• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
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  • 优先权
    • 专利摘要:
    The subject of the invention is a process for manufacturing a wrought aluminum alloy product comprising the following steps: a) casting of an alloy plate comprising, as a percentage by weight, Cu: 2.1 to 2.8 ; Li: 1.1 to 1.7; Mg: 0.2 to 0.9; Mn: 0.2 to 0.6; Ti: 0.01 - 0.2; Ag <0.1; Zr <0.08; Fe and Si ≤ 0.1 each; unavoidable impurities ≤ 0.05% each and 0.15% in total; remains aluminum; b) homogenization of said plate at 480-520 ° C for 5 to 60 hours; c) hot rolling and optionally cold rolling of said plate homogenized into a sheet; d) dissolving the sheet at 470-520 ° C for 15 minutes to 4 hours; e) quenching the dissolved sheet; f) traction in a controlled manner of the sheet dissolved and quenched with a permanent deformation of 1 to 6%; g) tempering of the drawn sheet metal by heating to a temperature of at least 160 ° C. for a maximum duration of 30 hours.
    公开号:FR3075078A1
    申请号:FR1762674
    申请日:2017-12-20
    公开日:2019-06-21
    发明作者:Pablo Lorenzino
    申请人:Constellium Issoire SAS；
    IPC主号:
    专利说明:

    IMPROVED MANUFACTURING PROCESS OF ALUMINUM-COPPER-LITHIUM ALLOY SHEET FOR MANUFACTURING AIRCRAFT FUSELAGE
    Field of the invention
    The present invention generally relates to the methods of manufacturing aluminum-based 2XXX alloy sheets comprising lithium, in particular such improved methods particularly suited to the constraints of the aeronautical and space industry. The methods according to the invention are especially suitable for the manufacture of fuselage sheets.
    State of the art
    A continuous research effort is carried out in the aeronautical and space industries both in terms of the composition of the alloys and in terms of the manufacturing processes. Al-Cu-Li alloys are particularly advantageous for manufacturing rolled aluminum alloy products, in particular fuselage elements, because they offer compromises of properties generally higher than conventional alloys, in particular in terms of compromise between the fatigue, damage tolerance and mechanical strength. This allows in particular to reduce the thickness of wrought products made of Al-Cu-Li alloy, thus further maximizing the reduction in weight that they bring. On the other hand, when manufacturing such products, it is important to take into account the constraints of the aeronautical industry where any saving of time in the manufacture of semi-finished products constitutes a significant competitive advantage.
    Document EP 1 966 402 B2 discloses in particular fuselage sheets with particularly advantageous properties, these sheets being produced using an alloy comprising in particular, in percentage by weight, Cu: 2.1 to 2.8; Li: 1.1 to 1.7; Ag: 0.1 to 0.8; Mg: 0.2 to 0.6; Mn: 0.2 to 0.6; Zr <0.04; Fe and Si <0.1 each; unavoidable impurities <0.05 each and 0.15 in total; remains aluminum. As detailed in Example 2 below, such a product cannot however be subjected to a manufacturing process optimized in terms of tempering time without a deterioration in its properties, in particular its compromise between mechanical strength and toughness.
    There is a need for products made of aluminum-copper-lithium alloy exhibiting an excellent compromise of properties, in particular in terms of antinomic properties such as the properties of static mechanical strength and those of toughness. Said products must also have good thermal stability, good resistance to corrosion, while being able to be obtained by a simple process, economical and capable of providing a significant competitive advantage.
    Object of the invention
    The subject of the invention is a process for manufacturing a wrought aluminum alloy product comprising the following steps:
    at. casting of an alloy plate comprising, in percentage by weight: Cu: 2.1 to 2.8; Li: 1.1 to 1.7; Mg: 0.2 to 0.9; Mn: 0.2 to 0.6; Ag <0.1; Zr <0.08; Ti 0.01 to 0.2; Fe and Si <0.1 each; unavoidable impurities <0.05 each and 0.15 in total; remains aluminum;
    b. homogenization of said plate at 480-520 ° C for 5 to 60 hours;
    vs. hot rolling and optionally cold rolling of said plate homogenized into a sheet;
    d. dissolving the sheet at 470-520 ° C for 15 minutes to 4 hours;
    e. quenching of the sheet in solution;
    f. controlled pulling of the dissolved and quenched sheet with a permanent deformation of 1 to 6%;
    g. tempering of the fractionated sheet by heating to a temperature of at least 160 ° C for a maximum of 30 hours.
    Description of the figures
    Figure 1: Curve R in the direction T-L (CCT760 test piece) for a sheet of alloy A Figure 2: Toughness Ktôo (T-L) as a function of the elastic limit Rpo, 2 (TL) for a sheet of alloy A
    Figure 3: Curve R in the direction T-L (CCT760 test piece) for a sheet of alloy B
    Figure 4: Tenacity Kq as a function of the temperature of the second tempering step during a two-stage tempering applied to a 2A97 alloy product (according to Zhong et al., 2011) Figure 5: Tenacity Kq as a function of temperature of income applied to an 8090 alloy product (according to Duncan and Martin, 1991)
    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. 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 density depends on the composition and is determined by calculation rather than by a weight measurement method. The values are calculated in accordance with the procedure of The Aluminum Association, which is described on pages 2-12 and 2-13 of "Aluminum Standards and Data". The definitions of metallurgical states are given in European standard EN 515 (1993).
    The static mechanical characteristics in tension, in other words the tensile strength Rm, the conventional elastic limit at 0.2% elongation Rpo, 2, and the elongation at break A%, are determined by a tensile test according to standard NF EN ISO 6892-1 / ASTM E8 -E8M-13, the sampling and the direction of the test being defined by standard EN 485-1.
    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 standard E561-10 (2010). The critical stress intensity factor 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 length of initial crack at the beginning of the monotonic charge, at the critical load. These two values are calculated for a test piece of the required shape. Ka PP represents the factor Kco corresponding to the test piece which was used to carry out the curve test R. Ketr represents the factor Kc corresponding to the test piece which was used to carry out the curve test R. Aaeff (max ) represents the crack extension of the last valid point of the curve R. The length of the curve R - namely the maximum crack extension of the curve - is an important parameter in itself, in particular for the design of fuselage . Kr60 represents the effective stress intensity factor for an effective crack extension Aaeff of 60 mm.
    Unless otherwise stated, the definitions of EN 12258 (2012) apply.
    Seeking to further optimize the products suitable for use in the aeronautical industry both in terms of properties and of manufacturing processes, the inventors have found quite surprisingly that, unlike other alloys of the 2xxx family containing Li , it was possible to produce an Al-Cu-Li alloy product with optimized properties using a simple and particularly economical process. Thus, the method according to the invention comprises in particular a step of tempering the fractionated sheet by heating to a temperature of at least 160 ° C. for a maximum duration of 30 hours. At the end of the process of the invention, the product of particular composition has an equal or different toughness of less than 8%, preferably less than 5%, more preferably still of less than 4% or even 2%, of that of the same product manufactured according to a conventional process of the prior art, in particular a process identical to that of the invention with the exception of tempering which would typically be tempering by heating at around 152 ° C. for around 48 hours. At the end of the process of the invention, the product of particular composition advantageously has a conventional elastic limit Rp0,2 (TL) equal or different from less than 8%, preferably less than 5%, more preferably still less 4% or even 2%, of that of the same product manufactured according to a conventional process of the prior art, in particular a process identical to that of the invention with the exception of tempering which would typically be tempering by heating to around 152 ° C for about 48 hours.
    The process for manufacturing a wrought aluminum alloy product according to the invention firstly comprises a step of casting a particular alloy plate. Thus, the alloy comprises, as a percentage by weight, Cu: 2.1 to 2.8; Li: 1.1 to 1.7; Mg: 0.2 to 0.9; Mn: 0.2 to 0.6; Ti 0.01 to 0.2; Ag <0.1; Zr <0.08; Fe and Si <0.1 each; unavoidable impurities <0.05 each and 0.15 in total; remains aluminum.
    In an advantageous embodiment, the aluminum alloy plate comprises from 2.2 to 2.6% by weight of Cu, preferably from 2.3 to 2.5% by weight. The inventors have discovered that if the copper content is more than 2.8% or even 2.6% or even 2.5% by weight, the toughness properties may in some cases drop rapidly, while, if the content copper is less than 2.1% or even 2.2% or even 2.3% by weight, the mechanical strength may be too low.
    The aluminum alloy plate comprises 1.1 to 1.7% by weight of lithium. Preferably, it comprises from 1.2 to 1.6% by weight of Li, or also from 1.25 to 1.55% by weight. A lithium content higher than 1.7% or even 1.6% or even 1.55% by weight can cause problems of thermal stability. A lithium content of less than 1.1% or even 1.2% or even 1.25% by weight can lead to inadequate mechanical strength and a lower gain in terms of density.
    The aluminum alloy plate comprises from 0.2 to 0.9% by weight of magnesium. According to an advantageous mode, the aluminum alloy plate comprises from 0.25 to 0.75% by weight of Mg.
    The aluminum alloy plate comprises from 0.01 to 0.2% by weight of titanium. The addition of titanium in different forms, Ti, TiB or TiC makes it possible in particular to control the granular structure during the casting plate. According to an advantageous mode, the aluminum alloy plate comprises from 0.01 to 0.10% by weight of Ti.
    The plate further comprises less than 0.1% by weight of silver. Advantageously, the aluminum alloy plate comprises less than 0.05% by weight of Ag, preferably less than 0.04% by weight.
    The aluminum alloy plate comprises from 0.2 to 0.6% by weight of manganese. Preferably, it comprises from 0.25 to 0.45% by weight of Mn. The aluminum alloy plate comprises less than 0.08% by weight of zirconium. In an even more preferred mode, it comprises less than 0.05% by weight of Zr, preferably less than 0.04% by weight and, even more preferably, less than 0.03% or even 0.01% by weight . A low zirconium content makes it possible to improve the toughness of the Al-Cu-Li-Ag-MgMn alloys according to the invention; in particular, the length of the curve R is significantly increased. The use of manganese instead of zirconium in order to control the granular structure has several additional advantages such as obtaining a recrystallized structure and isotropic properties, in particular for a thickness of 0.8 to 12.7 mm. Advantageously, the recrystallization rate of the products according to the invention is greater than 80%, preferably greater than 90%.
    Iron and silicon generally affect the toughness properties. The amount of iron should be limited to 0.1% by weight (preferably 0.05% by weight) and the amount of silicon should be limited to 0.1% by weight (preferably 0.05% by weight ).
    Inevitable impurities should be limited to 0.05% by weight each and 0.15% by weight in total.
    The manufacturing method according to the invention further comprises a step of homogenizing the casting plate at a temperature of 480 to 520 ° C. for 5 to 60 hours and, preferably, this step is carried out between 490 and 510 ° C. for 8 to 20 hours. Homogenization temperatures above 520 ° C tend to reduce the toughness performance in some cases.
    The homogenized plate is then hot rolled and optionally cold rolled into a sheet. In an advantageous embodiment, the hot rolling is carried out at an initial temperature of 420 to 490 ° C, preferably from 440 to 470 ° C. The hot rolling is preferably carried out to obtain a thickness of between approximately 4 and 12.7 mm. For a thickness of approximately 4 mm or less, a cold rolling step can be optionally added, if necessary. In the case of sheet metal production, the sheet obtained has a thickness of between 0.8 and 12.7 mm, and the invention is more advantageous for sheets of 1.6 to 9 mm thick, and even more advantageous for sheets from 2 to 7 mm thick.
    The laminated product is then dissolved, preferably by heat treatment at a temperature of 470 to 520 ° C for 15 min to 4 hours, then typically quenched with water at room temperature.
    The product dissolved is then subjected to a tensile step in a controlled manner with a permanent deformation of 1 to 6%. Preferably, the traction in a controlled manner is carried out with a permanent deformation of between 2.5 and 5%.
    Unexpectedly, the inventors have discovered that the alloy product according to the invention can be manufactured using an optimized process, the step of tempering said process being able to be carried out at particularly high temperatures, in particular above 160 ° C and even more so that the duration of the income can be, consequently, greatly reduced. Quite surprisingly, this process optimization can be carried out without deterioration of the properties of the product, in particular without affecting the conventional limit elasticity compromise Rp0.2 (LT) - Kapp toughness (TL).
    Thus, the towed product is subjected to a step of tempering by a particular heating at a temperature of at least 160 ° C for a maximum duration of 30 hours. Preferably the tempering can even be carried out at a temperature of at least 162 ° C, preferably of at least 165 ° C and, more preferably still, of at least 170 ° C for a maximum duration of 30 hours, advantageously 28 hours even 25h or 20h.
    In a preferred embodiment, the tempering is carried out at an equivalent time t, at 165 ° C. of between 15 and 35 hours, preferably between 20 and 30 hours. The equivalent time t, at 165 ° C is defined by the formula:
    -16400 / T) dt exp (-16400 / Tref) where T (in Kelvin) is the instantaneous metal processing temperature, which changes with time t (in hours), and T re f is a reference temperature set at 428 K. ti is expressed in hours. The constant Q / R = 16400 K is derived from the activation energy for the diffusion of Cu, for which the value Q = 136100 J / mol was used.
    At the end of the process according to the invention, the product of particular composition has a Kapp toughness (TL) equal or different from less than 8%, preferably less than 5%, more preferably still from less than 4 or even 2%, of that of the same product manufactured according to a conventional process of the prior art, in particular a process identical to that of the invention with the exception of tempering which would typically be tempering by heating at around 152 ° C. for around 48 hours. At the end of the process of the invention, the product of particular composition also advantageously has a conventional elastic limit Rp0,2 (LT) equal or different from less than 8%, preferably less than 5%, more preferably still from less than 4 or even 2%, of that of the same product manufactured according to a conventional process of the prior art, in particular a process identical to that of the invention with the exception of the tempering which would typically be tempering by heating to about 152 ° C for about 48 hours.
    According to a preferred embodiment, the method according to the invention makes it possible to obtain a product having at least one, advantageously at least two or even three or more of the following properties:
    conventional yield strength, Rp0.2 (L), of at least 330 MPa, preferably at least 335 MPa and, more preferably still, at least 340 MPa;
    conventional yield strength, Rp0.2 (LT), of at least 325 MPa; preferably at least 330 MPa and, more preferably still, at least 335 MPa;
    toughness under plane stress, Kapp (T-L), of at least 130 MPaVm; preferably at least 135 MPaVm and, more preferably still, at least 140 MPaVm;
    effective stress intensity factor for an effective crack extension Aa e ff of 60 mm, Kr60 (TL), of at least 175 MPaVm; preferably at least 180 MPaVm and, more preferably still, at least 185 MPaVm.
    In addition, according to a preferred embodiment compatible with the preceding modes, the method according to the invention makes it possible to obtain a product having very good thermal stability. Thus, advantageously the product obtained directly at the end of the process according to the invention, that is to say after the tempering by heating at a temperature of at least 160 ° C for a maximum duration of 30 hours , and at the end of a heat treatment of 100 h at 85 ° C., has a toughness under plane stress, Kapp (TL), and / or an effective stress intensity factor for an effective crack extension Aa e ff of 60 mm, Kr60 (TL), which does not differ by more than 7%, preferably not more than 5% and, more preferably still not more than 4% or even 2%.
    Advantageously, the product according to the invention is a sheet and more preferably a thin sheet, more preferably still a thin sheet of fuselage. The product according to the invention can therefore advantageously be used in an aircraft fuselage panel.
    These aspects, as well as others of the invention, are explained in more detail with the aid of the following illustrative and nonlimiting examples.
    Examples
    Example 1
    The alloy A of composition presented in table 1 is an alloy according to the invention.
    Table 1- Chemical composition (% by weight)
    Casting reference Yes Fe Cu mn mg Zr Li Ag Ti AT 0.01 0.03 2.3 0.3 0.3 <0.01 1.4 <0.01 0.03
    Analysis on SOES solid (optical emission spectrometry by sparks).
    Average over three samples.
    The process used for manufacturing the sheet of alloy A was as follows: a plate of thickness approximately 400 mm in alloy A was poured, homogenized at 508 ° C for approximately 12 hours then scalped. The plate was hot rolled to obtain a sheet having a thickness of 4 mm. It was dissolved at around 500 ° C and then quenched in cold water. The sheet was then fractionated with a permanent elongation of 3 to 4%. The following revenues were made on different samples of the sheet: 48h-152 ° C, 40h-155 ° C, 30h-160 ° C and 25h-165 ° C.
    For each of the tempering conditions, a part of the sheets was subjected to a thermal stability test of 100 h at 80 ° C.
    The toughness of the sheets was characterized by R curve tests according to standard ASTM E561-10 (2010). The tests were carried out with a CCT test specimen (W = 760 mm, 2a0 = 253 mm) full thickness. The set of results is reported in Table 2 and illustrated by Figure 1.
    Table 2 - R curve summary data
    Income conditions Kr (MPa m) to Aa e ff (mm) 10 20 30 40 50 60 70 80 48h at 152 ° C 104.4 133.3 152.9 166.4 179.2 190.9 201.9 212.3 40hà155 ° C 116.7 141.2 157.5 172.7 183.7 192.5 203.3 212.2 30hà160 ° C 102.1 131.7 152.4 166.7 179.9 191.6 199.6 209.7 25h at 165 ° C 101.8 130.5 149.2 164.9 177.0 188.9 199.3 209.4 48h at 152 ° C + 100h at 85 ° C 104.7 133.9 153.6 167.3 181.1 192.8 202.0 212.3 40h at 155 ° C + 100h at 85 ° C 100.4 132.7 153.2 167.9 181.3 193.2 203.3 213.1 30h at 160 ° C + 100h at 85 ° C 98.5 134.0 154.6 170.5 183.3 194.1 204.4 215.4 25h at 165 ° C + 100h at 85 ° C 108.2 134.6 153.1 168.2 180.7 191.5 201.3 210.9
    Samples were taken at full thickness to measure the static mechanical characteristics in tension and the toughness in the T-L direction. The test pieces 5 used for the toughness measurement were CCT760 geometry test pieces: 760mm (L) x 1250mm (TL).
    The results are reported in Table 3 and illustrated by FIG. 2. FIG. 2 shows the maintenance of a good compromise between the elastic limit and the toughness, in particular the maintenance of excellent toughness whatever the conditions of returned.
    Table 3 - Mechanical properties and toughness tests
    Income conditions Rp0.2 (LT) in MPa Rm (LT) in MPa AT%(L) Kapp (T-L) in MPaVm 48h at 152 ° C 334 393 12.9 145.0 40h at 155 ° C 338 395 13.0 144.7 30h at 160 ° C 337 394 13.0 143.0 25h at 165 ° C 343 397 12.6 142.9 48h at 152 ° C + 1000h at 85 ° C 337 394 12.3 144.7 40h at 155 ° C + 100h at 85 ° C 349 406 13.1 145.4 30h at 160 ° C + 100h at 85 ° C 348 403 12.7 146.9 25h at 165 ° C + 1000h at 85 ° C 350 404 12.0 144.0
    Example 2
    The alloy B with the composition presented in Table 4 is a reference alloy known in particular from document EP 1 966 402 B2.
    Table 4 - Chemical composition (% by weight)
    Casting reference Yes Fe Cu mn mg Zr Li Ag Ti B 0.03 0.03 2.4 0.3 0.3 <0.01 1.4 0.34 0.02
    Analysis on SOES solid (optical emission spectrometry by sparks).
    Average over three samples.
    The process used for the manufacture of the sheet of alloy B was as follows: a plate of thickness approximately 400 mm of alloy B was poured, homogenized at 500 ° C for approximately 12 hours then scalped. The plate was hot rolled to obtain a sheet having a thickness of 5 mm. It was dissolved at around 500 ° C and then quenched in cold water. The sheet was then pulled with a permanent elongation of 1 to 5%. The following revenues were made on different samples of the sheet: 48h-152 ° C, and 25h-165 ° C.
    The toughness of the sheets was characterized by tests of R curves according to standard ASTM E561-10 (2010). The tests were carried out with a CCT test specimen (W = 760 mm, 2a0 = 253 mm) full thickness. The set of results is reported in Table 5 and illustrated in Figure 3.
    Table 5 - R curve summary data
    Income conditions Kr (MPaMn) to Aa e ff (mm) 10 20 30 40 50 60 70 80 48h at 152 ° C 101 130 150 166 179 190 200 209 25h at 165 ° C 99 119 135 147 157 164 171 177
    Samples were taken at full thickness to measure the static mechanical characteristics in tension and the toughness in the T-L direction. The test pieces used for the toughness measurement were CCT760 geometry test pieces: 760mm (L) x 1250mm (TL)
    The results are reported in Table 4.
    Table 3 - Mechanical properties and toughness tests
    Income conditions Rp0.2 (LT) in MPa Rm (LT) inMPa AT%(L) Kapp (T-L) in MPaVm 48hàl52 ° C 343 411 11.2 142 25h at 165 ° C 367 428 10.3 123
    Example 3
    The effects of high temperature tempering have also been studied in the literature. This example uses the data presented in the articles cited below, highlighting the known impact on the toughness of a high temperature tempering such as that of the invention on aluminum alloys comprising in particular copper and lithium. :
    _ Effects of aging treatment on strength and fracture toughness of 2A97 aluminumlithium alloy, S. Zhong et al., The Chinese Journal of Nonferrous Metals, Vol 21, n3, 2011 _ The effect of aging temperature on the fracture toughness of an 8090 Al- Li alloy, KJ Duncan and JW Martin, Journal of Materials Science Letters, Vol 10, Issue 18, pp 1098-1100, 1991
    The article by Zhong et al. relates to the Al-Cu-Li 2A97 alloy. It highlights the decrease in toughness induced by the increase in temperature of the second tempering step during a two-step tempering on a 2A97 alloy product. Figure 4 shows the following income conditions:
    - 16h at 135 ° C + 32h at 135 ° C;
    4 p.m. at 135 ° C + 6 p.m. at 150 ° C (6% decrease in toughness compared to bi-level tempering 4 p.m. at 135 ° C + 32 h at 135 ° C);
    16h at 135 ° C + 6h at 175 ° C (decrease in toughness of 16% compared to a bi-level income 16h at 135 ° C + 32h at 135 ° C).
    The article by Duncan and Martin relates to the Al-Li 8090 alloy. The objective of this article was to study the variation of the toughness with the increase in the tempering temperature in a material of constant hardness (properties similar statics). It has thus been demonstrated a decrease in toughness induced by the increase in tempering temperature on an 8090 alloy product for the same tempering state (same hardness). Figure 5 shows the following income conditions:
    - 320 hours at 30 ° C;
    78h at 150 ° C (decrease in toughness of 9% compared to an income of 320h at 130 ° C);
    32h at 170 ° C (decrease in toughness of 20% compared to an income of 320h at 130 ° C);
    8.3h at 190 ° C (decrease in toughness of 27% compared to an income of 320h at 130 ° C).
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. A method of manufacturing a wrought aluminum alloy product comprising the following steps:
    at. casting of an alloy plate comprising:
    [2" id="c-fr-0002]
    2.1 to 2.8% by weight of Cu;
    1.1 to 1.7% by weight of Li;
    0.2 to 0.9% by weight of Mg;
    0.2 to 0.6% by weight of Mn;
    0.01 to 0.2% by weight of Ti less than 0.1% by weight of Ag;
    less than 0.08% by weight of Zr;
    an amount of Fe and Si less than or equal to 0.1% by weight each, and unavoidable impurities at a content less than or equal to 0.05% by weight each and 0.15% by weight in total;
    remains aluminum;
    b. homogenization of said plate at 480-520 ° C for 5 to 60 hours;
    vs. hot rolling and optionally cold rolling of said plate homogenized into a sheet;
    d. dissolving the sheet at 470-520 ° C for 15 minutes to 4 hours;
    e. quenching of the sheet in solution;
    f. controlled pulling of the dissolved and quenched sheet with a permanent deformation of 1 to 6%;
    g. tempering of the fractionated sheet by heating to a temperature of at least 160 ° C, preferably at least 165 ° C, for a maximum period of 30 hours, preferably 25 hours.
    2. The manufacturing method according to claim 1 wherein step g of tempering is carried out at an equivalent time ti at 165 ° C between 15 and 35 hours, preferably between 20 and 30 hours, the equivalent time ti at 165 ° C being defined by the formula:
    _ j exp (-16400 / T) dt t / _ exp (-16400 / Tref) where T (in Kelvin) is the instantaneous metal processing temperature, which changes over time t (in hours), and T re f is a reference temperature fixed at 428 K.
    [3" id="c-fr-0003]
    3. Manufacturing process according to any one of the preceding claims, in which the aluminum alloy plate comprises from 2.2 to 2.6% by weight of Cu, preferably from 2.3 to 2.5% by weight.
    [4" id="c-fr-0004]
    4. Manufacturing process according to any one of the preceding claims, in which the aluminum alloy plate comprises from 1.2 to 1.6% by weight of Li, preferably from 1.25 to 1.55% by weight.
    [5" id="c-fr-0005]
    5. Manufacturing process according to any one of the preceding claims, in which the aluminum alloy plate comprises from 0.25 to 0.75% by weight of Mg.
    [6" id="c-fr-0006]
    6. The manufacturing method according to claim 1, in which the aluminum alloy plate comprises from 0.25 to 0.45% by weight of Mn.
    [7" id="c-fr-0007]
    7. The manufacturing method according to claim 1, in which the aluminum alloy plate comprises less than 0.05% by weight of Ag, preferably less than 0.04% by weight.
    [8" id="c-fr-0008]
    8. The manufacturing method according to any one of the preceding claims wherein the aluminum alloy plate comprises less than less than 0.05% by weight of Zr, preferably less than 0.04% by weight.
    [9" id="c-fr-0009]
    9. Manufacturing process according to any one of the preceding claims, in which the hot rolling is carried out at an initial temperature of 420 to 490 ° C, preferably from 440 to 470 ° C.
    [10" id="c-fr-0010]
    10. The manufacturing method according to any one of the preceding claims wherein Ja traction in a controlled manner of the sheet is carried out with a permanent deformation between 2.5 and 5%.
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    WO2021111069A1|2021-06-10|Aluminum-copper-lithium alloy thin sheets with improved toughness, and process for manufacturing an aluminum-copper-lithium alloy thin sheet
    同族专利:
    公开号 | 公开日
    JP2021508357A|2021-03-04|
    FR3075078B1|2020-11-13|
    WO2019122639A1|2019-06-27|
    EP3728667A1|2020-10-28|
    CN111492074A|2020-08-04|
    CA3085811A1|2019-06-27|
    US20210071285A1|2021-03-11|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    WO2006131627A1|2005-06-06|2006-12-14|Alcan Rhenalu|High-strength aluminum-copper-lithium sheet metal for aircraft fuselages|
    WO2010055225A1|2008-11-14|2010-05-20|Alcan Rhenalu|Products made of an aluminium-copper-lithium alloy|
    WO2011141647A2|2010-05-12|2011-11-17|Alcan Rhenalu|Aluminum-copper-lithium alloy for lower surface element|
    WO2013054013A1|2011-10-14|2013-04-18|Constellium France|Improved method for processing sheet metal made of an al-cu-li alloy|
    US8771441B2|2005-12-20|2014-07-08|Bernard Bes|High fracture toughness aluminum-copper-lithium sheet or light-gauge plates suitable for fuselage panels|
    FR2894985B1|2005-12-20|2008-01-18|Alcan Rhenalu Sa|HIGH-TENACITY ALUMINUM-COPPER-LITHIUM PLASTER FOR AIRCRAFT FUSELAGE|
    FR2925523B1|2007-12-21|2010-05-21|Alcan Rhenalu|ALUMINUM-LITHIUM ALLOY IMPROVED LAMINATED PRODUCT FOR AERONAUTICAL APPLICATIONS|
    FR3014448B1|2013-12-05|2016-04-15|Constellium France|ALUMINUM-COPPER-LITHIUM ALLOY PRODUCT FOR INTRADOS ELEMENT WITH IMPROVED PROPERTIES|CN110423926B|2019-07-29|2020-12-29|中国航发北京航空材料研究院|Heat-resistant aluminum-lithium alloy and preparation method thereof|
    FR3104172A1|2019-12-06|2021-06-11|Constellium Issoire|Improved toughness aluminum-copper-lithium alloy thin sheets and manufacturing process|
    CN111945084A|2020-08-01|2020-11-17|安徽家园铝业有限公司|Heat treatment process of aluminum alloy section|
    CN113388760A|2021-06-17|2021-09-14|上海华峰铝业股份有限公司|Al-Cu-Mn-Zr aluminum alloy, aluminum alloy composite plate and preparation method and application thereof|
    法律状态:
    2018-12-26| PLFP| Fee payment|Year of fee payment: 2 |
    2019-06-21| PLSC| Publication of the preliminary search report|Effective date: 20190621 |
    2019-12-26| PLFP| Fee payment|Year of fee payment: 3 |
    2020-12-27| PLFP| Fee payment|Year of fee payment: 4 |
    2021-12-27| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1762674|2017-12-20|
    FR1762674A|FR3075078B1|2017-12-20|2017-12-20|IMPROVED MANUFACTURING PROCESS OF ALUMINUM-COPPER-LITHIUM ALLOY SHEETS FOR THE MANUFACTURE OF AIRCRAFT FUSELAGE|FR1762674A| FR3075078B1|2017-12-20|2017-12-20|IMPROVED MANUFACTURING PROCESS OF ALUMINUM-COPPER-LITHIUM ALLOY SHEETS FOR THE MANUFACTURE OF AIRCRAFT FUSELAGE|
    CN201880082024.2A| CN111492074A|2017-12-20|2018-12-17|Improved method for producing aluminium-copper-lithium alloy plates for the production of aircraft fuselages|
    JP2020530363A| JP2021508357A|2017-12-20|2018-12-17|Improved method of manufacturing aluminum-copper-lithium alloy sheet metal for manufacturing airplane fuselage|
    US16/955,424| US20210071285A1|2017-12-20|2018-12-17|Improved process for manufacturing sheet metal made of aluminum-copper-lithium alloy for manufacturing an airplane fuselage|
    CA3085811A| CA3085811A1|2017-12-20|2018-12-17|Improved process for manufacturing sheets made of aluminium-copper-lithium alloy for aircraft fuselage manufacture|
    EP18833951.9A| EP3728667A1|2017-12-20|2018-12-17|Improved process for manufacturing sheets made of aluminium-copper-lithium alloy for aircraft fuselage manufacture|
    PCT/FR2018/053316| WO2019122639A1|2017-12-20|2018-12-17|Improved process for manufacturing sheets made of aluminium-copper-lithium alloy for aircraft fuselage manufacture|
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