EP1945825A1 - Al-cu-mg alloy suitable for aerospace application - Google Patents
Al-cu-mg alloy suitable for aerospace applicationInfo
- Publication number
- EP1945825A1 EP1945825A1 EP06818278A EP06818278A EP1945825A1 EP 1945825 A1 EP1945825 A1 EP 1945825A1 EP 06818278 A EP06818278 A EP 06818278A EP 06818278 A EP06818278 A EP 06818278A EP 1945825 A1 EP1945825 A1 EP 1945825A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- aluminium alloy
- product
- alloy product
- processed
- alloy
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 229910000861 Mg alloy Inorganic materials 0.000 title 1
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 78
- 239000000956 alloy Substances 0.000 claims abstract description 78
- 229910000838 Al alloy Inorganic materials 0.000 claims abstract description 72
- 230000007797 corrosion Effects 0.000 claims abstract description 54
- 238000005260 corrosion Methods 0.000 claims abstract description 54
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 10
- 239000004411 aluminium Substances 0.000 claims abstract description 10
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 10
- 239000012535 impurity Substances 0.000 claims abstract description 9
- 238000010791 quenching Methods 0.000 claims description 17
- 238000004519 manufacturing process Methods 0.000 claims description 16
- 229910052804 chromium Inorganic materials 0.000 claims description 13
- 230000000171 quenching effect Effects 0.000 claims description 11
- 238000010438 heat treatment Methods 0.000 claims description 10
- 238000000034 method Methods 0.000 claims description 10
- 230000032683 aging Effects 0.000 claims description 9
- 239000000203 mixture Substances 0.000 claims description 9
- 239000000243 solution Substances 0.000 claims description 8
- 238000005266 casting Methods 0.000 claims description 6
- 238000005242 forging Methods 0.000 claims description 5
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 4
- 235000012438 extruded product Nutrition 0.000 claims description 3
- 238000005096 rolling process Methods 0.000 claims description 3
- 239000000470 constituent Substances 0.000 claims description 2
- 238000001125 extrusion Methods 0.000 claims description 2
- 238000007654 immersion Methods 0.000 claims description 2
- 238000003303 reheating Methods 0.000 claims description 2
- 239000006104 solid solution Substances 0.000 claims description 2
- 239000007921 spray Substances 0.000 claims description 2
- 238000005482 strain hardening Methods 0.000 claims description 2
- 238000012360 testing method Methods 0.000 description 14
- 230000000052 comparative effect Effects 0.000 description 10
- 238000001000 micrograph Methods 0.000 description 10
- XEEYBQQBJWHFJM-UHFFFAOYSA-N iron Substances [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 8
- 239000011572 manganese Substances 0.000 description 7
- 238000005275 alloying Methods 0.000 description 6
- 229910052710 silicon Inorganic materials 0.000 description 4
- 238000002791 soaking Methods 0.000 description 4
- 229910052742 iron Inorganic materials 0.000 description 3
- 239000000126 substance Substances 0.000 description 3
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 238000005336 cracking Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000004299 exfoliation Methods 0.000 description 2
- 238000000265 homogenisation Methods 0.000 description 2
- 238000005098 hot rolling Methods 0.000 description 2
- 229910052749 magnesium Inorganic materials 0.000 description 2
- 239000010703 silicon Substances 0.000 description 2
- 229910052709 silver Inorganic materials 0.000 description 2
- 230000035882 stress Effects 0.000 description 2
- 229910052726 zirconium Inorganic materials 0.000 description 2
- 229910017818 Cu—Mg Inorganic materials 0.000 description 1
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 description 1
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 1
- 238000005097 cold rolling Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000001934 delay Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000004512 die casting Methods 0.000 description 1
- 230000001747 exhibiting effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000001746 injection moulding Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 229910052748 manganese Inorganic materials 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 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
- C22C21/12—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
Definitions
- the invention relates to an aluminium wrought alloy, in particular an Al-Cu- Mg type alloy (or AA2000 series aluminium alloy as designated by the Aluminium
- the present invention relates to an aluminium alloy product having high strength, high fracture toughness exhibiting low crack propagation and high resistance to intergranular corrosion.
- Products made from the aluminium alloy according to the invention are very suitable for aerospace applications but not limited thereto.
- the alloy can be processed to various product forms such as sheet, thin plate or an extruded product, a forged product, or a welded product.
- the aluminium alloy product can be uncoated or coated or plated with another aluminium alloy in order to improve desired properties even further.
- AA2000 series aluminium alloys in aeroplanes is as fuselage or skin plate, for which purpose typically AA2024 in the T351 temper is used or as lower wing plate for which purpose typically AA2024 in the T351 temper and AA2324 in the T39 temper is used.
- Intergranular corrosion of an aluminium alloy not only affects the integrity of the structure for which it is used, in which may corroded grain boundaries may act as a nucleus for cracks which propagate under the influence of the alternating load during operation of the structure. Therefore, the occurrence of intergranular corrosion sets limits to the use of aluminium alloys of the AA2000 series with high levels of the mentioned alloying elements.
- the most commonly used aluminium alloys form the AA2000 series for aerospace application are AA2024, AA2024HDT ("High Damage Tolerant") and AA2324.
- the present invention is directed to a AA2000 series aluminium alloy having the capability of achieving a balance of properties in any relevant product made of the alloy that is better than the balance of properties of the variety of commercially available aluminium alloys of the AA2000 series, nowadays used for such a product or of AA2000 series aluminium alloys disclosed so far.
- One object of the present invention is to provide an aluminium alloy wrought product, in particular suitable for aerospace application within the AA2000 series alloys having an improved balance of high strength and fracture toughness and high resistance to intergranular corrosion.
- Another object of the present invention is to provide an aluminium alloy wrought product as referred to above which shows a high resistance to exfoliation corrosion and stress corrosion cracking.
- a further object of the present invention is to provide an aluminium alloy wrought product as referred to above which is tolerant to the usual variation in process parameters during its manufacturing process.
- Yet another object of the present invention is to provide an aluminium alloy wrought product as referred to above which is weldable and suitable for use in welded constructions.
- Yet another object of the present invention is to provide an aluminium wrought product as referred to above in a form which is suitable for use in an aerospace structure.
- a further object of the present invention is to provide a method of manufacturing an aluminium alloy wrought product as mentioned hereinabove.
- an aluminium alloy wrought product having high strength and high fracture toughness and high resistance to intergranular corrosion, the aluminium alloy comprising in weight %:
- Fig. 1 shows a Cr-Ti diagram setting out the Cr-Ti range for the invention together with narrower preferred ranges.
- Figs. 2a, 2b show micrographs of a cross section of a sample of an alloy according to the invention in T3 temper and of a comparative alloy after corrosion testing.
- Figs. 3a, 3b show micrographs of a cross section of a sample of an alloy according to the invention in T6 temper and of a comparative alloy after corrosion testing.
- the present invention provides an aluminium alloy wrought product having high strength and high fracture toughness and high resistance to intergranular corrosion, the aluminium alloy comprising in weight %:
- composition of the aluminium alloy according to our invention leads to an alloy product having a high resistance to intergranular corrosion while maintaining a higher strength and higher toughness as compared to the conventional AA2024 alloy.
- the alloy product of the invention also exhibits a high resistance to exfoliation corrosion and stress corrosion cracking.
- Good results are also obtained in a preferred embodiment of the invention wherein 0.03% ⁇ Ti ⁇ 0.3%, preferably 0.05% ⁇ Ti ⁇ 0.2%. According to this embodiment good properties can also be achieved with a lower concentration of Ti.
- Another embodiment has the range wherein 0.05% ⁇ Cr ⁇ 0.3%, preferably
- a further embodiment has the range wherein 0.1% ⁇ Ti + Cr ⁇ 0.4%. It has been found that within the given range Ti and Cr can be substituted by each other while maintaining good resistance against intergranular corrosion and good mechanical properties.
- the Cu level is selected in the range wherein 4.4% ⁇ Cu ⁇ 5.5%, more preferably 4.7% ⁇ Cu ⁇ 5.3%.
- the Mg level is selected in the range wherein 0.3% ⁇ Mg ⁇ 1.2%, more preferably 0.4% ⁇ Mg ⁇ 0.75%.
- Iron can be present in the range of up to 0.20% and preferably is kept to a maximum of 0.15%, more preferably to a maximum of 0.1%.
- a typical preferred iron level would be in the range of 0.03% to 0.08%.
- Silicon can be present in a range of up to 0.20% and preferably is kept to a maximum of 0.15%, more preferably to a maximum of 0.1%.
- a typical preferred silicon level would be as low as possible and would typically be for practical reasons in a range of 0.02% to 0.07%.
- Zirconium can be present in the alloy product according to the invention in an amount of up to 0.20%.
- a suitable Zr level is a range of 0.04% to 0.15%.
- a more preferred upper limit for the Zr level is 0.13%, and even more preferably not more than 0.11%.
- Manganese can be added alone or in combination with other dispersoid formers.
- a preferred maximum for the Mn level is 0.80% and a preferred minimum level is 0.15%.
- a preferred range for the Mn level is in the range of wherein 0.2% ⁇ Mn ⁇ 0.5%.
- a second drawback is that also in relation to the price of Ag, any scrap of the alloy should be carefully handled and recycled to reclaim the Ag.
- the alloy is free of Ag.
- the alloy is substantially free of Ag. With “substantially free” is meant that no purposeful addition of Ag was made to the chemical composition but that due to impurities and/or leaking from contact with manufacturing equipment, trace quantities of Ag may nevertheless find their way into the aluminium alloy product.
- the alloy has a composition consisting of, in wt.%:
- Si ⁇ 0.15% preferably ⁇ 0.1%, and the balance being aluminium and other impurities or incidental elements each ⁇ 0.05%, total ⁇ 0.15%, and is substantially free of Ag. More preferred narrower ranges for the various alloying elements are set out in this specification and claims.
- the aluminium alloy product according to the invention is in the T3x, T6x or T8x temper.
- the appropriate temper is selected to give the alloy product desired properties. Temper designations are according to the Aluminium Association.
- the product is preferably provided in the form of a sheet, plate, forging or extrusion for use in an aerospace structure.
- the aluminium alloy product according to the invention shows an excellent balance of properties for application as plate over a wide variety of thickness, preferably in the form of a plate having a thickness in the range of 0.7 to 80 mm. In the plate thickness range of 0.6 to 1.5 mm the aluminium alloy product is also of particular interest as automotive body sheet.
- the properties of the aluminium alloy product will be excellent for fuselage sheet and preferably the thickness is up to 25 mm.
- the properties are excellent for wing plates, e.g. lower wing plate, when tensile strength and fatigue properties are of great importance.
- the aluminium alloy products can also be used for stringers or to form an integral wing panel and stringer for use in an aircraft wing structure.
- aluminium alloy product according to the invention can also be used as tooling plate or mould plate, e.g. for moulds for manufacturing formed plastic products for example via die-casting or injection moulding.
- higher Fe and Si levels up to 0.4% for each of these elements are acceptable.
- the invention is also embodied in a method for the manufacture of an aluminium alloy product having high strength and high fracture toughness and a high resistance to intergranular corrosion comprising the steps of: a. casting an ingot having a composition according to the invention; b. homogenising and/or pre-heating the ingot after casting; c. hot working the ingot into a worked product by one of more methods selected from the group consisting of rolling, extruding and forging; d. optional reheating the worked product, and e. optional further hot working and/or cold working to a desired work piece form; f. solution heat treating said formed work piece at a temperature and time sufficient to place into solid solutions substantially all soluble constituents in the alloy; g.
- the method according to the invention yields aluminium alloy product having excellent resistance to intergranular corrosion and having high strength and excellent fatigue properties.
- the alloy products of the present invention are regularly prepared by melting and alloying an aluminium alloy product and may be direct chill (“D. C") cast into ingots or other suitable casting techniques. Homogenisation treatment is typically carried out in one or more steps, each step having a temperature preferably in the range of 46O 0 C to 535 0 C.
- the pre-heat temperature involves heating the ingot to the hot working temperature which is typically in a temperature range of 400 0 C to 48O 0 C.
- Working the alloy product can be done by one or more methods selected from the group consisting of rolling, extruding and forging. For the present alloy product hot rolling is preferred. Solution heat treatment is typically carried out in the same temperature range as used for homogenisation although somewhat shorter soaking times can be selected.
- artificial ageing preferably comprises an ageing step at a temperature in the range of 135 0 C to 21O 0 C, preferably for 5 to 20 hours.
- the natural ageing preferably comprises a step of ageing at room temperature during 1 to 10 days.
- the aluminium alloy product is aged to a temper selected from the group comprising T3, T351 , T39, T6, T651 , and T87.
- the aluminium alloy product is processed to fuselage sheet, preferably to fuselage sheet having a thickness of less then 30 mm.
- the aluminium alloy product is processed to lower wing plate.
- the aluminium alloy product is processed to upper wing plate.
- the aluminium alloy product is processed to an extruded product.
- the aluminium alloy product is processed to a forged product. In yet another embodiment the aluminium alloy product is processed to a thin plate having a thickness in the range of 15 to 40 mm.
- the aluminium alloy product is processed to a thick plate having a thickness up to 300 mm.
- Fig. 1 shows a Cr-Ti diagram setting out the Cr-Ti range for the invention together with narrower preferred ranges.
- Fig. 1 shows schematically the ranges for the Cr and Ti content for the alloy according to the invention. The broadest range is identified by a rectangular box with angular points A, B, C, D.
- Fig. 1 also shows schematically a preferred range of a balanced content of both Cr and Ti.
- the broadest range thereof is identified by a quadrangular box with angular points E, F, G, H.
- the point P indicates the Cr and Ti content of a sample of an alloy according to the invention which was used for testing (also referred to as Alloy 3 in the following examples).
- alloys 1 and 2 indicate the Cr and Ti content of two comparative alloys, also used for testing and also referred to as alloys 1 and 2. Alloys 1 and 2 fall outside the invention.
- Alloy 2 has, with the exception of the Cr and Ti content, the same chemical composition as Alloy 3 according to the invention.
- Alloy 1 has a chemical composition typical for a conventional AA2024 alloy.
- the alloys listed in Table 1 were processed as follows: Casting an ingot;
- Alloy 1 homogenising the ingot at a heating rate of 30 °C/h to 465 0 C, soaking at that temperature for 2 hours followed by further heating at a rate of 15 °C/h to 495 0 C and soaking at that temperature for 24 hours followed by air cooling to room temperature.
- Quenching the cold rolled plate by either direct water quenching or quenching in water after holding 10 sec. in still air.
- Stretching and ageing the cold rolled plate by either: o Stretching and natural ageing for 5 days at room temperature to T3x tempers (viz. T3, T351 , and T39); or o Stretching and artificial ageing for 12 hours at 175 0 C to T6x and T8x tempers (viz. T6, T651 , 187).
- Table 2 shows that a balanced addition of Cr and Ti according to an embodiment of the invention gives rise to outstanding intergranular corrosion free properties in the T3x tempers with a markedly lower pit depth compared with the other alloys.
- Figs. 2a, 2b, 3a and 3b show micrographs of a cross section of a sample of an alloy according to the invention in T3 temper and of a comparative alloy after corrosion testing.
- Fig. 2a shows a micrograph of a cross section of a sample of comparative alloy 1 (Ref. AA2024) in T3 temper after corrosion testing.
- the micrograph clearly shows pitting corrosion and intergranular corrosion to a depth of more than 150 ⁇ m.
- Fig. 2b shows a micrograph of a cross section of a sample of an alloy according to the invention (alloy 3) also in T3 temper after corrosion testing. The samples show only slight pitting, with a maximum depth of 60 ⁇ m and no intergranular corrosion.
- Figs. 3a, 3b show micrographs of a cross section of sample of an alloy according to the invention in T6 temper and of a comparative alloy after corrosion testing.
- Fig. 3a shows a micrograph of a cross section of a sample of a comparative alloy 1 (Ref. AA2024) in T6 temper after corrosion testing.
- the micrograph clearly shows local intergranular corrosion, extending to a depth of about 220 ⁇ m.
- Fig. 3b shows a micrograph of a cross section of a sample of an alloy according to the invention (alloy 3) also in T6 temper after corrosion testing.
- the sample exhibits pitting with only slight intergranular corrosion to a depth of less than 160 ⁇ m.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Extrusion Of Metal (AREA)
- Metal Rolling (AREA)
Abstract
Description
Claims
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP06818278.1A EP1945825B1 (en) | 2005-10-25 | 2006-10-24 | Al-cu-mg alloy suitable for aerospace application |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP05077448 | 2005-10-25 | ||
PCT/EP2006/010216 WO2007048565A1 (en) | 2005-10-25 | 2006-10-24 | Al-cu-mg alloy suitable for aerospace application |
EP06818278.1A EP1945825B1 (en) | 2005-10-25 | 2006-10-24 | Al-cu-mg alloy suitable for aerospace application |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1945825A1 true EP1945825A1 (en) | 2008-07-23 |
EP1945825B1 EP1945825B1 (en) | 2014-06-25 |
Family
ID=36572409
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP06818278.1A Active EP1945825B1 (en) | 2005-10-25 | 2006-10-24 | Al-cu-mg alloy suitable for aerospace application |
Country Status (6)
Country | Link |
---|---|
EP (1) | EP1945825B1 (en) |
CN (1) | CN101297054A (en) |
BR (1) | BRPI0617699A2 (en) |
CA (1) | CA2627070C (en) |
RU (1) | RU2418876C2 (en) |
WO (1) | WO2007048565A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2020200869A1 (en) * | 2019-04-03 | 2020-10-08 | Aleris Rolled Products Germany Gmbh | Method of producing a high-energy hydroformed structure from a 2xxx-series alloy |
Families Citing this family (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN101649433B (en) * | 2009-07-10 | 2012-11-21 | 西南铝业(集团)有限责任公司 | Method for processing aluminum alloy plates |
CN103168111B (en) * | 2010-10-08 | 2015-07-29 | 美铝公司 | The 2XXX aluminium alloy improved and production method thereof |
EP2559779B1 (en) * | 2011-08-17 | 2016-01-13 | Otto Fuchs KG | High temperature Al-Cu-Mg-Ag alloy and method for producing a semi-finished product or product from such an aluminium alloy |
CN102925829A (en) * | 2012-11-22 | 2013-02-13 | 哈尔滨工业大学 | Heat treating method for Al-Cu-Mg-Si-based aluminium alloy thin-walled annular member |
JP6057855B2 (en) * | 2013-07-31 | 2017-01-11 | 株式会社神戸製鋼所 | Aluminum alloy extruded material for cutting |
RU2573164C1 (en) * | 2014-10-02 | 2016-01-20 | Федеральное государственное автономное образовательное учреждение высшего профессионального образования "Белгородский государственный национальный исследовательский университет" (НИУ "БелГУ") | High-strength wrought aluminium-based alloy |
CN105002408A (en) * | 2015-07-12 | 2015-10-28 | 河北钢研德凯科技有限公司 | High-quality, high-strength cast aluminum alloy material and preparation method |
CN105239029B (en) * | 2015-10-23 | 2017-12-08 | 中铝材料应用研究院有限公司 | Control the heat treatment method that the even dispersion of phase containing Mn separates out in Al Cu Mg Mn alloys |
CN105908028B (en) * | 2016-06-16 | 2018-02-27 | 江苏大学 | A kind of method for designing high-hardenability high-strength aluminum alloy main component |
CN110114498A (en) * | 2016-10-24 | 2019-08-09 | 形状集团 | Multistage aluminium alloy for producing vehicle part is formed and hot-working method |
CN108118273B (en) * | 2017-12-11 | 2019-11-12 | 中南大学 | A method of improving aluminium alloy corrosion resistance |
CN109136697B (en) * | 2018-08-28 | 2020-12-22 | 兰州飞行控制有限责任公司 | High-strength aluminum-copper aluminum alloy |
CN110724866A (en) * | 2019-11-28 | 2020-01-24 | 西南铝业(集团)有限责任公司 | No zirconium blank of accurate wheel hub die forging of 2014 aluminum alloy aviation |
CN111020321B (en) * | 2019-12-11 | 2021-09-14 | 兰州飞行控制有限责任公司 | Al-Cu series casting alloy suitable for forging processing and preparation method thereof |
CN111101038A (en) * | 2019-12-20 | 2020-05-05 | 山东南山铝业股份有限公司 | Multi-element heat-resistant aluminum alloy and preparation method thereof |
FR3111143B1 (en) * | 2020-06-04 | 2022-11-18 | Constellium Issoire | High temperature performance aluminum copper magnesium alloy products |
CN112281033B (en) * | 2020-09-25 | 2021-09-28 | 中南大学 | Method for simultaneously improving corrosion resistance and heat resistance of aluminum-copper-magnesium alloy oil well pipe |
CN113897524A (en) * | 2021-10-09 | 2022-01-07 | 山东创新精密科技有限公司 | Aluminum alloy with high conductivity uniformity and preparation method and application thereof |
CN114134376A (en) * | 2021-12-08 | 2022-03-04 | 无锡市世达精密焊管制造有限公司 | Mg-Cu aluminum alloy and preparation method thereof |
CN115821131B (en) * | 2022-12-05 | 2024-05-14 | 山东南山铝业股份有限公司 | Low fatigue crack growth rate 2-series aluminum alloy section bar and manufacturing method thereof |
CN115927936B (en) * | 2022-12-22 | 2023-06-09 | 北京机科国创轻量化科学研究院有限公司 | High-strength and high-toughness aluminum alloy and preparation method thereof |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5652063A (en) * | 1995-03-22 | 1997-07-29 | Aluminum Company Of America | Sheet or plate product made from a substantially vanadium-free aluminum alloy |
FR2802946B1 (en) * | 1999-12-28 | 2002-02-15 | Pechiney Rhenalu | AL-CU-MG ALLOY AIRCRAFT STRUCTURAL ELEMENT |
US7604704B2 (en) * | 2002-08-20 | 2009-10-20 | Aleris Aluminum Koblenz Gmbh | Balanced Al-Cu-Mg-Si alloy product |
US7323068B2 (en) * | 2002-08-20 | 2008-01-29 | Aleris Aluminum Koblenz Gmbh | High damage tolerant Al-Cu alloy |
US8043445B2 (en) * | 2003-06-06 | 2011-10-25 | Aleris Aluminum Koblenz Gmbh | High-damage tolerant alloy product in particular for aerospace applications |
FR2858984B1 (en) * | 2003-08-19 | 2007-01-19 | Corus Aluminium Walzprod Gmbh | AL-CU HIGH-TENACITY ALLOY PRODUCT AND PROCESS FOR PRODUCING THE SAME |
-
2006
- 2006-10-24 EP EP06818278.1A patent/EP1945825B1/en active Active
- 2006-10-24 CA CA2627070A patent/CA2627070C/en active Active
- 2006-10-24 RU RU2008115928/02A patent/RU2418876C2/en active
- 2006-10-24 CN CNA2006800395315A patent/CN101297054A/en active Pending
- 2006-10-24 WO PCT/EP2006/010216 patent/WO2007048565A1/en active Application Filing
- 2006-10-24 BR BRPI0617699-2A patent/BRPI0617699A2/en not_active Application Discontinuation
Non-Patent Citations (1)
Title |
---|
See references of WO2007048565A1 * |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2020200869A1 (en) * | 2019-04-03 | 2020-10-08 | Aleris Rolled Products Germany Gmbh | Method of producing a high-energy hydroformed structure from a 2xxx-series alloy |
Also Published As
Publication number | Publication date |
---|---|
CA2627070A1 (en) | 2007-05-03 |
CN101297054A (en) | 2008-10-29 |
RU2008115928A (en) | 2009-10-27 |
CA2627070C (en) | 2014-07-29 |
RU2418876C2 (en) | 2011-05-20 |
WO2007048565A1 (en) | 2007-05-03 |
BRPI0617699A2 (en) | 2011-08-02 |
EP1945825B1 (en) | 2014-06-25 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CA2627070C (en) | Al-cu-mg alloy suitable for aerospace application | |
RU2477331C2 (en) | Product from aluminium alloy with high resistance to damages, namely to be used in aviation and space industry | |
RU2404276C2 (en) | PRODUCT FROM HIGH-STRENGTH, HIGH-VISCOSITY Al-Zn ALLOY AND MANUFACTURING METHOD OF SUCH PRODUCT | |
RU2353693C2 (en) | ALLOY Al-Zn-Mg-Cu | |
CA2596190C (en) | Al-zn-cu-mg aluminum base alloys and methods of manufacture and use | |
US7666267B2 (en) | Al-Zn-Mg-Cu alloy with improved damage tolerance-strength combination properties | |
US11976347B2 (en) | Al—Zn—Cu—Mg alloys and their manufacturing process | |
US20140212326A1 (en) | Aluminum-copper-lithium alloys | |
JP2006522872A (en) | High strength Al-Zn alloy and method for producing such an alloy product | |
CN113302327A (en) | 7xxx series aluminum alloy products | |
CN110832094A (en) | Improved thick wrought7XXX aluminum alloys and methods of making the same | |
CA3074942A1 (en) | Al-zn-cu-mg alloys with high strength and method of fabrication | |
US20070151637A1 (en) | Al-Cu-Mg ALLOY SUITABLE FOR AEROSPACE APPLICATION | |
EP3880856A2 (en) | 2xxx aluminum alloys | |
US20190368009A1 (en) | High Strength, Better Fatigue Crack Deviation Performance, and High Anisotropic Ductility 7xxx Aluminum Alloy Products and Methods of Making Such Products |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
17P | Request for examination filed |
Effective date: 20080515 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR |
|
DAX | Request for extension of the european patent (deleted) | ||
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
INTG | Intention to grant announced |
Effective date: 20140304 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: ALERIS ALUMINIUM GMBH |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: ALERIS ROLLED PRODUCTS GERMANY GMBH |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: EP |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: REF Ref document number: 674772 Country of ref document: AT Kind code of ref document: T Effective date: 20140715 |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: FG4D |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R096 Ref document number: 602006042066 Country of ref document: DE Effective date: 20140807 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20140926 Ref country code: FI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20140625 Ref country code: CY Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20140625 Ref country code: LT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20140625 |
|
REG | Reference to a national code |
Ref country code: NL Ref legal event code: VDEP Effective date: 20140625 |
|
REG | Reference to a national code |
Ref country code: LT Ref legal event code: MG4D |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20140625 Ref country code: LV Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20140625 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: ES Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20140625 Ref country code: SK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20140625 Ref country code: PT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20141027 Ref country code: RO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20140625 Ref country code: EE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20140625 Ref country code: CZ Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20140625 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: NL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20140625 Ref country code: PL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20140625 Ref country code: IS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20141025 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R026 Ref document number: 602006042066 Country of ref document: DE |
|
PLBI | Opposition filed |
Free format text: ORIGINAL CODE: 0009260 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20140625 Ref country code: DK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20140625 |
|
26 | Opposition filed |
Opponent name: C-TEC CONSTELLIUM TECHNOLOGY CENTER Effective date: 20150325 |
|
PLAX | Notice of opposition and request to file observation + time limit sent |
Free format text: ORIGINAL CODE: EPIDOSNOBS2 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MC Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20140625 Ref country code: LU Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20141024 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R026 Ref document number: 602006042066 Country of ref document: DE Effective date: 20150325 |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: MM4A |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LI Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20141031 Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20141031 |
|
PLAF | Information modified related to communication of a notice of opposition and request to file observations + time limit |
Free format text: ORIGINAL CODE: EPIDOSCOBS2 |
|
PLBB | Reply of patent proprietor to notice(s) of opposition received |
Free format text: ORIGINAL CODE: EPIDOSNOBS3 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 10 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20141024 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20140625 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: BG Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20140625 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: TR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20140625 Ref country code: BE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20140625 Ref country code: HU Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO Effective date: 20061024 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 11 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 12 |
|
PLCK | Communication despatched that opposition was rejected |
Free format text: ORIGINAL CODE: EPIDOSNREJ1 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE PATENT HAS BEEN GRANTED |
|
APAH | Appeal reference modified |
Free format text: ORIGINAL CODE: EPIDOSCREFNO |
|
APBM | Appeal reference recorded |
Free format text: ORIGINAL CODE: EPIDOSNREFNO |
|
APBP | Date of receipt of notice of appeal recorded |
Free format text: ORIGINAL CODE: EPIDOSNNOA2O |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R100 Ref document number: 602006042066 Country of ref document: DE |
|
APBU | Appeal procedure closed |
Free format text: ORIGINAL CODE: EPIDOSNNOA9O |
|
PLBN | Opposition rejected |
Free format text: ORIGINAL CODE: 0009273 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: OPPOSITION REJECTED |
|
27O | Opposition rejected |
Effective date: 20180315 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 13 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R082 Ref document number: 602006042066 Country of ref document: DE Representative=s name: WEICKMANN & WEICKMANN PATENT- UND RECHTSANWAEL, DE |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R081 Ref document number: 602006042066 Country of ref document: DE Owner name: NOVELIS KOBLENZ GMBH, DE Free format text: FORMER OWNER: ALERIS ROLLED PRODUCTS GERMANY GMBH, 56070 KOBLENZ, DE |
|
P01 | Opt-out of the competence of the unified patent court (upc) registered |
Effective date: 20230517 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20230920 Year of fee payment: 18 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20230920 Year of fee payment: 18 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20230920 Year of fee payment: 18 Ref country code: AT Payment date: 20230921 Year of fee payment: 18 |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: HC Ref document number: 674772 Country of ref document: AT Kind code of ref document: T Owner name: NOVELIS KOBLENZ GMBH, DE Effective date: 20240110 |