EP1544315A1 - Produit corroyé et élément de structure pour aéronef en alliage Al-Zn-Cu-Mg - Google Patents
Produit corroyé et élément de structure pour aéronef en alliage Al-Zn-Cu-Mg Download PDFInfo
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- EP1544315A1 EP1544315A1 EP04356196A EP04356196A EP1544315A1 EP 1544315 A1 EP1544315 A1 EP 1544315A1 EP 04356196 A EP04356196 A EP 04356196A EP 04356196 A EP04356196 A EP 04356196A EP 1544315 A1 EP1544315 A1 EP 1544315A1
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- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 71
- 239000000956 alloy Substances 0.000 title claims abstract description 71
- 229910017818 Cu—Mg Inorganic materials 0.000 title description 9
- 238000005496 tempering Methods 0.000 claims abstract description 4
- 239000000047 product Substances 0.000 claims description 68
- 238000012360 testing method Methods 0.000 claims description 28
- 229910052799 carbon Inorganic materials 0.000 claims description 14
- 229910052751 metal Inorganic materials 0.000 claims description 14
- 239000002184 metal Substances 0.000 claims description 14
- 239000010936 titanium Substances 0.000 claims description 13
- 238000010276 construction Methods 0.000 claims description 12
- 238000004519 manufacturing process Methods 0.000 claims description 10
- 238000007670 refining Methods 0.000 claims description 10
- 238000010791 quenching Methods 0.000 claims description 8
- 230000000171 quenching effect Effects 0.000 claims description 8
- 239000003351 stiffener Substances 0.000 claims description 8
- 238000004090 dissolution Methods 0.000 claims description 7
- 238000003754 machining Methods 0.000 claims description 7
- 229910052719 titanium Inorganic materials 0.000 claims description 7
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 6
- 238000005482 strain hardening Methods 0.000 claims description 5
- 239000010455 vermiculite Substances 0.000 claims description 5
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 4
- 229910052742 iron Inorganic materials 0.000 claims description 3
- 229910001338 liquidmetal Inorganic materials 0.000 claims description 3
- 229910052726 zirconium Inorganic materials 0.000 claims description 3
- PXFBZOLANLWPMH-UHFFFAOYSA-N 16-Epiaffinine Natural products C1C(C2=CC=CC=C2N2)=C2C(=O)CC2C(=CC)CN(C)C1C2CO PXFBZOLANLWPMH-UHFFFAOYSA-N 0.000 claims description 2
- 239000003795 chemical substances by application Substances 0.000 claims description 2
- 229910052802 copper Inorganic materials 0.000 claims description 2
- 239000012467 final product Substances 0.000 claims description 2
- 229910052749 magnesium Inorganic materials 0.000 claims description 2
- AZDRQVAHHNSJOQ-UHFFFAOYSA-N alumane Chemical group [AlH3] AZDRQVAHHNSJOQ-UHFFFAOYSA-N 0.000 claims 1
- 239000011248 coating agent Substances 0.000 claims 1
- 238000000576 coating method Methods 0.000 claims 1
- 229910052782 aluminium Inorganic materials 0.000 abstract description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 abstract description 3
- 238000005097 cold rolling Methods 0.000 abstract 1
- 239000000470 constituent Substances 0.000 abstract 1
- 238000007598 dipping method Methods 0.000 abstract 1
- 239000000203 mixture Substances 0.000 description 16
- 206010016256 fatigue Diseases 0.000 description 15
- 230000035882 stress Effects 0.000 description 15
- 239000011701 zinc Substances 0.000 description 14
- 239000000126 substance Substances 0.000 description 12
- 239000010949 copper Substances 0.000 description 11
- 238000000034 method Methods 0.000 description 11
- 239000011777 magnesium Substances 0.000 description 9
- 230000003068 static effect Effects 0.000 description 9
- XEEYBQQBJWHFJM-UHFFFAOYSA-N iron Substances [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 8
- 230000008569 process Effects 0.000 description 8
- 238000005096 rolling process Methods 0.000 description 8
- 230000007423 decrease Effects 0.000 description 7
- 239000001768 carboxy methyl cellulose Substances 0.000 description 6
- 238000005266 casting Methods 0.000 description 5
- 150000003839 salts Chemical class 0.000 description 5
- 239000000243 solution Substances 0.000 description 5
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 5
- 230000007797 corrosion Effects 0.000 description 4
- 238000005260 corrosion Methods 0.000 description 4
- 238000005098 hot rolling Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 238000004513 sizing Methods 0.000 description 4
- 230000004584 weight gain Effects 0.000 description 4
- 235000019786 weight gain Nutrition 0.000 description 4
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 description 3
- 230000006835 compression Effects 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- 238000007747 plating Methods 0.000 description 3
- 238000009864 tensile test Methods 0.000 description 3
- 229910052725 zinc Inorganic materials 0.000 description 3
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 2
- 241001080024 Telles Species 0.000 description 2
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 2
- 230000032683 aging Effects 0.000 description 2
- 244000052616 bacterial pathogen Species 0.000 description 2
- 230000000052 comparative effect Effects 0.000 description 2
- 238000005336 cracking Methods 0.000 description 2
- 125000004122 cyclic group Chemical group 0.000 description 2
- 238000000265 homogenisation Methods 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 238000011068 loading method Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 229910052710 silicon Inorganic materials 0.000 description 2
- 239000010703 silicon Substances 0.000 description 2
- 238000007711 solidification Methods 0.000 description 2
- 230000008023 solidification Effects 0.000 description 2
- 238000009987 spinning Methods 0.000 description 2
- 239000003381 stabilizer Substances 0.000 description 2
- 230000009466 transformation Effects 0.000 description 2
- 229910052727 yttrium Inorganic materials 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 229910000878 H alloy Inorganic materials 0.000 description 1
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 1
- 229910001199 N alloy Inorganic materials 0.000 description 1
- 229910001096 P alloy Inorganic materials 0.000 description 1
- 238000012356 Product development Methods 0.000 description 1
- 229920000297 Rayon Polymers 0.000 description 1
- 230000004308 accommodation Effects 0.000 description 1
- 239000011825 aerospace material Substances 0.000 description 1
- 230000003042 antagnostic effect Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 125000004429 atom Chemical group 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
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- 125000004432 carbon atom Chemical group C* 0.000 description 1
- 229910052729 chemical element Inorganic materials 0.000 description 1
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Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/10—Alloys based on aluminium with zinc 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
- C22F1/053—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 zinc as the next major constituent
Definitions
- the invention relates to rolled, spun or forged products in Al-Zn-Cu-Mg alloy treated by dissolving, quenching, cold working and tempering, and in particular structural elements elaborated from such products and intended for aircraft construction.
- U.S. Patent 5,865,911 (Aluminum Company of America) discloses an Al-Zn-Cu-Mg alloy of composition Zn 5.9 - 6.7, Mg 1.6 - 1.86, Cu 1.8 - 2.4, Zr 0.08 - 0.15 for the manufacture of structural elements for aircraft. These structural elements are optimized to show high mechanical strength, toughness and fatigue resistance.
- the patent application WO 02/052053 describes three alloys of Al-Zn-Cu-Mg type. of composition (a) Zn 7.3 + Cu 1.6; (b) Zn 6.7 + Cu 1.9; (c) Zn 7.4 + Cu 1.9; each of these three alloys also containing Mg 1.5 + Zr 0.11. She describes also suitable thermomechanical treatment processes for the manufacture of structural elements for aircraft.
- Also known alloy 7040 whose standardized chemical composition is: Zn 5.7 - 6.7 Mg 1.7 - 2.4 Cu 1,5 - 2,3 Zr 0.05 - 0.12 If ⁇ 0.10 Fe ⁇ 0.13 Ti ⁇ 0.06 Mn ⁇ 0.04 other elements ⁇ 0.05 each and ⁇ 0.15 in total.
- alloy 7475 whose standardized chemical composition is: Zn 5.2 - 6.2 Mg 1.9-2.6 Cu 1.2-1.9 Cr 0.18-0.25 If ⁇ 0.10 Fe ⁇ 0.12 Ti ⁇ 0.06 Mn ⁇ 0.06 other elements ⁇ 0.05 each and ⁇ 0.15 in total.
- alloys of the 2xxx series for example alloy 2324.
- Alloys conventionally used for fuselage structure elements belong to the 2xxx series, for example alloy 2024.
- the present invention aims to obtain aircraft structural elements, and fuselage elements, of Al-Zn-Cu-Mg alloy, having, for example, compared with the prior art, an improved mechanical strength, for a tolerance to comparable damage, and sufficient formability.
- the subject of the invention is a wrought product, in particular a laminated, spun or forged product, made of an alloy of composition (% by weight): Zn 6.7 - 7.3 Cu 1.9 - 2.5 Mg 1.0 - 2.0 Zr 0.07 - 0.13 Fe ⁇ 0.15 If ⁇ 0, 1 5 other elements ⁇ 0.05 each and ⁇ 0.15 in total, the rest Al in which Mg / Cu ⁇ 1, treated by dissolving, quenching, cold working, and tempering. Cold working can be obtained by controlled pulling and / or cold processing, for example rolling or drawing.
- the invention also relates to a structural element for construction aeronautical component, in particular an aircraft fuselage element, or an underside element aircraft wing, or an integral structure element for an aircraft, manufactured from a wrought product, and in particular from such a rolled product or spun.
- the static mechanical characteristics ie the ultimate tensile strength R m , the yield strength R p0,2 and the elongation at break A, are determined by a tensile test according to the standard EN 10002-1, the location and direction of specimen collection being defined in EN 485-1.
- the fatigue strength is determined by a test according to ASTM E 466, and the fatigue crack growth rate (so-called da / dn test) according to ASTM E 647.
- the curve R is determined according to ASTM standard E 561. From the curve R, the critical stress intensity factor K c is calculated, ie the intensity factor which causes the instability of the crack. .
- the stress intensity factor K CO is also calculated by assigning to the critical load the initial length of the crack at the beginning of the monotonic loading. These two values are calculated for a specimen of the desired shape. K app means the Kco corresponding to the test piece used for the R curve test.
- the size of the crack at the end of the fatigue pre-cracking step is W / 4 for the test pieces of the type M (T), and W / 2 for CT type specimens, where W is the specimen width as defined in ASTM E 561.
- spun product includes so-called “stretched” products, i.e. products that are developed by spinning followed by stretching.
- structural element or “structural element” of a mechanical construction a mechanical part whose failure is likely to endanger the security of the said construction, its users, its users or others.
- these structural elements include the elements that make up the fuselage (such as fuselage skin (fuselage skin in English), stiffeners or fuselage stringers, watertight bulkheads (bulkheads), circumferential frames, wings (such as wing skin, stiffeners, ribs (ribs) and spars) and the empennage including stabilizers horizontal and vertical (horizontal or vertical stabilizers), as well as floor beams, seat rails and doors.
- integral structure the structure of a part of an airplane that has been designed to ensure as much as possible the continuity of the material on a dimension as large as possible to reduce the number of points mechanical assembly.
- An integral structure may be manufactured either by machining in the mass, either by using shaped parts obtained for example by spinning, forging or molding, or by welding of structural elements made of weldable alloys. We thus obtain elements of size structure larger and in one piece, without mechanical assembly or with a fewer mechanical assembly points compared to an assembled structure in which sheets, thin or strong depending on the destination of the structural element (for example: fuselage element or wing element), are fixed, the most often by riveting, on stiffeners and / or frames (which can be made by machining from spun or rolled products).
- the present invention can be applied to an aluminum alloy containing between 6.7% and 7.3% zinc.
- the zinc content must be high enough to ensure good mechanical properties, but if it is too high, the sensitivity of the quenching alloy increases, which risks, particularly for thick products, degrade the compromise of the properties concerned.
- the product is a sheet of thickness less than 20 mm. In an other advantageous embodiment of the invention, the product is a thick plate of thickness greater than about 20 mm.
- the chemical composition of the Al-Zn-Cu-Mg alloy has been chosen so as to the Mg / Cu ratio of the alloy which is the subject of the invention is less than 1. preferred, this ratio is maintained at a value below 0.9. A lower value at 0.85 or even about 0.8 is preferred.
- the Applicant has found that a zirconium content of between 0.07 and 0.13% gives access for this composition to Al-Zn-Cu-Mg major elements, to a better compromise between R p0.2 , toughness ( at ambient or cold temperature) and fatigue resistance (in particular speed of propagation of fatigue cracks). Above 0.12%, there is a significant risk of forming Al 3 Zr type primary phases, unless the cooling is sufficiently rapid; in the case of semi-continuous casting, such a sufficient speed can be achieved, especially when casting billets.
- the Zr content must be less than 0.12%, and the best results were obtained with a content between 0.07 and 0.09%.
- a zirconium content up to 0.13% may be suitable for billets.
- the silicon and iron contents must be maintained each below 0.15%, and preferably below 0.10%, to have good tenacity.
- the content of iron does not exceed 0.07%, and the silicon content does not exceed 0.06%.
- the alloy according to the invention can be cast according to one of the known techniques of those skilled in the art to obtain a raw form, such as a spinning billet, or a rolling plate. This raw form, possibly after scalping, is then homogenized, typically for a period of 15 to 16 hours at a temperature between 470 and 485 ° C.
- the raw form is then hot processed to form spun products (including bars, tubes or profiles), hot-rolled sheet or parts forged.
- the hot rolling of thick products according to the invention could occur at a temperature of about 350 ° C, much lower than traditionally practiced for this type of product (which is about 415 to 440 ° C), without affecting the compromise of properties required for thick products used in aircraft structures.
- the hot transformation can possibly be followed by a transformation Cold.
- a transformation Cold For example, spun and drawn tubes can be made.
- spun and drawn tubes can be made.
- This solution can be in any suitable oven, such as air oven (horizontal or vertical), or oven bath of salts.
- this dissolution in solution is carried out at a temperature between 470 and 480 ° C, and preferably between 475 and 480 ° C for a period duration of at least 4 hours.
- the dissolution temperature is between 470 ° C and 475 ° C, and the dissolution time, the optimum value of which depends on the thickness of the product is typically at least one hour.
- the products are quenched, preferably in a liquid medium such as water, said liquid preferably having a temperature not exceeding 40 ° C.
- the products are then generally subjected to controlled traction with a permanent elongation of the order of 1 to 5%, and preferably 1.5 to 3%.
- the products are subject to a treatment of income, which influences in a important on the final properties of the product.
- income which influences in a important on the final properties of the product.
- the product according to the invention leads to new products which have particularly interesting characteristics for aeronautical construction.
- These products may be in the form of sheets, including fuselage sheets, thick sheets for intrados or for integral structures, or in the form of profiles, or in the form of forged parts.
- the rolled products according to the invention whether they are thick or thin, have a yield strength R p0.2 (L) of at least 460 MPa, preferably at least 480 MPa, and even more preferentially of at least 500 MPa.
- sheets having a thickness greater than about 20 mm, having a yield strength R p0.2 (L) of at least 520 MPa, a K app are obtained.
- K app LT
- the value of K app (LT) is stable, or even higher, cold compared to its temperature value. room. Specifically, this value is slightly increased from room temperature when measured at -54 ° C. This is particularly interesting since -54 ° C is about the typical temperature reached by the structural elements during the flight of a civilian jet aircraft.
- the products according to the invention advantageously replace the alloy structural elements known alloys 2x24, for example alloy 2024 or 2324.
- rolled products according to the invention may have a thickness of less than 10 mm and thus be used as a fuselage liner. They can also have a thickness greater than about 10 mm and thus be used as intrados. of the rolled products with a thickness greater than about 40 mm may be used for manufacture of structural elements by integral machining, as described below. Rolled products with a thickness greater than about 60 mm can be used for the manufacture of stiffeners or frames, especially for large aircraft capacity.
- the products according to the invention can be plated on at least one face according to methods and with the alloys usually used to plate the products in Al-Zn-Cu-Mg type alloys. This is particularly interesting for sheet metal used for the manufacture of aircraft fuselage elements, which must withstand the corrosion.
- a useable plating alloy is 7072.
- a particularly advantageous use of the products according to the invention is related to the concept of the integral structure in aeronautical construction.
- a big part of the aircraft structures are dimensioned according to a compromise between damage tolerance and resistance to static loads.
- the requirements of tolerance for damage are specified for example in the article "Damage Tolerance Certification of Commercial Aircraft by T. Swift, ASM Handbook vol. 19 (1996), pp 566 - 576.
- Sizing under static loadings is explained by example in the book “Airframe Stress Analysis and Sizing” by Mr. Niu, Hong Kong Conmilit Press Ltd, 1999, in particular pages 607 to 654. From the point of view of the material, it is known that, generally, the damage tolerance of the alloys of the series 7xxx, and in particular their toughness, decreases when their yield strength increases.
- a toughness gain of x% to constant yield strength as with the alloy according to the invention can be translated weight gain of the same level, or even higher if allowing a load stronger on the part considered also allows the lightening of other components.
- a yield strength gain of x%, with a constant damage tolerance can result in a weight gain of the order of x / 3% to x%.
- x is typically between 15 and 30%.
- the continuity between the stiffeners and the skin means that the damage tolerance becomes more critical than in a component assembled by riveting. Indeed, given stress, the stress intensity factor increases sharply when the stiffener is crossed by a crack, since it must be admitted that this stiffener will necessarily be cracked.
- the present inventors have found that products with high tenacity, for a given elastic limit, are particularly well suited to the manufacture of integral structures.
- fuselage barge panels or wing covers are manufactured by integral machining of products according to one of the preceding embodiments, given that said products, and in particular the plates for machining advantageously have a thickness of at least 40 mm; this value also depends on the type of aircraft, and especially its size.
- the product according to the invention with a yield strength R p0.2 (L) at half thickness of at least 540 MPa and a K app toughness (LT) measured on a specimen of type M (T).
- the Applicant has found that refining the grain at a reduced level compared to the usual practice during casting provides a compromise of properties, including a level of tenacity, particularly interesting.
- a TiC refining agent for example adding A13% Ti0.15% C thread
- the solidification germ obtained with this approach having a different germination-growth compromise germs obtained by refining for example with A15% Ti1% B (ie a seed type TiB 2 ).
- the level of this refining can be quantified by the amount of C added, since it corresponds indirectly to the amount of added solidification nuclei, as well as by the amount of free Ti (not combined with C) in the alloy.
- the stoichiometry of the seed is not definitively quantified, it can be considered that the seed is composed of TiC, each C atom combining with a Ti atom to form said seeds.
- affinants Al - x% Ti - y% C there are different types of affinants Al - x% Ti - y% C, in general the Ti being added in excess of C.
- the amount of added seed is proportional to the amount of refining (in kilograms) added per tonne of molten metal multiplied by y%, that is to say proportional to A (number of kilograms of refining added per tonne of metal) x y%.
- the addition of seeds can be quantified by specifying 3 g / t of added C (2 x 0.0015 kg / t).
- an affine containing titanium and carbon so that the amount of carbon added is between 0.4 and 3 g / t of carbon, preferably between 0.6 and 2 g / t, and so that the total Ti content in the final product is between 50 and 500 ppm (by weight), preferably between 150 and 300 ppm.
- N alloy was developed whose chemical composition was in accordance with the invention.
- the liquid metal was first treated in a holding furnace by injection of gas using an Irma ® type rotor, and then into a pocket type Alpur ®, both brands owned by the plaintiff.
- the refining was done in line, that is to say in the channel between the holding oven and the Alpur ® pocket, 1.1 kg / ton of Al-3% Ti-0.15% C wire (9.5 mm diameter). We sank a industrial size plate. It was relaxed for 10 hours at 350 ° C.
- the product thus cast was homogenized after scalping for 15 hours at a temperature between 471 ° C and 482 ° C (880 ° F to 900 ° F), then rolled to hot to a thickness of 5 mm (0.2 inches).
- the start temperature of rolling was 450 ° C (840 ° F), and the end-of-rolling temperature was 349 ° C (660 ° F).
- Sheets of width 178 mm (7 inches) and length 508 mm (20 inches) were taken. These coupons were dissolved in a salt bath oven for 1 hour at 472 ° C, then quenched with water, and triturated until a permanent deformation of 2%.
- the coupons thus obtained subsequently suffered a two-stage artificial aging treatment, the first step being 6 hours at 105 ° C, the second stage being 18 hours at 155 ° C, in order to reach the peak of mechanical properties.
- the alloy was cast by treating the liquid metal first in a holding furnace by injection of gas using an Irma ® type rotor, and then into a pocket type Alpur ®.
- the refining was done online, that is to say in the channel between the oven of maintenance and the Alpur ® bag, at a rate of 0.7 kg / tonne of AT5B wire (diameter 9.5 mm).
- the plates were relaxed for 10h at 350 ° C. These plates have undergone a homogenization for 12 hours at 500 ° C., followed by hot rolling (temperature end of rolling between 230 and 255 ° C) up to a thickness of 6 mm.
- 7xxx alloy plates according to the prior art have also been cast (reference G), in the same foundry device as the 2xxx alloy sheets described previously.
- a plate was obtained which was then homogenized for 24 hours. hours at 470 ° C then 24 hours at 495 ° C, then hot rolled (end temperature of rolling between 230 and 255 ° C) up to a thickness of 6 mm.
- a solution treatment of 1 hour at 450 ° C in a salt bath oven was then made on a coupon of 600 mm by 200 mm. This operation was followed quenching with water and pulling to obtain a permanent deformation of 2%.
- the coupon then underwent an artificial aging treatment of 5 hours at 100 ° C then 6 hours at 155 ° C, in order to reach the peak of mechanical properties (state T6).
- An AA7475 alloy plate was also cast (reference H) following conventional methods of the prior art.
- the plate thus obtained was homogenized for 9 hours at 480 ° C, then co-hot rolled at a temperature of about 270 ° C, with a sheet 7072, to obtain a plated sheet of thickness 4.5 mm.
- the 7072 plating was about 2% of the final thickness.
- the product thus obtained was dissolved in a salt bath oven for 45 minutes at 478 ° C, then quenched with water at a temperature of about 20 ° C, and then underwent a traction to obtain a permanent deformation of 2%. He then suffered a four-hour income operation at 120 ° C, then 24 hours at 162 ° C (state T76).
- the tensile strength R m (in MPa), the conventional yield stress at 0.2% elongation R p0.2 (in MPa) and the elongation at break A (in%) were measured by a tensile test according to EN 10002-1.
- the sheet according to the invention has in both directions measured tensile strength and yield strength much higher than those 2xxx alloy sheets.
- the elongation of the sheet according to the invention is lower that of the sheet E, but sufficient compared to the intended applications.
- the alloy according to the invention is present in both directions measured a breaking strength and a yield strength significantly improved, for comparable lengthening.
- the sheet according to the invention has a Kapp much higher than the alloy sheets 7xxx of the prior art, and of the same order of magnitude as 2xxx alloy sheets.
- Fatigue behavior was also tested according to ASTM E 647, by measuring the crack propagation velocity in sheet N compared with E, F and G.
- the specimens used were of type C (T), with W of 76.2 mm (3 inches).
- the comparative results are shown in Table 4.
- the sheet Y had a thickness of 6 mm.
- Fatigue results sheet metal da / dN (10) TL (10 -4 mm / cycles) da / dN (30) TL (10 -4 mm / cycles) ⁇ K at 100 ⁇ inch / cycle [MPa ⁇ m] N (invention) 1.4 29 27.5 Y (invention) 1.3 33 27 E (2024A) 1.4 30 27 BOY WUT 1.1 38 25.9
- the sheet according to the invention behaves at least as well in fatigue as the sheets according to the prior art.
- a 3.2 mm thick Y sheet had da / dN (10) TL of 1.7 10 -4 mm / cycles, da / dN (30) TL of 10 -4 mm / cycles, and ⁇ K at 100 ⁇ inch. / cycle of 28.3 MPa ⁇ m.
- An alloy M was developed whose chemical composition was in accordance with the invention.
- an alloy plate 2324 according to the prior art (reference I) was developed according to a conventional casting process.
- the chemical compositions of alloys M and I measured on a spectrometric counter taken from the casting channel, are collated in the table: Chemical composition Alloy Yes Fe Cu mn mg Zn Zr M 0.05 0.06 2.05 - 1.64 7.08 0.08 I (AA2324) ⁇ 0.10 ⁇ 0.12 3.8-4.4 0.3-0.9 1.2-1.8 ⁇ 0.20 ⁇ 0.05
- the alloy plates M were homogenized for 15 hours at 479 ° C, then slowly cooled to 420 - 440 ° C and rolled to a thickness of 25.4 mm.
- the output temperature of the hot rolling mill was 354 ° C, which is significantly lower than that which is usually practiced for this type of product.
- the sheets thus obtained were then subjected to solution treatment. at 479 ° C for 4 hours (total time about 1/3 of which was spent climbing temperature), then quenched, and tractionned so that the permanent deformation resulting from it being 2%.
- the sheets then underwent an artificial income treatment for 8 hours at 160 ° C.
- the alloy 1 (AA2324) was subjected to a conventional range until an alloy sheet AA 2324, thickness 25.4 mm in the T39 state, that is to say a homogenization step, was obtained. hot rolling, followed by dissolution and quenching, followed by cold working by about 9%, and controlled pulling to obtain a permanent deformation of between 1.5 and 3 %.
- breaking strength and yield strength of the sheet according to the invention are substantially higher than those of the sheet I used generally for these applications, and this for quite elongations comparable.
- the alloy according to the invention has under all conditions a toughness better than the conventional alloy 1.
- the alloy according to the invention has a K app (LT) at -54 ° C which is of the same order as at room temperature.
- Fatigue behavior was also tested according to ASTM E 647, by measuring the speed of propagation of cracks in sheet metal M by compared to sheet I.
- the specimens used were of type C (T), with B equal to 0.375 inches, and W equal to 101.6 mm (4 inches).
- exfoliating corrosion behavior of the plates of this test was evaluated according to ASTM G34; this test was done on the surface, and at mid-thickness, in the conditions adapted to the alloys 7xxx for the sheet metal M according to the invention, and under conditions suitable for 2xxx alloys for sheet I.
- the sample M according to the invention has been classified EA, both at the surface and at mid-thickness, while the sample I according to the prior art has been classified EA surface, and EB mid-thickness.
- the sheet according to the invention is therefore at least as powerful, if not more performing, in resistance to exfoliating corrosion, than the sheet according to the prior art.
- the sheet M is better for each of the following physical parameters: static mechanical characteristics, K app , fatigue resistance, crack propagation speed.
- Example 2 A P alloy similar to the M alloy of Example 2 was developed. from this alloy, following a manufacturing range similar to that of Example 2, fully hot rolled plates (inlet temperature: 420 - 440 ° C) with a thickness of 75 mm.
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Abstract
Description
Zn 5,7 - 6,7 | Mg 1,7 - 2,4 | Cu 1,5 - 2,3 | Zr 0,05 - 0,12 |
Si ≤ 0,10 | Fe ≤ 0,13 | Ti ≤ 0,06 | Mn ≤ 0,04 |
Zn 5,2 - 6,2 | Mg 1,9-2,6 | Cu 1,2-1,9 | Cr 0,18-0,25 |
Si ≤ 0,10 | Fe ≤ 0,12 | Ti ≤ 0,06 | Mn ≤ 0,06 |
Zn 6,7 - 7,3 | Cu 1,9 - 2,5 | Mg 1,0 - 2,0 | Zr 0,07 - 0,13 |
Fe ≤ 0,15 | Si ≤ 0, 1 5 |
dans lequel Mg / Cu < 1,
traité par mise en solution, trempe, écrouissage à froid, et revenu. L'écrouissage à froid peut être obtenu par traction contrôlée et/ou transformation à froid, par exemple laminage ou étirage.
Composition chimique | ||||||||
Alliage | Si | Fe | Cu | Mn | Mg | Zn | Zr | Cr |
N (invention) | 0,05 | 0,06 | 2,05 | - | 1,64 | 7,08 | 0,08 | - |
Y (invention) | 0,04 | 0,05 | 2,16 | - | 1,80 | 6,76 | 0,09 | - |
E (2024A) | <0,06 | 0,06 | 4,12 | 0,4 | 1,37 | - | - | - |
G | 0,05 | 0,08 | 1,47 | - | 1,56 | 4,27 | 0,11 | - |
H (7475) | 0,03 | 0,06 | 1,5 | - | 2,22 | 5,73 | - | 0,21 |
Placage (7072) | 0,15 | 0,35 | <0,02 | <0,05 | <0,10 | 1,05 | <0,03 | <0,03 |
Caractéristiques mécaniques statiques | |||||||
Tôle | Epaisseur [mm] | Sens L | Sens TL | ||||
Rm [MPa] | Rp0,2 [MPa] | A [%] | Rm [MPa] | Rp0,2 [MPa] | A [%] | ||
N | 5,08 | 539 | 508 | 13,9 | 541 | 495 | 13,9 |
Y | 6 | 557 | 530 | 13,9 | 555 | 519 | 13,6 |
E | 6,35 | 482 | 365 | 22,8 | 466 | 319 | 23,5 |
G | 6,35 | 435 | 373 | 15,1 | 436 | 366 | 14,8 |
H | 4,6 | 475 | 414 | 13,3 | 484 | 414 | 12,5 |
Les résultats sont reportés dans le tableau 3 ci-dessous.
mesures de Kapp | |
Tôle | Kapp [MPa√m] |
N (invention) | 107 |
E (2024 A) | 105 |
G | 97 |
H (7475 plaqué) | 87 |
Résultats de fatigue | |||
Tôle | da/dN (10) T-L (10-4 mm/cycles) | da/dN (30) T-L (10-4 mm/cycles) | ΔK à 100µ inch/cycle [MPa√m] |
N (invention) | 1,4 | 29 | 27,5 |
Y (invention) | 1,3 | 33 | 27 |
E (2024A) | 1,4 | 30 | 27 |
G | 1,1 | 38 | 25,9 |
Composition chimique | |||||||
Alliage | Si | Fe | Cu | Mn | Mg | Zn | Zr |
M | 0.05 | 0.06 | 2,05 | - | 1,64 | 7,08 | 0,08 |
I (AA2324) | <0,10 | <0,12 | 3,8-4,4 | 0,3-0,9 | 1,2-1,8 | <0,20 | <0,05 |
Caractéristiques mécaniques statiques | ||||
Tôle | Epaisseur [mm] | Sens L | ||
Rm [MPa] | Rp0,2 [MPa] | A [%] | ||
M | 25,4 | 570 | 540 | 12,3 |
I | 25,4 | 490 | 470 | 14 |
mesures de Kc et Kapp | |||||
Tôle | KC (L-T) éprouvette M(T) [MPa√m] température ambiante | Kapp (L-T) éprouvette M(T) [MPa√m] température ambiante | Kapp (L-T) éprouvette C(T) [MPa√m] température ambiante | Kapp (L-T) éprouvette C(T) [MPa√m] à -54°C | Kapp (L-T) éprouvette M(T) [MPa√m] à -54°C |
M | 199 | 140 | 118 | 124 | 126 |
I | 177 | 121 | 96 | 99 | - |
Résultats de fatigue | ||
Tôle | Nombre de cycles (moyenne Log sur 5 tests) Eprouvette « à encoches » | Nombre de cycles (moyenne Log sur 5 tests) Eprouvette « à double trou » |
M | 299213 | 330737 |
I | 181402 | 337730 |
Résultats de fatigue Valeurs de ΔK pour une vitesse de fissuration donnée | |
Tôle | ΔK à 2,54µm/cycle (10-4 inch/cycle) [MPa√m] |
M | 30,8 |
I | 26,8 |
- Premier palier : montée en température de 30 °C / heure jusqu'à 120°C et un maintien pendant 6 heures à cette température de 120°C.
- Deuxième palier : montée en température de 15°C / heure jusqu'à 160°C et un maintien pendant 5 heures (procédé A), 10 heures (procédé B) ou 15 heures (procédé C) à cette température de 160°C.
Procédé | Rp0.2 (L) [MPa] | Rm (L) [MPa] | A (L) [%] | KIC(L-T) [MPa√m] | Kapp(L-T) [MPa√m] |
A | 542 | 561 | 9,7 | 30,1 | 57,1 |
B | 525 | 549 | 10,2 | 32,8 | 63,2 |
C | 507 | 537 | 11,3 | 34,6 | 72,5 |
Claims (26)
- Produit corroyé, notamment laminé, filé ou forgé, en alliage de type AlZnCuMg, caractérisé en ce qu'il comporte (% en poids) :
Zn 6,7-7,3 % Cu 1,9-2,5 % Mg 1,0 - 2,0 % Zr 0,07- 0,13 % Fe<0,15% Si < 0,15 % - Produit selon la revendication 1, caractérisé en ce que Zr ≤ 0,12%.
- Produit selon la revendication 1, caractérisé en ce que Zr 0,07 - 0,09 %.
- Produit selon une quelconque des revendications 1 à 3, caractérisé en ce que Cu 2,0 - 2,3 %.
- Produit selon une quelconque des revendications 1 à 4, caractérisé en ce que Mg 1,5-1,8 %.
- Produit selon une quelconque des revendications 1 à 5, caractérisé en ce que Mg / Cu ≤ 0,80.
- Produit selon une quelconque des revendications 1 à 6, caractérisé en ce que l'alliage contient entre 50 et 500 ppm de titane, et préférentiellement entre 150 et 300 ppm de titane.
- Produit selon une quelconque des revendications 1 à 7, caractérisé en ce qu'il a été élaboré à partir d'un métal affiné avec un affinant qui contient du Ti et du C.
- Produit selon une quelconque des revendications 1 à 8 d'une épaisseur inférieure à 20 mm, caractérisé en ce que(a) Kapp (T-L) (mesurée à la température ambiante sur éprouvette C(T) avec W = 127 mm et B = 5,5 mm) > 100 MPa√m, et préférentiellement > 103 MPa√m), et(b) RP0.2(L) >500 MPa, préférentiellement > 520 MPa et encore plus préférentiellement > 530 MPa.
- Produit selon une quelconque des revendications 1 à 9, caractérisé en ce que Rm(L) > 500 MPa, et préférentiellement > 530 MPa.
- Produit selon une quelconque des revendications 1 à 8 ou 10, caractérisé en ce que Rp0.2(L) > 460 MPa, préférentiellement > 480 MPa, et encore plus préférentiellement > 500 MPa.
- Tôle avec une épaisseur inférieure à 20 mm selon une quelconque des revendications 2 à 8, présentant au moins deux des couples de propriétés sélectionnés parmi :(c) Rm(L) > 520 MPa et Rp0.2(TL) > 515 MPa ;(d) Rp0.2(L) > 500 MPa et Rp0.2(TL) > 480 MPa ;(e) Rp0,2(L) > 500 MPa et Kapp(T-L) > 100 MPa√m (mesurée à la température ambiante sur éprouvette C(T) avec W=127 mm et B = 5,5 mm).
- Tôle selon la revendication 12, caractérisée en ce que da/dn au sens T-L est inférieur à 28 x 10-4 mm/cycles, déterminé à ΔK = 30 MPa√m.
- Tôle d'une épaisseur comprise entre 1 et 10 mm selon une quelconque des revendications 1 à 13, caractérisée en ce que KC(T-L), mesuré sur une éprouvette avec W=760 mm, est supérieur à 130 MPa√m, et / ou en ce que KC(L-T), mesuré sur une éprouvette avec W=760 mm, est supérieur à 160 MPa√m.
- Tôle d'une épaisseur supérieure à 3 mm selon une quelconque des revendications 2 à 14, caractérisée en ce qu'elle a été laminée uniquement à chaud.
- Tôle avec une épaisseur supérieure à 10 mm selon une quelconque des revendications 2 à 13 ou 15, caractérisée en ce qu'elle a été soumise à une mise en solution d'au moins 4 heures à une température comprise entre 470 et 480°C, et préférentiellement comprise entre 475 et 480°C.
- Tôle avec une épaisseur inférieure à 10 mm selon une quelconque des revendications 2 à 15, caractérisée en ce qu'elle a été soumise à une mise en solution d'au moins 1 heure à une température comprise entre 470 et 475°C.
- Tôle avec une épaisseur supérieure à 20 mm selon une quelconque des revendications 2 à 11 ou 16 à 17, présentant au moins deux caractéristiques sélectionnées parmi(a) Rm(L) > 540 MPa ;(b) Rp0.2(L) > 535 MPa ;(c) Kapp(L-T) > 100 MPa√m (mesurée à la température ambiante sur éprouvette C(T) avec W=127 mm et B = 7,6 mm) ;(d) ΔK à une vitesse de propagation de fissure de 2,54 µm / cycle > 28 MPa√m ;(e) KIC(L-T) > 28 MPa√m.
- Tôle avec une épaisseur supérieure à 20 mm selon une quelconque des revendications 2 à 11 ou 16 à 18, présentant au moins deux caractéristiques sélectionnées parmi(a) une limite d'élasticité Rp0,2(L) d'au moins 520 MPa ;(b) un Kapp(L-T) (mesuré à la température ambiante selon ASTM E 561 sur une éprouvette de type C(T) avec W = 406 mm et une épaisseur B = 6,35 mm) d'au moins 130 MPa√m ;(c) un KC(L-T) (mesuré à la température ambiante sur une éprouvette de type C(T) avec W = 406 mm et une épaisseur B = 6,35 mm) d'au moins 185 MPa√m .
- Tôle selon une quelconque des revendications 1 à 19, caractérisée en ce qu'elle est plaquée d'au moins une face.
- Produit selon une quelconque des revendications 1 à 20, caractérisé en ce qu'il a été élaboré à partir d'un métal liquide auquel on a ajouté un affinant contenant du titane et du carbone, de manière à ce la quantité de carbone ajoutée se situe entre 0,4 et 3 g/t de carbone, préférentiellement entre 0,6 et 2 g/t, et de manière à ce que la teneur totale en Ti dans le produit final se situe entre 50 et 500 ppm (en poids), préférentiellement entre 150 et 300 ppm.
- Elément de structure pour construction aéronautique fabriqué à partir d'au moins un produit selon une quelconque des revendications 1 à 22.
- Structure intégrale pour construction aéronautique incorporant un ou plusieurs produits selon une quelconque des revendications 1 à 22.
- Utilisation d'un produit laminé selon une quelconque des revendications 2 à 16 ou 16 ou 18 ou 22 d'une épaisseur inférieure à 10 mm comme revêtement de fuselage.
- Utilisation d'un produit, notamment laminé, selon une quelconque des revendications 1 à 12 ou 16, 17, ou 19 à 22 d'une épaisseur supérieure à 40 mm pour la fabrication par usinage d'éléments de structure d'avions.
- Utilisation d'un produit, notamment laminé, selon une quelconque des revendications 1 à Il ou 16, 17, ou 19 à 22 d'une épaisseur supérieure à 60 mm pour la fabrication de raidisseurs ou cadres d'avions.
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US52959403P | 2003-12-16 | 2003-12-16 | |
US529594P | 2003-12-16 |
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EP1544315A1 true EP1544315A1 (fr) | 2005-06-22 |
EP1544315B1 EP1544315B1 (fr) | 2012-08-22 |
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US (1) | US20050150578A1 (fr) |
EP (1) | EP1544315B1 (fr) |
ES (1) | ES2393706T3 (fr) |
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WO2010081889A1 (fr) * | 2009-01-16 | 2010-07-22 | Aleris Aluminum Koblenz Gmbh | Procédé de fabrication d'un produit de type tôle d'alliage d'aluminium présentant de faibles taux de contrainte résiduelle |
US8083871B2 (en) | 2005-10-28 | 2011-12-27 | Automotive Casting Technology, Inc. | High crashworthiness Al-Si-Mg alloy and methods for producing automotive casting |
US8206517B1 (en) | 2009-01-20 | 2012-06-26 | Alcoa Inc. | Aluminum alloys having improved ballistics and armor protection performance |
US8840737B2 (en) | 2007-05-14 | 2014-09-23 | Alcoa Inc. | Aluminum alloy products having improved property combinations and method for artificially aging same |
US9314826B2 (en) | 2009-01-16 | 2016-04-19 | Aleris Rolled Products Germany Gmbh | Method for the manufacture of an aluminium alloy plate product having low levels of residual stress |
WO2019007817A1 (fr) | 2017-07-03 | 2019-01-10 | Constellium Issoire | Alliages al-zn-cu-mg et leur procédé de fabrication |
FR3071513A1 (fr) * | 2017-09-26 | 2019-03-29 | Constellium Issoire | Alliages al-zn-cu-mg a haute resistance et procede de fabrication |
US10301710B2 (en) | 2005-01-19 | 2019-05-28 | Otto Fuchs Kg | Aluminum alloy that is not sensitive to quenching, as well as method for the production of a semi-finished product |
EP3670690A1 (fr) | 2018-12-20 | 2020-06-24 | Constellium Issoire | Alliages al-zn-cu-mg et leur procédé de fabrication |
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Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4863528A (en) * | 1973-10-26 | 1989-09-05 | Aluminum Company Of America | Aluminum alloy product having improved combinations of strength and corrosion resistance properties and method for producing the same |
EP0587274A1 (fr) * | 1992-08-13 | 1994-03-16 | Reynolds Metals Company | Procédé de fabrication d'un alliage aluminium-zinc-magnésium-cuivre présentant une meilleure résistance à l'écaillage et une haute ténacité à la rupture et le produit obtenu selon ce procédé |
EP0589807A1 (fr) * | 1992-09-22 | 1994-03-30 | Société Métallurgique de Gerzat | Alliage d'aluminium pour corps creux sous pression |
WO2002052053A1 (fr) * | 2000-12-21 | 2002-07-04 | Alcoa Inc. | Produits en alliage d'aluminium et procede de vieillissement artificiel |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CA1173277A (fr) * | 1979-09-29 | 1984-08-28 | Yoshio Baba | Materiau pour lisses d'aeronef, et methode de production connexe |
US5865911A (en) * | 1995-05-26 | 1999-02-02 | Aluminum Company Of America | Aluminum alloy products suited for commercial jet aircraft wing members |
JP4285916B2 (ja) * | 2001-02-16 | 2009-06-24 | 株式会社神戸製鋼所 | 高強度、高耐食性構造用アルミニウム合金板の製造方法 |
US20050006010A1 (en) * | 2002-06-24 | 2005-01-13 | Rinze Benedictus | Method for producing a high strength Al-Zn-Mg-Cu alloy |
CA2528614C (fr) * | 2003-06-24 | 2012-06-05 | Pechiney Rhenalu | Produits en alliages al-zn-mg-cu a compromis caracteristiques mecaniques statiques/tolerance aux dommages ameliore |
-
2004
- 2004-12-15 ES ES04356196T patent/ES2393706T3/es active Active
- 2004-12-15 EP EP04356196A patent/EP1544315B1/fr active Active
- 2004-12-16 US US11/012,358 patent/US20050150578A1/en not_active Abandoned
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4863528A (en) * | 1973-10-26 | 1989-09-05 | Aluminum Company Of America | Aluminum alloy product having improved combinations of strength and corrosion resistance properties and method for producing the same |
EP0587274A1 (fr) * | 1992-08-13 | 1994-03-16 | Reynolds Metals Company | Procédé de fabrication d'un alliage aluminium-zinc-magnésium-cuivre présentant une meilleure résistance à l'écaillage et une haute ténacité à la rupture et le produit obtenu selon ce procédé |
EP0589807A1 (fr) * | 1992-09-22 | 1994-03-30 | Société Métallurgique de Gerzat | Alliage d'aluminium pour corps creux sous pression |
WO2002052053A1 (fr) * | 2000-12-21 | 2002-07-04 | Alcoa Inc. | Produits en alliage d'aluminium et procede de vieillissement artificiel |
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EP3026136A1 (fr) * | 2007-05-14 | 2016-06-01 | Alcoa Inc. | Produits en alliage d'aluminium présentant des combinaisons de propriétés améliorées et procédés pour leur vieillissement artificiel |
WO2008156532A3 (fr) * | 2007-05-14 | 2009-01-29 | Alcoa Inc | Produits en alliage d'aluminium présentant des combinaisons de propriétés améliorées et procédés pour leur vieillissement artificiel |
WO2008156532A2 (fr) * | 2007-05-14 | 2008-12-24 | Alcoa Inc. | Produits en alliage d'aluminium présentant des combinaisons de propriétés améliorées et procédés pour leur vieillissement artificiel |
US8673209B2 (en) | 2007-05-14 | 2014-03-18 | Alcoa Inc. | Aluminum alloy products having improved property combinations and method for artificially aging same |
US8840737B2 (en) | 2007-05-14 | 2014-09-23 | Alcoa Inc. | Aluminum alloy products having improved property combinations and method for artificially aging same |
US9314826B2 (en) | 2009-01-16 | 2016-04-19 | Aleris Rolled Products Germany Gmbh | Method for the manufacture of an aluminium alloy plate product having low levels of residual stress |
WO2010081889A1 (fr) * | 2009-01-16 | 2010-07-22 | Aleris Aluminum Koblenz Gmbh | Procédé de fabrication d'un produit de type tôle d'alliage d'aluminium présentant de faibles taux de contrainte résiduelle |
US8206517B1 (en) | 2009-01-20 | 2012-06-26 | Alcoa Inc. | Aluminum alloys having improved ballistics and armor protection performance |
WO2019007817A1 (fr) | 2017-07-03 | 2019-01-10 | Constellium Issoire | Alliages al-zn-cu-mg et leur procédé de fabrication |
FR3071513A1 (fr) * | 2017-09-26 | 2019-03-29 | Constellium Issoire | Alliages al-zn-cu-mg a haute resistance et procede de fabrication |
WO2019063490A1 (fr) | 2017-09-26 | 2019-04-04 | Constellium Issoire | Alliages al-zn-cu-mg à haute résistance et procédé de fabrication |
EP3670690A1 (fr) | 2018-12-20 | 2020-06-24 | Constellium Issoire | Alliages al-zn-cu-mg et leur procédé de fabrication |
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US20050150578A1 (en) | 2005-07-14 |
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