EP1831415B2 - Procédé de fabrication d'un alliage de al-zn à haute résistance et de grande durete - Google Patents
Procédé de fabrication d'un alliage de al-zn à haute résistance et de grande durete Download PDFInfo
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- EP1831415B2 EP1831415B2 EP05802352.4A EP05802352A EP1831415B2 EP 1831415 B2 EP1831415 B2 EP 1831415B2 EP 05802352 A EP05802352 A EP 05802352A EP 1831415 B2 EP1831415 B2 EP 1831415B2
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- 238000004519 manufacturing process Methods 0.000 title claims abstract description 9
- 229910001297 Zn alloy Inorganic materials 0.000 title claims description 10
- 239000000956 alloy Substances 0.000 claims abstract description 64
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 63
- 230000007797 corrosion Effects 0.000 claims abstract description 29
- 238000005260 corrosion Methods 0.000 claims abstract description 29
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 12
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 12
- 239000004411 aluminium Substances 0.000 claims abstract description 8
- 238000000034 method Methods 0.000 claims description 25
- 230000032683 aging Effects 0.000 claims description 22
- 229910052749 magnesium Inorganic materials 0.000 claims description 18
- 229910052802 copper Inorganic materials 0.000 claims description 13
- 238000010438 heat treatment Methods 0.000 claims description 12
- 238000005097 cold rolling Methods 0.000 claims description 10
- 238000005098 hot rolling Methods 0.000 claims description 10
- 239000000203 mixture Substances 0.000 claims description 10
- 239000012535 impurity Substances 0.000 claims description 7
- 238000005266 casting Methods 0.000 claims description 4
- 238000010791 quenching Methods 0.000 claims description 4
- 230000000171 quenching effect Effects 0.000 claims description 3
- 229910052726 zirconium Inorganic materials 0.000 claims description 3
- 229910052735 hafnium Inorganic materials 0.000 claims description 2
- 238000003303 reheating Methods 0.000 claims description 2
- 229910052719 titanium Inorganic materials 0.000 claims description 2
- 238000011282 treatment Methods 0.000 claims description 2
- GNFTZDOKVXKIBK-UHFFFAOYSA-N 3-(2-methoxyethoxy)benzohydrazide Chemical compound COCCOC1=CC=CC(C(=O)NN)=C1 GNFTZDOKVXKIBK-UHFFFAOYSA-N 0.000 claims 4
- 229910018137 Al-Zn Inorganic materials 0.000 abstract 1
- 229910018573 Al—Zn Inorganic materials 0.000 abstract 1
- 239000000047 product Substances 0.000 description 60
- 239000011777 magnesium Substances 0.000 description 20
- 239000011701 zinc Substances 0.000 description 18
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 15
- 239000010949 copper Substances 0.000 description 15
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 10
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 description 10
- 229910052725 zinc Inorganic materials 0.000 description 10
- 238000004299 exfoliation Methods 0.000 description 8
- 239000011572 manganese Substances 0.000 description 8
- 229910000838 Al alloy Inorganic materials 0.000 description 7
- 230000035882 stress Effects 0.000 description 5
- 239000010936 titanium Substances 0.000 description 5
- 229910052748 manganese Inorganic materials 0.000 description 4
- 239000000126 substance Substances 0.000 description 4
- 101100315624 Caenorhabditis elegans tyr-1 gene Proteins 0.000 description 3
- 230000000052 comparative effect Effects 0.000 description 3
- 239000012467 final product Substances 0.000 description 3
- 238000002791 soaking Methods 0.000 description 3
- 229910052684 Cerium Inorganic materials 0.000 description 2
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 238000001953 recrystallisation Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 1
- 238000005275 alloying Methods 0.000 description 1
- 238000010420 art technique Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000000265 homogenisation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000005482 strain hardening Methods 0.000 description 1
- 229910052720 vanadium Inorganic materials 0.000 description 1
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 present invention relates to a high-strength high-toughness AI-Zn alloy wrought product with elevated amounts of Zn for maintaining good corrosion resistance, and to a method for producing such a high-strength high-toughness AI-Zn alloy product and to a plate product of such alloy. More specifically, the present invention relates to a high strength, high toughness AI-Zn alloy designated by the AA7000-series of the international nomenclature of the Aluminum Association for structural aeronautical applications. Even more specifically, the present invention relates to a new chemistry window for an AI-Zn alloy having improved combinations of strength and toughness by maintaining good corrosion resistance, which does not need specific ageing or temper treatments.
- Aluminium alloys AA7050 and AA7150 exhibit high strength in T6-type tempers. Also precipitation-hardened AA7x75, AA7x55 alloy products exhibit high strength values in the T6 temper.
- the T6 temper is known to enhance the strength of the alloy, wherein the aforementioned AA7x50, AA7x75 and AA7x55 alloy products which contain high amounts of zinc, copper and magnesium are known for their high strength-to-weight ratios and, therefore, find application in particular in the aerospace industry.
- these applications result in exposure to a wide variety of climatic conditions necessitating careful control of working and ageing conditions to provide adequate strength and resistance to corrosion, including both stress corrosion and exfoliation.
- T74 temper is a limited over-aged condition, between T73 and T76, in order to obtain an acceptable level of tensile strength, stress corrosion resistance, exfoliation corrosion resistance and fracture toughness.
- T74 temper is performed by over-ageing the aluminium alloy product at temperatures of 121°C for 6 to 24 hours and followed by 171°C for about 14 hours.
- each of EP-0377779 , EP 0 368 005 , US-5,221,377 and US-5,496,426 disclose alloy products and an improved process for producing an 7055 alloy for sheet or thin plate applications in the field of aerospace such as upper-wing members with high toughness and good corrosion properties which comprises the steps of working a body having a composition consisting of, about in wt.%: Zn 7.6 to 8.4, Cu 2.2 to 2.6, Mg 1.8 to 2.1 or 2.2, and one or more elements selected from Zr, Mn V and Hf, the total of the elements not exceeding 0.6 wt.%, the balance aluminium plus incidental impurities, solution heat treating and quenching the product and artificially ageing the product by either heating the product three times in a row to one or more temperatures from 79°C to 163°C or heating such product first to one or more temperatures from 79°C to 141°C for two hours or more and heating the product to one or more temperatures from 148°C to 174°C.
- alloy designations and temper designations refer to the Aluminum Association designations in Aluminum Standards and Data and the Registration Records, all published by the US Aluminum Association.
- an AI-Zn alloy product with an improved combination of high toughness and high strength by maintaining good corrosion resistance
- said alloy comprising, and preferably consisting of, (in weight percent): Zn 6.0 to 11.0 Cu 1.4 to 2.2 Mg 1.4 to 2.4 Zr 0.05 to 0.15 Ti ⁇ 0.05, Hf and/or V ⁇ 0.25, optionally Sc and/or Ce 0.05 to 0.25, and optionally Mn 0.05 to 0.12, and inevitable impurities and balance aluminium, preferably other elements each less than 0.05 and less than 0.50 in total, and wherein the alloy product has a substantially fully unrecrystallized microstructure at the position T/10 of the finished product.
- Such chemistry window for an AA7000-series alloy exhibits excellent properties when produced to relatively thin plate products, and which is preferably useable in aerospace upper-wing applications having gauges in the range of 20 mm to 60 mm.
- the above defined chemistry has properties which are comparable or better than existing alloys of the AA7x50 or AA7x55 series in the T77-temper, without using the above described cumbersome and complicated T77 three-step ageing cycles.
- the chemistry leads to an aluminium product which is more cost effective and is also simpler to produce since less processing steps are necessary. Additionally, the chemistry allows new manufacturing techniques like age forming or age creep forming which is not feasible when a T77-temper alloy is applied. Even better, the chemistry as defined above can also be aged to the T77-temper whereby the corrosion resistance further improves.
- a selected range of elements using a higher amount of Zn and a specific combination of a particular range of Mg and Cu, exhibit substantially better combinations of strength and toughness and maintaining a good corrosion performance such as exfoliation corrosion resistance and stress corrosion cracking resistance.
- the present invention uses the chemistry in combination with a method to produce a rolled product from such chemistry, as explained herein below, to obtain a substantially fully unrecrystallized microstructure at least at the position T/10 of the finished product. More preferably the product is unrecystallized across the whole thickness. With unrecystallized we mean that more than 80%, preferably more than 90% of the gauge of the finished rolled product is substantially unrecrystallized.
- the present invention is disclosing an alloy product which is in particular suitable for upper wing skin applications for aircrafts and having a thickness in the range of 20 to 60 mm, preferably 30 to 50 mm.
- Copper and magnesium are important elements for adding strength to the alloy. Too low amounts of magnesium and copper result in a decrease of strength while too high amounts of magnesium and copper result in a lower corrosion performance and problems with the weldability of the alloy product. Prior art techniques used special ageing procedures to ameliorate the strength while low amounts of magnesium and copper are used in order to achieve a good corrosion performance. In order to achieve a compromise in strength, toughness and corrosion performance copper and magnesium amounts (in wt.%) of between 1.7 and 2.2%, preferably between 1.7 and 2.1% for Mg and 1.8 and 2.1% for Cu have been found to give a good balance for thin plate products. Throughout the claimed chemistry of the present invention it is now possible to achieve strength levels in the region of a T6-temper alloy while maintaining corrosion performance characteristics similar to those of T74-temper alloys.
- the invention discloses a balance of magnesium and copper amounts to zinc, especially the balance of magnesium to zinc, which gives the alloy these performance characteristics.
- the improved corrosion resistance of the alloy according to the invention has exfoliation properties ("EXCO") of EB or better, preferably EA or better.
- the amount (in weight%) of zinc is preferably in a range of 7.4 to 9.6%, more preferably in a range of 8.0 to 9.6%, most preferably in a range of 8.4 to 8.9%. Testing has found an optimum zinc level of about 8.6%. Further details are given in the examples as described in more details hereinbelow.
- a Sc-containing alloy is an excellent candidate for obtaining high strength versus high notch toughness levels.
- Sc is in a range of [Zr] + 1.5 [Sc] ⁇ 0.15%.
- Preferred amounts (in weight%) of Sc or Ce are in a range of 0.03 to 0.06% when the amount of Zn is about 8.70% and Mg and Cu are about 2.10%. The levels of the unit propagation energy are considerably good for an alloy with additional Sc, Ce or Mn alloying elements.
- a method for producing a high strength, high toughness AI-Zn alloy product with good corrosion resistance comprises the steps of claim 1.
- microstructure of the alloy product remains substantially fully unrecrystallized underneath its surface when the inventive method step of pre-working the product and hot rolling and cold rolling the pre-worked product are applied.
- the method includes a first hot rolling of the ingot which has been homogenised into a pre-worked product, hot rolling the re-heated product to about 150 to 250 (in final-gauge%) and then cold rolling the hot rolled product to the final gauge or hot rolling the re-heated product to about 105 to 140 (in final-gauge%) and then cold rolling the hot rolled product to the final gauge.
- "Final-gauge%” means a percentage in thickness compared to the thickness of the final product. 200 final-gauge% means a thickness which is twice as much as the thickness of the finally worked product.
- the present invention it is advantageous to hot roll the re-heated product at low temperatures in the range of 300°C to 420°C so that the alloy does not recrystallise.
- the present invention is useful for hot-working the ingot after casting and cold-working into a worked product with a gauge in the range of 20 to 60 mm.
- the present invention also concerns a plate product of high strength, high toughness AI-Zn alloy of the aforementioned composition which plate product is preferably a thin aircraft member, even more preferably an elongate structural shape member such as an upper-wing member, a thin skin member of an upper-wing or of a stringer of an aircraft.
- the properties of the claimed alloy may further be enhanced by an artificial ageing step comprising a first heat treatment at a temperature in a range of 105°C to 135°C, preferably around 120°C for 2 to 20 hours, preferably around 8 hours and a second heat treatment at a higher temperature then 135°C but below 210°C, preferably around 155°C for 4 to 12 hours, preferably 8 to 10 hours.
- an artificial ageing step comprising a first heat treatment at a temperature in a range of 105°C to 135°C, preferably around 120°C for 2 to 20 hours, preferably around 8 hours and a second heat treatment at a higher temperature then 135°C but below 210°C, preferably around 155°C for 4 to 12 hours, preferably 8 to 10 hours.
- step 5 variant 1 being comparative examples and variants 2 and 3 being examples of the invention
- Sc-containing alloy 14 is advantageous if high strength versus high notch toughness is needed. Small amounts of manganese do increase the strength but at the cost of some toughness.
- the toughness versus tensile yield strength (Rp) shown in Table 4 clearly shows that the best toughness versus tensile yield strength value is obtained for alloys having around 8.6 to 8.7 weight% zinc. Alloys with lower levels of zinc will show similar toughness values but the tensile strength is -generally speaking- lower whereas high levels of zinc result in higher strength levels but lower toughness levels. Small amounts of manganese do increase the strength at the cost of toughness.
- magnesium levels are of less than 2.4% with an optimum of about 1.7%.
- magnesium levels are at about 1.7%, excellent toughness properties are obtained but the strength levels decrease.
- magnesium levels of about 2.1% the best strength levels are obtained.
- magnesium is best in between 1.7 and 2.1%.
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- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- Organic Chemistry (AREA)
- Metallurgy (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Crystallography & Structural Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Metal Rolling (AREA)
- Forging (AREA)
- Powder Metallurgy (AREA)
- Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
- Manufacture And Refinement Of Metals (AREA)
- Superconductors And Manufacturing Methods Therefor (AREA)
Claims (18)
- Procédé pour produire un produit en alliage Al-Zn à haute résistance, à ténacité élevée, offrant une bonne résistance à la corrosion, comprenant les étapes consistant à :a.) couler un lingot comportant la composition suivante, en pourcentage par poids :Zn de 6,0 à 11,0 %Cu de 1,4 à 2,2 %Mg de 1,4 à 2,4%Zr de 0,05 à 0,15%Ti < 0,05%Hf et/ou V < 0,25%facultativement Sc et/ou Ce - de 0,05 à 0,25 %
facultativement Mn - de 0,05 à 0,12 %, et
des impuretés inévitables et le reste étant de
l'aluminium,b.) homogénéiser et/ou à préchauffer le lingot après coulage,c.) travailler à chaud le lingot pour en faire un produit pré-ouvré,d.) réchauffer le produit pré-ouvré et effectuer un laminage à chaud du produit réchauffé, effectuer un laminage à froid du produit ayant été laminé à chaud d'un degré de 10 à 20% jusqu'à l'épaisseur finale,e.) effectuer un traitement thermique par mise en solution et tremper le produit ayant été traité thermiquement par mise en solution,f.) étirer ou comprimer facultativement le produit trempé en alliage, etg.) soumettre facultativement à un vieillissement le produit trempé et facultativement étiré ou comprimé afin d'obtenir le revenu désiré,
et dans le cadre duquel le produit lors de son étape de revenu final a une microstructure à non-recristallisation sensiblement totale au moins à la position T/10 du produit fini. - Procédé selon la revendication 1, le laminage à chaud du produit réchauffé étant effectué jusqu'à environ 150-250 (en pourcentage de l'épaisseur finale), et puis le laminage à froid du produit ayant été laminé à chaud est effectué jusqu'à l'épaisseur finale.
- Procédé selon la revendication 1 ou 2, le laminage à chaud du produit réchauffé étant effectué jusqu'à environ 105-140 (en pourcentage de l'épaisseur finale), et puis le laminage à froid du produit ayant été laminé à chaud est effectué jusqu'à l'épaisseur finale.
- Procédé selon l'une quelconque des revendications 1 à 3, comprenant le laminage à chaud du produit réchauffé à des températures faibles dans la gamme de 300°C à 420°C afin d'empêcher le produit en alliage de se recristalliser.
- Procédé selon l'une quelconque des revendications 1 à 4, le vieillissement artificiel réalisé au cours de l'étape g.) consistant en un revenu sélectionné à partir du groupe constitué de T79 et de T76, et de préférence au moyen d'un traitement de vieillissement en deux phases.
- Procédé selon l'une quelconque des revendications 1 à 5, le vieillissement artificiel réalisé au cours de l'étape g.) consistant en une première phase de vieillissement à une température dans la gamme de 105°C à 135°C pendant 2 à 20 heures, et en une deuxième phase de vieillissement à une température supérieure à 135°C mais inférieure à 210°C pendant 4 à 12 heures jusqu'à un revenu sélectionné parmi les trempes T79 et T76.
- Procédé selon la revendication 6, le vieillissement artificiel réalisé au cours de l'étape g.) consistant en une première phase de vieillissement à une température aux alentours de 120°C pendant 2 à 20 heures, et en une deuxième phase de vieillissement à une température supérieure à 135°C mais inférieure à 210°C pendant 4 à 12 heures jusqu'à un revenu sélectionné parmi les trempes T79 et T76.
- Procédé selon la revendication 6 ou 7, le vieillissement artificiel réalisé au cours de l'étape g.) consistant en une première phase de vieillissement à une température aux alentours de 120°C pendant 2 à 20 heures, et en une deuxième phase de vieillissement à une température aux alentours de 155°C pendant 4 à 12 heures jusqu'à un revenu sélectionné parmi les trempes T79 et T76.
- Procédé selon l'une quelconque des revendications 1 à 8, la teneur en Zn se situant dans une gamme de 7,4 à 9,6 % par poids.
- Procédé selon la revendication 9, la teneur en Zn se situant dans une gamme de 8,0 à 9,6 % par poids, et de préférence dans une gamme de 8,4 à 8,9 % par poids.
- Procédé selon l'une quelconque des revendications 1 à 10, la teneur en Cu se situant dans une gamme de 1,7 à 2,2 % par poids, et de préférence dans une gamme de 1,8 à 2,1 % par poids.
- Procédé selon la revendication 11, la teneur en Mg se situant dans une gamme de 1,7 à 2,2 % par poids, et de préférence dans une gamme de 1,7 à 2,1 % par poids.
- Procédé selon l'une quelconque des revendications 1 à 12, la teneur en Sc se situant dans une gamme de [Zr]+1,5 [Sc]<0,15 % par poids.
- Procédé selon l'une quelconque des revendications 1 à 13, la teneur en Sc se situant dans une gamme de 0,03 à 0,06 %, et la teneur en Ce se situant dans une gamme de 0,03 à 0,06 %.
- Procédé selon l'une quelconque des revendications 1 à 14, la teneur en impuretés inévitables étant < 0,05 % par poids chacune, et le total étant < 0,5 % par poids.
- Procédé selon l'une quelconque des revendications 1 à 15, plus de 80 %, et de préférence plus de 90 %, de l'épaisseur du produit laminé fini ayant une microstructure sensiblement non-recristallisée.
- Procédé selon l'une quelconque des revendications 1 à 16, le produit en Al-Zn étant une fine plaque dont l'épaisseur se situe dans la gamme de 20 à 60 mm, et de préférence de 30 à 50 mm.
- Procédé selon l'une quelconque des revendications 1 à 17, le produit en Al-Zn étant un produit sélectionné à partir du groupe constitué des postes suivants : un élément mince pour avions, un élément d'aile haute, un élément à revêtement mince d'une aile haute ou un longeron d'un avion.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP05802352.4A EP1831415B2 (fr) | 2004-10-05 | 2005-10-04 | Procédé de fabrication d'un alliage de al-zn à haute résistance et de grande durete |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP04077721 | 2004-10-05 | ||
PCT/EP2005/010809 WO2006037648A1 (fr) | 2004-10-05 | 2005-10-04 | Produit d'alliage al-zn de haute resistance et haute tenacite et procede de production dudit produit |
EP05802352.4A EP1831415B2 (fr) | 2004-10-05 | 2005-10-04 | Procédé de fabrication d'un alliage de al-zn à haute résistance et de grande durete |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1831415A1 EP1831415A1 (fr) | 2007-09-12 |
EP1831415B1 EP1831415B1 (fr) | 2009-03-18 |
EP1831415B2 true EP1831415B2 (fr) | 2014-10-15 |
Family
ID=34928547
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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EP05802352.4A Active EP1831415B2 (fr) | 2004-10-05 | 2005-10-04 | Procédé de fabrication d'un alliage de al-zn à haute résistance et de grande durete |
Country Status (10)
Country | Link |
---|---|
EP (1) | EP1831415B2 (fr) |
JP (1) | JP5068654B2 (fr) |
CN (1) | CN101068943B (fr) |
AT (1) | ATE426050T1 (fr) |
BR (1) | BRPI0517538B1 (fr) |
CA (1) | CA2592132C (fr) |
DE (2) | DE102005045341A1 (fr) |
FR (1) | FR2876118B1 (fr) |
RU (1) | RU2404276C2 (fr) |
WO (1) | WO2006037648A1 (fr) |
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---|---|---|---|---|
KR20090127185A (ko) * | 2007-03-30 | 2009-12-09 | 디렉터 제너럴, 디펜스 리써치 앤드 디벨롭먼트 오거니제이션 | 합금 조성물 및 그 제조방법 |
CN101407876A (zh) * | 2008-09-17 | 2009-04-15 | 北京有色金属研究总院 | 适于大截面主承力结构件制造的铝合金材料及其制备方法 |
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CN101928865A (zh) * | 2010-04-27 | 2010-12-29 | 中国兵器工业第五九研究所 | 弹用超高强度铝合金 |
CN101979692B (zh) * | 2010-11-24 | 2012-05-30 | 中国兵器工业第五九研究所 | 一种Al-Zn-Mg-Cu系超高强铝合金的制备工艺 |
CN102703782A (zh) * | 2012-04-20 | 2012-10-03 | 北京工业大学 | 一种超高强高淬透性Al-Zn-Mg-Cu合金 |
CN102760508B (zh) * | 2012-07-18 | 2014-05-28 | 中南大学 | 含Hf和Ce的高电导率抗蠕变铝合金电缆导体及制备方法 |
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CN104294117A (zh) * | 2014-10-29 | 2015-01-21 | 严静儿 | 一种高延展性铝合金 |
CN104294116A (zh) * | 2014-10-29 | 2015-01-21 | 严静儿 | 一种高性能铝合金 |
CN105112746B (zh) * | 2015-09-25 | 2017-05-17 | 沈阳工业大学 | 一种高强Al‑Zn‑Mg‑Cu‑Ce‑Y‑Er‑La‑Sc变形铝合金及其制备方法 |
AU2016344192B2 (en) * | 2015-10-30 | 2020-03-26 | Novelis Inc. | High strength 7xxx aluminum alloys and methods of making the same |
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KR102566987B1 (ko) * | 2023-04-24 | 2023-08-14 | 한국재료연구원 | 고강도 알루미늄-아연-마그네슘-구리 합금 후판 및 그 제조방법 |
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US5496426A (en) * | 1994-07-20 | 1996-03-05 | Aluminum Company Of America | Aluminum alloy product having good combinations of mechanical and corrosion resistance properties and formability and process for producing such product |
ATE245207T1 (de) * | 1996-09-11 | 2003-08-15 | Aluminum Co Of America | Aluminiumlegierung für verkehrsflugzeugflügel |
US6315842B1 (en) * | 1997-07-21 | 2001-11-13 | Pechiney Rhenalu | Thick alznmgcu alloy products with improved properties |
US6562154B1 (en) * | 2000-06-12 | 2003-05-13 | Aloca Inc. | Aluminum sheet products having improved fatigue crack growth resistance and methods of making same |
FR2820438B1 (fr) * | 2001-02-07 | 2003-03-07 | Pechiney Rhenalu | Procede de fabrication d'un produit corroye a haute resistance en alliage alznmagcu |
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2005
- 2005-09-22 DE DE102005045341A patent/DE102005045341A1/de not_active Ceased
- 2005-09-29 FR FR0509944A patent/FR2876118B1/fr active Active
- 2005-10-04 AT AT05802352T patent/ATE426050T1/de active
- 2005-10-04 BR BRPI0517538-0A patent/BRPI0517538B1/pt active IP Right Grant
- 2005-10-04 CN CN2005800339556A patent/CN101068943B/zh active Active
- 2005-10-04 CA CA2592132A patent/CA2592132C/fr active Active
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- 2005-10-04 JP JP2007533966A patent/JP5068654B2/ja active Active
- 2005-10-04 RU RU2007116979/02A patent/RU2404276C2/ru active
- 2005-10-04 EP EP05802352.4A patent/EP1831415B2/fr active Active
- 2005-10-04 WO PCT/EP2005/010809 patent/WO2006037648A1/fr active Application Filing
Non-Patent Citations (1)
Title |
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"International Alloy Designations and Chemical Composition Limits for Wrought Aluminum and Wrought Aluminum Alloys", 1998, THE ALUMINUM ASSOCIATION, WASHINGTON, pages: 7 - 9 † |
Also Published As
Publication number | Publication date |
---|---|
JP2008516079A (ja) | 2008-05-15 |
CN101068943B (zh) | 2011-11-23 |
DE602005013429D1 (de) | 2009-04-30 |
WO2006037648A1 (fr) | 2006-04-13 |
RU2404276C2 (ru) | 2010-11-20 |
EP1831415A1 (fr) | 2007-09-12 |
CN101068943A (zh) | 2007-11-07 |
CA2592132C (fr) | 2014-08-05 |
ATE426050T1 (de) | 2009-04-15 |
BRPI0517538B1 (pt) | 2015-06-16 |
EP1831415B1 (fr) | 2009-03-18 |
DE102005045341A1 (de) | 2006-07-20 |
BRPI0517538A (pt) | 2008-10-14 |
CA2592132A1 (fr) | 2006-04-13 |
FR2876118B1 (fr) | 2010-08-20 |
RU2007116979A (ru) | 2008-11-20 |
JP5068654B2 (ja) | 2012-11-07 |
FR2876118A1 (fr) | 2006-04-07 |
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