EP2569456B1 - Aluminium-kupfer-lithium-legierung für niedrigeres oberflächenelement - Google Patents
Aluminium-kupfer-lithium-legierung für niedrigeres oberflächenelement Download PDFInfo
- Publication number
- EP2569456B1 EP2569456B1 EP11725129.8A EP11725129A EP2569456B1 EP 2569456 B1 EP2569456 B1 EP 2569456B1 EP 11725129 A EP11725129 A EP 11725129A EP 2569456 B1 EP2569456 B1 EP 2569456B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- product
- weight
- mpa
- thickness
- product according
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 239000001989 lithium alloy Substances 0.000 title description 6
- -1 Aluminum-copper-lithium Chemical compound 0.000 title description 4
- 229910000733 Li alloy Inorganic materials 0.000 title description 4
- 229910045601 alloy Inorganic materials 0.000 claims description 37
- 239000000956 alloy Substances 0.000 claims description 37
- 229910052804 chromium Inorganic materials 0.000 claims description 8
- 229910052744 lithium Inorganic materials 0.000 claims description 8
- 229910052726 zirconium Inorganic materials 0.000 claims description 8
- 229910052782 aluminium Inorganic materials 0.000 claims description 7
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 7
- 229910052748 manganese Inorganic materials 0.000 claims description 7
- 238000004519 manufacturing process Methods 0.000 claims description 7
- 229910052709 silver Inorganic materials 0.000 claims description 7
- 229910052802 copper Inorganic materials 0.000 claims description 6
- 229910052735 hafnium Inorganic materials 0.000 claims description 6
- 239000012535 impurity Substances 0.000 claims description 6
- 229910052706 scandium Inorganic materials 0.000 claims description 6
- 229910052719 titanium Inorganic materials 0.000 claims description 5
- 238000010438 heat treatment Methods 0.000 claims description 4
- 229910052742 iron Inorganic materials 0.000 claims description 4
- 229910052749 magnesium Inorganic materials 0.000 claims description 4
- 229910052710 silicon Inorganic materials 0.000 claims description 4
- 238000005242 forging Methods 0.000 claims description 3
- 238000001953 recrystallisation Methods 0.000 claims description 3
- 238000005096 rolling process Methods 0.000 claims description 3
- 239000004411 aluminium Substances 0.000 claims 1
- 238000001125 extrusion Methods 0.000 claims 1
- 239000010949 copper Substances 0.000 description 13
- 239000011572 manganese Substances 0.000 description 12
- 239000011777 magnesium Substances 0.000 description 11
- 238000000265 homogenisation Methods 0.000 description 9
- 238000000034 method Methods 0.000 description 8
- 239000000203 mixture Substances 0.000 description 7
- XEEYBQQBJWHFJM-UHFFFAOYSA-N iron Substances [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 6
- 239000000126 substance Substances 0.000 description 5
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 4
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 description 4
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 4
- 238000005266 casting Methods 0.000 description 4
- 238000010276 construction Methods 0.000 description 4
- 239000004332 silver Substances 0.000 description 4
- 239000011701 zinc Substances 0.000 description 4
- 239000002970 Calcium lactobionate Substances 0.000 description 3
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 description 3
- 238000005259 measurement Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 239000003381 stabilizer Substances 0.000 description 3
- 239000003351 stiffener Substances 0.000 description 3
- 230000035882 stress Effects 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 2
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 2
- 229910001338 liquidmetal Inorganic materials 0.000 description 2
- 238000010791 quenching Methods 0.000 description 2
- 230000000171 quenching effect Effects 0.000 description 2
- 239000010703 silicon Substances 0.000 description 2
- 238000009987 spinning Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910001148 Al-Li alloy Inorganic materials 0.000 description 1
- 229910017539 Cu-Li Inorganic materials 0.000 description 1
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 description 1
- JFBZPFYRPYOZCQ-UHFFFAOYSA-N [Li].[Al] Chemical compound [Li].[Al] JFBZPFYRPYOZCQ-UHFFFAOYSA-N 0.000 description 1
- 230000004913 activation Effects 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000005097 cold rolling Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000004090 dissolution Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 229940082150 encore Drugs 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 238000005496 tempering Methods 0.000 description 1
- 238000009864 tensile test Methods 0.000 description 1
- 229910052720 vanadium Inorganic materials 0.000 description 1
- 239000010455 vermiculite Substances 0.000 description 1
- 229910052725 zinc Inorganic materials 0.000 description 1
Images
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/12—Alloys based on aluminium with copper as the next major constituent
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
- C22F1/057—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
Definitions
- the present invention generally relates to aluminum alloy products and, more particularly, to such products, their methods of manufacture and use, particularly in the aerospace industry.
- Aluminum-lithium alloys are very interesting in this respect, since lithium can reduce the density of aluminum by 3% and increase the modulus of elasticity by 6% for each weight percent of lithium added.
- the US Patent 5,032,359 discloses a large family of aluminum-copper-lithium alloys in which the addition of magnesium and silver, in particular between 0.3 and 0.5 percent by weight, makes it possible to increase the mechanical strength.
- the US Patent 5,198,045 discloses a family of alloys comprising (in% by weight) (2,4-3,5) Cu, (1,35-1,8) Li, (0,25-0,65) Mg, (0.25 -0.65) Ag, (0.08-0.25) Zr. Wrought products made with these alloys combine a density of less than 2.64 g / cm 3 and a compromise between the mechanical strength and the interesting toughness.
- the patent US 7,229,509 discloses a family of alloys comprising (in% 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, (up to 0.4) Zr or other affinants such as Cr, Ti, Hf, Sc and V.
- the examples presented have a compromise between the mechanical strength and toughness improved but their density is greater than 2.7 g / cm 3 .
- the patent EP 1,966,402 discloses an alloy containing no zirconium for fuselage plates of substantially recrystallized structure comprising (in% by weight) (2.1-2.8) Cu, (1.1-1.7) Li, (0, 2-0.6) Mg, (0.1-0.8) Ag, (0.2-0.6) Mn.
- the patent EP 1,891,247 discloses an alloy for fuselage plates comprising (in% by weight) (3.0-3.4) Cu, (0.8-1.2) Li, (0.2-0.6) Mg, ( 0.2-0.5) Ag and at least one of Zr, Mn, Cr, Sc, Hf and Ti, wherein the Cu and Li contents are Cu + 5/3 Li ⁇ 5.2 .
- the patent US5,455,003 discloses a process for producing aluminum-copper-lithium alloys having improved strength and toughness properties at cryogenic temperature. This method applies in particular to an alloy comprising (in% by weight) (2.0-6.5) Cu, (0.2-2.7) Li, (0-4.0) Mg, (0- 4.0) Ag, (0-3.0) Zn.
- International demand WO 2010/055225 discloses a manufacturing method in which a bath of liquid metal comprising 2.0 to 3.5 wt.% Cu, 1.4 to 1.8 wt.% Li, 0.1 to 0.5 wt. weight of Ag, 0.1 to 1.0% by weight of Mg, 0.05 to 0.18% by weight of Zr, 0.2 to 0.6% by weight of Mn and at least one selected element among Cr, Sc, Hf and Ti, the amount of the element, if selected, being from 0.05 to 0.3% by weight for Cr and for Sc, 0.05 to 0.5% by weight for Hf and from 0.01 to 0.15% by weight for Ti, the remainder being aluminum and unavoidable impurities; casting a raw form from the bath of liquid metal and homogenizing said raw form at a temperature between 515 ° C and 525 ° C so that the time equivalent to 520 ° C for homogenization is between 5 and 20 hours.
- alloy AA2196 comprising (in% by weight) (2.5-3.3) Cu, (1.4-2.1) Li, (0.25-0.8) Mg, is known , 25-0.6) Ag, (0.04-0.18) Zr and at most 0.35 Mn.
- Yet another object of the invention is the use of a product according to the invention as an aircraft wing-bottom element.
- Figure 1 Shape of the profile of example 1. The dimensions are given in mm. The thickness of the sole is 26.3 mm.
- alloys are 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 method of measuring weight.
- 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 the metallurgical states are given in the European standard EN 515.
- the static mechanical characteristics in other words the ultimate ultimate tensile strength R m , the tensile yield strength Rp 0.2 and the elongation at break A, are determined by a tensile test. according to standard EN 10002-1 or NF EN ISO 6892-1, the location to which the parts are taken and their meaning being defined by the EN 485-1 standard.
- the stress intensity factor (K Q ) is determined according to ASTM E 399.
- the ASTM E 399 gives in 9.1.3 and 9.1.4 criteria to determine if K Q is a valid K 1C value .
- K 1C is always a value K Q the reciprocal is not true.
- the criteria of paragraphs 9.1.3 and 9.1.4 of the standard ASTM E399 are not always verified, however for a given test piece geometry, the K Q values presented are always comparable with each other, the specimen geometry making it possible to obtain a valid value of K 1C that is not always accessible. given the constraints related to the dimensions of the sheets or profiles.
- the thickness of the selected test piece is a thickness deemed suitable by those skilled in the art to obtain a valid value of K 1C .
- the values of the apparent tensile strength factor (K app ) and the tensile stress intensity factor (K c ) are as defined in ASTM E561.
- the thickness of the profiles is defined according to EN 2066: 2001: the cross section is divided into elementary rectangles of dimensions A and B; A being always the largest dimension of the elementary rectangle and B can be considered as the thickness of the elementary rectangle. The sole is the elementary rectangle with the largest dimension A.
- a "structural element” or “structural element” of a mechanical construction is called a mechanical part for which the static and / or dynamic mechanical properties are particularly important for the performance of the structure, and for which a structural calculation is usually prescribed or realized. These are typically elements whose failure is likely to endanger the safety of the said construction, its users, its users or others.
- these structural elements include the elements that make up the fuselage (such as fuselage skin (fuselage skin in English), stiffeners or stringers, bulkheads, fuselage (circumferential frames), wings (such as wing skin), stiffeners (stiffeners), ribs (ribs) and spars) and empennage including horizontal stabilizers and vertical stabilizers horizontal or vertical stabilizers, as well as floor beams, seat tracks and doors.
- fuselage such as fuselage skin (fuselage skin in English
- stiffeners or stringers such as fuselage skin
- bulkheads fuselage (circumferential frames)
- wings such as wing skin
- stiffeners stiffeners (stiffeners), ribs (ribs) and spars
- empennage including horizontal stabilizers and vertical stabilizers horizontal or vertical stabilizers, as well as floor beams, seat tracks and doors.
- the copper content of the alloy for which the surprising effect is observed is between 2.12 and 2.37% by weight, preferably between 2.12 or 2.20 and 2.37% or 2.30% by weight. weight.
- the lithium content is between 1.3 and 1.6% or even between 1.30 and 1.60% by weight. In an advantageous embodiment, the lithium content is between 1.35 and 1.55% by weight.
- the silver content is between 0.1 and 0.5% by weight.
- the silver content is between 0.15 and 0.35% by weight. In one embodiment of the invention, which has the advantage of minimizing the density, the silver content is at most 0.25% by weight.
- the magnesium content is between 0.2 and 0.6% by weight and preferably it is less than 0.4% by weight.
- the simultaneous addition of zirconium and manganese is an essential feature of the invention. The zirconium content must be between 0.05 and 0.15% by weight and the manganese content must be between 0.1 and 0.5% by weight.
- the alloy also contains 0.01 to 0.12 wt.% Ti to control grain size during casting.
- the alloy according to the invention may also optionally contain at least one element selected from Cr, Sc, and Hf, the amount of the element, if it is chosen, being from 0.05 to 0.3% by weight for Cr and for Sc, 0.05 to 0.5% by weight for Hf. It is preferable to limit the content of unavoidable impurities in the alloy so as to achieve the most favorable damage tolerance properties.
- the unavoidable impurities include iron and silicon, these elements have a content of less than 0.1% by weight each and preferably a content of less than 0.08% by weight and 0.06% by weight for iron and silicon , respectively, the other impurities have a content of less than 0.05% by weight each and 0.15% by weight in total.
- the zinc content is preferably less than 0.04% by weight.
- the composition is adjusted so as to obtain a density at room temperature of less than 2.65 g / cm 3, even more preferably less than 2.64 g / cm 3, in some cases even less than 2.63 g / cm 3. .
- the alloy according to the invention can be used to manufacture spun, rolled and / or forged products.
- the alloy according to the invention is used to manufacture sheets.
- the products according to the invention preferably have a substantially non-recrystallized structure, having a recrystallization rate of less than 30% and preferably less than 15%.
- the spun products and in particular the extruded profiles obtained by the process according to the invention are advantageous.
- the thick sections that is to say the thickness of at least one elementary rectangle is greater than 8 mm, and preferably greater than 12 mm or 15 mm are the most advantageous.
- the products according to the invention have a very high tenacity.
- the products according to the invention are obtained by a process comprising the steps of casting, homogenization, hot deformation, dissolution, quenching, stress relief and tempering.
- the homogenization temperature is preferably between 480 and 540 ° C for 5 to 60 hours.
- the homogenization temperature is between 515 ° C and 525 ° C so that the equivalent time t (eq) at 520 ° C for homogenization is between 5 and 20 hours and preferably between 6 and 15 hours.
- the formula giving t (eq) takes into account the heating and cooling phases.
- the homogenization temperature is about 520 ° C and the duration of treatment is between 8 and 20 hours.
- the raw form is generally cooled to room temperature before being preheated for hot deformation.
- Preheating aims to achieve an initial deformation temperature preferably between 400 and 500 ° C and preferably of the order of 450 ° C to 480 ° C allowing the deformation of the raw form.
- Hot deformation is typically performed by spinning, rolling and / or forging to obtain a spun, rolled and / or forged product.
- the product thus obtained is then put in solution preferably by heat treatment between 490 and 530 ° C for 15 min to 8 h, then quenched typically with water.
- the product then undergoes a controlled pull of 1 to 5% and preferably of at least 2%.
- cold rolling is carried out with a reduction of between 5% and 15% before the controlled pulling step.
- Known steps such as planing, straightening, shaping may optionally be performed before or after the controlled pull.
- An income is produced at a temperature between 120 and 170 ° C for 5 to 100 h, preferably between 150 and 160 ° C for 20 to 60 h.
- the preferred metallurgical states are for the plates the states T84 and T89 and for the profiles the state T8511.
- the products according to the invention can be used as structural elements, in particular in aeronautical construction.
- the products according to the invention are used as an aircraft wing surface element.
- Table 1 Chemical composition (% by weight) ⁇ / u> Reference Yes Fe Cu mn mg Zn Zr Li Ag Ti AT 0.03 0.05 2.37 0.29 0.37 0.01 0.13 1.37 0.28 0.04 B 0.03 0.05 2.50 0.31 0.35 0.01 0.13 1.43 0.25 0.04 VS 0.03 0.06 2.62 0.30 0.35 0.01 0.14 1.42 0.24 0.04
- Alloys A, B and C were cast as billets.
- the billets were homogenized for 8 hours at 520 ° C. the equivalent time at 520 ° C. was 9.5 hours.
- the billets were heated to 450 ° C +/- 40 ° C and then hot spun to obtain profiles according to the Figure 1 .
- the profiles thus obtained were dissolved at 524 +/- 2 ° C, quenched with water temperature below 40 ° C, and fractionated with a permanent elongation of between 2 and 5%.
- the profiles received an income of 30 hours at 152 ° C corresponding to the maximum value of toughness.
- the samples were taken on the sole.
- Alloys D, E, F, G and H were cast as plates.
- the plates were homogenized for 8 h at 520 ° C. After homogenization, the plates were heated and then hot rolled to obtain sheets of thickness 14, 25 or 60 mm.
- the sheets thus obtained were dissolved at 524 ⁇ 1 ° / -2 ° C., quenched with water of temperature below 40 ° C., and triturated with a permanent elongation of between 3 and 5%.
- the sheets were tempered for 30 to 60 hours at 155 ° C. Samples were taken at medium thickness for 14 mm and 25 mm thick plates and at mid-thickness and quarter-thickness for 60 mm thick plates.
- the specimens used for the tenacity measurements had a thickness of 12.5 mm for 14 mm thick sheets, 20 mm for 25 mm thick sheets, 25 mm for 60 mm thick sheets, measured thickness and 40 mm for 60 mm thick sheets measured at mid-thickness. R-curve measurements were also made at mid-thickness for certain income conditions.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Metal Rolling (AREA)
- Heat Treatment Of Steel (AREA)
- Forging (AREA)
- Conductive Materials (AREA)
- Extrusion Of Metal (AREA)
- Footwear And Its Accessory, Manufacturing Method And Apparatuses (AREA)
Claims (9)
- Strangpress-, Walz- und/oder Schmiedeerzeugnis, dessen Rekristallisationsgrad weniger als 30 % beträgt, aufweisend eine Legierung auf Aluminiumbasis enthaltend:2,12 bis 2,37 Gew.-% Cu,1,3 bis 1,6 Gew.-% Li,0,1 bis 0,5 Gew.-% Ag,0,2 bis 0,6 Gew.-% Mg,0,05 bis 0,15 Gew.-% Zr,0,1 bis 0,5 Gew.-% Mn,0,01 bis 0,12 Gew.-% Ti,wahlweise mindestens ein Element ausgewählt unter Cr, Sc und Hf, wobei die Menge des Elements, falls gewählt, 0,05 bis 0,3 Gew.-% für Cr und Sc, 0,05 bis 0,5 Gew.-% für Hf beträgt,
eine Menge Fe und Si von jeweils höchstens 0,1 Gew.-% und unvermeidbare Verunreinigungen mit einem Gehalt von jeweils höchstens 0,05 Gew.-% und insgesamt 0,15 Gew.-%. - Erzeugnis nach Anspruch 1, aufweisend 2,20 bis 2,30 Gew.-% Cu, 1,35 bis 1,55 Gew.-% Li, 0,15 bis 0,35 Gew.-% Ag, 0,2 bis 0,4 Gew.-% Mg.
- Erzeugnis nach Anspruch 1 oder Anspruch 2, dessen Rekristallisationsgrad weniger als 15 % beträgt.
- Erzeugnis nach irgendeinem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass es sich um ein Profil handelt, bei dem die Dicke mindestens eines Elementarrechtecks mehr als 8 mm und vorzugsweise mehr als 12 mm beträgt.
- Erzeugnis nach irgendeinem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass es sich um ein gewalztes Erzeugnis handelt, dessen Dicke mindestens 14 mm und vorzugsweise mindestens 20 mm beträgt.
- Erzeugnis nach Anspruch 6, welches in halber Dicke im Zustand T84(a) bei einer Dicke zwischen 20 mm und 40 mm eine Dehngrenze Rp0,2 in L-Richtung von mindestens 410 MPa und vorzugsweise mindestens 420 MPa und eine Bruchzähigkeit KQ(L-T) von mindestens
- Verfahren zur Herstellung eines Erzeugnisses nach irgendeinem der Ansprüche 1 bis 7, bei dem:(a) eine Rohform aus einer Legierung nach einem der Ansprüche 1 bis 3 gegossen wird,(b) die Rohform bei 480 bis 540°C für 5 bis 60 Stunden homogenisiert wird,(c) die Rohform durch Strangpressen, Walzen und/oder Schmieden mit einer anfänglichen Warmumformungstemperatur von 400 bis 500°C warmumgeformt wird, um ein Walz- und/oder Schmiedeerzeugnis zu erhalten,(d) das Erzeugnis bei 490 bis 530°C für 15 Minuten bis 8 Stunden lösungsgeglüht wird,(e) das Erzeugnis abgeschreckt wird,(f) das Erzeugnis mit einer bleibenden Verformung von 1 bis 5 % kontrolliert gereckt wird,(g) das Erzeugnis durch Erwärmen auf 120 bis 170°C für 5 bis 100 Stunden ausgelagert wird.
- Verwendung eines Erzeugnisses nach irgendeinem der Ansprüche 1 bis 7 als Flügelunterseitenelement eines Flugzeugs.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1002033A FR2960002B1 (fr) | 2010-05-12 | 2010-05-12 | Alliage aluminium-cuivre-lithium pour element d'intrados. |
US33444610P | 2010-05-13 | 2010-05-13 | |
PCT/FR2011/000290 WO2011141647A2 (fr) | 2010-05-12 | 2011-05-11 | Alliage aluminium-cuivre-lithium pour element d'intrados |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2569456A2 EP2569456A2 (de) | 2013-03-20 |
EP2569456B1 true EP2569456B1 (de) | 2017-09-06 |
Family
ID=43086197
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP11725129.8A Active EP2569456B1 (de) | 2010-05-12 | 2011-05-11 | Aluminium-kupfer-lithium-legierung für niedrigeres oberflächenelement |
Country Status (7)
Country | Link |
---|---|
US (1) | US20110278397A1 (de) |
EP (1) | EP2569456B1 (de) |
CN (1) | CN102985573A (de) |
BR (1) | BR112012028658A2 (de) |
CA (1) | CA2798480C (de) |
FR (1) | FR2960002B1 (de) |
WO (1) | WO2011141647A2 (de) |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2558564B1 (de) | 2010-04-12 | 2018-07-18 | Arconic Inc. | Aluminium-lithium-legierungen der serie 2xxx mit geringem stärkeunterschied |
FR2997706B1 (fr) | 2012-11-08 | 2014-11-07 | Constellium France | Procede de fabrication d'un element de structure d'epaisseur variable pour construction aeronautique |
FR3014448B1 (fr) | 2013-12-05 | 2016-04-15 | Constellium France | Produit en alliage aluminium-cuivre-lithium pour element d'intrados a proprietes ameliorees |
FR3014904B1 (fr) | 2013-12-13 | 2016-05-06 | Constellium France | Produits files pour planchers d'avion en alliage cuivre lithium |
FR3026747B1 (fr) * | 2014-10-03 | 2016-11-04 | Constellium France | Toles isotropes en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselages d'avion |
US11313019B2 (en) | 2015-12-23 | 2022-04-26 | Norsk Hydro Asa | Method for producing a heat treatable aluminum alloy with improved mechanical properties |
FR3047253B1 (fr) | 2016-02-03 | 2018-01-12 | Constellium Issoire | Toles epaisses en alliage al - cu - li a proprietes en fatigue ameliorees |
EP3504086B1 (de) | 2016-08-26 | 2022-08-03 | Shape Corp. | Warmformverfahren zum transversalen biegen eines extrudierten aluminiumträgers zum warmformen eines karosseriebauteils |
US11072844B2 (en) | 2016-10-24 | 2021-07-27 | Shape Corp. | Multi-stage aluminum alloy forming and thermal processing method for the production of vehicle components |
FR3075078B1 (fr) | 2017-12-20 | 2020-11-13 | Constellium Issoire | Procede de fabrication ameliore de toles en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselage d'avion |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5032359A (en) | 1987-08-10 | 1991-07-16 | Martin Marietta Corporation | Ultra high strength weldable aluminum-lithium alloys |
US5455003A (en) | 1988-08-18 | 1995-10-03 | Martin Marietta Corporation | Al-Cu-Li alloys with improved cryogenic fracture toughness |
US5151136A (en) * | 1990-12-27 | 1992-09-29 | Aluminum Company Of America | Low aspect ratio lithium-containing aluminum extrusions |
US5198045A (en) | 1991-05-14 | 1993-03-30 | Reynolds Metals Company | Low density high strength al-li alloy |
RU2180930C1 (ru) * | 2000-08-01 | 2002-03-27 | Государственное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" | Сплав на основе алюминия и способ изготовления полуфабрикатов из этого сплава |
US20030226935A1 (en) * | 2001-11-02 | 2003-12-11 | Garratt Matthew D. | Structural members having improved resistance to fatigue crack growth |
WO2004106570A1 (en) | 2003-05-28 | 2004-12-09 | Pechiney Rolled Products | New al-cu-li-mg-ag-mn-zr alloy for use as stractural members requiring high strength and high fracture toughness |
EP2017361A1 (de) * | 2005-06-06 | 2009-01-21 | Alcan Rhenalu | Aluminium-Kupfer-Lithium-Blech mit hoher Zähigkeit für Flugzeugrumpf |
CN101189353A (zh) * | 2005-06-06 | 2008-05-28 | 爱尔康何纳吕公司 | 用于飞机机身的高韧度的铝-铜-锂合金板材 |
FR2894985B1 (fr) | 2005-12-20 | 2008-01-18 | Alcan Rhenalu Sa | Tole en aluminium-cuivre-lithium a haute tenacite pour fuselage d'avion |
FR2925523B1 (fr) * | 2007-12-21 | 2010-05-21 | Alcan Rhenalu | Produit lamine ameliore en alliage aluminium-lithium pour applications aeronautiques |
FR2938553B1 (fr) * | 2008-11-14 | 2010-12-31 | Alcan Rhenalu | Produits en alliage aluminium-cuivre-lithium |
-
2010
- 2010-05-12 FR FR1002033A patent/FR2960002B1/fr active Active
-
2011
- 2011-05-11 EP EP11725129.8A patent/EP2569456B1/de active Active
- 2011-05-11 BR BR112012028658A patent/BR112012028658A2/pt not_active Application Discontinuation
- 2011-05-11 CA CA2798480A patent/CA2798480C/fr active Active
- 2011-05-11 CN CN2011800340703A patent/CN102985573A/zh active Pending
- 2011-05-11 WO PCT/FR2011/000290 patent/WO2011141647A2/fr active Application Filing
- 2011-05-12 US US13/106,395 patent/US20110278397A1/en not_active Abandoned
Non-Patent Citations (1)
Title |
---|
None * |
Also Published As
Publication number | Publication date |
---|---|
WO2011141647A2 (fr) | 2011-11-17 |
WO2011141647A3 (fr) | 2012-11-01 |
US20110278397A1 (en) | 2011-11-17 |
CA2798480A1 (fr) | 2011-11-17 |
BR112012028658A2 (pt) | 2016-08-09 |
FR2960002B1 (fr) | 2013-12-20 |
CN102985573A (zh) | 2013-03-20 |
CA2798480C (fr) | 2018-01-16 |
FR2960002A1 (fr) | 2011-11-18 |
EP2569456A2 (de) | 2013-03-20 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP2569456B1 (de) | Aluminium-kupfer-lithium-legierung für niedrigeres oberflächenelement | |
EP2364378B1 (de) | Produkte aus aluminium-kupfer-lithium-legierung | |
EP3077559B1 (de) | Aluminium-/kupfer-/lithiumlegierungsmaterial für ein flügelunterseitenelement mit verbesserten eigenschaften und verfahren zu dessen herstellung | |
EP2449142B1 (de) | Aluminium-kupfer-lithium-legierung mit verbesserten mechanische beständigkeit und zähigkeit | |
EP2766503B1 (de) | Verbessertes verfahren zum bearbeiten von metallblechen aus einer al-cu-li-legierung | |
EP2655680B1 (de) | Aluminium-kupfer-lithium-legierung mit verbesserter druckfestigkeit und beständigkeit | |
EP1492895B1 (de) | Produkte aus al-zn-mg-cu-legierung | |
EP2710163B1 (de) | Aluminium-magnesium-lithiumlegierung mit erhöhter zähigkeit | |
EP1766102B1 (de) | Verfahren zur herstellung hochfester und ermüdungsfester aluminiumlegierungsprodukte | |
EP3011068B1 (de) | Bogenrückenstrukturelement aus einer aluminium-kupfer-lithium-legierung | |
EP3201371B1 (de) | Verfahren zur herstellung eines knetproduktes aus einer aluminium-magnesium-lithium legierung, knetprodukt und vervendung des knetproduktes | |
FR2907796A1 (fr) | Produits en alliage d'aluminium de la serie aa7000 et leur procede de fabrication | |
FR2907466A1 (fr) | Produits en alliage d'aluminium de la serie aa7000 et leur procede de fabrication | |
EP3384061B1 (de) | Aluminium-kupfer-lithium-legierung mit verbesserter mechanischer festigkeit und erhöhter zähigkeit | |
EP3201372B1 (de) | Isotropische bleche aus aluminium-lithium-kupfer legierung für die herstellung von flugzeugrümpfen und herstellungsverfahren davon | |
EP2836620B1 (de) | Aluminium-kupfer-lithium-legierung mit verbesserter schlagzähigkeit | |
EP3788178B1 (de) | Aluminium-kupfer-lithium-legierung mit verbesserter kompressionsfestigkeit und erhöhter beständigkeit | |
RU2581953C1 (ru) | ВЫСОКОПРОЧНЫЙ ДЕФОРМИРУЕМЫЙ СПЛАВ НА ОСНОВЕ АЛЮМИНИЯ СИСТЕМЫ Al-Zn-Mg-Cu ПОНИЖЕННОЙ ПЛОТНОСТИ И ИЗДЕЛИЕ, ВЫПОЛНЕННОЕ ИЗ НЕГО | |
EP3610047B1 (de) | Aluminium-kupfer-lithium-legierungsprodukte | |
FR3026411A1 (fr) | Procede de fabrication de produits en alliage aluminium magnesium lithium | |
FR3026410A1 (fr) | Produit corroye en alliage aluminium magnesium lithium |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
17P | Request for examination filed |
Effective date: 20121206 |
|
AK | Designated contracting states |
Kind code of ref document: A2 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
DAX | Request for extension of the european patent (deleted) | ||
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: CONSTELLIUM ISSOIRE |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
INTG | Intention to grant announced |
Effective date: 20170331 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: EP Ref country code: AT Ref legal event code: REF Ref document number: 926017 Country of ref document: AT Kind code of ref document: T Effective date: 20170915 |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: FG4D Free format text: LANGUAGE OF EP DOCUMENT: FRENCH |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R096 Ref document number: 602011041293 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: NL Ref legal event code: MP Effective date: 20170906 |
|
REG | Reference to a national code |
Ref country code: LT Ref legal event code: MG4D |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: FI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170906 Ref country code: HR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170906 Ref country code: NO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20171206 Ref country code: SE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170906 Ref country code: LT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170906 |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: MK05 Ref document number: 926017 Country of ref document: AT Kind code of ref document: T Effective date: 20170906 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: ES Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170906 Ref country code: BG Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20171206 Ref country code: GR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20171207 Ref country code: LV Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170906 Ref country code: RS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170906 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: NL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170906 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: RO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170906 Ref country code: PL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170906 Ref country code: CZ Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170906 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 8 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170906 Ref country code: EE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170906 Ref country code: AT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170906 Ref country code: SM Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170906 Ref country code: SK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170906 Ref country code: IS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20180106 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 602011041293 Country of ref document: DE |
|
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170906 |
|
26N | No opposition filed |
Effective date: 20180607 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170906 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170906 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
REG | Reference to a national code |
Ref country code: BE Ref legal event code: MM Effective date: 20180531 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MC Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170906 |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: MM4A |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20180531 Ref country code: LI Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20180531 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LU Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20180511 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20180511 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: BE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20180531 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: TR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170906 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: HU Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO Effective date: 20110511 Ref country code: PT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170906 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MK Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20170906 Ref country code: CY Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170906 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: AL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170906 |
|
P01 | Opt-out of the competence of the unified patent court (upc) registered |
Effective date: 20230411 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20230525 Year of fee payment: 13 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20240527 Year of fee payment: 14 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20240530 Year of fee payment: 14 |