EP2836620B1 - Alliage aluminium cuivre lithium à résistance au choc améliorée - Google Patents
Alliage aluminium cuivre lithium à résistance au choc améliorée Download PDFInfo
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- EP2836620B1 EP2836620B1 EP13722480.4A EP13722480A EP2836620B1 EP 2836620 B1 EP2836620 B1 EP 2836620B1 EP 13722480 A EP13722480 A EP 13722480A EP 2836620 B1 EP2836620 B1 EP 2836620B1
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- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 title claims description 6
- 229910052782 aluminium Inorganic materials 0.000 title claims description 6
- 239000004411 aluminium Substances 0.000 title claims 2
- 229910052744 lithium Inorganic materials 0.000 title description 11
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 title description 8
- 229910045601 alloy Inorganic materials 0.000 claims description 28
- 239000000956 alloy Substances 0.000 claims description 28
- 238000000034 method Methods 0.000 claims description 8
- 239000003351 stiffener Substances 0.000 claims description 8
- 238000010276 construction Methods 0.000 claims description 6
- 238000004519 manufacturing process Methods 0.000 claims description 6
- 229910052742 iron Inorganic materials 0.000 claims description 5
- 238000010791 quenching Methods 0.000 claims description 4
- 230000000171 quenching effect Effects 0.000 claims description 4
- 229910052725 zinc Inorganic materials 0.000 claims description 4
- 238000010438 heat treatment Methods 0.000 claims description 3
- 239000012535 impurity Substances 0.000 claims description 3
- 238000001953 recrystallisation Methods 0.000 claims description 2
- 235000012438 extruded product Nutrition 0.000 claims 13
- 238000001125 extrusion Methods 0.000 claims 1
- 239000010949 copper Substances 0.000 description 16
- 239000011777 magnesium Substances 0.000 description 14
- 239000011572 manganese Substances 0.000 description 11
- 238000010521 absorption reaction Methods 0.000 description 10
- 229910052802 copper Inorganic materials 0.000 description 10
- 229910052709 silver Inorganic materials 0.000 description 10
- 229910052749 magnesium Inorganic materials 0.000 description 9
- 229910052748 manganese Inorganic materials 0.000 description 8
- 230000003068 static effect Effects 0.000 description 8
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 7
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 description 7
- 239000004332 silver Substances 0.000 description 7
- 238000012360 testing method Methods 0.000 description 7
- 239000010936 titanium Substances 0.000 description 7
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 6
- 230000007797 corrosion Effects 0.000 description 6
- 238000005260 corrosion Methods 0.000 description 6
- 239000000203 mixture Substances 0.000 description 6
- 229910052726 zirconium Inorganic materials 0.000 description 6
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 description 5
- 239000001989 lithium alloy Substances 0.000 description 5
- 229910052719 titanium Inorganic materials 0.000 description 5
- 229910000838 Al alloy Inorganic materials 0.000 description 4
- 229910000733 Li alloy Inorganic materials 0.000 description 4
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 4
- -1 aluminum-copper-lithium Chemical compound 0.000 description 4
- 230000002349 favourable effect Effects 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 230000035939 shock Effects 0.000 description 4
- 238000009987 spinning Methods 0.000 description 4
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 3
- 230000002411 adverse Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000005259 measurement Methods 0.000 description 3
- 239000002970 Calcium lactobionate Substances 0.000 description 2
- 238000005266 casting Methods 0.000 description 2
- 229910052804 chromium Inorganic materials 0.000 description 2
- 238000012937 correction Methods 0.000 description 2
- 229910052735 hafnium Inorganic materials 0.000 description 2
- 238000000265 homogenisation Methods 0.000 description 2
- 238000009864 tensile test Methods 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 229910017539 Cu-Li Inorganic materials 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000004090 dissolution Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000007654 immersion Methods 0.000 description 1
- 238000010348 incorporation Methods 0.000 description 1
- 238000005304 joining Methods 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
- 238000007670 refining Methods 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000003756 stirring Methods 0.000 description 1
- 238000005482 strain hardening Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000005496 tempering Methods 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
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
- B21C23/00—Extruding metal; Impact extrusion
- B21C23/002—Extruding materials of special alloys so far as the composition of the alloy requires or permits special extruding methods of sequences
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
- B21C23/00—Extruding metal; Impact extrusion
- B21C23/02—Making uncoated products
- B21C23/04—Making uncoated products by direct extrusion
- B21C23/14—Making other products
- B21C23/142—Making profiles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
- B21C29/00—Cooling or heating work or parts of the extrusion press; Gas treatment of work
- B21C29/003—Cooling or heating of work
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
- B21C35/00—Removing work or waste from extruding presses; Drawing-off extruded work; Cleaning dies, ducts, containers, or mandrels
- B21C35/02—Removing or drawing-off work
- B21C35/023—Work treatment directly following extrusion, e.g. further deformation or surface treatment
-
- 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
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
Definitions
- the invention relates to spun products made of aluminum-copper-lithium alloys, more particularly, such products, their manufacturing and use processes, intended in particular for aeronautical and aerospace construction.
- Aluminum alloy spun products are developed to produce high strength parts for the aerospace industry and the aerospace industry in particular.
- Aluminum alloy spun products are used in the aerospace industry for many applications, such as stiffeners or fuselage rails, fuselage frames, wing stiffeners, floor profiles or beams, as well as track rails. seat.
- Ductile aluminum alloys have a significant ability to absorb impact energy during impact, in particular because they deform plastically.
- the specific energy absorption capacity during a shock of an aluminum alloy profile can be connected to the curve obtained during a tensile test of the material in question, in particular to the area under the curve deformation force. It can thus be evaluated by the product R m x A% or R p0.2 x A% in the direction L and in the direction TL.
- AlCuLi alloys are known.
- the patent US 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 patent US5,455,003 discloses a process for manufacturing Al-Cu-Li alloys which have improved mechanical strength and toughness at cryogenic temperature, particularly through proper work-hardening and tempering.
- the patent US7,438,772 discloses alloys comprising, in weight percent, Cu: 3-5, Mg: 0.5-2, Li: 0.01-0.9 and discourage the use of higher lithium contents due to degradation compromise between toughness and mechanical strength.
- the patent US 7,229,509 discloses an alloy comprising (% by weight): (2.5-5.5) Cu, (0.1-2.5) Li, (0.2-1.0) Mg, (0.2-0, 8) Ag, (0.2-0.8) Mn, 0.4 max Zr or other grain refining agents such as Cr, Ti, Hf, Sc, V.
- the patent application US 2009/142222 A1 discloses alloys comprising (in% by weight), 3.4 to 4.2% Cu, 0.9 to 1.4% Li, 0.3 to 0.7% Ag, 0.1 to 0, 6% Mg, 0.2 to 0.8% of Zn, 0.1 to 0.6% Mn and 0.01 to 0.6% of at least one element for controlling the granular structure. This application also describes a process for manufacturing spun products.
- the patent application WO 2009/036953 discloses an alloy for structural elements comprising (in% by weight) 3.4 to 6.0% Cu, 0.9 to 1.7% Li, about 0.2 to 0.8% Mg, about 0 , 1 to 0.8% Ag, about 0.1 to 0.8% Mn, up to 1.5% Zn and one or more members selected from the group consisting of Zr, Cr, Ti, Sc and Hf, with Fe ⁇ 0.15 and Si ⁇ 0.15.
- AA2195 alloy comprising (in% by weight) 3.7 to 4.3% Cu, 0.8 to 1.2% Li, 0.25 to 0.8% Mg, O, is also known.
- Yet another object of the invention is the use of a product according to the invention for the aeronautical construction as a stiffener or smooth fuselage, fuselage frame, wing stiffener, profile or beam floor or seat rail.
- 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 tension in other words the tensile strength R m , the conventional yield stress at 0.2% elongation R p0.2 , and the elongation at break A% are determined by a tensile test according to standard NF EN ISO 6892-1, the sampling and the direction of the test being defined by the EN 485-1 standard.
- the stress intensity factor (K Q ) is determined according to ASTM E399.
- ASTM E399 gives the criteria to determine if K Q is a valid K 1C value .
- the thickness of the spun products 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 selected class of aluminum-copper-lithium alloys makes it possible to manufacture spun products having improved properties with respect to those of known products, in particular in terms of energy absorption during impact, static mechanical strength properties, corrosion resistance and low density.
- the simultaneous addition of manganese, titanium, zirconium, magnesium and silver allows for the selected copper and lithium contents, to obtain a compromise between a representative parameter of the energy absorption during a shock and the yield point particularly advantageous.
- the copper content is at least 4.2% by weight, preferably at least 4.3% and most preferably at least 4.35% by weight. In one embodiment of the invention, the copper content is at least 4.50% by weight.
- the copper content is at most 4.8 wt.%, Preferably at most 4.7 wt.% And most preferably 4.55 wt.%.
- the selected copper content improves in particular the static mechanical properties.
- a high copper content is, however, unfavorable especially for the density of the alloy.
- the lithium content is at least 0.9% by weight and preferably at least 0.95% by weight.
- the lithium content is at most 1.1% by weight and preferably at most 1.05% by weight. In one embodiment of the invention, the lithium content is at most 1.04% by weight.
- the selected lithium content improves in particular the energy absorbed during an impact.
- An excessively low lithium content is however unfavorable, especially for the density of the alloy.
- the addition of manganese is an important aspect of the present invention.
- the manganese content is at least 0.2% by weight and preferably at least 0.3% by weight.
- the manganese content is at most 0.6% by weight and preferably at most 0.5% by weight. In one embodiment of the invention, the manganese content is at most 0.40% by weight.
- the addition of manganese in these amounts improves in particular the compromise between the desired properties.
- the magnesium content is at least 0.2% by weight and preferably at least 0.30% by weight.
- the magnesium content is at most 0.6% by weight and preferably at most 0.50% by weight.
- the magnesium content is at most 0.40% by weight.
- the silver content is at least 0.15% by weight.
- Content silver is at most 0.25% by weight.
- the present inventors have found that surprisingly silver addition of more than 0.25% by weight could have an adverse effect on the energy absorption during an impact. It is important to combine the silver content from 0.15% to 0.25% by weight to a controlled pull after dissolution and quenching with a permanent deformation of 2 to 4%, in particular because a controlled pull of less than 2% does not then allow to obtain the desired mechanical strength.
- the addition of magnesium and silver is necessary to achieve the favorable compromise between static mechanical strength, absorbed energy, density and toughness.
- the zirconium content is at least 0.07% by weight and preferably at least 0.10% by weight.
- the zirconium content is at most 0.15% by weight and preferably at most 0.13% by weight.
- the addition of zirconium is in particular necessary to maintain the essentially non-recrystallized structure desired for the spun products according to the invention.
- the titanium content is between 0.01 and 0.15% by weight and preferably between 0.02 and 0.05% by weight.
- the addition of titanium makes it possible in particular to obtain a controlled granular structure of the raw form obtained after casting.
- the amount of Fe and Si is less than or equal to 0.1% by weight each. Preferably, the content of Fe and Si is less than 0.08% by weight each.
- the Zn content is less than 0.2% by weight, preferably less than 0.15% by weight and preferably less than 0.1% by weight.
- the presence of Zn can have an adverse effect on the compromise between static mechanical resistance, absorbed energy, density and toughness, especially since this element adversely affects the density of the alloy without having a favorable effect on the static mechanical resistance, absorbed energy and toughness.
- the unavoidable impurities are maintained at a content of less than or equal to 0.05% by weight each and 0.15% by weight in total.
- the products according to the invention preferably have, for a thickness of between 5 and 16 mm, a tenacity K 1C (LT) of at least 24 MPa m and preferably at least 25 MPa m and for a thickness of between 17 and 30 mm a tenacity K 1C (LT) of at least 21 MPa m and preferably at least 22 22 MPa m .
- LT tenacity K 1C
- the products according to the invention have an excellent resistance to corrosion.
- the spun products according to the invention have a resistance of at least 30 days when a stress corrosion test according to ASTM G44 and ASTM G49 standards on specimens taken in the TL direction for a voltage of 450 MPa.
- the spun products according to the invention are particularly advantageous for aircraft construction.
- the products according to the invention are used for aeronautical construction as a stiffener or smooth fuselage, fuselage frame, wing stiffener, profile or beam floor or seat rail.
- the products according to the invention are used as a floor beam, in particular as a beam of the lower floor of the aircraft, or cargo floor, this floor being particularly important during the impact.
- the raw forms were homogenized at a temperature of 490 ° C to 520 ° C adapted according to their composition, spun as spun product described in FIG. Figure 1 whose thickness of the elementary rectangles is between 17 and 22 mm, with an initial hot deformation temperature of about 460 ° C.
- the spun products obtained were dissolved at a temperature suitable for the alloy of between 500 ° C. and 520 ° C., quenched, triturated for about 3% and recovered for 30 hours at 155 ° C.
- the figure 2 presents the trade-off between the elastic limit and the EA parameter.
- the alloy according to the invention makes it possible to reach a particularly advantageous compromise.
- the alloy spun product A according to the invention underwent a stress corrosion test according to ASTM G44 and ASTM G49 standards for a tension of 450 MPa on specimens taken in the TL direction. No rupture was observed after 30 days of testing.
- the alloys A and B presented in Example 1 were spun as a spun product of a different shape and having lower elementary rectangles thicknesses between 5 and 12 mm.
- the crude forms were homogenized 15h at 500 ° C and then 20-25 h at 510 ° C, spun as I-spun product with an initial hot deformation temperature of about 460 ° C.
- the spun products obtained were dissolved at a temperature of approximately 510 ° C., quenched, triturated approximately 3.5% and returned for 30 hours at 155 ° C.
- the mechanical properties in the longitudinal direction were measured on "full thickness” specimens taken from the various elementary rectangles of the spun product (thicknesses 5, 7 and 12 mm) and averaged for the different sections obtained.
- the "full thickness” measurement underestimates the real value measured at mid-thickness on machined specimens, because of the effect of the different microstructure close to the surface.
- a correction factor was introduced to account for this bias, however, the factor was chosen such that the actual machined test specimen value would likely be greater than the indicated corrected value.
- the mechanical properties in the transverse direction were measured on machined specimens taken from the zone of smaller thickness, the only possible zone for this type of measurement because of the length of the specimens necessary for this measurement.
- the toughness properties were measured on specimens taken from the thickest zone.
- the structure of the spun products obtained was essentially non-recrystallized. The degree of recrystallized granular structure between 1 ⁇ 4 and 1 ⁇ 2 thickness was less than 10%.
- the spun product according to the invention achieves a more favorable compromise than the spun product of reference between the mechanical strength and the EA parameter.
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Description
L'invention concerne les produits filés en alliages aluminium-cuivre-lithium, plus particulièrement, de tels produits, leurs procédés de fabrication et d'utilisation, destinés notamment à la construction aéronautique et aérospatiale.The invention relates to spun products made of aluminum-copper-lithium alloys, more particularly, such products, their manufacturing and use processes, intended in particular for aeronautical and aerospace construction.
Des produits filés en alliage d'aluminium sont développés pour produire des pièces de haute résistance destinées notamment à l'industrie aéronautique et à l'industrie aérospatiale.Aluminum alloy spun products are developed to produce high strength parts for the aerospace industry and the aerospace industry in particular.
Les produits filés en alliage d'aluminium sont utilisés dans l'industrie aéronautique pour de nombreuses applications, tels que les raidisseurs ou lisses de fuselage, les cadres de fuselage, les raidisseurs de voilure, les profilés ou poutres de plancher ainsi que les rails de siège.Aluminum alloy spun products are used in the aerospace industry for many applications, such as stiffeners or fuselage rails, fuselage frames, wing stiffeners, floor profiles or beams, as well as track rails. seat.
L'incorporation progressive de davantage de matériaux composites dans les structures aéronautiques a modifié les exigences en ce qui concerne les produits filés incorporés dans les avions, notamment pour des éléments de structure tels que les poutres de plancher. Il est apparu que l'absorption d'énergie lors d'un choc, ou plus particulièrement lors d'un crash, est un critère désormais important pour sélectionner ce produit. Les autres propriétés essentielles sont des caractéristiques mécaniques les plus élevées possible, de façon à diminuer le poids des structures, et la tenue à la corrosion.
Une grandeur telle que la capacité spécifique d'absorption peut être utilisée pour caractériser l'absorption d'énergie lors d'un choc.
La capacité spécifique d'absorption d'énergie lors d'un choc peut être mesurée lors d'un test d'écrasement dans lequel on mesure l'effort fourni en fonction du déplacement réalisé lors de l'écrasement. Il s'agit de la quantité d'énergie dépensée pour écraser une unité de masse de matériau dans la phase d'écrasement stable. Les alliages d'aluminium ductiles ont une capacité importante d'absorption de l'énergie d'impact lors du choc, en particulier car ils se déforment plastiquement. En première approximation la capacité spécifique d'absorption d'énergie lors d'un choc d'un profilé en alliage d'aluminium peut être reliée à la courbe obtenue lors d'un test en traction du matériau considéré, en particulier à l'aire sous la courbe force déformation. On peut ainsi l'évaluer par le produit Rm x A% ou Rp0,2 x A% dans le sens L et dans le sens TL.The gradual incorporation of more composite materials into aeronautical structures has changed the requirements for spun products incorporated in aircraft, particularly for structural members such as floor beams. It appeared that the absorption of energy during a shock, or more particularly during a crash, is now an important criterion for selecting this product. The other essential properties are the highest possible mechanical characteristics, so as to reduce the weight of the structures, and the resistance to corrosion.
A magnitude such that the specific absorption capacity can be used to characterize the energy absorption during an impact.
The specific energy absorption capacity during an impact can be measured during a crash test in which the force provided is measured as a function of the displacement achieved. during the crash. This is the amount of energy expended to crush a unit mass of material in the stable crush phase. Ductile aluminum alloys have a significant ability to absorb impact energy during impact, in particular because they deform plastically. As a first approximation, the specific energy absorption capacity during a shock of an aluminum alloy profile can be connected to the curve obtained during a tensile test of the material in question, in particular to the area under the curve deformation force. It can thus be evaluated by the product R m x A% or R p0.2 x A% in the direction L and in the direction TL.
Les alliages AlCuLi sont connus.AlCuLi alloys are known.
Le brevet
Le brevet
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La demande de brevet
La demande de brevet
On connait par ailleurs l'alliage AA2195 comprenant (en % en poids) 3,7 à 4,3 % de Cu, 0,8 à 1,2 % de Li, 0,25 à 0,8 % de Mg, 0,25 à 0,6 % de Ag, moins de 0,25% de Mn, moins de 0,25% de Zn 0,08 à 0,16 % de Zr, moins de 0,10% de Ti, moins de 0,15 % de Fe et moins de 0,12 % de Si. Des profilés en alliage 2195 sont décris par exemple dans le document
Il existe un besoin pour des produits filés en alliage aluminium-cuivre-lithium présentant des propriétés améliorées par rapport à celles des produits connus, en particulier en termes d'absorption d'énergie lors d'un choc, de propriétés de résistance mécanique statique et de résistance à la corrosion, tout en ayant une faible densité. Simultanément il convient de maintenir une ténacité satisfaisante pour ces produits.The patent application
The patent application
AA2195 alloy comprising (in% by weight) 3.7 to 4.3% Cu, 0.8 to 1.2% Li, 0.25 to 0.8% Mg, O, is also known. 25 to 0.6% Ag, less than 0.25% Mn, less than 0.25% Zn 0.08 to 0.16% Zr, less than 0.10% Ti, less than 0, 15% Fe and less than 0.12% Si. 2195 alloy sections are described for example in the document
There is a need for aluminum-copper-lithium alloy spun products having improved properties over those of the known products, particularly in terms of energy absorption during impact, static mechanical strength properties and resistance to corrosion, while having a low density. At the same time, it is necessary to maintain a satisfactory tenacity for these products.
Un premier objet de l'invention est un produit filé dont l'épaisseur d'au moins un rectangle élémentaire, définie selon la norme EN 2066:2001, est comprise entre 1 mm et 30 mm, en alliage à base d'aluminium comprenant
- 4,2 à 4,8 % en poids de Cu,
- 0,9 à 1,1 % en poids de Li,
- 0,15 à 0,25 % en poids de Ag,
- 0,2 à 0,6 % en poids de Mg,
- 0,07 à 0,15 % en poids de Zr,
- 0,2 à 0,6 % en poids de Mn,
- 0,01 à 0,15 % en poids de Ti
- 4.2 to 4.8% by weight of Cu,
- 0.9 to 1.1% by weight of Li,
- 0.15 to 0.25% by weight of Ag,
- 0.2 to 0.6% by weight of Mg,
- 0.07 to 0.15% by weight of Zr,
- 0.2 to 0.6% by weight of Mn,
- 0.01 to 0.15% by weight of Ti
Un autre objet de l'invention est un procédé de fabrication d'un produit filé selon l'invention dans lequel :
- (a) on coule une forme brute en alliage selon l'invention,
- (b) on homogénéise ladite forme brute à une température de 490°C à 520 °C pendant 8 à 48 heures,
- (c) on déforme à chaud par filage ladite forme brute avec une température initiale de déformation à chaud de 420 °C à 480 °C pour obtenir un produit filé,
- (d) on met en solution ledit produit filé à une température de 500 °C à 520 °C pendant 15 minutes à 8 heures,
- (e) on trempe,
- (f) on tractionne de façon contrôlée ledit produit filé avec une déformation permanente de 2 à 4%,
- (g) optionnellement on effectue un dressage dudit produit filé,
- (h) on réalise un revenu dudit produit filé par chauffage à une température de 100 °C à 170°C pendant 5 à 100 heures.
- (a) casting a raw form of alloy according to the invention,
- (b) homogenizing said crude form at a temperature of 490 ° C to 520 ° C for 8 to 48 hours,
- (c) hot-spinning said raw form with an initial hot deformation temperature of 420 ° C to 480 ° C to obtain a spun product,
- (d) dissolving said spun product at a temperature of 500 ° C to 520 ° C for 15 minutes to 8 hours,
- (e) quenching,
- (f) controlling said spun product in a controlled manner with a permanent deformation of 2 to 4%,
- (g) optionally, a dressing is carried out of said spun product,
- (h) yielding said spun product by heating at a temperature of 100 ° C to 170 ° C for 5 to 100 hours.
Encore un autre objet de l'invention est l'utilisation d'un produit selon l'invention pour la construction aéronautique comme raidisseur ou lisse de fuselage, cadre de fuselage, raidisseur de voilure, profilé ou poutre de plancher ou rail de siège.Yet another object of the invention is the use of a product according to the invention for the aeronautical construction as a stiffener or smooth fuselage, fuselage frame, wing stiffener, profile or beam floor or seat rail.
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Figure 1 : Vue en coupe du produit filé de l'exemple 1.Figure 1 : Sectional view of the spun product of Example 1. -
Figure 2 : Compromis entre la limite d'élasticité et le paramètre EA pour les produits filés de l'exemple 1.Figure 2 : Compromise between the yield strength and the EA parameter for the spun products of Example 1.
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. L'expression 1,4 Cu signifie que la teneur en cuivre exprimée en % en poids est multipliée par 1,4. 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
Les caractéristiques mécaniques statiques en traction, en d'autres termes la résistance à la rupture Rm, la limite d'élasticité conventionnelle à 0,2% d'allongement Rp0,2, et l'allongement à la rupture A%, sont déterminés par un essai de traction selon la norme NF EN ISO 6892-1, le prélèvement et le sens de l'essai étant définis par la norme EN 485-1.Unless stated otherwise, all the information concerning the chemical composition of the alloys is expressed as a percentage by weight based on the total weight of the alloy. The expression 1.4 Cu means that the copper content expressed in% by weight is multiplied by 1.4. The designation of alloys is 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 static mechanical characteristics in tension, in other words the tensile strength R m , the conventional yield stress at 0.2% elongation R p0.2 , and the elongation at break A% are determined by a tensile test according to standard NF EN ISO 6892-1, the sampling and the direction of the test being defined by the EN 485-1 standard.
Le facteur d'intensité de contrainte (KQ) est déterminé selon la norme ASTM E399. La norme ASTM E399 donne les critères qui permettent de déterminer si KQ est une valeur valide de K1C. Pour une géométrie d'éprouvette donnée, les valeurs de KQ obtenues pour différents matériaux sont comparables entre elles pour autant que les limites d'élasticité des matériaux soient du même ordre de grandeur.
Sauf mention contraire, les définitions de la norme EN 12258 s'appliquent.
L'épaisseur des produits filés 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. La semelle est le rectangle élémentaire présentant la plus grande dimension A.The stress intensity factor (K Q ) is determined according to ASTM E399. ASTM E399 gives the criteria to determine if K Q is a valid K 1C value . For a given specimen geometry, the K Q values obtained for different materials are comparable to each other as long as the elasticity limits of the materials are of the same order of magnitude.
Unless otherwise specified, the definitions of EN 12258 apply.
The thickness of the spun products 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.
Selon la présente invention, une classe sélectionnée d'alliages d'aluminium-cuivre-lithium permet de fabriquer des produits filés présentant des propriétés améliorées par rapport à celles des produits connus, en particulier en termes d'absorption d'énergie lors d'un choc, de propriétés de résistance mécanique statique, de résistance à la corrosion et ayant une faible densité.
L'addition simultanée de manganèse, de titane, de zirconium, de magnésium et d'argent, permet pour les teneurs en cuivre et en lithium sélectionnées, d'obtenir un compromis entre un paramètre représentatif de l'absorption d'énergie lors d'un choc et la limite d'élasticité particulièrement avantageux.According to the present invention, a selected class of aluminum-copper-lithium alloys makes it possible to manufacture spun products having improved properties with respect to those of known products, in particular in terms of energy absorption during impact, static mechanical strength properties, corrosion resistance and low density.
The simultaneous addition of manganese, titanium, zirconium, magnesium and silver allows for the selected copper and lithium contents, to obtain a compromise between a representative parameter of the energy absorption during a shock and the yield point particularly advantageous.
La teneur en cuivre est au moins de 4,2 % en poids, de préférence au moins 4,3 % et de manière préférée au moins 4,35 % en poids. Dans un mode de réalisation de l'invention la teneur en cuivre est au moins de 4,50 % en poids. La teneur en cuivre est au plus de 4,8 % en poids, de préférence au plus 4,7 % en poids et de manière préférée au plus 4,55 % en poids. La teneur en cuivre sélectionnée améliore notamment les propriétés mécaniques statiques. Une teneur en cuivre élevée est cependant défavorable notamment pour la densité de l'alliage.
La teneur en lithium est au moins de 0,9 % en poids et de préférence au moins 0,95 %.en poids. La teneur en lithium est au plus de 1,1 % en poids et de préférence au plus 1,05 % en poids. Dans un mode de réalisation de l'invention la teneur en lithium est au plus de 1,04 % en poids. La teneur en lithium sélectionnée améliore notamment l'énergie absorbée lors d'un choc. Une teneur en lithium trop faible est cependant défavorable notamment pour la densité de l'alliage.
L'addition de manganèse est un aspect important de la présente invention. La teneur en manganèse est au moins de 0,2 % en poids et de préférence au moins 0,3 % en poids. La teneur en manganèse est au plus de 0,6 % en poids et de préférence au plus 0,5 % en poids. Dans un mode de réalisation de l'invention la teneur en manganèse est au plus de 0,40 % en poids. L'addition de manganèse dans ces quantités améliore en particulier le compromis entre les propriétés recherchées.
La teneur en magnésium est au moins 0,2% en poids et de préférence au moins 0,30% en poids. La teneur en magnésium est au plus de 0,6 % en poids et de préférence au plus de 0,50 % en poids. Dans un mode de réalisation de l'invention la teneur en magnésium est au plus de 0,40 % en poids. La teneur en argent est au moins de 0,15 % en poids. La teneur en argent est au plus de 0,25 % en poids. Les présents inventeurs ont constaté que de manière surprenante une addition d'argent de plus de 0,25% en poids pouvait avoir un effet défavorable sur l'absorption d'énergie lors d'un choc. Il est important de combiner la teneur en argent de 0,15% à 0,25% en poids à une traction contrôlée après mise en solution et trempe avec une déformation permanente de 2 à 4%, notamment car une traction contôlée inférieure à 2% ne permet pas alors d'obtenir la résistance mécanique souhaitée. L'addition de magnésium et d'argent est nécessaire pour atteindre le compromis favorable entre résistance mécanique statique, énergie absorbée, densité et ténacité.
La teneur en zirconium est au moins de 0,07 % en poids et de préférence au moins de 0,10% en poids. La teneur en zirconium est au plus de 0,15% en poids et de préférence au plus de 0,13 % en poids. L'addition de zirconium est notamment nécessaire pour maintenir la structure essentiellement non-recristallisée souhaitée pour les produits filés selon l'invention.
La teneur en titane est comprise entre 0,01 et 0,15 % en poids et de préférence entre 0,02 et 0,05 % en poids. L'addition de titane permet notamment d'obtenir une structure granulaire contrôlée de la forme brute obtenue après la coulée.
La quantité de Fe et de Si est inférieure ou égale à 0,1 % en poids chacun. De préférence la teneur en Fe et en Si est inférieure à 0,08 % en poids chacun.
La teneur en Zn est inférieure à 0,2 % en poids, de préférence inférieure à 0,15 % en poids et de manière préférée inférieure à 0,1 % en poids. La présence de Zn peut avoir un effet défavorable sur le compromis entre résistance mécanique statique, énergie absorbée, densité et ténacité, notamment car cet élément nuit à la densité de l'alliage sans apporter d'effet favorable sur la résistance mécanique statique, l'énergie absorbée et la ténacité.
Les impuretés inévitables sont maintenues à une teneur inférieure ou égale à 0,05% en poids chacune et 0,15% en poids au total.The copper content is at least 4.2% by weight, preferably at least 4.3% and most preferably at least 4.35% by weight. In one embodiment of the invention, the copper content is at least 4.50% by weight. The copper content is at most 4.8 wt.%, Preferably at most 4.7 wt.% And most preferably 4.55 wt.%. The selected copper content improves in particular the static mechanical properties. A high copper content is, however, unfavorable especially for the density of the alloy.
The lithium content is at least 0.9% by weight and preferably at least 0.95% by weight. The lithium content is at most 1.1% by weight and preferably at most 1.05% by weight. In one embodiment of the invention, the lithium content is at most 1.04% by weight. The selected lithium content improves in particular the energy absorbed during an impact. An excessively low lithium content is however unfavorable, especially for the density of the alloy.
The addition of manganese is an important aspect of the present invention. The manganese content is at least 0.2% by weight and preferably at least 0.3% by weight. The manganese content is at most 0.6% by weight and preferably at most 0.5% by weight. In one embodiment of the invention, the manganese content is at most 0.40% by weight. The addition of manganese in these amounts improves in particular the compromise between the desired properties.
The magnesium content is at least 0.2% by weight and preferably at least 0.30% by weight. The magnesium content is at most 0.6% by weight and preferably at most 0.50% by weight. In one embodiment of the invention, the magnesium content is at most 0.40% by weight. The silver content is at least 0.15% by weight. Content silver is at most 0.25% by weight. The present inventors have found that surprisingly silver addition of more than 0.25% by weight could have an adverse effect on the energy absorption during an impact. It is important to combine the silver content from 0.15% to 0.25% by weight to a controlled pull after dissolution and quenching with a permanent deformation of 2 to 4%, in particular because a controlled pull of less than 2% does not then allow to obtain the desired mechanical strength. The addition of magnesium and silver is necessary to achieve the favorable compromise between static mechanical strength, absorbed energy, density and toughness.
The zirconium content is at least 0.07% by weight and preferably at least 0.10% by weight. The zirconium content is at most 0.15% by weight and preferably at most 0.13% by weight. The addition of zirconium is in particular necessary to maintain the essentially non-recrystallized structure desired for the spun products according to the invention.
The titanium content is between 0.01 and 0.15% by weight and preferably between 0.02 and 0.05% by weight. The addition of titanium makes it possible in particular to obtain a controlled granular structure of the raw form obtained after casting.
The amount of Fe and Si is less than or equal to 0.1% by weight each. Preferably, the content of Fe and Si is less than 0.08% by weight each.
The Zn content is less than 0.2% by weight, preferably less than 0.15% by weight and preferably less than 0.1% by weight. The presence of Zn can have an adverse effect on the compromise between static mechanical resistance, absorbed energy, density and toughness, especially since this element adversely affects the density of the alloy without having a favorable effect on the static mechanical resistance, absorbed energy and toughness.
The unavoidable impurities are maintained at a content of less than or equal to 0.05% by weight each and 0.15% by weight in total.
Les produits filés selon l'invention sont préparés à l'aide d'un procédé dans lequel tout d'abord on coule une forme brute en alliage selon l'invention. De préférence, la forme brute est une billette de filage. La forme brute est ensuite homogénéisée à une température de 490°C à 520 °C pendant 8 à 48 heures. L'homogénéisation peut être réalisée en un ou plusieurs paliers. La forme brute peut être refroidie jusqu'à température ambiante après homogénéisation ou directement amenée à la température de déformation à chaud. La forme brute homogénéisée est déformée à chaud par filage avec une température initiale de déformation à chaud de 420 °C à 480 °C pour obtenir un produit filé. La température de filage utilisée permet notamment d'obtenir la structure essentiellement non-recristallisée souhaitée.
Les produits filés selon l'invention sont des profilés dont l'épaisseur d'au moins un des rectangles élémentaires est comprise entre 1 mm et 30 mm, de préférence entre 2 à 20 mm et de manière préférée entre 5 et 16 mm. Les produits filés utilisés en construction aéronautique comprennent généralement plusieurs segments ou rectangles élémentaires d'épaisseurs différentes. Une difficulté rencontrée avec ces produits est d'atteindre des propriétés satisfaisantes dans les différents segments. L'alliage selon l'invention permet notamment d'obtenir un compromis favorable entre résistance mécanique statique, énergie absorbée, densité et ténacité pour des rectangles élémentaires d'épaisseurs différentes.
Le produit filé ainsi obtenu est ensuite mis en solution à une température de 500 °C à 520 °C pendant 15 minutes à 8 heures puis trempé avec de l'eau à température ambiante. La trempe est effectuée de préférence à l'eau, par aspersion ou par immersion.
Le produit filé ainsi mis en solution et trempé est ensuite tractionné avec une déformation permanente de 2 à 4%. Une déformation permanente par traction trop faible, telle qu'une déformation par traction de 1,5%, ne permet pas d'atteindre le compromis entre propriétés souhaité. Une déformation permanente par traction trop élevée, telle qu'une déformation de 6 % ne permet notamment pas de garantir les caractéristiques dimensionnelles du produit filé, typiquement en ce qui concerne les angles entre les différents rectangles élémentaires. Il peut être nécessaire de réaliser une opération de dressage du produit filé pour obtenir les propriétés souhaitées d'un point de vue dimensionnel.
Le produit filé est enfin revenu par chauffage à une température de 100 °C à 170°C pendant 5 à 100 heures. Le revenu peut être effectué en un ou plusieurs paliers. De manière préférée, le revenu est effectué en un palier à une température comprise entre 130 °C et 170 °C et avantageusement entre 150 et 160 °C pendant une durée de 20 à 40 h.
Les produits filés ainsi obtenus ont de préférence une structure granulaire essentiellement non-recristallisée. Dans le cadre de la présente invention, on appelle structure granulaire essentiellement non-recristallisée une structure granulaire telle que le taux de recristallisation entre ¼ et ½ épaisseur d'un rectangle élémentaire est inférieur à 30% et de préférence inférieur à 10%.
Les produits filés selon l'invention ont des propriétés mécaniques particulièrement avantageuses.
Ainsi de manière préférée, les produits filés selon l'invention ont comme propriétés à mi-épaisseur :
- pour une épaisseur comprise entre 5 et 16 mm
- une limite d'élasticité moyenne Rp0,2 dans le sens L d'au moins 630 MPa et de préférence d'au moins 635 MPa et
- une limite d'élasticité moyenne Rp0,2 dans le sens TL d'au moins 625 MPa et de préférence d'au moins 630 MPa et
- un facteur EA
- au moins égal à 14000 et de préférence au moins égal à 14500
et/ou - pour une épaisseur comprise entre 17 et 30 mm
- une limite d'élasticité moyenne Rp0,2 dans le sens L d'au moins 655 MPa et de préférence d'au moins 660 MPa et
- une limite d'élasticité moyenne Rp0,2 dans le sens TL d'au moins 600 MPa et de préférence d'au moins 605 MPa et
- un facteur EA
- au moins égal à 9500 et de préférence au moins égal à 9800.
The products spun according to the invention are profiles whose thickness of at least one of the elementary rectangles is between 1 mm and 30 mm, preferably between 2 to 20 mm and preferably between 5 and 16 mm. Spun products used in aeronautical construction generally comprise several segments or elementary rectangles of different thicknesses. A difficulty encountered with these products is to achieve satisfactory properties in the different segments. The alloy according to the invention makes it possible in particular to obtain a favorable compromise between static mechanical strength, absorbed energy, density and toughness for elementary rectangles of different thicknesses.
The spun product thus obtained is then dissolved at a temperature of 500 ° C to 520 ° C for 15 minutes to 8 hours and then quenched with water at room temperature. Quenching is preferably carried out with water, by spraying or immersion.
The spun product thus dissolved and quenched is then tractionned with a permanent deformation of 2 to 4%. A permanent deformation by too weak a traction, such as a deformation by traction of 1.5%, does not make it possible to reach the compromise between desired properties. A permanent deformation by traction that is too high, such as a deformation of 6%, makes it impossible in particular to guarantee the dimensional characteristics of the spun product, typically as regards the angles between the various elementary rectangles. It may be necessary to perform a dressing operation of the spun product to obtain the desired properties from a dimensional point of view.
The spun product was finally heated back to a temperature of 100 ° C to 170 ° C for 5 to 100 hours. The income can be made in one or more levels. Preferably, the income is carried out in a stage at a temperature between 130 ° C and 170 ° C and preferably between 150 and 160 ° C for a period of 20 to 40 hours.
The spun products thus obtained preferably have a substantially non-recrystallized granular structure. In the context of the present invention, the term granular structure essentially non-recrystallized a granular structure such that the recrystallization rate between ¼ and ½ thickness of an elementary rectangle is less than 30% and preferably less than 10%.
The spun products according to the invention have particularly advantageous mechanical properties.
Thus, preferably, the products spun according to the invention have as properties at mid-thickness:
- for a thickness between 5 and 16 mm
- an average yield strength R p0,2 in the L direction of at least 630 MPa and preferably at least 635 MPa and
- a mean yield strength R p0.2 in the TL direction of at least 625 MPa and preferably at least 630 MPa and
- an EA factor
- at least 14000 and preferably at least 14500
and or - for a thickness of between 17 and 30 mm
- a mean yield strength R p0,2 in the L direction of at least 655 MPa and preferably at least 660 MPa and
- an average yield strength R p0,2 in the TL direction of at least 600 MPa and preferably at least 605 MPa and
- an EA factor
- at least 9500 and preferably at least 9800.
Ainsi les produits selon l'invention ont de préférence pour une épaisseur comprise entre 5 et 16 mm une ténacité K1C(L-T), d'au moins
Enfin les produits selon l'invention présentent une excellente résistance à la corrosion. Ainsi les produits filés selon l'invention présentent une résistance d'au moins 30 jours lors d'un test de corrosion sous contrainte selon les normes ASTM G44 et ASTM G49 sur des éprouvettes prélevées dans le sens TL pour une tension de 450 MPa.Finally, the products according to the invention have an excellent resistance to corrosion. Thus the spun products according to the invention have a resistance of at least 30 days when a stress corrosion test according to ASTM G44 and ASTM G49 standards on specimens taken in the TL direction for a voltage of 450 MPa.
Les produits filés selon l'invention sont particulièrement avantageux pour la construction aéronautique. Ainsi, les produits selon l'invention sont utilisés pour la construction aéronautique comme raidisseur ou lisse de fuselage, cadre de fuselage, raidisseur de voilure, profilé ou poutre de plancher ou rail de siège. Dans un mode de réalisation préféré on utilise les produits selon l'invention comme poutre de plancher, notamment comme poutre du plancher inférieur des avions, ou plancher cargo, ce plancher étant particulièrement important lors du choc.The spun products according to the invention are particularly advantageous for aircraft construction. Thus, the products according to the invention are used for aeronautical construction as a stiffener or smooth fuselage, fuselage frame, wing stiffener, profile or beam floor or seat rail. In a preferred embodiment, the products according to the invention are used as a floor beam, in particular as a beam of the lower floor of the aircraft, or cargo floor, this floor being particularly important during the impact.
Dans cet exemple, cinq alliages dont la composition est donnée dans le tableau 1 ont été préparés et coulés sous une forme brute.
Les formes brutes ont été homogénéisées à une température de 490°C à 520 °C adaptée selon leur composition, filées sous forme de produit filé décrit dans la
Les propriétés mécaniques obtenues pour des échantillons cylindriques de diamètre 10 mm prélevés à mi-épaisseur et quart-largeur dans la semelle d'épaisseur 18 mm des produits filés sont présentées dans le tableau 2. Afin d'évaluer l'absorption d'énergie lors d'un choc on a calculé le paramètre
La structure des produit filés obtenus était essentiellement non-recristallisée. Le taux de structure granulaire recristallisée entre ¼ et ½ épaisseur était inférieur à 10 %.
La
Le produit filé en alliage A selon l'invention a subit un test de corrosion sous contrainte selon les normes ASTM G44 et ASTM G49 pour une tension de 450 MPa sur des éprouvettes prélevées dans le sens TL. Aucune rupture n'a été observée après 30 jours de test.The alloy spun product A according to the invention underwent a stress corrosion test according to ASTM G44 and ASTM G49 standards for a tension of 450 MPa on specimens taken in the TL direction. No rupture was observed after 30 days of testing.
Dans cet exemple, les alliages A et B présentés dans l'exemple 1 ont été filés sous forme d'un produit filé d'une forme différente et présentant des épaisseurs de rectangles élémentaires plus faibles, comprises entre 5 et 12 mm. Les formes brutes ont été homogénéisées 15h à 500 °C puis 20 à 25h à 510 °C, filées sous forme de produit filé en I avec une température initiale de déformation à chaud d'environ 460 °C. Les produits filés obtenus ont été mis en solution à une température d'environ 510 °C, trempés, tractionnés environ 3,5 % et revenus 30h à 155 °C.In this example, the alloys A and B presented in Example 1 were spun as a spun product of a different shape and having lower elementary rectangles thicknesses between 5 and 12 mm. The crude forms were homogenized 15h at 500 ° C and then 20-25 h at 510 ° C, spun as I-spun product with an initial hot deformation temperature of about 460 ° C. The spun products obtained were dissolved at a temperature of approximately 510 ° C., quenched, triturated approximately 3.5% and returned for 30 hours at 155 ° C.
Les propriétés mécaniques dans la direction longitudinale ont été mesurées sur des éprouvettes « pleine épaisseur », prélevées dans les différents rectangles élémentaires du produit filé (épaisseurs 5, 7 et 12 mm) et moyennées pour les différents profilés obtenus. La mesure « pleine épaisseur » sous estime la valeur réelle mesurée à mi-épaisseur sur des éprouvettes usinées, à cause de l'effet de la microstructure différente proche de la surface. Un facteur de correction a été introduit pour tenir compte de ce biais, cependant le facteur a été choisi de telle façon que la valeur réelle sur éprouvette usinée serait sans doute supérieure à la valeur corrigée indiquée. Les propriétés mécaniques dans la direction transverse ont été mesurées sur des éprouvettes usinées prélevées dans la zone de plus faible épaisseur, seule zone possible pour ce type de mesure en raison de la longueur des éprouvettes nécessaire pour cette mesure. Les propriétés de ténacité ont été mesurées sur des éprouvettes prélevées dans la zone de plus forte épaisseur.
La structure des produit filés obtenus était essentiellement non-recristallisée. Le taux de structure granulaire recristallisée entre ¼ et ½ épaisseur était inférieur à 10 %.The mechanical properties in the longitudinal direction were measured on "full thickness" specimens taken from the various elementary rectangles of the spun product (thicknesses 5, 7 and 12 mm) and averaged for the different sections obtained. The "full thickness" measurement underestimates the real value measured at mid-thickness on machined specimens, because of the effect of the different microstructure close to the surface. A correction factor was introduced to account for this bias, however, the factor was chosen such that the actual machined test specimen value would likely be greater than the indicated corrected value. The mechanical properties in the transverse direction were measured on machined specimens taken from the zone of smaller thickness, the only possible zone for this type of measurement because of the length of the specimens necessary for this measurement. The toughness properties were measured on specimens taken from the thickest zone.
The structure of the spun products obtained was essentially non-recrystallized. The degree of recrystallized granular structure between ¼ and ½ thickness was less than 10%.
Les propriétés mécaniques ainsi obtenues sont présentées dans le Tableau 3.
A nouveau, le produit filé selon l'invention atteint un compromis plus favorable que le produit filé de référence entre la résistance mécanique et le paramètre EA.Again, the spun product according to the invention achieves a more favorable compromise than the spun product of reference between the mechanical strength and the EA parameter.
Claims (12)
- Extruded product for which the thickness of at least one elementary rectangle, defined according to the standard EN 2066:2001, is between 1 mm and 30 mm, made of an aluminium-based alloy comprising
4.2wt% to 4.8wt% of Cu,
0.9wt% to 1.1wt% of Li,
0.15wt% to 0.25wt% of Ag,
0.2wt% to 0.6wt% of Mg,
0.07wt% to 0.15wt% of Zr,
0.2wt% to 0.6wt% of Mn,
0.01wt% to 0.15wt% of Ti,
a quantity of Zn less than 0.2wt%, a quantity of Fe and Si each less than or equal to 0.1wt%, and inevitable impurities each with a content less than or equal to 0.05wt% and 0.15wt% in total. - Extruded product according to claim 1, comprising 4.3wt% to 4.7wt% of Cu and preferably 4.35wt% to 4.55wt% of Cu.
- Extruded product according to claim 1 or claim 2, comprising 0.95wt% to 1.05wt% of Li.
- Extruded product according to any one of claims 1 to 3 comprising 0.30wt% to 0.50wt% of Mg and/or 0.10wt% to 0.13wt% of Zr.
- Extruded product according to any one of claims 1 to 4 comprising 0.3wt% to 0.5wt% of Mn.
- Extruded product according to any one of claims 1 to 5 comprising less than 0.15wt% Zn and preferably less than 0.1wt% Zn.
- Extruded product according to any one of claims 1 to 6 characterised in that it is a profile for which the thickness of said at least one elementary rectangle is between 2 mm and 20 mm and preferably between 5 mm and 16 mm.
- Product according to any one of claims 1 to 7 for which the recrystallisation rate between ¼ and ½ thickness of said elementary rectangle is less than 30% and preferably less than 10%.
- Extruded product according to any one of claims 1 to 8 having at mid-thickness
for a thickness of between 5 mm and 16 mm
an average tensile yield stress Rp0.2 in the L-direction of at least 630 MPa and preferably of at least 635 MPa and
an average tensile yield stress Rp0.2 in the TL-direction at least 625 MPa and preferably at least 630 MPa and
a factor EA
and/or
for a thickness between 17 mm and 30 mm
an average tensile yield stress Rp0.2 in the L-direction of at least 655 MPa and preferably of at least 660 MPa and
an average tensile yield stress Rp0.2 in the TL-direction of at least 600 MPa and preferably of at least 605 MPa and
a factor EA - Process for manufacturing a product according to any one of claims 1 to 10 wherein:(a) an alloy unwrought product is cast according to one of claims 1 to 6,(b) said unwrought product is homogenised at a temperature of 490°C to 520°C for 8 to 48 hours,(c) said unwrought product is hot worked by extrusion at an initial hot working temperature of 420°C to 480°C to obtain an extruded product,(d) said extruded product undergoes solution heat treatment at a temperature of 500°C to 520°C for 15 minutes to 8 hours,(e) quenching,(f) said extruded product undergoes controlled stretching with a permanent set of 2 to 4%,(g) optionally, said extruded product is straightened,(h) said extruded product is aged by heating at a temperature of 100°C to 170°C for 5 to 100 hours.
- Use of a product according to any one of claims 1 to 10 for aeronautic construction as a fuselage stiffener or stringer, circumferential frame, wing stiffener, floor profile or beam or seat track.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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DE13722480.4T DE13722480T1 (en) | 2012-04-11 | 2013-04-10 | ALUMINUM COPPER LITHIUM ALLOY WITH IMPROVED COMPACTNESS |
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US201261622774P | 2012-04-11 | 2012-04-11 | |
FR1201063A FR2989387B1 (en) | 2012-04-11 | 2012-04-11 | LITHIUM COPPER ALUMINUM ALLOY WITH IMPROVED SHOCK RESISTANCE |
PCT/FR2013/000096 WO2013153292A1 (en) | 2012-04-11 | 2013-04-10 | Aluminium copper lithium alloy with improved impact strength |
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EP2836620A1 EP2836620A1 (en) | 2015-02-18 |
EP2836620B1 true EP2836620B1 (en) | 2019-03-27 |
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EP13722480.4A Active EP2836620B1 (en) | 2012-04-11 | 2013-04-10 | Alliage aluminium cuivre lithium à résistance au choc améliorée |
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US (1) | US9945010B2 (en) |
EP (1) | EP2836620B1 (en) |
CN (1) | CN104220616B (en) |
BR (1) | BR112014025110B1 (en) |
CA (1) | CA2869733C (en) |
DE (1) | DE13722480T1 (en) |
FR (1) | FR2989387B1 (en) |
WO (1) | WO2013153292A1 (en) |
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FR3007423B1 (en) | 2013-06-21 | 2015-06-05 | Constellium France | EXTRADOS STRUCTURE ELEMENT IN ALUMINUM COPPER LITHIUM ALUMINUM |
FR3014904B1 (en) * | 2013-12-13 | 2016-05-06 | Constellium France | PRODUCTS FILES FOR PLASTER FLOORS IN LITHIUM COPPER ALLOY |
RU2560485C1 (en) * | 2014-06-10 | 2015-08-20 | Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") | High-strength heat-treatable aluminium alloy and article made thereof |
WO2018037390A2 (en) | 2016-08-26 | 2018-03-01 | Shape Corp. | Warm forming process and apparatus for transverse bending of an extruded aluminum beam to warm form a vehicle structural component |
MX2019004494A (en) | 2016-10-24 | 2019-12-18 | Shape Corp | Multi-stage aluminum alloy forming and thermal processing method for the production of vehicle components. |
CN107964641B (en) * | 2017-10-18 | 2021-02-05 | 中国航发北京航空材料研究院 | Heat treatment method for improving creep forming performance of aluminum-lithium alloy |
US20190233921A1 (en) * | 2018-02-01 | 2019-08-01 | Kaiser Aluminum Fabricated Products, Llc | Low Cost, Low Density, Substantially Ag-Free and Zn-Free Aluminum-Lithium Plate Alloy for Aerospace Application |
FR3080860B1 (en) * | 2018-05-02 | 2020-04-17 | Constellium Issoire | LITHIUM COPPER ALUMINUM ALLOY WITH IMPROVED COMPRESSION RESISTANCE AND TENACITY |
CN110423927A (en) * | 2019-07-17 | 2019-11-08 | 中南大学 | A kind of Ultrahigh strength aluminum lithium alloy and preparation method thereof |
CN110952010A (en) * | 2019-12-18 | 2020-04-03 | 东北轻合金有限责任公司 | Manufacturing method of high-temperature-resistant aluminum alloy plate for rocket tank body |
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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 |
US7438772B2 (en) | 1998-06-24 | 2008-10-21 | Alcoa Inc. | Aluminum-copper-magnesium alloys having ancillary additions of lithium |
DE04753337T1 (en) | 2003-05-28 | 2007-11-08 | Alcan Rolled Products Ravenswood LLC, Ravenswood | NEW AL-CU-LI-MG-AG-MN-ZR ALLOY FOR CONSTRUCTION APPLICATIONS REQUIRING HIGH STRENGTH AND HIGH BROKENNESS |
CA2700250C (en) * | 2007-09-21 | 2016-06-28 | Aleris Aluminum Koblenz Gmbh | Al-cu-li alloy product suitable for aerospace application |
CN104674090A (en) | 2007-12-04 | 2015-06-03 | 美铝公司 | Improved aluminum-copper-lithium alloys |
FR2969177B1 (en) * | 2010-12-20 | 2012-12-21 | Alcan Rhenalu | LITHIUM COPPER ALUMINUM ALLOY WITH ENHANCED COMPRESSION RESISTANCE AND TENACITY |
-
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- 2013-04-10 WO PCT/FR2013/000096 patent/WO2013153292A1/en active Application Filing
- 2013-04-10 CA CA2869733A patent/CA2869733C/en active Active
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CA2869733A1 (en) | 2013-10-17 |
FR2989387A1 (en) | 2013-10-18 |
WO2013153292A1 (en) | 2013-10-17 |
CN104220616B (en) | 2017-12-15 |
FR2989387B1 (en) | 2014-11-07 |
DE13722480T1 (en) | 2015-06-25 |
US20130269840A1 (en) | 2013-10-17 |
CN104220616A (en) | 2014-12-17 |
CA2869733C (en) | 2021-07-20 |
EP2836620A1 (en) | 2015-02-18 |
BR112014025110B1 (en) | 2019-04-24 |
US9945010B2 (en) | 2018-04-17 |
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