EP3610047B1 - Aluminium-copper-lithium alloy products - Google Patents
Aluminium-copper-lithium alloy products Download PDFInfo
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- EP3610047B1 EP3610047B1 EP18724941.2A EP18724941A EP3610047B1 EP 3610047 B1 EP3610047 B1 EP 3610047B1 EP 18724941 A EP18724941 A EP 18724941A EP 3610047 B1 EP3610047 B1 EP 3610047B1
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- 239000001989 lithium alloy Substances 0.000 title description 8
- -1 Aluminium-copper-lithium Chemical compound 0.000 title description 5
- 229910000733 Li alloy Inorganic materials 0.000 title description 5
- 239000010949 copper Substances 0.000 claims description 15
- 239000011572 manganese Substances 0.000 claims description 14
- 229910052782 aluminium Inorganic materials 0.000 claims description 11
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 11
- 238000000034 method Methods 0.000 claims description 11
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 9
- 229910052744 lithium Inorganic materials 0.000 claims description 9
- 239000010936 titanium Substances 0.000 claims description 9
- 238000004519 manufacturing process Methods 0.000 claims description 7
- 239000003351 stiffener Substances 0.000 claims description 7
- 229910000838 Al alloy Inorganic materials 0.000 claims description 6
- 229910052804 chromium Inorganic materials 0.000 claims description 6
- 229910052735 hafnium Inorganic materials 0.000 claims description 6
- 229910001338 liquidmetal Inorganic materials 0.000 claims description 6
- 229910052720 vanadium Inorganic materials 0.000 claims description 6
- 229910052726 zirconium Inorganic materials 0.000 claims description 6
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 5
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 claims description 5
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 claims description 5
- 239000004411 aluminium Substances 0.000 claims description 5
- 229910052802 copper Inorganic materials 0.000 claims description 5
- 229910052748 manganese Inorganic materials 0.000 claims description 5
- 238000010438 heat treatment Methods 0.000 claims description 4
- 238000005266 casting Methods 0.000 claims description 3
- 238000000265 homogenisation Methods 0.000 claims description 3
- 238000010791 quenching Methods 0.000 claims description 3
- 230000000171 quenching effect Effects 0.000 claims description 3
- 229910052751 metal Inorganic materials 0.000 claims description 2
- 239000002184 metal Substances 0.000 claims description 2
- 238000005482 strain hardening Methods 0.000 claims description 2
- 230000032683 aging Effects 0.000 claims 2
- 229910045601 alloy Inorganic materials 0.000 description 30
- 239000000956 alloy Substances 0.000 description 30
- 239000011777 magnesium Substances 0.000 description 14
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 description 12
- 229910052709 silver Inorganic materials 0.000 description 12
- 239000004332 silver Substances 0.000 description 12
- XEEYBQQBJWHFJM-UHFFFAOYSA-N iron Substances [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 11
- 238000005496 tempering Methods 0.000 description 9
- 239000011701 zinc Substances 0.000 description 9
- 239000000203 mixture Substances 0.000 description 7
- 230000003068 static effect Effects 0.000 description 7
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 6
- 229910052749 magnesium Inorganic materials 0.000 description 6
- 235000012438 extruded product Nutrition 0.000 description 5
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 description 4
- 238000010276 construction Methods 0.000 description 4
- 229910052742 iron Inorganic materials 0.000 description 4
- 229910052710 silicon Inorganic materials 0.000 description 4
- 229910052725 zinc Inorganic materials 0.000 description 4
- 239000002970 Calcium lactobionate Substances 0.000 description 3
- 229910017539 Cu-Li Inorganic materials 0.000 description 3
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 3
- 229910000767 Tm alloy Inorganic materials 0.000 description 3
- 238000001125 extrusion Methods 0.000 description 3
- 238000005242 forging Methods 0.000 description 3
- 238000005096 rolling process Methods 0.000 description 3
- 239000010703 silicon Substances 0.000 description 3
- 238000009987 spinning Methods 0.000 description 3
- 238000012512 characterization method Methods 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 239000003381 stabilizer Substances 0.000 description 2
- 229910052719 titanium Inorganic materials 0.000 description 2
- 241001080024 Telles Species 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- AZDRQVAHHNSJOQ-UHFFFAOYSA-N alumane Chemical class [AlH3] AZDRQVAHHNSJOQ-UHFFFAOYSA-N 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 229940082150 encore Drugs 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
- 229910052706 scandium Inorganic materials 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000009864 tensile test Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Images
Classifications
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- 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
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/12—Alloys based on aluminium with copper as the next major constituent
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/12—Alloys based on aluminium with copper as the next major constituent
- C22C21/16—Alloys based on aluminium with copper as the next major constituent with magnesium
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/12—Alloys based on aluminium with copper as the next major constituent
- C22C21/18—Alloys based on aluminium with copper as the next major constituent with zinc
Definitions
- the invention relates in general to wrought products in aluminium-copper-lithium alloys, and more particularly to such products in the form of sections intended to produce stiffeners in aeronautical construction.
- Aluminum alloys containing lithium are very attractive in this regard, as lithium can reduce the density of aluminum by 3% and increase the modulus of elasticity by 6% for each weight percent of lithium added.
- their performance must match that of commonly used alloys, particularly in terms of the trade-off between static strength properties (yield strength, fracture toughness) and damage tolerance properties ( toughness, resistance to the propagation of fatigue cracks), these properties generally being contradictory.
- These alloys must also have sufficient corrosion resistance, be able to be shaped according to the usual methods and have low residual stresses so that they can be machined integrally.
- the patent US 5,198,045 describes a family of Weldalite TM alloys comprising (wt%) (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. THE Wrought products made with these alloys combine a density of less than 2.64 g/cm 3 and an interesting compromise between mechanical strength and toughness.
- the patent US 7,229,509 describes a family of Weldalite TM alloys comprising (wt%) (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 elements such as Cr, Ti, Hf, Sc and V.
- the examples shown have a compromise between mechanical strength and improved toughness but their density is greater than 2.7 g/cm 3 .
- the patent application WO2007/080267 discloses a zirconium-free Weldalite TM alloy for use in fuselage sheets comprising (wt%) (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 AA2196 alloy is also known, comprising (in % by weight) (2.5-3.3) Cu, (1.4-2.1) Li, (0.25-0.8) Mg, (0 .25-0.6) Ag, (0.04-0.18) Zr and at most 0.35 Mn.
- Yet another object of the invention is a structural element incorporating at least one product according to the invention.
- the static mechanical characteristics in other words the breaking strength R m , the conventional yield strength at 0.2% elongation R p0.2 ("yield strength") and l elongation at break A, are determined by a tensile test according to standard EN 10002-1 (2001), the sampling and direction of the test being defined by standard EN 485-1 (2016).
- K Q The stress intensity factor
- the thickness of the sections is defined according to standard EN 2066:2001: the cross section is divided into elementary rectangles of dimensions A and B; A always being the largest dimension of the elementary rectangle and B being able to be considered as the thickness of the elementary rectangle.
- structural element or "structural element” of a mechanical construction is used here to mean 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 performed. These are typically elements whose failure is likely to endanger the safety of the said construction, of the users, of the users or of others.
- these elements of structure include in particular the elements that make up the fuselage (such as the fuselage skin), the fuselage stiffeners or stringers, the bulkheads (bulkheads), the fuselage frames (circumferential frames), the wings (such as the wing skin), the stiffeners (stringers or stiffeners), the ribs (ribs) and spars (spars) and the empennage composed in particular of horizontal and vertical stabilizers (horizontal or vertical stabilizers), as well as floor beams, seat tracks and doors.
- a selected class of aluminum alloys containing specific and critical contents of copper, lithium, magnesium, zinc, manganese and zirconium but containing essentially no silver makes it possible to prepare products wrought having in particular an improved compromise between toughness and mechanical strength compared to that of products containing essentially no silver.
- the present inventors have found that, surprisingly, it is possible for products to obtain a compromise that is at least equivalent between the properties of static mechanical strength and the properties of tolerance to damage than that obtained with an aluminum-copper-lithium alloy containing silver, such as in particular the AA2196 alloy, by making a narrow selection of the quantities of lithium, copper, magnesium, manganese, zinc and zirconium.
- the copper content of the products according to the invention is between 2.5 and 3.4% by weight. In an advantageous embodiment of the invention, the copper content is at least 2.8 or preferably at least 2.9% by weight and/or at most 3.2 and preferably at most 3.1% by weight. weight.
- the lithium content of the products according to the invention is between 1.6 and 2.2% by weight.
- the lithium content is between 1.65% and 1.8% by weight.
- the lithium content is at most 1.75% by weight.
- the magnesium content of the products according to the invention is between 0.4 and 0.9% by weight and preferably it is at least 0.5% by weight and, more preferably still greater than 0.6% in weight.
- the magnesium content is at plus 0.8% by weight.
- the present inventors have found that when the magnesium content is less than 0.30% by weight the advantageous compromise between mechanical strength and damage tolerance is not obtained.
- the manganese content of the products according to the invention is between 0.2 and 0.6% by weight and, preferably, it is at least 0.3% by weight and, even more preferably at least 0.33% by weight and more preferably at least 0.4% by weight. In another embodiment, the manganese content is between 0.2 and 0.4% by weight, preferably between 0.25 and 0.35% by weight.
- the present inventors have found that when the manganese content is less than 0.2% by weight, the tenacity KQ (L-T), in the L-T direction, advantageous according to the invention is not obtained.
- the zirconium content of the products according to the invention is between 0.08 and 0.18% by weight and, preferably, it is from 0.12 to 0.16% by weight and, even more preferably, 0 .14 to 0.15% by weight. In another embodiment, the zirconium content is advantageously between 0.09 and 0.12% by weight, preferably between 0.09 and 0.11% by weight, or even between 0.09 and 0.10% in weight.
- the zinc content is less than 0.4% by weight, preferably it is 0.05 and 0.35% by weight.
- the zinc content is 0.2 to 0.3% by weight, which can contribute to achieving the desired compromise between toughness and mechanical strength.
- the silver content is less than 0.15% by weight, preferably less than 0.10% by weight and, more preferably still, less than 0.05% by weight.
- the present inventors have found that the advantageous compromise between strength and damage tolerance known for alloys typically containing 0.2 to 0.4% by weight silver can be obtained for alloys containing essentially no silver. with the composition selection made.
- the sum of the iron content and the silicon content is at most 0.20% by weight.
- the iron and silicon contents are each at most 0.08% by weight.
- the iron and silicon contents are at most 0.06% and 0.04% by weight, respectively.
- the alloy also contains at least one element which can contribute to the control of the grain size chosen from among Ti, Sc, Cr, Hf and V, the content of the element, if chosen, being from 0.01 to 0 .15% by weight, preferably 0.01 to 0.05% by weight for Ti; from 0.01 to 0.15% by weight, preferably 0.02 to 0.1% by weight for Sc; 0.01 to 0.5% by weight, preferably 0.02 to 0.1% by weight for Hf and 0.01 to 0.3% by weight, preferably 0.02 to 0.1% by weight for Cr and from 0.01 to 0.3% by weight, preferably 0.01 to 0.05% by weight for V.
- the alloy according to the invention is particularly intended for the manufacture of rolled, extruded and/or forged products and, even more particularly, extruded products.
- the products according to the invention have a particularly advantageous compromise between mechanical strength and toughness.
- the products according to the invention have, in a spun, solution-treated, tempered, drawn and tempered state, in particular for thicknesses up to 50 mm or even between 8 and 50 mm, or even between 15 and 35 mm, a yield strength measured at 0.2% elongation in the L direction, Rp0.2 (L), of at least 510 MPa and a toughness KQ (LT), in the LT direction, of at least 21 MPa ⁇ m and such that KQ (LT) > - 0.2667*Rp0.2 (L) + 169.
- the specimens used for the KQ measurements are of the CT type with a thickness of 20 mm and a width of 50 mm.
- the process for manufacturing the products according to the invention comprises steps of production, casting, rolling, extrusion and/or forging, solution treatment, quenching, stress relieving and tempering.
- a bath of liquid metal is prepared so as to obtain an aluminum alloy of composition according to the invention.
- the liquid metal bath is then cast in a raw form, typically a rolling plate, an extrusion billet or a forging blank.
- the raw form is then homogenized at a temperature of between 450° C. and 550° and preferably between 520° C. and 530° C. for a period of between 6 and 15 hours.
- the raw form is optionally cooled down to room temperature before being preheated with a view to being hot deformed.
- the hot deformation is carried out by rolling, extrusion and/or forging so as to obtain a rolled, extruded and/or forged product, preferably an extruded product.
- the product thus obtained is then placed in solution by heat treatment between 490 and 550° C. for 15 min to 8 h, then quenched typically with water at room temperature.
- the product then undergoes controlled stress relief, preferably by traction, with a permanent deformation of 1 to 15% and preferably of 2 to 4%.
- the extruded product has, at the end of the process steps detailed above, a thickness ranging up to 50 mm or even between 8 and 50 mm, or even between 15 and 35 mm.
- Tempering is carried out comprising heating at a temperature of between 140 and 170°C for 5 to 70 hours so that said product has a conventional yield strength measured at 0.2% elongation in the L direction, R p0.2 (L), of at least 510 MPa and a toughness K Q (LT), in the LT direction, of at least 21 MPa m and such that K Q (LT) > -0.2667 ⁇ R p0.2 (L) + 169.
- the extruded product with a conventional yield strength measured at 0.2% elongation in the L direction, Rp0.2 (L), of at least 525 MPa and a tenacity KQ ( L-T), in the L-T direction, of at least 23 MPa ⁇ m and such that KQ (L-T) > -0.2667*Rp0.2 (L) + 171.
- the spun product advantageously has a thickness, up to 50 mm or between 8 and 50 mm, or even between 15 and 35 mm.
- an object of the invention is a structural element incorporating at least one product according to the invention or a product manufactured using a process according to the invention.
- a structural element incorporating at least one product according to the invention or made from such a product is advantageous, in particular for aeronautical construction.
- the products according to the invention are particularly advantageous for the production of structural elements such as stiffeners or frames for the manufacture of intrados or extrados elements of an aircraft wing, preferably stiffeners, spars and ribs, or also floor beams and seat rails.
- the alloy billets 67, 74 a and b, 66, 68 and 69 were then homogenized for 8 to 10 hours at 524°C.
- the billet in alloy 2 was homogenized for 8 hours at 500°C then 24 hours at 527°C while that in alloy 5 was homogenized for 8 hours at 520°C.
- the billets were reheated to 450°C +/- 40°C then hot-spinned to obtain W profiles according to the figure 1 for alloy 2, 67, 74 a and b, 66, 68 and 69 and Z according to picture 2 for alloys 5.
- the profiles thus obtained were put in solution at 524°C, quenched and stretched with a permanent elongation of between 2 and 5%.
- Samples taken from the end of the section were tested to determine their static mechanical properties as well as their toughness (K Q ).
- the location of the samples is indicated in dotted lines on the figure 1 And 2 .
- the test pieces used for measuring the static properties were 10 mm in diameter and taken so that the direction of the axis of the test piece corresponded to the direction of spinning (direction L).
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Description
L'invention concerne en général les produits corroyés en alliages aluminium-cuivre-lithium, et plus particulièrement de tels produits sous la forme de profilés destinés à réaliser des raidisseurs en construction aéronautique.The invention relates in general to wrought products in aluminium-copper-lithium alloys, and more particularly to such products in the form of sections intended to produce stiffeners in aeronautical construction.
Un effort de recherche continu est réalisé afin de développer des matériaux qui puissent simultanément réduire le poids et augmenter l'efficacité des structures d'avions à hautes performances. Les alliages d'aluminium contenant du lithium sont très intéressants à cet égard, car le lithium peut réduire la densité de l'aluminium de 3 % et augmenter le module d'élasticité de 6 % pour chaque pourcent en poids de lithium ajouté. Pour que ces alliages soient sélectionnés dans les avions, leur performance doit atteindre celle des alliages couramment utilisés, en particulier en terme de compromis entre les propriétés de résistance mécanique statique (limite élastique, résistance à la rupture) et les propriétés de tolérance aux dommages (ténacité, résistance à la propagation des fissures en fatigue), ces propriétés étant en général antinomiques. Ces alliages doivent de plus présenter une résistance à la corrosion suffisante, pouvoir être mis en forme selon les procédés habituels et présenter de faibles contraintes résiduelles de façon à pouvoir être usinés de façon intégrale.A continuous research effort is carried out in order to develop materials which can simultaneously reduce the weight and increase the efficiency of the structures of high performance aircraft. Aluminum alloys containing lithium are very attractive in this regard, as lithium can reduce the density of aluminum by 3% and increase the modulus of elasticity by 6% for each weight percent of lithium added. For these alloys to be selected in aircraft, their performance must match that of commonly used alloys, particularly in terms of the trade-off between static strength properties (yield strength, fracture toughness) and damage tolerance properties ( toughness, resistance to the propagation of fatigue cracks), these properties generally being contradictory. These alloys must also have sufficient corrosion resistance, be able to be shaped according to the usual methods and have low residual stresses so that they can be machined integrally.
On connait plusieurs alliages Al-Cu-Li pour lesquels une addition d'argent est effectuée.Several Al-Cu-Li alloys are known for which silver is added.
Le brevet
Le brevet
Le brevet
La demande de brevet
On connait par ailleurs l'alliage AA2196 comprenant (en % en poids) (2,5-3,3)Cu, (1,4-2,1) Li, (0,25-0,8) Mg, (0,25-0,6) Ag, (0,04-0,18) Zr et au plus 0,35 Mn.The AA2196 alloy is also known, comprising (in % by weight) (2.5-3.3) Cu, (1.4-2.1) Li, (0.25-0.8) Mg, (0 .25-0.6) Ag, (0.04-0.18) Zr and at most 0.35 Mn.
La limitation de la quantité d'argent est économiquement très favorable. Cependant, on constate que les produits selon l'art antérieur faits en alliage ne contenant essentiellement pas d'argent ne permettent pas d'obtenir des propriétés aussi avantageuses que celles des produits faits avec des alliages contenant de l'argent tels que l'alliage AA2196.Limiting the amount of money is economically very favorable. However, it is noted that the products according to the prior art made of an alloy containing essentially no silver do not make it possible to obtain properties as advantageous as those of the products made with alloys containing silver such as the alloy AA2196.
Il existe un besoin pour des produits en alliage aluminium-cuivre-lithium, notamment des produits filés, présentant une densité réduite et des propriétés sensiblement équivalentes à celles de produits connus contenant de l'argent, en particulier en termes de compromis entre les propriétés de résistance mécanique statique et les propriétés de tolérance aux dommages. La stabilité thermique, la résistance à la corrosion, l'aptitude à l'usinage et la densité de ces produits notamment doivent également être satisfaisantes par rapport à celles de produits connus contenant de l'argent tout en ayant une faible densité.There is a need for aluminum-copper-lithium alloy products, in particular extruded products, having a reduced density and properties substantially equivalent to those of known products containing silver, in particular in terms of compromise between the properties of static mechanical strength and damage tolerance properties. The thermal stability, the resistance to corrosion, the machinability and the density of these products in particular must also be satisfactory with respect to those of known products containing silver while having a low density.
Un premier objet de l'invention est un produit en alliage à base d'aluminium comprenant, en % en poids,
- Cu : 2,5-3,4 ; préférentiellement 2,8-3,2 ;
- Li : 1,6-2,2 ; préférentiellement 1,65-1,8 ;
- Mg : 0,4-0,9 ; préférentiellement 0,5-0,8 ;
- Mn : 0,2 - 0,6 ; préférentiellement 0,3-0,6 ;
- Zr : 0,08 - 0,18 ; préférentiellement 0,12-0,16 ;
- Zn : < 0,4 préférentiellement 0,05-0,4 ; plus préférentiellement de 0,2-0,4 ;
- Ag : < 0,15 ; préférentiellement <0,1 ; plus préférentiellement encore <0,05 ;
- Fe + Si ≤ 0,20 ;
- au moins un élément choisi parmi
- Ti : 0,01 - 0,15 ; préférentiellement 0,01-0,05 ;
- Sc : 0,01 - 0,15, préférentiellement 0,02-0,1 ;
- Cr : 0,01 - 0,3, préférentiellement 0,02-0,1 ;
- Hf : 0,01 - 0,5 ; préférentiellement 0,02-0,1 ;
- V : 0,01 - 0,3, préférentiellement 0,01-0,05 ;
- autres éléments ≤ 0,05 chacun et ≤ 0,15 au total, reste aluminium.
- Cu: 2.5-3.4; preferentially 2.8-3.2;
- Li: 1.6-2.2; preferably 1.65-1.8;
- Mg: 0.4-0.9; preferably 0.5-0.8;
- Mn: 0.2 - 0.6; preferably 0.3-0.6;
- Zr: 0.08-0.18; preferably 0.12-0.16;
- Zn: <0.4 preferably 0.05-0.4; more preferably 0.2-0.4;
- Ag: <0.15; preferably <0.1; more preferably still <0.05;
- Fe + Si ≤ 0.20;
- at least one element chosen from
- Ti: 0.01-0.15; preferably 0.01-0.05;
- Sc: 0.01-0.15, preferably 0.02-0.1;
- Cr: 0.01-0.3, preferably 0.02-0.1;
- Hf: 0.01 - 0.5; preferably 0.02-0.1;
- V: 0.01-0.3, preferably 0.01-0.05;
- other elements ≤ 0.05 each and ≤ 0.15 in total, rest aluminium.
Un deuxième objet de l'invention est un procédé de fabrication d'un produit filé, laminé et/ou forgé à base d'alliage d'aluminium comprenant les étapes :
- a) élaboration d'un bain de métal liquide comprenant, en pourcentage en poids, Cu :
- 2,5-3,4 ; Li : 1,6-2,2 ; Mg : 0,4-0,9 ; Mn : 0,2 - 0,6 ; Zr : 0,08 - 0,18 ; Zn : < 0,4 ;
- Ag : < 0,15 ; Fe + Si ≤ 0,20 ; au moins un élément choisi parmi Ti, Sc, Cr, Hf et V, la teneur dudit élément, s'il est choisi, étant Ti : 0,01 - 0,15 ; Sc : 0,01 - 0,15 ; Cr :
- 0,01 - 0,3 ; Hf : 0,01 - 0,5 ; V : 0,01 - 0,3 ; autres éléments ≤ 0,05 chacun et ≤ 0,15 au total, reste aluminium
- b) coulée d'une forme brute à partir dudit bain de métal liquide ;
- c) homogénéisation ladite forme brute ;
- d) déformation à chaud et, optionnellement, à froid de la forme brute en un produit filé, laminé et/ou forgé ;
- e) mise en solution et trempe dudit produit ;
- f) traction de façon contrôlée dudit produit avec une déformation permanente de 1 à 15%, préférentiellement de 2 à 4% ;
- g) revenu dudit produit par chauffage à 140 à 170°C pendant 5 à 70 heures. Avantageusement, le revenu est réalisé de façon à ce que ledit produit ait une limite d'élasticité conventionnelle mesurée à 0,2% d'allongement dans le sens L, Rp0,2 (L), d'au moins 510 MPa et une ténacité KQ (L-T), dans le sens L-T, d'au moins 21
- a) preparation of a bath of liquid metal comprising, in percentage by weight, Cu:
- 2.5-3.4; Li: 1.6-2.2; Mg: 0.4-0.9; Mn: 0.2 - 0.6; Zr: 0.08-0.18; Zn: <0.4;
- Ag: <0.15; Fe + Si ≤ 0.20; at least one element selected from Ti, Sc, Cr, Hf and V, the content of said element, if selected, being Ti: 0.01-0.15; sc: 0.01-0.15; Cr:
- 0.01 - 0.3; Hf: 0.01 - 0.5; V: 0.01 - 0.3; other elements ≤ 0.05 each and ≤ 0.15 in total, remainder aluminum
- b) casting a blank form from said bath of liquid metal;
- c) homogenizing said raw form;
- d) hot and, optionally, cold working of the raw shape into an extruded, rolled and/or forged product;
- e) dissolving and quenching said product;
- f) traction in a controlled manner of said product with a permanent deformation of 1 to 15%, preferably of 2 to 4%;
- g) tempering said product by heating at 140 to 170°C for 5 to 70 hours. Advantageously, tempering is carried out so that said product has a conventional elastic limit measured at 0.2% elongation in the direction L, R p0.2 (L), of at least 510 MPa and a toughness K Q (LT), in the LT direction, of at least 21
Encore un autre objet de l'invention est un élément de structure incorporant au moins un produit selon l'invention.Yet another object of the invention is a structural element incorporating at least one product according to the invention.
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Figure 1 : Forme du profilé W de l'exemple (on entend par « forme » la section transversale dudit profilé). Les cotes sont indiquées en mm. Les échantillons utilisés pour les caractérisations mécaniques ont été prélevés dans la zone indiquée par les pointillés.Figure 1 : Shape of the profile W of the example (the term "shape" is the cross section of said profile). Dimensions are given in mm. The samples used for the mechanical characterizations were taken from the area indicated by the dotted lines. -
Figure 2 : Forme du profilé Z de l'exemple (on entend par « forme » la section transversale dudit profilé). Les cotes sont indiquées en mm. Les échantillons utilisés pour les caractérisations mécaniques ont été prélevés dans la zone indiquée par les pointillés.Figure 2 : Shape of the profile Z of the example (the term "shape" means the cross section of said profile). Dimensions are given in mm. The samples used for the mechanical characterizations were taken from the area indicated by the dotted lines. -
Figure 3 : Compromis entre ténacité et résistance mécanique obtenu pour les profilés de l'exemple.Figure 3 : Compromise between toughness and mechanical resistance obtained for the profiles of the example.
Sauf mention contraire, toutes les indications concernant la composition chimique des alliages sont exprimées comme un pourcentage en poids basé sur le poids total de l'alliage. La désignation des alliages se fait en conformité avec les règlements de The Aluminium Association, connus de l'homme du métier. La densité dépend de la composition et est déterminée par calcul plutôt que par une méthode de mesure de poids. Les valeurs sont calculées en conformité avec la procédure de The Aluminium Association, qui est décrite pages 2-12 et 2.13 de « Aluminum Standards and Data ». Les définitions des états métallurgiques sont indiquées dans la norme européenne EN 515 (2009).Unless otherwise stated, all indications regarding the chemical composition of the alloys are expressed as a percentage by weight based on the total weight of the alloy. The designation of the alloys is made 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. Values are calculated in accordance with The Aluminum Association procedure, which is described pages 2-12 and 2.13 of “Aluminum Standards and Data”. The definitions of metallurgical tempers are given in the European standard EN 515 (2009).
Sauf mention contraire, les caractéristiques mécaniques statiques, en d'autres termes la résistance à la rupture Rm, la limite d'élasticité conventionnelle à 0,2% d'allongement Rp0,2 (« limite d'élasticité ») et l'allongement à la rupture A, sont déterminées par un essai de traction selon la norme EN 10002-1 (2001), le prélèvement et le sens de l'essai étant définis par la norme EN 485-1 (2016).Unless otherwise stated, the static mechanical characteristics, in other words the breaking strength R m , the conventional yield strength at 0.2% elongation R p0.2 ("yield strength") and l elongation at break A, are determined by a tensile test according to standard EN 10002-1 (2001), the sampling and direction of the test being defined by standard EN 485-1 (2016).
Le facteur d'intensité de contrainte (KQ) est déterminé selon la norme ASTM E 399 (2012). Ainsi, la proportion des éprouvettes définie au paragraphe 7.2.1 de cette norme est toujours vérifiée de même que la procédure générale définie au paragraphe 8. La norme ASTM E 399 (2012) donne aux paragraphes 9.1.3 et 9.1.4 des critères qui permettent de déterminer si KQ est une valeur valide de K1C. Ainsi, une valeur K1C est toujours une valeur KQ la réciproque n'étant pas vraie. Dans le cadre de l'invention, les critères des paragraphes 9.1.3 et 9.1.4 de la norme ASTM E399 (2012) ne sont pas toujours vérifiés, cependant pour une géométrie d'éprouvette donnée, les valeurs de KQ présentées sont toujours comparables entre elles, la géométrie d'éprouvette permettant d'obtenir une valeur valide de K1C n'étant pas toujours accessible compte tenu des contraintes liées aux dimensions des tôles ou profilés.The stress intensity factor (K Q ) is determined according to ASTM E 399 (2012). Thus, the proportion of specimens defined in paragraph 7.2.1 of this standard is always verified as well as the general procedure defined in paragraph 8. Standard ASTM E 399 (2012) gives in paragraphs 9.1.3 and 9.1.4 criteria which make it possible to determine whether K Q is a valid value of K 1C . Thus, a K 1C value is always a K Q value, the reciprocal not being true. In the context of the invention, the criteria of paragraphs 9.1.3 and 9.1.4 of standard ASTM E399 (2012) are not always verified, however for a given specimen geometry, the values of K Q presented are always comparable to each other, the geometry of the specimen making it possible to obtain a valid value of K 1C not always being accessible given the constraints linked to the dimensions of the sheets or sections.
Sauf mention contraire, les définitions de la norme EN 12258 (2012) s'appliquent. L'épaisseur des profilés est définie selon la norme EN 2066 :2001 : la section transversale est divisée en rectangles élémentaires de dimensions A et B ; A étant toujours la plus grande dimension du rectangle élémentaire et B pouvant être considéré comme l'épaisseur du rectangle élémentaire.Unless otherwise stated, the definitions of EN 12258 (2012) apply. The thickness of the sections is defined according to standard EN 2066:2001: the cross section is divided into elementary rectangles of dimensions A and B; A always being the largest dimension of the elementary rectangle and B being able to be considered as the thickness of the elementary rectangle.
On appelle ici « élément de structure » ou « élément structural » d'une construction mécanique une pièce mécanique pour laquelle les propriétés mécaniques statiques et/ou dynamiques sont particulièrement importantes pour la performance de la structure, et pour laquelle un calcul de structure est habituellement prescrit ou réalisé. Il s'agit typiquement d'éléments dont la défaillance est susceptible de mettre en danger la sécurité de ladite construction, de scs utilisateurs, des scs usagers ou d'autrui. Pour un avion, ces éléments de structure comprennent notamment les éléments qui composent le fuselage (tels que la peau de fuselage (fuselage skin en anglais), les raidisseurs ou lisses de fuselage (stringers), les cloisons étanches (bulkheads), les cadres de fuselage (circumferential frames), les ailes (tels que la peau de voilure (wing skin), les raidisseurs (stringers ou stiffeners), les nervures (ribs) et longerons (spars)) et l'empennage composé notamment de stabilisateurs horizontaux et verticaux (horizontal or vertical stabilisers), ainsi que les profilés de plancher (floor beams), les rails de sièges (seat tracks) et les portes.The term "structural element" or "structural element" of a mechanical construction is used here to mean 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 performed. These are typically elements whose failure is likely to endanger the safety of the said construction, of the users, of the users or of others. For an airplane, these elements of structure include in particular the elements that make up the fuselage (such as the fuselage skin), the fuselage stiffeners or stringers, the bulkheads (bulkheads), the fuselage frames (circumferential frames), the wings (such as the wing skin), the stiffeners (stringers or stiffeners), the ribs (ribs) and spars (spars) and the empennage composed in particular of horizontal and vertical stabilizers (horizontal or vertical stabilizers), as well as floor beams, seat tracks and doors.
Selon l'invention, une classe sélectionnée d'alliages d'aluminium contenant des teneurs spécifiques et critiques de cuivre, de lithium, de magnésium, de zinc, de manganèse et de zirconium mais ne contentant essentiellement pas d'argent permet de préparer des produits corroyés présentant notamment un compromis amélioré entre ténacité et résistance mécanique par rapport à celui de produits ne contenant essentiellement pas d'argent.According to the invention, a selected class of aluminum alloys containing specific and critical contents of copper, lithium, magnesium, zinc, manganese and zirconium but containing essentially no silver makes it possible to prepare products wrought having in particular an improved compromise between toughness and mechanical strength compared to that of products containing essentially no silver.
Les présents inventeurs ont constaté que de manière surprenante, il est possible pour des produits d'obtenir un compromis au moins équivalent entre les propriétés de résistance mécanique statique et les propriétés de tolérance aux dommages que celui obtenu avec un alliage aluminium-cuivre-lithium contenant de l'argent, tels que notamment l'alliage AA2196, en réalisant une sélection étroite des quantités de lithium, de cuivre, de magnésium, de manganèse, de zinc et de zirconium .The present inventors have found that, surprisingly, it is possible for products to obtain a compromise that is at least equivalent between the properties of static mechanical strength and the properties of tolerance to damage than that obtained with an aluminum-copper-lithium alloy containing silver, such as in particular the AA2196 alloy, by making a narrow selection of the quantities of lithium, copper, magnesium, manganese, zinc and zirconium.
La teneur en cuivre des produits selon l'invention est comprise entre 2,5 et 3,4 % en poids. Dans une réalisation avantageuse de l'invention, la teneur en cuivre est au moins de 2,8 ou préférentiellement au moins de 2,9 % en poids et/ou au plus de 3,2 et préférentiellement au plus de 3,1 % en poids.The copper content of the products according to the invention is between 2.5 and 3.4% by weight. In an advantageous embodiment of the invention, the copper content is at least 2.8 or preferably at least 2.9% by weight and/or at most 3.2 and preferably at most 3.1% by weight. weight.
La teneur en lithium des produits selon l'invention est comprise entre 1,6 et 2,2 % en poids. Avantageusement, la teneur en lithium est comprise entre 1,65 % et 1,8 % en poids. De manière préférée, la teneur en lithium est au plus de 1,75 % en poids.The lithium content of the products according to the invention is between 1.6 and 2.2% by weight. Advantageously, the lithium content is between 1.65% and 1.8% by weight. Preferably, the lithium content is at most 1.75% by weight.
La teneur en magnésium des produits selon l'invention est comprise entre 0,4 et 0,9 % en poids et de manière préférée elle est d'au moins 0,5% en poids et, plus préférentiellement encore supérieure à 0,6 % en poids. Avantageusement, la teneur en magnésium est d'au plus 0,8% en poids. Les présents inventeurs ont constaté que lorsque la teneur en magnésium est inférieure à 0,30 % en poids le compromis avantageux entre la résistance mécanique et la tolérance aux dommages n'est pas obtenu.The magnesium content of the products according to the invention is between 0.4 and 0.9% by weight and preferably it is at least 0.5% by weight and, more preferably still greater than 0.6% in weight. Advantageously, the magnesium content is at plus 0.8% by weight. The present inventors have found that when the magnesium content is less than 0.30% by weight the advantageous compromise between mechanical strength and damage tolerance is not obtained.
La teneur en manganèse des produits selon l'invention est comprise entre 0,2 et 0,6 % en poids et, de manière préférée, elle est d'au moins 0,3% en poids et, plus préférentiellement encore d'au moins 0,33% en poids et plus préférentiellement d'au moins 0,4% en poids. Dans un autre mode de réalisation, la teneur en manganèse est comprise entre 0,2 et 0,4% en poids, préférentiellement entre 0,25 et 0,35% en poids. Les présents inventeurs ont constaté que lorsque la teneur en manganèse est inférieure à 0,2 % en poids, la ténacité KQ (L-T), dans le sens L-T, avantageuse selon l'invention n'est pas obtenue.The manganese content of the products according to the invention is between 0.2 and 0.6% by weight and, preferably, it is at least 0.3% by weight and, even more preferably at least 0.33% by weight and more preferably at least 0.4% by weight. In another embodiment, the manganese content is between 0.2 and 0.4% by weight, preferably between 0.25 and 0.35% by weight. The present inventors have found that when the manganese content is less than 0.2% by weight, the tenacity KQ (L-T), in the L-T direction, advantageous according to the invention is not obtained.
La teneur en zirconium des produits selon l'invention est comprise entre 0,08 et 0,18 % en poids et, de manière préférée, elle est de 0,12 à 0,16% en poids et, plus préférentiellement encore, de 0,14 à 0,15% en poids. Dans un autre mode de réalisation, la teneur en zirconium est avantageusement comprise entre 0,09 et 0,12% en poids, préférentiellement entre 0,09 et 0,11 % en poids, voire même entre 0,09 et 0,10% en poids.The zirconium content of the products according to the invention is between 0.08 and 0.18% by weight and, preferably, it is from 0.12 to 0.16% by weight and, even more preferably, 0 .14 to 0.15% by weight. In another embodiment, the zirconium content is advantageously between 0.09 and 0.12% by weight, preferably between 0.09 and 0.11% by weight, or even between 0.09 and 0.10% in weight.
La teneur en zinc est inférieure à 0,4% en poids, préférentiellement elle est de 0,05 et 0,35 % en poids. Avantageusement, la teneur en zinc est 0,2 à 0,3 % en poids ce qui peut contribuer à atteindre le compromis recherché entre la ténacité et la résistance mécanique.The zinc content is less than 0.4% by weight, preferably it is 0.05 and 0.35% by weight. Advantageously, the zinc content is 0.2 to 0.3% by weight, which can contribute to achieving the desired compromise between toughness and mechanical strength.
La teneur en argent est inférieure à 0,15 % en poids, de préférence inférieure à 0,10 % en poids et, plus préférentiellement encore inférieure à 0,05 % en poids. Les présents inventeurs ont constaté que le compromis avantageux entre la résistance mécanique et la tolérance aux dommages connu pour des alliages contenant typiquement 0,2 à 0,4 % en poids d'argent peut être obtenu pour des alliages ne contenant essentiellement pas d'argent avec la sélection de composition effectuée.The silver content is less than 0.15% by weight, preferably less than 0.10% by weight and, more preferably still, less than 0.05% by weight. The present inventors have found that the advantageous compromise between strength and damage tolerance known for alloys typically containing 0.2 to 0.4% by weight silver can be obtained for alloys containing essentially no silver. with the composition selection made.
La somme de la teneur en fer et de la teneur en silicium est au plus de 0,20 % en poids. De préférence, les teneurs en fer et en silicium sont chacune au plus de 0,08 % en poids. Dans une réalisation avantageuse de l'invention, les teneurs en fer et en silicium sont au plus de 0,06 % et 0,04 % en poids, respectivement.The sum of the iron content and the silicon content is at most 0.20% by weight. Preferably, the iron and silicon contents are each at most 0.08% by weight. In an advantageous embodiment of the invention, the iron and silicon contents are at most 0.06% and 0.04% by weight, respectively.
L'alliage contient également au moins un élément pouvant contribuer au contrôle de la taille de grain choisi parmi Ti, Sc, Cr, Hf et V, la teneur de l'élément, s'il est choisi, étant de 0,01 à 0,15 % en poids, préférentiellement 0,01 à 0,05% en poids pour Ti ; de 0,01 à 0,15 % en poids, préférentiellement 0,02 à 0,1% en poids pour Sc ; 0,01 à 0,5 % en poids, préférentiellement 0,02 à 0,1% en poids pour Hf et de 0,01 à 0,3 % en poids, préférentiellement de 0,02 à 0,1% en poids pour Cr et de 0,01 à 0,3% en poids, préférentiellement 0,01 à 0,05% en poids pour V. De manière préférée, on choisit entre 0,02 et 0,04 % en poids de titane.The alloy also contains at least one element which can contribute to the control of the grain size chosen from among Ti, Sc, Cr, Hf and V, the content of the element, if chosen, being from 0.01 to 0 .15% by weight, preferably 0.01 to 0.05% by weight for Ti; from 0.01 to 0.15% by weight, preferably 0.02 to 0.1% by weight for Sc; 0.01 to 0.5% by weight, preferably 0.02 to 0.1% by weight for Hf and 0.01 to 0.3% by weight, preferably 0.02 to 0.1% by weight for Cr and from 0.01 to 0.3% by weight, preferably 0.01 to 0.05% by weight for V. Preferably, between 0.02 and 0.04% by weight of titanium is chosen.
L'alliage selon l'invention est particulièrement destiné à la fabrication de produits laminés, filés et/ou forgés et, plus particulièrement encore, de produits filés. Les produits selon l'invention présentent un compromis entre résistance mécanique et ténacité particulièrement avantageux.The alloy according to the invention is particularly intended for the manufacture of rolled, extruded and/or forged products and, even more particularly, extruded products. The products according to the invention have a particularly advantageous compromise between mechanical strength and toughness.
Les produits selon l'invention, présentent dans un état filé, mis en solution, trempé, tractionné et revenu, notamment pour des épaisseurs jusqu'à 50 mm ou encore comprises entre 8 et 50 mm, ou même entre 15 et 35 mm, une limite d'élasticité conventionnelle mesurée à 0,2% d'allongement dans le sens L, Rp0,2 (L), d'au moins 510 MPa et une ténacité KQ (L-T), dans le sens L-T, d'au moins 21 MPa√m et telle que KQ (L-T) > - 0,2667*Rp0,2 (L) + 169. Selon un mode de réalisation particulièrement avantageux, ils présentent, dans les conditions ci-avant décrites, une limite d'élasticité conventionnelle mesurée à 0,2% d'allongement dans le sens L, Rp0,2 (L), d'au moins 525 MPa et une ténacité KQ (L-T), dans le sens L-T, d'au moins 23 MPa√m et telle que KQ (L-T) > - 0,2667*Rp0,2 (L) + 171. Dans la présente invention, les éprouvettes utilisées pour les mesures de KQ sont de type CT d'épaisseur 20mm et de largeur 50mm.The products according to the invention have, in a spun, solution-treated, tempered, drawn and tempered state, in particular for thicknesses up to 50 mm or even between 8 and 50 mm, or even between 15 and 35 mm, a yield strength measured at 0.2% elongation in the L direction, Rp0.2 (L), of at least 510 MPa and a toughness KQ (LT), in the LT direction, of at least 21 MPa√m and such that KQ (LT) > - 0.2667*Rp0.2 (L) + 169. According to a particularly advantageous embodiment, they have, under the conditions described above, a conventional yield strength measured at 0.2% elongation in the L direction, Rp0.2 (L), of at least 525 MPa and a toughness KQ (LT), in the LT direction, of at least 23 MPa√m and such that KQ (LT) > - 0.2667*Rp0.2 (L) + 171. In the present invention, the specimens used for the KQ measurements are of the CT type with a thickness of 20 mm and a width of 50 mm.
Le procédé de fabrication des produits selon l'invention comprend des étapes d'élaboration, coulée, laminage, extrusion et/ou forgeage, mise en solution, trempe, détensionnement et revenu.The process for manufacturing the products according to the invention comprises steps of production, casting, rolling, extrusion and/or forging, solution treatment, quenching, stress relieving and tempering.
Dans une première étape, on élabore un bain de métal liquide de façon à obtenir un alliage d'aluminium de composition selon l'invention.In a first step, a bath of liquid metal is prepared so as to obtain an aluminum alloy of composition according to the invention.
Le bain de métal liquide est ensuite coulé sous une forme brute typiquement une plaque de laminage, une billette d'extrusion ou une ébauche de forge.The liquid metal bath is then cast in a raw form, typically a rolling plate, an extrusion billet or a forging blank.
La forme brute est ensuite homogénéisée à une température comprise entre 450°C et 550° et de préférence entre 520°C et 530°C pendant une durée comprise entre 6 et 15 heures.The raw form is then homogenized at a temperature of between 450° C. and 550° and preferably between 520° C. and 530° C. for a period of between 6 and 15 hours.
Après homogénéisation, la forme brute est optionnellement refroidie jusqu'à température ambiante avant d'être préchauffée en vue d'être déformée à chaud. La déformation à chaud est effectuée par laminage, extrusion et/ou forgeage de façon à obtenir un produit laminé, filé et/ou forgé, préférentiellement un produit filé.After homogenization, the raw form is optionally cooled down to room temperature before being preheated with a view to being hot deformed. The hot deformation is carried out by rolling, extrusion and/or forging so as to obtain a rolled, extruded and/or forged product, preferably an extruded product.
Le produit ainsi obtenu est ensuite mis en solution par traitement thermique entre 490 et 550 °C pendant 15 min à 8 h, puis trempé typiquement avec de l'eau à température ambiante.The product thus obtained is then placed in solution by heat treatment between 490 and 550° C. for 15 min to 8 h, then quenched typically with water at room temperature.
Le produit subit ensuite un détensionnement contrôlé, préférentiellement par traction, avec une déformation permanente de 1 à 15 % et préférentiellement de 2 à 4%. Avantageusement, le produit filé présente à l'issue des étapes de procédé ci-dessus détaillées une épaisseur allant jusqu'à 50 mm ou encore comprise entre 8 et 50 mm, ou même entre 15 et 35 mm.The product then undergoes controlled stress relief, preferably by traction, with a permanent deformation of 1 to 15% and preferably of 2 to 4%. Advantageously, the extruded product has, at the end of the process steps detailed above, a thickness ranging up to 50 mm or even between 8 and 50 mm, or even between 15 and 35 mm.
Un revenu est réalisé comprenant un chauffage à une température comprise entre 140 et 170°C pendant 5 à 70 heures de façon à ce que ledit produit ait une limite d'élasticité conventionnelle mesurée à 0,2% d'allongement dans le sens L, Rp0,2 (L), d'au moins 510 MPa et une ténacité KQ (L-T), dans le sens L-T, d'au moins 21
Selon un mode de réalisation particulièrement avantageux, le produit filé avec une limite d'élasticité conventionnelle mesurée à 0,2% d'allongement dans le sens L, Rp0,2 (L), d'au moins 525 MPa et une ténacité KQ (L-T), dans le sens L-T, d'au moins 23 MPa√m et tel que KQ (L-T) > -0,2667*Rp0,2 (L) + 171. Dans ledit mode de réalisation, le produit filé présente avantageusement une épaisseur, jusqu'à 50 mm ou encore comprises entre 8 et 50 mm, ou même entre 15 et 35 mm.According to a particularly advantageous embodiment, the extruded product with a conventional yield strength measured at 0.2% elongation in the L direction, Rp0.2 (L), of at least 525 MPa and a tenacity KQ ( L-T), in the L-T direction, of at least 23 MPa√m and such that KQ (L-T) > -0.2667*Rp0.2 (L) + 171. In said embodiment, the spun product advantageously has a thickness, up to 50 mm or between 8 and 50 mm, or even between 15 and 35 mm.
Les produits selon l'invention peuvent de manière avantageuse être utilisés dans des éléments de structure, en particulier d'avion. Ainsi, un objet de l'invention est un élément de structure incorporant au moins un produit selon l'invention ou un produit fabriqué à partir d'un procédé selon l'invention.The products according to the invention can advantageously be used in structural elements, in particular aircraft. Thus, an object of the invention is a structural element incorporating at least one product according to the invention or a product manufactured using a process according to the invention.
L'utilisation, d'un élément de structure incorporant au moins un produit selon l'invention ou fabriqué à partir d'un tel produit est avantageux, en particulier pour la construction aéronautique. Les produits selon l'invention sont particulièrement avantageux pour la réalisation d'éléments de structure tels que les raidisseurs ou les cadres pour la fabrication d'éléments intrados ou extrados d'aile d'avion, préférentiellement des raidisseurs, des longerons et des nervures, ou également les poutres de plancher et les rails de siège.The use of a structural element incorporating at least one product according to the invention or made from such a product is advantageous, in particular for aeronautical construction. The products according to the invention are particularly advantageous for the production of structural elements such as stiffeners or frames for the manufacture of intrados or extrados elements of an aircraft wing, preferably stiffeners, spars and ribs, or also floor beams and seat rails.
Ces aspects, ainsi que d'autres de l'invention sont expliqués plus en détails à l'aide des exemples illustratifs et non limitants suivants.These and other aspects of the invention are explained in more detail using the following illustrative and non-limiting examples.
Dans cet exemple, plusieurs billettes (384 mm de diamètre) en alliage Al-Cu-Li dont la composition est donnée dans le tableau 1 ont été coulées (alliages 67, 74 a et b, 66, 68 et 69). La composition de deux alliages de l'art antérieur AA2196 ont également été données dans le tableau 1 ci-après.
Les billettes en alliage 67, 74 a et b, 66, 68 et 69 ont ensuite été homogénéisées de 8 à 10h à 524°C. La billette en alliage 2 a été homogénéisée 8h à 500 °C puis 24h à 527 °C tandis que celle en alliage 5 a été homogénéisée 8h à 520 °C.The alloy billets 67, 74 a and b, 66, 68 and 69 were then homogenized for 8 to 10 hours at 524°C. The billet in alloy 2 was homogenized for 8 hours at 500°C then 24 hours at 527°C while that in alloy 5 was homogenized for 8 hours at 520°C.
Après homogénéisation, les billettes ont été réchauffées à 450 °C +/- 40 °C puis filées à chaud pour obtenir des profilés W selon la
Les profilés ont été soumis à un revenu tel qu'indiqué dans le tableau 2 : 30h à 152°C, 48h à 152°C, 30h à 160°C. Pour les alliages 2 et 5, le revenu a été effectué pendant 48h à 152 °C. Les temps équivalents ti à 160°C ont été calculés en prenant en compte le temps de montée jusqu'au palier de revenu et en considérant une vitesse de montée de 20°C/h.The profiles were subjected to tempering as indicated in Table 2: 30h at 152°C, 48h at 152°C, 30h at 160°C. For alloys 2 and 5, tempering was carried out for 48 hours at 152 °C. The equivalent times t i at 160° C. were calculated taking into account the rise time to the tempering plateau and considering a rise rate of 20° C./h.
Des échantillons prélevés en fin de profilé ont été testés pour déterminer leurs propriétés mécaniques statiques de même que leur ténacité (KQ). La localisation des prélèvements est indiquée en pointillés sur les
Les résultats obtenus sont donnés dans le tableau 2 ci-dessous et illustrés par la
Claims (11)
- An aluminium alloy product comprising, in % by weight,Cu: 2.5-3.4; preferably 2.8-3.2;Li: 1.6-2.2; preferably 1.65-1.8;Mg: 0.4-0.9; preferably 0.5-0.8;Mn: 0.2-0.6; preferably 0.3-0.6;Zr: 0.08-0.18; preferably 0.12-0.16;Zn: <0.4, preferably 0.05-0.4; more preferably 0.2-0.4;Ag: <0.15; preferably <0.1; yet more preferably <0.05;Fe + Si ≤ 0.20;at least one element selected from Ti, Sc, Cr, Hf and V, the content of the element, if it is selected, being:Ti: 0.01 - 0.15; preferably 0.01-0.05;Sc: 0.01-0.15, preferably 0.02-0.1;Cr: 0.01 - 0.3, preferably 0.02-0.1;Hf: 0.01-0.5; preferably 0.02-0.1;V: 0.01-0.3, preferably 0.01-0.05;other elements ≤ 0.05 each and ≤ 0.15 in total, the rest being aluminium.
- The product according to claim 1 wherein the copper content is 2.9 to 3.1% by weight.
- The product according to any one of claims 1 to 2 wherein the lithium content is 1.65 to 1.75% by weight.
- The product according to any one of claims 1 to 3 wherein the manganese content is 0.4 to 0.6% by weight.
- The product according to any one of claims 1 to 3 wherein the zirconium content is 0.14 to 0.15% by weight.
- A method for manufacturing an extruded, rolled and/or forged aluminium alloy product comprising the steps:a) preparing a liquid metal bath comprising, as a percentage by weight, Cu: 2.5-3.4; Li: 1.6-2.2; Mg: 0.4-0.9; Mn: 0.2-0.6; Zr: 0.08-0.18; Zn: <0.4; Ag: <0.15; Fe + Si ≤ 0.20; at least one element selected from Ti, Sc, Cr, Hf and V, the content of said element, if selected, being Ti: 0.01 - 0.15; Sc: 0.01 - 0.15; Cr: 0.01 - 0.3; Hf: 0.01-0.5; V: 0.01 - 0.3; other elements ≤ 0.05 each and ≤ 0.15 in total, the rest being aluminiumb) casting an unwrought form from said liquid metal bath;c) homogenising said unwrought form;d) hot and, optionally, cold-working the unwrought form into an extruded, rolled and/or forged product;e) solution heat treating and quenching said product;f) stretching said product in a controlled manner with a permanent set of 1 to 15%, preferably of 2 to 4%;g) ageing said product by heating at 140 to 170°C for 5 to 70 hours so that said product has a conventional yield strength measured at 0.2% elongation in the L direction, Rp0.2 (L), of at least 510 MPa and a toughness KQ (L-T), in the L-T direction, of at least 21 MPaVm and such that KQ (L-T) > -0.2667∗Rp0.2 (L) + 169.
- The method according to claim 6 wherein the homogenisation temperature is comprised between 520 °C and 530°C and the treatment duration is comprised between 6 and 15 hours.
- The method according to any one of claims 6 to 7 wherein the ageing is carried out at a temperature comprised between 150 to 165 °C for an equivalent time t i at 160°C comprised between 15 and 28h, preferably between 20 and 27h, t i being defined by the formula:
- The product obtained according to any one of claims 6 to 8 characterised in that it has a conventional yield strength measured at 0.2% elongation in the L direction, Rp0.2 (L), of at least 525 MPa and a toughness KQ (L-T), in the L-T direction, of at least 23 MPaVm and such that KQ (L-T) > -0.2667*Rp0.2 (L) + 171.
- A structural element incorporating at least one product according to any one of claims 1 to 5 or manufactured from a product obtained according to any one of claims 6 to 8.
- Use of a structural element according to claim 10 as a stiffener or a frame of lower surface or upper surface of airplane wing elements, or a floor beam or a seat rail.
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FR1753133A FR3065011B1 (en) | 2017-04-10 | 2017-04-10 | ALUMINUM-COPPER-LITHIUM ALLOY PRODUCTS |
PCT/FR2018/050886 WO2018189471A1 (en) | 2017-04-10 | 2018-04-09 | Aluminium-copper-lithium alloy products |
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US5032359A (en) | 1987-08-10 | 1991-07-16 | Martin Marietta Corporation | Ultra high strength weldable aluminum-lithium alloys |
US5198045A (en) | 1991-05-14 | 1993-03-30 | Reynolds Metals Company | Low density high strength al-li alloy |
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 |
FR2894985B1 (en) * | 2005-12-20 | 2008-01-18 | Alcan Rhenalu Sa | HIGH-TENACITY ALUMINUM-COPPER-LITHIUM PLASTER FOR AIRCRAFT FUSELAGE |
FR2938553B1 (en) * | 2008-11-14 | 2010-12-31 | Alcan Rhenalu | ALUMINUM-COPPER-LITHIUM ALLOY PRODUCTS |
FR3004464B1 (en) * | 2013-04-12 | 2015-03-27 | Constellium France | PROCESS FOR TRANSFORMING AL-CU-LI ALLOY SHEETS ENHANCING FORMABILITY AND RESISTANCE TO CORROSION |
FR3014448B1 (en) * | 2013-12-05 | 2016-04-15 | Constellium France | ALUMINUM-COPPER-LITHIUM ALLOY PRODUCT FOR INTRADOS ELEMENT WITH IMPROVED PROPERTIES |
FR3014905B1 (en) * | 2013-12-13 | 2015-12-11 | Constellium France | ALUMINUM-COPPER-LITHIUM ALLOY PRODUCTS WITH IMPROVED FATIGUE PROPERTIES |
FR3014904B1 (en) * | 2013-12-13 | 2016-05-06 | Constellium France | PRODUCTS FILES FOR PLASTER FLOORS IN LITHIUM COPPER ALLOY |
CN106521270B (en) * | 2016-12-07 | 2018-08-03 | 中国航空工业集团公司北京航空材料研究院 | A kind of heat treatment process improving aluminium lithium alloy corrosion resistance |
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BR112019021170A2 (en) | 2020-04-28 |
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WO2018189471A1 (en) | 2018-10-18 |
US20210087665A1 (en) | 2021-03-25 |
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CA3058021A1 (en) | 2018-10-18 |
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