• 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 sheet having a thickness of 0.5 to 9 mm of essentially recrystallized granular structure made of aluminum-based alloy comprising 2.8 to 3.2% by weight of Cu, 0.5 to 0.8% by weight. Li weight, 0.1 to 0.3% by weight of Ag, 0.2 to 0.7% by weight of Mg, 0.2 to 0.6% by weight of Mn, 0.01 to 0.15 % by weight of Ti, an amount of Zn of less than 0.2% by weight, an amount of Fe and Si of less than or equal to 0.1% by weight each, and unavoidable impurities with a content of less than or equal to 0 , 05% by weight each and 0.15% by weight in total, said sheet being obtained by a process comprising casting, homogenization, hot rolling and optional cold rolling, dissolution, quenching and tempering. The plates according to the invention are particularly advantageous for the manufacture of aircraft fuselage panels.
    公开号:FR3026747A1
    申请号:FR1402237
    申请日:2014-10-03
    公开日:2016-04-08
    发明作者:Juliette CHEVY；Bernard Bes；Jean Christophe Ehrstrom；Frank Eberl
    申请人:Constellium France SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The invention relates to aluminum-copper-lithium alloy rolled products, more particularly, to such products, to their processes for manufacturing and to in use, especially for aircraft and aerospace construction. State of the art Aluminum alloy rolled products are developed to produce fuselage elements intended in particular for the aeronautical industry and the aerospace industry. Aluminum - copper - lithium alloys are particularly promising for this type of product. U.S. Patent No. 5,032,359 discloses a broad family of aluminum-copper-lithium alloys in which the addition of magnesium and silver, particularly between 0.3 and 0.5 percent by weight, increases the resistance. mechanical. No. 5,455,003 discloses a process for producing Al-Cu-Li alloys which exhibit improved mechanical strength and toughness at cryogenic temperature, particularly through proper work-hardening and tempering. This patent recommends in particular the composition, in percentage by weight, Cu = 3.0-4.5, Li = 0.7-1.1, Ag = 0-0.6, Mg = 0.3-0.6. and Zn = 0 - 0.75. US Pat. No. 7,438,772 discloses alloys comprising, in weight percentage, Cu: 3-5, Mg: 0.5-2, Li: 0.01-0.9 and discourages the use of higher lithium contents. because of a compromise compromise between toughness and mechanical strength.
    [0002] US Pat. No. 7,229,509 describes 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. US Patent Application 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 at 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 structure control granular. This application also describes a process for manufacturing spun products. The patent application US 2011/0247730 describes alloys comprising (in% by weight), 2.75 to 5.0% Cu, 0.1 to 1.1% Li, 0.3 to 2.0% Ag, 0.2 to 0.8% Mg, 0.50 to 1.5% Zn, up to 1.0% Mn, with a Cu / Mg ratio of between 6.1 and 17, this alloy being not very sensitive to wrought iron. The patent application CN101967588 describes alloys of composition (in% by weight) Cu 2.8 - 4.0; Li 0.8 - 1.9; Mn 0.2-0.6; Zn 0.20 - 0.80, Zr 0.04-0.20, Mg 0.20-0.80, Ag 0.1-0.7, Si <0.10, Fe <0.10, Ti <0.12, it teaches the combined addition of zirconium and manganese. US patent application 2011/209801 relates to wrought products such as spun, rolled and / or forged products of aluminum-based alloy comprising, in% by weight, Cu: 3.0 - 3.9; Li: 0.8 - 1.3; Mg 0.6 - 1.0; Zr 0.05 -0.18 Ag 0.0-0.5; Mn: 0.0 - 0.5, Fe + Si <= 0.20; at least one of Ti: 0.01-0.15; Sc: 0.05 - 0.3; Cr: 0.05 - 0.3; Hf: 0.05-0.5; other elements <= 0.05 each and <= 0.15 in total, remains aluminum, the products being particularly useful for producing thick aluminum products intended to produce structural elements for the aeronautical industry.
    [0003] The characteristics required for aluminum sheets intended for fuselage applications are described, for example, in patent EP 1 891 247. It is desirable in particular for the sheet to have a high yield strength (to resist buckling) as well as a high plane stress toughness, characterized in particular by a high value of high tensile stress factor (Kapp) and a long curve R.
    [0004] EP 1 966 402 discloses an alloy comprising 2.1 to 2.8% by weight of Cu, 1.1 to 1.7% by weight of Li, 01 to 0.8% by weight of Ag, 0.2 0.6% by weight of Mg, 0.2 to 0.6% by weight of Mn, an amount of Fe and Si of less than or equal to 0.1% by weight each, and unavoidable impurities at a lower level. or equal to 0.05% by weight each and 0.15% by weight in total, the alloy being substantially free of zirconium, particularly suitable for obtaining recrystallized thin sheets. The fuselage sheets can be loaded in several directions and isotropic thin sheets having high properties and balanced in mechanical strength in the directions L and TL and tenacity for the directions L-T and T-L are much sought after. In addition it has been found that thin sheets obtained with certain alloys having high properties at certain thicknesses, for example 4 mm, may in certain cases have lower or anisotropic properties at another thickness, for example 2.5 mm. It is often not advantageous industrially to use different alloys for different thicknesses and an alloy to achieve high and isotropic properties regardless of the thickness would be particularly advantageous. There is a need for thin sheets, in particular of thickness 0.5 to 9 mm, of aluminum-copper-lithium alloy having improved and isotropic properties compared to those of the known products, in particular in terms of mechanical strength in the L and TL directions and toughness for the LT and TL directions over the entire thickness range. OBJECT OF THE INVENTION The object of the invention is a sheet having a thickness of 0.5 to 9 mm of essentially recrystallized granular structure of aluminum-based alloy comprising 3.8 to 3.2% by weight of Cu, 0.5 to 0.8% by weight of Li, 0.1 to 0.3% by weight of Ag, 0.2 to 0.7% by weight of Mg, 0.2 to 0.6% by weight of Mn, 0.01 to 0.15% by weight of Ti, an amount of Zn of less than 0.2% by weight, an amount of Fe and Si of less than or equal to 0.1% by weight each, and impurities inevitable at a content of less than or equal to 0.05% by weight each and 0.15% by weight in total, the said sheet being obtained by a process comprising casting, homogenization, hot rolling and optionally cold rolling, dissolution in solution , quenching and income. Another subject of the invention is the process for manufacturing a sheet according to the invention with a thickness of 0.5 to 9 mm in aluminum-based alloy in which, successively a) a liquid metal bath comprising 2.8 to 3.2% by weight of Cu, 0.5 to 0.8% by weight of Li, 0.1 to 0.3% by weight of Ag, 0.2 to 0.7% by weight of Mg 0.2 to 0.6 wt.% Mn, 0.01 to 0.15 wt.% Ti, Zn less than 0.2 wt.%, Fe and Si less than or equal to at 0.1% by weight each, and unavoidable impurities at a content of less than or equal to 0.05% by weight each and 0.15% by weight in total, b) casting a plate from said bath of liquid metal c) said plate is homogenized at a temperature between 480 ° C and 535 ° C; d) laminating said plate by hot rolling and optionally cold rolling into a sheet having a thickness between 0.5 mm and 9 mm; e) dissolving at a temperature of between 450 ° C and 535 ° C and quenching said sheet; 4 h) the sheet is controlledly tensile with a permanent deformation of 0.5 to 5%, the total cold deformation after dissolution and quenching being less than 15%; i) an income is made comprising heating at a temperature between 130 and 170 ° C and preferably between 150 and 160 ° C for 5 to 100 hours and preferably 40 to 40 hours. Yet another object of the invention is the use of a sheet according to the invention in an aircraft fuselage panel. DESCRIPTION OF THE FIGURES FIG. 1 - Curves R obtained in the L-T direction on sheets having a thickness of 4 to 5 mm for specimens with a width of 760 mm. Figure 2 - R curves obtained in the direction L-T on sheets of thickness 1.5 to 2.5 mm for specimens of width 760 mm. DESCRIPTION OF THE INVENTION Unless otherwise indicated, all the indications concerning the chemical composition of the alloys are expressed as a percentage by weight based on the total weight of the alloy. The term 1.4 Cu means that the copper content expressed in% by weight is multiplied by 1.4. The designation of alloys is in accordance with the regulations of The Aluminum Association, known to those skilled in the art. Unless otherwise stated, the definitions of the metallurgical states given in the European standard EN 515 apply. The static tensile mechanical characteristics, in other words the ultimate tensile strength Rin, the conventional yield stress at 0.2% elongation Rp0.2, 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 the EN 485-1 standard. In the context of the present invention, the term "substantially uncrystallized granular structure" refers to a granular structure such that the recrystallization rate at 1/2 thickness is less than 30% and preferably less than 10% and is called essentially recrystallized granular structure. a granular structure such that the recrystallization rate at 1/2 thickness is greater than 70% and preferably greater than 90%. The recrystallization rate is defined as the surface fraction on a metallographic section occupied by recrystallized grains.
    [0005] The grain sizes are measured according to ASTM E112. A curve giving the effective stress intensity factor as a function of the effective crack extension, known as the R curve, is determined according to ASTM E 561. The critical stress intensity factor Kc, in others 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 at the beginning of the monotonic load, to the critical load . These two values are calculated for a specimen of the required form. Kapp represents the Kco factor corresponding to the specimen that was used to perform the R curve test. Keff represents the Kc factor corresponding to the specimen that was used to perform the R curve test. of effective stress intensity for an effective crack extension Aaeff of 60 mm. Unless otherwise stated, the crack size at the end of the pre-fatigue cracking stage is W / 3 for M (T) type specimens, where W is the specimen width as defined in ASTM E561.
    [0006] Unless otherwise specified, the definitions of EN 12258 apply. The copper content of the products according to the invention is between 2.8 and 3.2% by weight. In an advantageous embodiment of the invention, the copper content is between 2.9 and 3.1% by weight. The lithium content of the products according to the invention is between 0.5 and 0.8% by weight and preferably between 0.55% and 0.75% by weight. Advantageously, the lithium content is at least 0.6% by weight. In one embodiment of the invention, the lithium content is between 0.64% and 0.73% by weight. The addition of lithium may contribute to the increase in strength and toughness, a too high or too low content does not provide a high value of toughness and / or a sufficient yield strength. The magnesium content of the products according to the invention is between 0.2 and 0.7% by weight, preferably between 0.3 and 0.5% by weight and preferably between 0.35 and 0.45% by weight. in weight. The manganese content is between 0.2 and 0.6% by weight and preferably between 0.25 and 0.35% by weight. In one embodiment of the invention, the manganese content is at most 0.45% by weight. The addition of manganese in the claimed amount controls the granular structure while avoiding the adverse effect on toughness that would generate too high a content. The silver content is between 0.1 and 0.3% by weight. In an advantageous embodiment of the invention, the silver content is between 0.15 and 0.28% by weight. The titanium content is between 0.01 and 0.15% by weight. Advantageously, the titanium content is at least 0.02% by weight and preferably at least 0.03% by weight.
    [0007] In an advantageous embodiment of the invention, the titanium content is at most 0.1% by weight and preferably at most 0.05% by weight. The addition of titanium helps to control the granular structure, especially during casting. The iron and silicon contents are each at most 0.1% by weight. In an advantageous embodiment of the invention, the iron and silicon contents are at most 0.08% and preferably at most 0.04% by weight. A controlled and limited iron and silicon content contributes to the improvement of the compromise between mechanical resistance and damage tolerance.
    [0008] The zinc content is less than 0.2% by weight and preferably less than 0.1% by weight. The zinc content is advantageously less than 0.04% by weight. The unavoidable impurities are maintained at a content of not more than 0.05% by weight each and 0.15% by weight in total. In particular, the zirconium content is less than or equal to 0.05% by weight, preferably less than or equal to 0.04% by weight and preferably less than or equal to 0.03% by weight. The method of manufacturing the sheets according to the invention comprises steps of production, casting, rolling, dissolution, quenching, controlled pulling and tempering. In a first step, 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 into a rolling plate form. The rolling plate is then homogenized at a temperature between 480 ° C and 535 ° and preferably between 490 ° C and 530 ° C and preferably between 500 ° C and 520 ° C. The homogenization time is preferably between 5 and 60 hours. In the context of the invention, a homogenization temperature that is too low or the absence of homogenization does not make it possible to achieve improved and isotropic properties compared to those of known products, in particular in terms of mechanical strength in L and TL directions and toughness for the LT and TL directions over the entire thickness range. After homogenization, the rolling plate is generally cooled to room temperature before being preheated for hot deformation. Preheating aims to achieve a temperature preferably between 400 and 500 ° C for deformation by hot rolling. The hot rolling and optionally cold rolling is performed so as to obtain a sheet thickness of 0.5 to 9 mm. Advantageously, during hot rolling, a temperature of greater than 400 ° C. is maintained up to a thickness of 20 mm and preferably a temperature of greater than 450 ° C. up to a thickness of 20 mm. Intermediate heat treatments during rolling and / or after rolling can be carried out in some cases. However, preferably, the process does not include any intermediate heat treatment during rolling and / or after rolling. The sheet thus obtained is then put into solution by heat treatment between 450 and 535 ° C, preferably between 490 ° C and 530 ° C and preferably between 500 ° C and 520 ° C, preferably for 5 min to 2 ° C. hours, then soaked. Advantageously, the dissolution time is at most 1 hour in order to minimize the surface oxidation. It is known to those skilled in the art that the precise conditions of dissolution must be chosen according to the thickness and the composition so as to solubilize the hardening elements. The sheet then undergoes cold deformation by controlled traction with a permanent deformation of 0.5 to 5% and preferably of 1 to 3%. Known steps such as rolling, flattening, deflashing, straightening and shaping may optionally be carried out after dissolution and quenching and before or after the controlled pull, however the total cold deformation after dissolution and quenching. must remain less than 15% and preferably less than 10%. High cold deformation after dissolution and quenching cause the appearance of many shear bands passing through several grains, these shear bands being undesirable.
    [0009] Typically, the quenched sheet may be subjected to a step of wrinkling or planing, before or after the controlled pull. Here, the term "deflashing / planing" means a cold deformation step without permanent deformation or with a permanent deformation less than or equal to 1%, to improve the flatness.
    [0010] An income is achieved comprising heating at a temperature between 130 and 170 ° C and preferably between 150 and 160 ° C for 5 to 100 hours and preferably 10 to 40 hours. Preferably, the final metallurgical state is a T8 state. In one embodiment of the invention, a short heat treatment is performed after controlled pulling and before tempering so as to improve the formability of the sheets. The sheets can thus be shaped by a process such as stretch-forming before being returned. The granular structure of the sheets according to the invention is essentially recrystallized. The combination of the composition according to the invention and the transformation parameters makes it possible to control the anisotropy index of the recrystallized grains. Thus the sheets according to the invention are such that the grain anisotropy index measured half thickness according to ASTM standard E112 by the intercepts method in the L / TC plane is less than 20, preferably less than 15 and preferably less than 10. Advantageously for sheets whose thickness is less than or equal to 3 mm , the grain anisotropy index measured at mid-thickness according to ASTM standard E112 by the intercepts method in the L / TC plane is less than or equal to 8, preferably less than or equal to 6 and preferably less than or The plates according to the invention have advantageous properties irrespective of the thickness of the products. The sheets according to the invention, the thickness of which is between 0.5 and 9 mm and particularly between 1.5 and 6 mm, advantageously have, in the T8 state, at least one of the following pairs of properties - a Kapp plane stress toughness. , measured on specimens of the CCT760 (2ao = 253 mm), in the LT and in the TL direction of at least 140 MPa-Vm and preferably at least 150 MPa-Vm and a Rp0.2 limit in the directions L and TL of at least 360 MPa and preferably at least 365 MPa, - a toughness in plane strain Kr60, measured on specimens of the CCT760 type (2ao = 253 mm), in the direction LT and in the TL direction greater than 190 MPa-Im and preferably greater than 200 MPa and a breaking strength Rm in directions L and TL of at least 410 MPa and preferably at least 415 MPa, and at least one following properties: - a ratio between the toughness in plane stress Kapp, measured on specimens 25 of the CCT760 type (2ao = 253 mm), in the TL and LT directions, Kapp (TL) / Kapp (LT), of between 0.85 and 1.15 and preferably between 0.90 and 1, A ratio between the breaking strength Rm in the L and TL directions, Rm (L) / Rm (TL), less than 1.06 and preferably less than 1.05. Without being bound by any particular theory, the present inventors believe that the combination between the composition, especially the limited zirconium content, the addition of manganese and the selected amount of magnesium, and the process of transformation, including the homogenization temperature. and hot rolling, allows to obtain the advantageous properties claimed.
    [0011] The resistance to intergranular corrosion of the sheets according to the invention is high. In a preferred embodiment of the invention, the sheet of the invention can be used without plating. The use of sheets according to the invention in an aircraft fuselage panel is advantageous. The sheets according to the invention are also advantageous in aerospace applications such as the manufacture of rockets.
    [0012] Example In this example, sheets of Al-Cu-Li alloy were prepared. 7 plates whose composition is given in Table 1 were cast. Table 1. Composition in% by weight of ammonia alloys Cu Li Mg Zr Mn Ag Fe Si Ti A 3.2 0.73 0.68 0.14 <0.01 0.26 0.03 0.04 0.03 B 3.0 0.70 0.64 0.17 <0.01 0.27 0.02 0.03 0.03 C 3.0 0.73 0.35 0.15 <0.01 0.27 0, 02 0.03 0.03 D 2.7 0.75 0.58 0.14 <0.01 0.28 0.03 0.02 0.03 E 2.9 0.73 0.45 0.14 < 0.01 0.29 0.04 0.02 0.03 F 2.9 0.68 0.42 0.03 0.28 0.28 0.03 0.02 0.03 G 2.9 0.75 0.44 0.05 0.28 0.26 0.03 0.02 0.03 The plates were homogenized for 12 hours at 505 ° C. The plates were hot-rolled to obtain sheets having a thickness of between 4.2 and 6.3 mm. Some sheets were then cold rolled to a thickness of between 1.5 and 2.5 mm. The detail of the sheets obtained and the income conditions are given in table 2. 11 Table 2: detail of the sheets obtained and the conditions of income Sheet Thickness after Thickness after Period of income at 155 ° C hot rolling cold rolling (mm ) (h) (mm) A # 1 4.2 - 36 A # 2 4.4 1.5 36 B # 1 4.6 - 36 B # 2 4.4 1.5 36 C # 1 4.3 - 24 C # 2 4,4 1,5 24 D # 1 4,3 - 40 D42 6,3 2,5 40 E # 1 4,3 - 36 E # 2 6,3 2,5 36 F # 1 4, 2 - 28 F # 2 4,2 2,5 28 G # 1 4,2 - 28 G # 2 4,2 2,5 28 After hot rolling and possibly cold rolling, the sheets were dissolved at 505 ° C. C then plucked, pulled with a permanent elongation of 2% and returned. The 10 income conditions are not all the same because the increase of the elasticity limit with the duration of income differs from one alloy to another. We tried to obtain a "peak" elasticity limit while limiting the duration of income. The income conditions are given in Table 2. The granular structure of the samples was characterized from microscopic observation of the cross-sections after anodic oxidation under polarized light. The granular structure of the sheets was essentially non-recrystallized for all the sheets except for the plates D # 2 E # 2 F # 1, F # 2, G # 1 and G42 for which the granular structure was essentially recrystallized. For sheets whose granular structure was essentially recrystallized, the grain size was determined in the mid-thickness L / TC plane according to ASTM E112 by the intercepts method from the microscopic observation of cross-sections. after anodic oxidation under polarized light. The anisotropy index is the ratio of grain size measured in the L direction divided by the grain size measured in the TC direction. The results are shown in Table 3.
    [0013] Table 3: Measured grain sizes for samples whose granular structure was essentially recrystallized Sheet Metal Direction L (iim) Direction TC (Iim) Anisotropy index D # 2 1260 21 60 E # 2 1100 23 48 F # 1 540 59 9 F42 135 37 4 G41 G # 2 The samples were mechanically tested to determine their static mechanical properties as well as their toughness. The mechanical characteristics were measured in full thickness. The tensile yield strength, the ultimate strength and the elongation at break are given in Table 4. Table 4: Mechanical characteristics expressed in MPa (R0.2, Rrn) or in percent (A%) Sheet Rp0 , 2 (L) R (L) A% (L) Rp0.2 (TL) R (TL) A% (TL) Itni (TL) A 1 469 513 12.2 439 481 15.8 1, 07 A42 475 522 11.7 441 489 14.0 1.07 B # 1 431 483 13.5 419 462 16.1 1.05 B # 2 431 486 12.9 414 460 17.1 1.06 C41 430 471 13.6 411 455 15.5 1.04 C42 423 472 12.2 399 451 15.9 1.05 D41 420 462 13.0 384 428 16.3 1.08 D42 403 437 11.6 371 428 13.9 1.02 E # 1 453 487 12.5 428 464 15.9 1.05 E # 2 433 464 11.4 395 458 11.4 1.01 F # 1 392 430 12.5 369 420 12.4 1.02 F # 2 400 437 11.9 368 419 13.4 1.04 G # 1 402 432 13.4 372 424 12.7 1.02 G42 412 440 12.9 378 426 13.1 1.03 13 Table 5 summarizes the results of the toughness tests on CCT test specimens with a width of 760 mm for these samples. Table 5 results of the R curves for CCT test pieces of width 760 mm. Sheet Kapp Kr60 Kapp (TL) / [MPa-Vm] [MPa-Nim] Kapp (LT) TL LT TL LT A41 187 161 247 213 1.16 A # 2 160 114 210 151 1.40 B41 180 178 238 238 1 , 01 B42 167 124 223 166 1.35 C # 1 182 165 242 219 1.10 C42 154 127 203 162 1.21 D41 174 150 230 200 1.16 D42 147 151 196 201 0.97 E41 181 159 240 213 1 , 14 E42 137 164 181 219 0.84 F # 1 154 169 203 223 0.91 F # 2 158 168 208 224 0.94 G41 153 172 202 228 0.89 G # 2 158 172 208 229 0.92 The Figures 1 and 2 illustrate the remarkable toughness of Examples F and G according to the invention in particular in the LT direction. 14
    权利要求:
    Claims (13)
    [0001]
    REVENDICATIONS1. Sheet of thickness 0.5 to 9 mm of essentially recrystallized granular structure of aluminum-based alloy comprising 2.8 to 3.2% by weight of Cu, 0.5 to 0.8% by weight of Li, 0 , 1 to 0.3% by weight of Ag, 0.2 to 0.7% by weight of Mg, 0.2 to 0.6% by weight of Mn, 0.01 to 0.15% by weight of Ti , an amount of Zn of less than 0.2% by weight, an amount of Fe and Si of less than or equal to 0.1% by weight each, and unavoidable impurities with a content of less than or equal to 0.05% by weight each and 0.15% by weight in total, said sheet being obtained by a process comprising casting, homogenization, hot rolling and optionally cold rolling, dissolution, quenching and tempering.
    [0002]
    2. Sheet according to claim 1, the copper content is between 2.9 and 3.1% by weight.
    [0003]
    3. Sheet according to claim 1 or claim 2 whose lithium content is between 0.55 and 0.75% by weight and preferably between 0.64 and 0.73% by weight.
    [0004]
    4. Sheet according to any one of claims 1 to 3, the silver content is between 0.15 and 0.28% by weight.
    [0005]
    5. Sheet according to any one of claims 1 to 4, the magnesium content is between 0.3 and 0.5% by weight and preferably between 0.35 and 0.45% by weight.
    [0006]
    6. Sheet according to any one of claims 1 to 5, the zirconium content is less than or equal to 0.04% by weight and preferably less than or equal to 0.03% by weight. 16 3026747
    [0007]
    7. Sheet according to any one of claims 1 to 6, the manganese content is between 0.2 and 0.45% by weight and preferably between 0.25 and 0.45% by weight.
    [0008]
    8. Sheet according to any one of claims 1 to 7 characterized in that the grain anisotropy index measured at mid-thickness according to ASTM standard E112 by the intercepts method in the L / TC plane is less than 20, preferably less than 15 and preferably less than 10.
    [0009]
    9. Sheet according to any one of claims 1 to 8, the thickness of which is between 0.5 and 9 mm and particularly between 1.5 and 6 mm have at T8 at least one of the following pairs of properties: - a Kapp plane strain toughness, measured on specimens of the CCT760 type (2ao = 253 mm), in the LT direction and in the TL direction of at least 140 MPelm and preferably at least 150 MPelm and a Rp0.2 limit in the directions L and TL of at least 360 MPa and preferably at least 365 MPa, - a toughness in plane strain Kr60, measured on specimens of the CCT760 type (2ao = 253 mm), in the direction LT and in the TL direction greater than 190 MPelm and preferably greater than 200 MPelm and a breaking strength Rm in directions L and TL of at least 410 MPa and preferably at least 415 MPa, and at least one of the following properties: - a ratio of toughness in plane strain Kapp, measured on specimens of the CCT760 type (2ao = 253 mm), in the TL and LT directions, Kapp (TL) / Kapp (LT), between 0.85 and 1.15 and preferably between 0.90 and 1.10 a ratio between the breaking strength Rm in the directions L and TL, Rm (L) / Rm (TL), less than 1.06 and preferably less than 1.05.
    [0010]
    10. A method of manufacturing a sheet thickness of 0.5 to 9 mm according to any one of claims 1 to 8 wherein, successively a) is developed a bath of liquid metal to obtain an aluminum alloy comprising 2 8 to 3.2 wt% Cu, 0.5 to 0.8 wt% Li, 0.1 to 0.3 wt% Ag, 0.2 to 0.7 wt% Mg, 0.2 to 0.6 wt.% Mn, 0.01 to 0.15 wt.% Ti, Zn less than 0.2 wt.%, Fe and lower Si or equal to 0.1% by weight each, and unavoidable impurities at a content of less than or equal to 0.05% by weight each and 0.15% by weight in total, b) pouring a plate from said bath of liquid metal c) said plate is homogenized at a temperature between 480 ° C and 535 ° C; d) laminating said plate by hot rolling and optionally cold rolling into a sheet having a thickness between 0.5 mm and 9 mm; e) dissolving at a temperature of between 450 ° C and 535 ° C and quenching said sheet; h) the sheet is controlledly tensile with a permanent deformation of 0.5 to 5%, the total cold deformation after dissolution and quenching is less than 15%; i) an income is made comprising heating at a temperature between 130 and 170 ° C and preferably between 150 and 160 ° C for 5 to 100 hours and preferably 10 to 40 hours.
    [0011]
    11. The method of claim 10 wherein the homogenization temperature is between 490 ° C and 530 ° C and preferably between 500 ° C and 520 ° C.
    [0012]
    12. The method of claim 10 or claim 11 wherein during hot rolling, maintaining a temperature above 400 ° C up to the thickness of 20 mm and preferably a temperature above 450 ° C until the thickness 20 mm.
    [0013]
    13. Use of a sheet according to any one of claims 1 to 9 in an aircraft fuselage panel.
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    同族专利:
    公开号 | 公开日
    CN106795595A|2017-05-31|
    BR112017006071A2|2017-12-12|
    WO2016051099A1|2016-04-07|
    JP2017534757A|2017-11-24|
    JP6692803B2|2020-05-13|
    EP3201372B1|2021-01-27|
    FR3026747B1|2016-11-04|
    US20170306454A1|2017-10-26|
    US11174535B2|2021-11-16|
    EP3201372A1|2017-08-09|
    CA2961712A1|2016-04-07|
    BR112017006071B1|2021-05-04|
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    法律状态:
    2015-10-19| PLFP| Fee payment|Year of fee payment: 2 |
    2016-04-08| PLSC| Publication of the preliminary search report|Effective date: 20160408 |
    2016-10-25| PLFP| Fee payment|Year of fee payment: 3 |
    2017-10-25| PLFP| Fee payment|Year of fee payment: 4 |
    2018-10-25| PLFP| Fee payment|Year of fee payment: 5 |
    2019-10-25| PLFP| Fee payment|Year of fee payment: 6 |
    2020-10-26| PLFP| Fee payment|Year of fee payment: 7 |
    2021-10-25| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1402237A|FR3026747B1|2014-10-03|2014-10-03|ALUMINUM-COPPER-LITHIUM ALLOY ISOTROPES FOR THE MANUFACTURE OF AIRCRAFT FUSELAGES|FR1402237A| FR3026747B1|2014-10-03|2014-10-03|ALUMINUM-COPPER-LITHIUM ALLOY ISOTROPES FOR THE MANUFACTURE OF AIRCRAFT FUSELAGES|
    BR112017006071-0A| BR112017006071B1|2014-10-03|2015-10-01|isotropic aluminum-copper-lithium alloy sheets for the manufacture of aircraft fuselages|
    EP15784082.8A| EP3201372B1|2014-10-03|2015-10-01|Isotropic sheets of aluminium-copper-lithium alloys for the fabrication of fuselages of aircrafts and method of manuacturing same|
    US15/515,891| US11174535B2|2014-10-03|2015-10-01|Isotropic plates made from aluminum-copper-lithium alloy for manufacturing aircraft fuselages|
    JP2017518117A| JP6692803B2|2014-10-03|2015-10-01|Aluminum-copper-lithium alloy isotropic sheet metal for aircraft fuselage manufacturing|
    CA2961712A| CA2961712A1|2014-10-03|2015-10-01|Isotropic aluminium-copper-lithium alloy sheets for producing aeroplane fuselages|
    CN201580053855.3A| CN106795595A|2014-10-03|2015-10-01|Isotropism aluminum bronze lithium alloy plate for manufacturing airframe|
    PCT/FR2015/052634| WO2016051099A1|2014-10-03|2015-10-01|Isotropic aluminium-copper-lithium alloy sheets for producing aeroplane fuselages|
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