 5.2; b) pouring a plate from said bath of liquid
  • a second object of the invention is a laminated product obtainable by a process according to the invention, having between 0 and 50 days after short thermal treatment, a combination of at least one property chosen from R p, 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 minus 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 that can be obtained by a process according to the invention, having a yield strength R p0.2 (L) at least substantially equal and a toughness K R greater than preferably at least 5%, to those obtained by a similar process not including short heat treatment.
  • Yet another object of the invention is the use of a product that can be obtained by a method according to the invention for the manufacture of an aircraft fuselage skin.
  • the plane stress toughness is determined by a curve of the stress intensity factor as a function of crack extension, known as the R curve, according to ASTM E 561.
  • the critical stress intensity factor K C in other words, the intensity factor which makes the crack unstable is calculated from the curve R.
  • the stress intensity factor K CO is also calculated by assigning the initial crack length to the critical load, at the beginning of the monotonous charge. These two values are calculated for a specimen of the required form.
  • K app represents the K CO factor corresponding to the specimen that was used to perform the R curve test.
  • K eff represents the K C factor corresponding to the specimen that was used to perform the R curve test.
  • ⁇ a eff (max) represents the crack extension of the last valid point of the R curve.
  • a "structural element” or “structural element” of a mechanical construction is called 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 realized.
  • 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 the elements that make up the fuselage (such as fuselage skin, fuselage skin in English), stiffeners or stringers, bulkheads, fuselage (circumferential frames), the wings (such as upper or lower wing skin, stringers or stiffeners), ribs and spars) and the composite empennage including horizontal and vertical stabilizers (horizontal or vertical stabilizers), as well as floor beams, seat tracks and doors.
  • fuselage such as fuselage skin, fuselage skin in English
  • stiffeners or stringers such as upper or lower wing skin, stringers or stiffeners
  • ribs and spars such as upper or lower wing skin, stringers or stiffeners
  • spars such as upper or lower wing skin, stringers or stiffeners
  • composite empennage including horizontal and vertical stabilizers (horizontal or vertical stabilizers), as well as floor beams, seat tracks and doors.
  • solution, quenching and 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 of between 130 and 170 ° C. C and preferably between 150 and 160 ° C for 0.1 to 13 hours, preferably 0.5 to 9 hours and preferably 1 to 5 hours.
  • the yield strength R p0,2 decreases significantly, that is to say at least 20 MPa or even more, whereas the elongation A% is increased it is to say that it is multiplied by a factor of at least 1.1, or even of at least 1.2, or at least 1.3, with respect to the state obtained without short heat treatment, typically T3 or T4.
  • the short heat treatment is therefore not an income with which one would obtain a state T8 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 a T3 or T4 state while 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. from 0.5 h to 6 h and preferably from 1 h to 4 h and preferably from 1 h to 3 h, the equivalent time t i to 150 h.
  • t i ⁇ exp - 16400 / T dt exp - 16400 / T ref
  • 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, 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 is at least the same or even improved by the method of the invention in the returned state compared to a method not comprising short heat treatment.
  • the compromise obtained between static mechanical strength and toughness is improved compared with 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, especially because of 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 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 stages of production, casting, rolling, dissolution, quenching, 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 15 mm and preferably between 1 and 8 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 15 minutes to 8 hours, and then typically quenched with water at room temperature or, preferably, with water. Cold water.
  • planing is carried out and / or controlled traction said sheet with a cumulative deformation of at least 0.5% and less than 3%.
  • 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 combination of controlled traction with a preferred permanent deformation and short heat treatment achieves optimum results in terms of formability and mechanical properties, especially when additional shaping and income are achieved.
  • the sheet obtained by the process 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. 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 less than 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 1, 45, R m / R p0.2 (LT) at least 1.45 and preferably at least 1.50.
  • 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 preferably less than 260 MPa.
  • the sheet is thus 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 cumulative deformation by planing and / or controlled traction 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 reaches a temperature between 130 and 170 ° C and preferably between 150 and 160 ° C for 5 to 100 hours and preferably 10 to 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.
  • 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 the state O or a product in the state W.
  • a simple income treatment is sufficient.
  • the product Compared to a product in the W state, it has the advantage of being stable and not requiring a cold room and not to cause problems related to the deformation of this state.
  • the product also has the advantage in general of not generating lines Lüders crippling during formatting.
  • the method according to the invention makes it possible to carry out the 3-dimensional shaping of a sheet at the end of the short heat treatment without the sheet being in a state T8, a state O or a state W before this setting shaped in 3 dimensions.
  • 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 mechanical strength in particular the tensile yield strength R p0.2 (L) is high and increases with the additional deformation, but that, contrary to their expectation, the tenacity measured by the curve R ( values of K R ) does not decrease significantly, in particular up to a crack extension value of 60 mm when increasing the additional deformation, even up to a generalized deformation of 8%.
  • the product that can be obtained by the process comprising the additional deformation and tempering steps has a tensile yield strength R p0.2 (L) of at least substantially equal and a higher toughness K R , preferably of at least 5%, to that obtained by a similar process not including short heat treatment.
  • the tensile yield strength R p0.2 (L) is at least 90% or preferably 95% of that obtained by a similar method not comprising short heat treatment.
  • An AA2198 alloy rolling plate was homogenized and then hot rolled to a thickness of 4 mm.
  • the sheets thus obtained were dissolved for 30 minutes at 505 ° C. and then quenched with water.
  • the sheets then underwent a short heat treatment of 2 hours at 150 ° C.
  • An AA2198 alloy rolling plate was homogenized and then hot rolled to a thickness of 4 mm.
  • the sheets thus obtained were dissolved for 30 minutes at 505 ° C. and then quenched with 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 show after deformation of lines Lüders crippling.
  • the sheets finally had an income of 12h at 155 ° C to obtain a T8 state.
  • a sheet was subjected directly after quenching to a controlled pull of 2% followed by an income of 14h at 155 ° C. in the T8 state, without intermediate short heat treatment.
  • the sheets were then glided and controlled in a controlled manner. Controlled traction was achieved with a permanent elongation of 1%. The sheets have been aged sufficiently to reach a stabilized T3 state.
  • the sheets then underwent 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.

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  • Engineering & Computer Science (AREA)
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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 wahlweise homogenisiert wird;
    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 ti 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, ti 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 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, 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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BR112014008685A2 (pt) 2017-04-25
WO2013054013A1 (fr) 2013-04-18
CN106222504A (zh) 2016-12-14
US20190071753A1 (en) 2019-03-07
DE12788613T1 (de) 2015-02-19
EP2766503A1 (de) 2014-08-20
US10968501B2 (en) 2021-04-06
CN106222504B (zh) 2019-10-18
CA2851592A1 (fr) 2013-04-18
CN103874775A (zh) 2014-06-18
FR2981365A1 (fr) 2013-04-19
FR2981365B1 (fr) 2018-01-12
US20130092294A1 (en) 2013-04-18

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