• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a process for manufacturing a wrought product of aluminum alloy composition, in% by weight, Mg: 3.8-4.2; Mn: 0.3 - 0.8 and preferably 0.5-0.7; Sc: 0.1-0.3; Zn: 0.1-0.4; Ti: 0.01-0.05; Zr: 0.07-0.15; Cr: <0.01, Fe: <0.15, Si <0.1; in which the homogenization is carried out at a temperature between 370 ° C and 450 ° C, for a period of between 2 and 50 hours such that the time equivalent to 400 ° C is between 5 and 100 hours, and the deformation to It is heated with an initial temperature of between 350 ° C. and 450 ° C. The invention also relates to the wrought products obtained by the process according to the invention, in particular the sheets whose thickness is less than 12 mm. The products according to the invention are advantageous because they have an improved compromise in terms of mechanical strength, toughness and hot forming ability.
    公开号:FR3057476A1
    申请号:FR1660049
    申请日:2016-10-17
    公开日:2018-04-20
    发明作者:Bernard Bes；Jean-Christophe Ehrstrom；Gaelle Pouget
    申请人:Constellium Issoire SAS；
    IPC主号:
    专利说明:

    Holder (s): CONSTELLIUM ISSOIRE Simplified joint-stock company.
    Extension request (s)
    Agent (s): C-TEC CONSTELLIUM TECHNOLOGY CENTER.
    M) AEROSPATIAL THIN SHEET.
    ALUMINUM-MAGNESIUM-SCANDIUM ALLOY FOR APPLICATIONS
    FR 3 057 476 - A1 (5 /) The invention relates to a process for manufacturing a wrought product made of aluminum alloy of composition, in% by weight, Mg: 3.8-4.2; Mn: 0.3-0.8 and preferably 0.50.7; Sc: 0.1-0.3; Zn: 0.1-0.4; Ti: 0.01 - 0.05; Zr: 0.07-0.15; Cr: <0.01; Fe: <0.15; Si <0.1; in which the homogenization is carried out at a temperature between 370 ° C and 450 ° C, for a time between 2 and 50 hours such that the time equivalent to 400 ° C is between 5 and 100 hours, and the deformation at hot is carried out with an initial temperature between 350 ° C and 450 ° C. The invention also relates to the wrought products obtained by the process according to the invention, in particular sheets whose thickness is less than 12 mm. The products according to the invention are advantageous because they exhibit an improved compromise in terms of mechanical strength, toughness and aptitude for hot forming.
    235 290 29S 300 305
    RpO.2: L (MPa)
    i
    THIN SHEETS OF ALUMINUM-MAGNESIUM-SCANDIUM ALLOY FOR AEROSPATIAL APPLICATIONS
    Field of the invention
    The subject of the invention is a process for the production of wrought products of aluminum and magnesium alloy, also known under the name of aluminum alloy of the 5XXX series according to the Aluminum Association, more particularly of products of Al alloy -Mg containing Sc with high mechanical strength, high toughness and good formability. The invention also relates to products capable of being obtained by said process as well as the reuse of these products intended for transport and in particular for aeronautical and space construction.
    State of the art
    Wrought aluminum alloy products are developed in particular to produce structural elements for the transportation industry, particularly the aeronautics and space industries. For these industries, product performance must constantly be improved and new alloys are developed to present in particular high mechanical strength, low density, high toughness, excellent corrosion resistance and very good workability. form. In particular, the shaping can be carried out hot, for example by creep (creep forming), and the mechanical properties must not decrease after this shaping.
    Al-Mg alloys have been extensively studied in the transport industry, especially road and sea transport, because of their excellent properties of use such as weldability, corrosion resistance and formability, especially in the United States. little hardened such as state O and state H111.
    These alloys, however, have relatively low mechanical strength for the aeronautics and space industries.
    US Patent 5,624,632 describes an alloy of composition 3 - 7% by weight of magnesium, 0.03 - 0.2% by weight of zirconium, 0.2 - 1.2% by weight of manganese, up to 0.15% by weight of silicon and 0.05 - 0, 5% by weight of an element forming dispersoids in the group scandium, erbium, yttrium, gadolinium, holmium and hafnium.
    The patent US 6,695,935 describes an alloy of composition, in% by weight, Mg 3.5-6.0, Mn 0.4-1.2, Zn 0.4-1.5, Zr 0.25 max., Cr 0.3 max., Ti 0.2 max., Fe 0.5 max., If 0.5 max., Cu 0.4 max, one or more elements in the group: Bi 0.005-0.1, Pb 0.005-0.1, Sn 0.01-0.1, Ag 0.01-0.5, Sc 0.01-0.5, Li 0.01-0.5, V 0.01- 0.3, Ce 0.01-0.3, Y 0.01-0.3, and Ni 0.01-0.3.
    Patent application WO 01/12869 describes an alloy of composition in% by weight 1.0-8.0% Mg, 0.05-0.6% Sc, 0.05-0.20% Hf and / or 0.05-0.20% Zr, 0.5-2.0% Cu and / or 0.5-2.0% Zn and in addition 0.1-0.8% by weight of Mn.
    Patent application WO2007 / 020041 describes an alloy of composition, in% by weight, Mg 3.5 to 6.0, Mn 0.4 to 1.2, Fe <0.5, Si <0.5, Cu <0.15, Zr <0.5, Cr <0.3, Ti 0.03 at 0.2, Sc <0.5, Zn <1.7, Li <0.5, Ag <0.4, optionally one or more elements forming dispersoids in the group erbium, yttrium, hafnium, vanadium, each <0.5% by weight.
    The products described in these patents are not sufficient in terms of compromise between mechanical strength, toughness and aptitude for hot forming. In particular, it is important that the mechanical properties do not decrease after a heat treatment at 300-350 ° C, a temperature typical of the shaping temperature.
    There is therefore a need for wrought products of Al-Mg alloy having a low density as well as improved properties compared to those of known products, in particular in terms of mechanical strength, toughness and aptitude for hot forming. Such products must also be able to be obtained according to a reliable, economical and easily adaptable manufacturing process to a conventional manufacturing line.
    Object of the invention
    A first object of the invention is a process for manufacturing a wrought aluminum alloy product in which:
    a) a liquid metal bath is prepared based on aluminum of composition, in% by weight,
    Mg: 3.8-4.2;
    Mn: 0.3-0.8; preferably 0.5 - 0.7 Sc: 0.1-0.3;
    Zn: 0.1-0.4;
    Ti: 0.01 - 0.05 preferably 0.015-0.030;
    Zr: 0.07-0.15 preferably 0.08-0.12;
    Cr: <0.01;
    Fe: <0.15;
    If <0.1;
    other elements <0.05 each and <0.15 in combination, aluminum remains;
    b) pouring a raw form from said metal bath;
    c) the said raw form is homogenized at a temperature between 370 ° C and 450 ° C, for a period between 2 and 50 hours such that the time equivalent to 400 ° C is between 5 and 100 hours, the equivalent time t (eq) at 400 ° C being defined by the formula:
    Jexp (-29122 / T) dt t (eq) = exp (-29122 / T re f) in which T is the instantaneous temperature expressed in Kelvin which changes with time t (in hours) and Tref is a reference reference temperature 400 ° C (673 K), t (eq) being expressed in hours, the constant Q / R = 29122 K being derived from the activation energy for the diffusion of Zr, Q = 242000 J / mol,
    d) it is deformed hot with an initial temperature between 350 ° C and 450 ° C and optionally deformed cold the raw form thus homogenized;
    e) optionally a leveling and / or straightening is carried out
    f) optionally annealing is carried out at a temperature between 300 ° C and 350 ° C.
    A second object of the invention is a wrought aluminum alloy product of composition, in% by weight,
    Mg: 3.8-4.2;
    Mn: 0.3 - 0.8 preferably 0.5-0.7;
    Sc: 0.1-0.3;
    Zn: 0.1-0.4;
    Ti: 0.01 - 0.05 preferably 0.015-0.030;
    Zr: 0.07-0.15 preferably 0.08-0.12;
    Cr: <0.01;
    Fe: <0.15;
    If <0.1;
    other elements <0.05 each and <0.15 in combination; remains aluminum.
    likely to be obtained by the process according to the invention.
    Description of the figures
    Figure 1: compromise of static mechanical strength property Rp0.2 L and Kr60 LT for a product according to the invention (A) and a reference product (B), after hot rolling (LAC) or after hot rolling and annealing (Annealed).
    Figure 2: compromise of static mechanical strength property Rp0.2 TL and Kr60 TL for a product according to the invention (A) and a reference product (B), after hot rolling (LAC) or after hot rolling and annealing (Annealed).
    Description of the invention
    Unless otherwise stated, all information regarding the chemical composition of the alloys is expressed as a percentage by weight based on the total weight of the alloy. By way of example, the expression 1.4 Cu means that the copper content expressed in% by weight is multiplied by 1.4. The designation of alloys is done in accordance with the regulations of "The Aluminum Association", known to those skilled in the art.
    The definitions of the metallurgical states are indicated in the European standard EN 515. The static mechanical characteristics in tension, in other words the breaking strength R m , the conventional elastic limit at 0.2% elongation R p o, 2, and the elongation at break A%, are determined by a tensile test according to standard NF EN ISO 6892-1, the sampling and the direction of the test being defined by standard EN 485-1.
    The toughness under plane stress is determined by means of a curve of the stress intensity factor Kr as a function of the effective crack extension Aa e ff known as the curve R, according to standard ASTME 561. The stress intensity factor critical Kc, in other words the intensity factor which makes the crack unstable, is calculated from the curve R. The stress intensity factor Kco 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 test piece of the required shape. K app represents the factor Kco corresponding to the test piece which was used to carry out the curve test R. K e ff represents the factor Kc corresponding to the test piece which was used to carry out the curve test R. Kr60 corresponds to the value of Kr for an effective crack extension Aa e ff = 60 mm.
    Without the scope of the invention, the granular structure of the samples is characterized in the LxTC plane at mid-thickness, t / 2 and is quantitatively evaluated after a metallographic attack of the anodic oxidation type and under polarized light:
    _ the term "essentially non-recrystallized" is used when the granular structure has little or no recrystallized grains, typically less than 20%, preferably less than 15% and more preferably still less than 10% of the grains are recrystallized (FIG. 1 is a micrograph representative of this so-called “essentially non-recrystallized” microstructure);
    _ the term “recrystallized” is used when the granular structure has a large proportion of recrystallized grains, typically more than 50%, preferably more than 60% and more preferably still more than 80% of the grains are recrystallized (FIG. 2 is a photograph representative of this so-called “recrystallized” microstructure);
    Unless otherwise stated, the definitions of EN 12258 apply.
    In the context of the present invention, 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 the failure of which is likely to endanger the safety of said structure, its users, its users or others. For an airplane, these structural elements include in particular the elements that make up the fuselage (such as the fuselage skin, the stiffeners or stringers of the fuselage (stringers), the bulkheads, the frames of fuselage (circumferential frames), the wings (such as upper or lower wing skin), stiffeners (stringers or stiffeners), ribs (ribs), spars, floor (floor beams) and the seat tracks (seat tracks)) and the empennage composed in particular of horizontal and vertical stabilizers (horizontal or vertical stabilizers), as well as the doors.
    The present inventors have found that for a composition according to the invention, it is possible, by controlling the homogenization conditions, to obtain an advantageous wrought product, the mechanical properties of which offer a compromise between mechanical strength and toughness useful for aeronautical construction and whose properties are stable after a heat treatment corresponding to hot forming conditions.
    According to the invention, a liquid metal bath based on aluminum is prepared, in% by weight, Mg: 3.8-4.2; Mn: 0.3 - 0.8 preferably 0.5-0.7; Sc: 0.1-0.3; Zn: 0.1-0.4; Ti: 0.01 - 0.05 preferably 0.015-0.030; Zr: 0.07-0.15 preferably 0.08-0.12; Cr: <0.01; Fe: <0.15; If <0.1 other elements 0 remain aluminum.
    The composition according to the invention is remarkable due to a small addition of titanium of 0.01 - 0.05 and preferably of 0.015 to 0.030% by weight and preferably of 0.018 to 0.024% by weight and by absence of addition of chromium, the content of which is less than 0.01% by weight. High static mechanical properties (Rp0.2, Rm) are obtained despite these low additions because the homogenization conditions are carefully controlled. Thus, it is surprisingly possible to avoid recrystallization during hot forming with low additions of titanium and in the absence of addition of chromium, and to simultaneously achieve high static mechanical properties, which could be obtained in particular by strong additions of Cr and Ti, and a high tenacity.
    The addition of Mn, Sc, Zn and Zr is necessary to obtain the desired compromise between mechanical strength, toughness and suitability for hot forming. The iron content is kept below 0.15% by weight and preferably less than 0.1% by weight. The silicon content is kept below 0.1% by weight and preferably less than 0.05% by weight. The presence of iron and silicon beyond the indicated maximums has an unfavorable impact, in particular on the toughness. The other elements are impurities, i.e. elements the presence of which is unintentional, their presence must be limited to 0.05% each and 0.15% in combination and preferably to 0.03% each and 0.10% in combination.
    According to the invention, the said raw form is homogenized at a temperature between 370 ° C and 450 ° C, for a period between 2 and 50 hours such that the time equivalent to 400 ° C is between 5 and 100 hours, the equivalent time t (eq) at 400 ° C being defined by the formula:
    fexp (-29122 / T) dt t (eq) = exp (-29122 / Tref) in which T is the instantaneous temperature expressed in Kelvin which changes with time t (in hours) and Tref is a reference temperature of 400 ° C (673 K), t (eq) being expressed in hours, the constant Q / R = 29122 K being derived from the activation energy for the diffusion of Zr, Q = 242000 J / mol.
    Preferably, the homogenization time is between 5 and 30 hours. Advantageously, the time equivalent to 400 ° C. is between 6 and 30 hours.
    Too low a temperature and / or duration of homogenization does not make it possible to form dispersoids to control the recrystallization. Surprisingly, when the temperature and / or duration of homogenization are too high, the properties obtained are not stable at the typical hot forming temperature of 300-350 ° C., in particular because the products recrystallize.
    The hot deformation can be carried out directly after homogenization without cooling to room temperature, the initial temperature of hot deformation must be between 350 and 450 ° C. Alternatively, the raw form can be cooled to room temperature after homogenization and the raw form can be warmed up to an initial hot deformation temperature between 350 and 450 ° C. In the case of reheating, care should be taken that the time equivalent to 400 ° C during reheating is low, typically less than 10%, in comparison with the time equivalent to 400 ° C during homogenization.
    During hot deformation, the temperature of the metal can in certain cases increase, however it should be taken care that the time equivalent to 400 ° C during hot deformation is low, typically less than 10%, in comparison with the time equivalent to 400 ° C during homogenization. It is in any case preferable that the temperature during the hot deformation does not exceed 460 ° C. and preferably does not exceed 440 ° C. After hot deformation, cold deformation can be carried out.
    In a first embodiment, the working is carried out by rolling to obtain a sheet. According to this first mode, the final thickness of the sheet obtained is less than 12 mm.
    In a second embodiment, the working is carried out by extrusion to obtain a profile.
    In the first embodiment, the hot deformation is typically carried out to a thickness of approximately 4 mm and then the cold deformation for a thickness of between 0.5 and 4 mm.
    After hot and optionally cold deformation, it may be advantageous to perform leveling and / or straightening. During leveling and / or straightening operations, the permanent deformation is typically less than 2%, preferably about 1%.
    Optionally, annealing is carried out at a temperature between 300 ° C and 350 ° C. The duration of the annealing is typically between 1 and 4 hours. This annealing has mainly a function of stabilization of the mechanical properties so that they do not evolve during a subsequent shaping at a neighboring temperature. The products according to the invention have the advantage of having very stable mechanical properties at this temperature. Thus for products whose final thickness of 4 to 6 mm is obtained by hot rolling, the variation in static mechanical property is at most 10% and preferably at most 6% after annealing between 300 and 350 ° C and for products whose final thickness of approximately 2 mm is obtained by cold rolling, the variation in static mechanical property is at most 40% and preferably at most 30% after annealing between 300 and 350 ° C. . It is therefore possible in the context of the method according to the invention not to carry out stabilization annealing and to proceed directly to shaping, in particular for products whose final thickness is obtained by hot rolling. Thanks to the process according to the invention, the products according to the invention retain an essentially non-recrystallized granular structure after annealing between 300 and 350 ° C.
    The sheets of thickness less than 12 mm obtained by the process according to the invention are advantageous, preferably having the following characteristics:
    (a) a conventional elastic limit measured at 0.2% elongation in the TL direction of at least 250 MPa, and preferably at least 260 MPa and / or ίο (b) an elastic limit conventional measured at 0.2% elongation in the L direction of at least 260 MPa, and preferably at least 270 MPa, these properties being achieved even in the case where the optional step of annealing at a temperature included between 300 ° C and 350 ° C is carried out.
    Advantageously, the sheets of thickness less than 4 mm obtained by the method according to the invention have a conventional elastic limit measured at 0.2% elongation in the TL direction of at least 300 MPa, and preferably of at least 320 MPa, these properties being achieved even in the case where the optional annealing step at a temperature between 300 ° C and 350 ° C is carried out.
    The sheets according to the invention preferably have advantageous toughness properties, in particular:
    (c) a tenacity Kr60, measured on CCT760 type test pieces in the LT direction (with 2ao = 253 mm), for an effective crack extension Aa e ff of 60 mm of at least 155 MPaVm, and preferably of at least 165 MPaVm and / or (d) tenacity Kr60, measured on CCT760 type test pieces in the TL direction (with 2ao = 253 mm), for an effective crack extension Aa e ff of 60 mm of at least 160 MPa Vm, and preferably at least 170 MPa Vm.
    Preferably, for the products according to the invention, the tenacity Kr in the T-L direction is greater than that in the L-T direction.
    Preferably the Kapp toughness, measured on CCT760 type test pieces in the T-L direction (with 2ao = 253 mm), is at least 125 MPa, and preferably at least 130 MPa
    The products according to the invention can be shaped at a temperature between 300 ° C and 350 ° C to obtain structural elements for aircraft, preferably fuselage elements.
    The aircraft fuselage elements according to the invention are advantageous because they have (a) a conventional elastic limit measured at 0.2% elongation in the direction TL is at least 250 MPa, and preferably d '' at least 260 MPa and / or (b) a conventional elastic limit measured at 0.2% elongation in the direction L is at least 260 MPa, and preferably at least 270 MPa.
    Examples
    Example 1
    Several 400 mm thick plates, the composition of which is given in table 1, were cast.
    Yes Fe Cr Mn Mg Zn Ti Zr Sc AT 0.02 0.05 <0.01 0.62 4.05 0.28 0.023 0.10 0.19 B 0.02 0.04 <0.01 0.59 3.99 0.29 0.038 0.10 0.19
    Table 1: Composition in% by weight (analysis by optical spark emission spectrometer, S-OES).
    The alloy plate A was homogenized for 5 h at 445 ° C. while the alloy plate B was homogenized for 15 h at 515 ° C. The plates thus homogenized were hot rolled directly after homogenization with a hot rolling start temperature of 415 ° C for plate A and 480 ° C for plate B, to obtain sheets having a thickness of 4 mm.
    The results obtained after hot rolling are shown in Figures 1 and 2 and in Table 2.
    The static mechanical characteristics in tension of the sheet of alloy A remained high both in the state as hot rolled (LAC) and in the annealed state (annealing treatment for 4 hours at 325 ° C.) while those of Alloy B sheet dropped after annealing.
    Alloy sheet A Thickness 4 mm Alloy sheet B Thickness 4 mm LAKE LAKE Annealed Annealed Rp0.2 L, MPa 303 287 233 289 Rm L, MPa 400 364 352 393 A L,% 14.5 14.8 17.6 16.2 Rp0.2 TL, MPa 311 276 238 292 Rm TL, MPa 396 361 349 387 At TL,% 17.7 18.2 23.0 19.5 Kapp MPaVm L-T 129.1 128.5 129.9 Kapp MPa ^ m T-L 134.0 125.8 134.9 Kr60 MPaVm L-T 171.5 171.2 172.9 KrôOMPaVm T-L 177.1 164 178.9
    Table 2: Static mechanical characteristics obtained for the various sheets in the hot rolled state (LAC) and in the annealed state (4 hours at 325 ° C).
    The 4 mm sheets were cold rolled to a thickness of 2 mm in three 5 passes without intermediate heat treatment, then underwent leveling. Various heat treatments have been carried out after cold rolling. The results of the mechanical tensile tests are presented in Table 3.
    Annealing after cold rolling Alloy sheet AThickness 2 mm Alloy sheet BThickness 2 mm Rp02(TL) Rp02(TL) Rm (TL) A% TL Rm (TL) A% TL - 417 358 422 10.5 466 9.95 2 h 275 ° C 349.5 256 355 18.2 415 19 2h 325 ° C 333 168 311 23.0 405 21.7 2 h 375 ° C 297.5 156 301 23.1 393 21.4
    Table 3: Static mechanical characteristics obtained for the various cold-rolled sheets which have been annealed under different conditions.
    The granular structure of the sheets was observed after a metallographic attack of the anodic oxidation type and under polarized light after cold rolling (LAF) or after cold rolling and annealing for 2 hours at 325 ° C.
    A qualitative evaluation of the microstructure was carried out:
    Table 4 presents the results of the microstructural observations of the composition A and B sheets in the raw cold rolling state and after treatment.
    Alloy Reference Microstructure AT LAF Essentially non-recrystallized 2h325 ° C Essentially non-recrystallized B LAF Essentially non-recrystallized 2h325 ° C Recrystallized
    Table 4: Microstructure (LxTC plane, mid-thickness) of the sheets
    Alloy A according to the invention has excellent resistance to recrystallization.
    Example 2
    In this example, we studied the effect of the homogenization conditions before hot deformation on the mechanical properties. Alloy blocks of dimension A
    250 x 180 x 120 mm have been hot rolled under different conditions, up to a thickness of 8 or 12 mm. The conditions are described in Table 5
    Temperaturehomogenization(° C) Durationhomogenization(h) T (eq)at400° C Initial rolling temperature(° C) Thicknessfinal(mm) Final rolling temperature (° C) CD2 450 15 298 440 12 329 CD3 400 15 15 390 12 319 CD4 450 15 298 440 8 325 CFI 450 5 99 440 8 330 CF2 450 5 99 12 327 CF3 400 5 5 405 12 320 CF4 515 17 9341 8 325
    Table 5: conditions for transforming different blocks into alloy A
    The mechanical properties were measured on the sheets as rolled or having undergone a treatment. The results are presented in Table 6
    LAKE Annealing 4h 325 ° C block meaning RpO, 2 Rm AT Rp0.2 Rm AT MPa MPa % MPa MPa % CD2 L 251 377 15.4 243 370 16.0 CD3 L 286 398 14.5 278 391 15.4 CD4 L 260 371 13.6 252 366 16.7 CFI L 275 381 16.1 267 373 17.1 CF2 L 268 390 12.9 262 382 13.8 CF3 L 288 399 14.8 280 392 15.4 CF4 L 223 341 15.7 209 339 17.3
    Table 6 Static mechanical characteristics obtained for the various sheets in the hot rolled state (LAC) and in the annealed state (4 hours at 325 ° C).
    The products obtained by the process according to the invention (CD3, CFI, CF2, CF3) have advantageous mechanical characteristics, in particular Rp0.2 in the L direction of at least 260 MPa after LAC and after annealing from 4 hours to 325.
    权利要求:
    Claims (9)
    [1" id="c-fr-0001]
    Claims
    1. Process for manufacturing a wrought aluminum alloy product in which:
    a) a liquid metal bath is prepared based on aluminum of composition, in% by weight,
    Mg: 3.8-4.2;
    Mn: 0.3-0.8 and preferably 0.5-0.7;
    Sc: 0.1-0.3;
    Zn: 0.1-0.4;
    Ti: 0.01-0.05 and preferably 0.015-0.030;
    Zr: 0.07-0.15 and preferably 0.08-0.12;
    Cr: <0.01;
    Fe: <0.15;
    If <0.1;
    other elements <0.05 each and <0.15 in combination, aluminum remains;
    b) pouring a raw form from said metal bath;
    c) the said raw form is homogenized at a temperature between 370 ° C and 450 ° C, for a period between 2 and 50 hours such that the time equivalent to 400 ° C is between 5 and 100 hours, the equivalent time t (eq) at 400 ° C being defined by the formula:
    Jexp (-29122 / T) dt t (eq) = exp (-29122 / T re f) in which T is the instantaneous temperature expressed in Kelvin which changes with time t (in hours) and Tref is a reference reference temperature 400 ° C (673 K), t (eq) being expressed in hours, the constant Q / R = 29122 K being derived from the activation energy for the diffusion of Zr, Q = 242000 J / mol,
    d) it is deformed hot with an initial temperature between 350 ° C and 450 ° C and optionally deformed cold the raw form thus homogenized;
    e) optionally a leveling and / or straightening is carried out
    f) optionally annealing is carried out at a temperature between 300 ° C and
    350 ° C.
    [2" id="c-fr-0002]
    2. Method according to claim 1 wherein the duration of homogenization is between 5 and 30 hours.
    [3" id="c-fr-0003]
    3. Method according to any one of claims 1 to 2 wherein the working is carried out by rolling to obtain a sheet and in which the final thickness of the sheet obtained is less than 12 mm.
    [4" id="c-fr-0004]
    4. Method according to any one of claims 1 to 2 wherein the working is carried out by extrusion to obtain a profile.
    [5" id="c-fr-0005]
    5. Wrought product in aluminum alloy composition, in% by weight,
    Mg: 3.8-4.2;
    Mn: 0.3-0.8 and preferably 0.5-0.7;
    Sc: 0.1-0.3;
    Zn: 0.1-0.4;
    Ti: 0.01-0.05 and preferably 0.015-0.030;
    Zr: 0.07-0.15 and preferably 0.08-0.12;
    Cr: <0.01;
    Fe: <0.15;
    If <0.1;
    other elements <0.05 each and <0.15 in combination; aluminum residue, capable of being obtained by the process according to any one of claims 1 to 4.
    [6" id="c-fr-0006]
    6. Wrought product according to claim 5 in the form of a sheet of thickness less than 12 mm capable of being obtained by the process according to claim 3, characterized in that (a) its conventional elastic limit measured at 0.2 % elongation in the TL direction is at least 250 MPa, and preferably at least 260 MPa and / or (b) its conventional elastic limit measured at 0.2% elongation in the L direction is at least 260 MPa, and preferably at least 270 MPa MPa-x / m.
    [7" id="c-fr-0007]
    7. Sheet according to claim 6 characterized in that (c) its toughness Kr60, measured on CCT760 type test pieces in the direction LT (with 2ao = 253 mm), for an effective crack extension Aa e ir of 60 mm d '' at least 155 MPaVm, and preferably at least 165 MPaVm and / or (d) its tenacity Kr60, measured on CCT760 type test pieces in the TL direction (with 2ao = 253 mm), for an effective crack extension aa e ir 60 mm of at least 160 MPa Vm, and preferably at least 170 MPa Vm.
    [8" id="c-fr-0008]
    8. Method according to any one of claims 1 to 4 wherein at the end of step f is carried out shaping at a temperature between 300 ° C and 350 ° C.
    [9" id="c-fr-0009]
    9. Aircraft fuselage element capable of being obtained according to the method according to claim 8 characterized in that (a) its conventional elastic limit measured at 0.2% elongation in the direction TL is at least minus 250 MPa, and preferably at least 260 MPa and / or (b) its conventional elastic limit measured at 0.2% elongation in the direction L is at least 260 MPa, and preferably d '' at least 270 MPa
    1/1
    类似技术:
    公开号 | 公开日 | 专利标题
    EP2766503B1|2016-12-07|Improved method for processing sheet metal made of an al-cu-li alloy
    EP2449142B1|2017-05-03|Aluminium-copper-lithium alloy with improved mechanical resistance and toughness
    EP2984195B1|2019-01-16|Process of manufacturing a rolled al-cu-li sheet with improved formability and corrosion resistance
    EP1966402B1|2009-03-18|Sheet made of high-toughness aluminium alloy containing copper and lithium for an aircraft fuselage
    EP1644546B1|2016-04-20|Use of pipes made from al/zn/mg/cu alloys with improved compromise between static mechanical properties and tolerance to damage
    FR2902442A1|2007-12-21|ALLOY OF AA6XXX SERIES WITH HIGH DAMAGE TO AEROSPACE INDUSTRY
    EP2364378B1|2014-01-08|Products in aluminium-copper-lithium alloy
    EP3526358B1|2020-07-22|Thin sheets made of an aluminium-magnesium-scandium alloy for aerospace applications
    EP3011068A1|2016-04-27|Extrados structural element made from an aluminium copper lithium alloy
    EP3201372B1|2021-01-27|Isotropic sheets of aluminium-copper-lithium alloys for the fabrication of fuselages of aircrafts and method of manuacturing same
    EP3384061B1|2020-02-05|Aluminium-copper-lithium alloy having improved mechanical strength and improved toughness
    CA3085811A1|2019-06-27|Improved process for manufacturing sheets made of aluminium-copper-lithium alloy for aircraft fuselage manufacture
    CA2960947A1|2016-04-07|Method for manufacturing products made of magnesium-lithium-aluminum alloy
    EP1544316A2|2005-06-22|Thick sheet made of Al-Zn-Cu-Mg recrystallised alloy with low Zirconium content
    EP3362584B1|2019-08-07|Thin sheets made from aluminium-magnesium-zirconium alloys for aerospace applications
    FR3080860A1|2019-11-08|LITHIUM COPPER ALUMINUM ALLOY WITH ENHANCED COMPRESSION RESISTANCE AND TENACITY
    FR3026411A1|2016-04-01|METHOD FOR MANUFACTURING LITHIUM MAGNESIUM ALUMINUM ALLOY PRODUCTS
    FR3080861A1|2019-11-08|METHOD FOR MANUFACTURING LITHIUM COPPER ALUMINUM ALLOY WITH IMPROVED RESISTANCE AND TENABILITY
    同族专利:
    公开号 | 公开日
    EP3526358B1|2020-07-22|
    FR3057476B1|2018-10-12|
    EP3526358A1|2019-08-21|
    US20190249285A1|2019-08-15|
    CA3037115A1|2018-04-26|
    CN109844151A|2019-06-04|
    WO2018073533A1|2018-04-26|
    CN109844151B|2021-03-19|
    BR112019006323A2|2019-06-25|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2889852A1|2005-08-16|2007-02-23|Corus Aluminium Walzprod Gmbh|Aluminum alloy for aircraft, land vehicle and marine use contains small quantities of magnesium, manganese and other elements for high strength and corrosion resistance|CN113302329A|2019-01-17|2021-08-24|爱励轧制产品德国有限责任公司|Method for manufacturing AlMgSc series alloy products|US5624632A|1995-01-31|1997-04-29|Aluminum Company Of America|Aluminum magnesium alloy product containing dispersoids|
    JP4954369B2|1998-12-18|2012-06-13|アレリス、アルミナム、コブレンツ、ゲゼルシャフト、ミット、ベシュレンクテル、ハフツング|Method for producing aluminum-magnesium-lithium alloy product|
    AU750846B2|1999-05-04|2002-08-01|Corus Aluminium Walzprodukte Gmbh|Exfoliation resistant aluminium-magnesium alloy|
    US6139653A|1999-08-12|2000-10-31|Kaiser Aluminum & Chemical Corporation|Aluminum-magnesium-scandium alloys with zinc and copper|
    ES2286556T3|2003-05-20|2007-12-01|Aleris Aluminum Duffel Bvba|ALLOY FORGED ALUMINUM.|
    DE10352932B4|2003-11-11|2007-05-24|Eads Deutschland Gmbh|Cast aluminum alloy|
    RU2280705C2|2004-09-15|2006-07-27|Открытое акционерное общество "Каменск-Уральский металлургический завод"|Aluminum-based alloy and articles made from this alloy|
    CN101233252B|2005-08-16|2013-01-09|阿勒里斯铝业科布伦茨有限公司|High strength weldable al-mg alloy|
    CA2768503A1|2009-07-24|2011-01-27|Alcoa Inc.|Improved 5xxx aluminum alloys and wrought aluminum alloy products made therefrom|
    US20120103476A1|2010-10-29|2012-05-03|Alcoa Inc.|5xxx aluminum alloys, and methods for producing the same|
    FR2969177B1|2010-12-20|2012-12-21|Alcan Rhenalu|LITHIUM COPPER ALUMINUM ALLOY WITH ENHANCED COMPRESSION RESISTANCE AND TENACITY|
    FR2975403B1|2011-05-20|2018-11-02|Constellium Issoire|MAGNESIUM LITHIUM ALUMINUM ALLOY WITH IMPROVED TENACITY|
    FR2981365B1|2011-10-14|2018-01-12|Constellium Issoire|PROCESS FOR THE IMPROVED TRANSFORMATION OF AL-CU-LI ALLOY SHEET|
    KR101246106B1|2012-06-13|2013-03-20|주식회사 대호에이엘|Aluminium alloy plate for automobile interor/exterior materials and its manufacturing method|
    FR3026411B1|2014-09-29|2018-12-07|Constellium France|METHOD FOR MANUFACTURING LITHIUM MAGNESIUM ALUMINUM ALLOY PRODUCTS|
    CN106715735A|2014-09-29|2017-05-24|伊苏瓦尔肯联铝业|Wrought product made of a magnesium-lithium-aluminum alloy|CN113508185A|2019-12-27|2021-10-15|俄罗斯工程技术中心有限责任公司|Aluminium base alloy|
    RU2734675C1|2020-05-21|2020-10-21|Федеральное государственное бюджетное учреждение науки Самарский федеральный исследовательский центр Российской академии наук |Method of making rolled articles from thermally nonhardenable aluminum-magnesium system alloys and an article obtained using said method|
    法律状态:
    2017-10-25| PLFP| Fee payment|Year of fee payment: 2 |
    2018-04-20| PLSC| Publication of the preliminary search report|Effective date: 20180420 |
    2018-10-25| PLFP| Fee payment|Year of fee payment: 3 |
    2019-10-25| PLFP| Fee payment|Year of fee payment: 4 |
    2020-10-26| PLFP| Fee payment|Year of fee payment: 5 |
    2021-10-25| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1660049A|FR3057476B1|2016-10-17|2016-10-17|ALUMINUM-MAGNESIUM-SCANDIUM ALLOY THIN SHEET FOR AEROSPATIAL APPLICATIONS|
    FR1660049|2016-10-17|FR1660049A| FR3057476B1|2016-10-17|2016-10-17|ALUMINUM-MAGNESIUM-SCANDIUM ALLOY THIN SHEET FOR AEROSPATIAL APPLICATIONS|
    CA3037115A| CA3037115A1|2016-10-17|2017-10-17|Thin sheets made of an aluminium-magnesium-scandium alloy for aerospace applications|
    PCT/FR2017/052856| WO2018073533A1|2016-10-17|2017-10-17|Thin sheets made of an aluminium-magnesium-scandium alloy for aerospace applications|
    EP17794387.5A| EP3526358B1|2016-10-17|2017-10-17|Thin sheets made of an aluminium-magnesium-scandium alloy for aerospace applications|
    CN201780064272.XA| CN109844151B|2016-10-17|2017-10-17|Sheet made of an aluminium-magnesium-scandium alloy for aerospace applications|
    BR112019006323A| BR112019006323A2|2016-10-17|2017-10-17|aluminum-magnesium-scandium thin sheets for aerospace applications|
    US16/342,096| US20190249285A1|2016-10-17|2017-10-17|Thin sheets made of an aluminum-magnesium-scandium alloy for aerospace applications|
    [返回顶部]