WO1997027343A1 - PRODUITS EPAIS EN ALLIAGE A1ZnMgCu A PROPRIETES AMELIOREES - Google Patents
PRODUITS EPAIS EN ALLIAGE A1ZnMgCu A PROPRIETES AMELIOREES Download PDFInfo
- Publication number
- WO1997027343A1 WO1997027343A1 PCT/FR1997/000144 FR9700144W WO9727343A1 WO 1997027343 A1 WO1997027343 A1 WO 1997027343A1 FR 9700144 W FR9700144 W FR 9700144W WO 9727343 A1 WO9727343 A1 WO 9727343A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- thickness
- mpavm
- mpa
- product
- product according
- Prior art date
Links
Classifications
-
- 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
-
- 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
Definitions
- the invention relates to aluminum alloy products of the AlZnMgCu type (series 7000 according to the designation of the Aluminum Association) with a thickness greater than 60 mm. These products can be hot-rolled plates or sheets, forged blocks or spun products. In the case where the product is not of parallelepiped shape, the term thickness is understood to mean the smallest dimension of the product at the time of quenching (for example the thickness of the thinnest wall for a profile).
- Thick products laminated, forged or spun from ahiminhim alloy of the 7000 series are used to produce, by cutting, surfacing or mass machining, high resistance parts intended for the aeronautical industry, for example wing elements such as wing spars or fishplates. as well as fuselage elements such as frames, or parts for mechanical construction such as components of machine tools or molds of plastics.
- the alloy must be able to be cast and transformed under good conditions to lead to an acceptable metallurgical quality.
- the transformation after casting of the plate or billet usually comprises a homogenization, a hot transformation by rolling, forging or spinning, dissolving, quenching (for example by immersion or spraying with a liquid hardening), possibly stress relieving by cold traction or by compression, maturation and tempering.
- the cooling during quenching can be more or less rapid.
- the quenching speed here denotes the average cooling speed (in ° C./s) of the product between 450 and 280 ° C., relative to the quarter of a thickness.
- a product is said to be sensitive to quenching if its static mechanical characteristics, such as its elastic limit, decrease when the quenching speed decreases, which, of course, is more likely to occur on thick products.
- a fiber structure is generally sought which is obtained by avoiding too great recrystallization of the alloy.
- anti-crystallization elements such as Zr, Ti, Cr, Mn, V, Hf or Se are added to the composition.
- the compositions registered with the AJuminum Association of alloys 7010 and 7050 comprise an addition of Zr at contents of between 0.10 and 0.16% respectively, and between 0.08 and 0.15%.
- the Russian metallurgists have proposed, to reduce the sensitivity to hardening, the alloy V93, or 1930 according to the Russian standard GOST 11069, which does not contain anti-recrystallizing elements, but has a composition very far from those of alloys 7010 or 7050 , with in particular a high iron content (between 0.20 and 0.45%) unfavorable to toughness and resistance to fatigue.
- the object of the invention is to find, for alloys 7000 with copper with the addition of zirconium, a particular composition range for thick products which makes them very insensitive to quenching, in which recrystallization is controlled to a very low level. retaining a commercial purity of iron and siUcium, which leads to high mechanical strength and toughness, as well as to good behavior in fatigue, without detrimental effect on the resistance to corrosion under stress.
- the subject of the invention is a rolled, extruded or forged product of AlZnMgCu alloy with a thickness> 60 mm and preferably> 125 mm, of composition (% by weight): 5.9 ⁇ Zn ⁇ 8.7
- the products according to the invention have a volume fraction of recrystallized grains, measured in the part situated between quarter thickness and mid thickness, ⁇ 35%.
- the magnesium content is preferably kept higher than the copper content.
- the subject of the invention is also an alloy product with a more restricted composition: 5.9 ⁇ Zn ⁇ 8.7
- the toughness in plane deformation is preferably> 28 MPaVm in the S-L direction and>
- the invention also relates to the same composition products as above and after having income during an equivalent time t (eq) between 600 and 1000 hours, the following properties: a) Ro, 2 in quarter thickness L and TL directions > 425 MPa, b) a tenacity in plane deformation direction SL> 25 (pref. 28) MPaVm and direction LT> 74 (pref. 75) - 0.08e - 0.07 R O ⁇ L , MPaVm. c) a voltage corrosion threshold> 240 MPa (preferably 300 MPa).
- the properties are as follows: a) Ro, 2 directions L and TL> 400 MPa, b) tenacity in plane deformation direction SL> 28 MPaVm and direction LT> 76 (pref. 77) - 0.08e - 0.07 Ro , 2 (W MPaVm, c) a voltage corrosion threshold> 240 MPa.
- t (eq) (Jexp (-16000 / T) dt) / exp (-16000 / T ref ) where T is the instantaneous temperature in ° K during tempering and T re f is a reference temperature chosen at 120 ° C (393 ° K).
- t (eq) is expressed in hours.
- FIG. 1 represents the elastic limit at 0.2% Ro. 2 directions L as a function of the thickness of a set of sheets of alloy 7050 in the state T7451 of the prior art.
- Figure 2 shows in the same way Ro, 2- way TL as a function of the thickness of the same set of sheets.
- FIG. 3 represents, in an Mg-Cu diagram, the composition domain of the invention (in broken lines), as well as the preferred domain (in thin solid lines), and the restricted domain (in thick solid lines)
- the inventors determined a range of composition of alloys 7000, containing copper and zirconium, with commercial contents of iron and silicon, making it possible to control the recrystallization, and leading, from a thickness of approximately 60 mm, to a reduction in the sensitivity to quenching of the product when the thickness of the product increases, while maintaining good toughness and good resistance to corrosion under stress, with a range of conventional industrial transformation.
- the magnesium content of the alloy is reduced compared to that of alloys 7010 or 7050, since it is centered around 2% instead of 2.3%, but it cannot be lower than 1.7% if we want to keep sufficient mechanical characteristics.
- Copper is centered around 1.7%, which corresponds to an increase compared to 7010, but a decrease compared to 7050. It is important to maintain a certain balance between Cu and Mg: if Cu + Mg> 4.1 , the tenacity - elastic limit compromise degrades and makes the product uninteresting. It may be advantageous to keep the Mg content higher than that of Cu.
- the composition domain according to the invention, as well as the preferred domain, is represented on an Mg-Cu diagram in FIG. 3. Mainly used as an anti-recrystallizing element, z ⁇ conium, avoiding manganese and chromium as much as possible, which increase the sensitivity to quenching. The Zr content must exceed 0.05% to act on recrystallization, but must remain below 0.15% to avoid sensitivity to quenching and to avoid problems with casting. Iron and silicon are at levels equivalent to that of 7010 and 7050.
- the range of production of the product according to the invention is similar to that of products made of alloys 7000, for example in 7010 and 7050. It comprises the casting of a plate or a rod, homogenization at a temperature between 450 and 485 ° C, a hot transformation in one or more stages by rolling, spinning or forging at a temperature between 370 and 460 ° C and controlled to obtain the desired recrystallization rate, quenching by immersion or by spraying, with cold water or at a temperature below 95 ° C., stress relieving by deformation at room temperature (controlled traction or compression) at a rate of less than 5%, and possibly a tempering treatment, to obtain, for example, T6 states, T74, T76, T751, T7451 or T7651, especially in the case of the use of these products for plastics molds.
- the 6 plates were scalped, homogenized respectively at 475 ° C (7050) and 465 ° C (alloy F), laminated for each of the alloys, one to the thickness 130 mm, the other to 150 mm and the third at 200 mm.
- 7050 the rolling inlet and outlet temperatures were 415 and 435 ° C; for alloy F according to the invention, they were 410 and 425 ° C.
- the 6 sheets dissolved in 480 ° C, quenched by immersion in cold water and drawn with a deformation rate of the order of 2%.
- the sheets were then subjected to a two-bearing type tempering: 6 h at 120 ° C and 17 h at 165 ° C for sheets in aUiage 7050, 6 h at 115 ° C and 10 h at 172 ° C for sheets in auUiage F.
- the sheets in aUiage according to the invention have a total lack of sensitivity to quenching when the thickness increases, which is not the case for sheets in conventional 7050, as was already apparent from FIGS. 1 and 2
- the contents of Mg and Cu are lower, one unexpectedly obtains, for these thicknesses, an equal or greater mechanical resistance. There is also a much better tenacity.
- the cast plates were homogenized around 470 ° C and laminated in 3 passes to the thickness 6 inches (152 mm), 7.5 inches (190 mm) or 8 inches (203 mm) depending on the cases indicated in Table 3.
- the rolling exit temperatures are also shown in Table 3.
- the sheets were dissolved in 480 ° C, quenched by immersion in cold water and subjected to controlled traction with a deformation rate of 2%.
- the sheets were then subjected to a two-bearing type tempering: 6 hours at 15 ° C and 10 hours at 172 ° C for sheets in alloy G (according to the invention), 6 hours at 120 ° C and 17 hours at 165 ° C for sheets in aUiage 7050 (prior art).
- the elasticity limit R0.2 at quarter thickness in the directions L and TL and the toughness K, c were measured in the directions LT (at quarter thickness), TL (at quarter thick) and SL (mid-thickness) according to ASTM E399.
- the recrystallization rate of each of the sheets at quarter thickness and half thickness was also measured. This measurement was made on samples treated T351, then treated for 6 h at 160 ° C., then in and attacked with a solution containing 84 parts of chromic solution, 15 parts of nitric solution and 1 part of hydrofluoric solution, at room temperature for about '/ _ h.
- the recrystallization rate was measured by image analysis on micrographs of these samples, the recrystallized grains appearing in light on the non-recrystallized matrix in dark. All the results are reported in Table 3.
- the sheets according to the invention have an elastic limit of the same order or greater than that of 7050 with a higher level of toughness, in particular in the LT direction. Indeed, the tenacity LT of the sheet in aUiage 7050 does not reach 31.4 MPaVm for the thickness 152 mm, nor 28.1 MPaVm for the thickness 190 mm, that is to say the values corresponding to 74 - 0.08e - 0.07
- Alloy A is a conventional 7050
- alloy B an optimized 7050 with low Mg content.
- the alloys C, D and E have compositions according to the invention.
- the cast plates were homogenized around 470 ° C and hot rolled to thicknesses of 8 inches (203 mm) or 8.5 inches (215 mm).
- the sheets were dissolved in 480 ° C, quenched by immersion in cold water and subjected to controlled traction with a deformation rate of 2%.
- recrystallization is critical in order to obtain a compromise between toughness and acceptable elastic limit. More particularly, the value of the recrystallization rate should not exceed approximately 35% between quarter thickness and half thickness to ensure that the value of KI C (LT) measured at quarter thickness is always greater than the reference value 74 - 0.08e - 0.07
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Heat Treatment Of Steel (AREA)
- Heat Treatment Of Articles (AREA)
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP97901668A EP0876514B1 (fr) | 1996-01-25 | 1997-01-24 | PRODUITS EPAIS EN ALLIAGE A1ZnMgCu A PROPRIETES AMELIOREES |
CA002244148A CA2244148C (fr) | 1996-01-25 | 1997-01-24 | Produits epais en alliage alznmgcu a proprietes ameliorees |
DE0876514T DE876514T1 (de) | 1996-01-25 | 1997-01-24 | Dicke werkstuecke aus al-zn-mg-cu legierung mit verbesserten eigenschaften |
DE69700330T DE69700330T2 (de) | 1996-01-25 | 1997-01-24 | Dicke werkstuecke aus al-zn-mg-cu legierung mit verbesserten eigenschaften |
JP52661497A JP4235260B2 (ja) | 1996-01-25 | 1997-01-24 | 特性が向上したA1ZnMgCu合金製の厚い製品 |
US08/897,832 US6027582A (en) | 1996-01-25 | 1997-07-21 | Thick alZnMgCu alloy products with improved properties |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9601103A FR2744136B1 (fr) | 1996-01-25 | 1996-01-25 | Produits epais en alliage alznmgcu a proprietes ameliorees |
FR96/01103 | 1996-01-25 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO1997027343A1 true WO1997027343A1 (fr) | 1997-07-31 |
Family
ID=9488644
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR1997/000144 WO1997027343A1 (fr) | 1996-01-25 | 1997-01-24 | PRODUITS EPAIS EN ALLIAGE A1ZnMgCu A PROPRIETES AMELIOREES |
Country Status (6)
Country | Link |
---|---|
EP (1) | EP0876514B1 (fr) |
JP (1) | JP4235260B2 (fr) |
CA (1) | CA2244148C (fr) |
DE (2) | DE876514T1 (fr) |
FR (1) | FR2744136B1 (fr) |
WO (1) | WO1997027343A1 (fr) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6726878B1 (en) | 1999-10-05 | 2004-04-27 | Federalnoe Gosudarstvennoe Unitarnoe Predpriyatie “Vserossiisky Nauchno-Issle-Dovatelsky Institut Aviatsionnykh Materialov” | High strength aluminum based alloy and the article made thereof |
EP1544316A2 (fr) * | 2003-12-16 | 2005-06-22 | Pechiney Rhenalu | Tôle épaisse en alliage Al-Zn-Cu-Mg recristallisée à faible teneur en Zr |
US7776167B2 (en) | 2002-12-06 | 2010-08-17 | Alcan Rhenalu, Inc. | Edge-on stress-relief of aluminum plates |
RU2484169C2 (ru) * | 2006-09-04 | 2013-06-10 | Алюминиум Ленд Гезельшафт М.Б.Х. | Алюминиевый сплав и способ его получения |
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 |
Families Citing this family (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
IL156386A0 (en) | 2000-12-21 | 2004-01-04 | Alcoa Inc | Aluminum alloy products and artificial aging method |
DE10163039C1 (de) * | 2001-12-21 | 2003-07-24 | Daimler Chrysler Ag | Warm- und kaltumformbares Bauteil aus einer Aluminiumlegierung und Verfahren zu seiner Herstellung |
FR2838136B1 (fr) * | 2002-04-05 | 2005-01-28 | Pechiney Rhenalu | PRODUITS EN ALLIAGE A1-Zn-Mg-Cu A COMPROMIS CARACTERISTIQUES STATISTIQUES/TOLERANCE AUX DOMMAGES AMELIORE |
FR2848480B1 (fr) | 2002-12-17 | 2005-01-21 | Pechiney Rhenalu | Procede de fabrication d'elements structuraux par usinage de toles epaisses |
WO2004056501A2 (fr) * | 2002-12-17 | 2004-07-08 | Pechiney Rhenalu | Procede de fabrication d'elements de structure par usinage de toles epaisses |
DE112004003147B4 (de) | 2003-04-10 | 2022-11-17 | Novelis Koblenz Gmbh | Al-Zn-Mg-Cu-Legierung |
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 |
US7883591B2 (en) | 2004-10-05 | 2011-02-08 | Aleris Aluminum Koblenz Gmbh | High-strength, high toughness Al-Zn alloy product and method for producing such product |
US8277580B2 (en) * | 2005-02-10 | 2012-10-02 | Constellium France | Al-Zn-Cu-Mg aluminum base alloys and methods of manufacture and use |
KR20090026337A (ko) * | 2006-06-30 | 2009-03-12 | 알칸 롤드 프로덕츠-레이븐스우드, 엘엘씨. | 고강도의 열처리 가능 알루미늄 합금 |
WO2008003504A2 (fr) | 2006-07-07 | 2008-01-10 | Aleris Aluminum Koblenz Gmbh | Produits en alliage d'aluminium série aa7000, et procédé de fabrication correspondant |
US8608876B2 (en) | 2006-07-07 | 2013-12-17 | Aleris Aluminum Koblenz Gmbh | AA7000-series aluminum alloy products and a method of manufacturing thereof |
FR3068370B1 (fr) * | 2017-07-03 | 2019-08-02 | Constellium Issoire | Alliages al- zn-cu-mg et procede de fabrication |
FR3071513B1 (fr) * | 2017-09-26 | 2022-02-11 | Constellium Issoire | Alliages al-zn-cu-mg a haute resistance et procede de fabrication |
CN114144536A (zh) * | 2019-06-03 | 2022-03-04 | 诺维尔里斯公司 | 超高强度铝合金产品及其制造方法 |
CN111172436B (zh) * | 2020-01-07 | 2021-04-30 | 西南交通大学 | 一种强度超过800MPa的超高强铝合金等温模锻件及其制备方法 |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3881966A (en) * | 1971-03-04 | 1975-05-06 | Aluminum Co Of America | Method for making aluminum alloy product |
WO1980000711A1 (fr) * | 1978-09-29 | 1980-04-17 | Boeing Co | Alliage d'aluminium |
EP0377779A1 (fr) * | 1989-01-13 | 1990-07-18 | Aluminum Company Of America | Produit en alliage d'aluminium ayant des combinaisons de résistance mécanique, de ténacité et de résistance à la corrosion modifiées |
US5277719A (en) * | 1991-04-18 | 1994-01-11 | Aluminum Company Of America | Aluminum alloy thick plate product and method |
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 |
-
1996
- 1996-01-25 FR FR9601103A patent/FR2744136B1/fr not_active Expired - Lifetime
-
1997
- 1997-01-24 WO PCT/FR1997/000144 patent/WO1997027343A1/fr not_active Application Discontinuation
- 1997-01-24 DE DE0876514T patent/DE876514T1/de active Pending
- 1997-01-24 DE DE69700330T patent/DE69700330T2/de not_active Revoked
- 1997-01-24 JP JP52661497A patent/JP4235260B2/ja not_active Expired - Lifetime
- 1997-01-24 CA CA002244148A patent/CA2244148C/fr not_active Expired - Lifetime
- 1997-01-24 EP EP97901668A patent/EP0876514B1/fr not_active Revoked
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3881966A (en) * | 1971-03-04 | 1975-05-06 | Aluminum Co Of America | Method for making aluminum alloy product |
WO1980000711A1 (fr) * | 1978-09-29 | 1980-04-17 | Boeing Co | Alliage d'aluminium |
EP0377779A1 (fr) * | 1989-01-13 | 1990-07-18 | Aluminum Company Of America | Produit en alliage d'aluminium ayant des combinaisons de résistance mécanique, de ténacité et de résistance à la corrosion modifiées |
US5277719A (en) * | 1991-04-18 | 1994-01-11 | Aluminum Company Of America | Aluminum alloy thick plate product and method |
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 |
Non-Patent Citations (2)
Title |
---|
J.A.WAGNER ET AL: "THE EFFECT OF COPPER, CHROMIUM, AND ZIRCONIUM ON THE MECHANICAL PROPERTIES OF AL-ZN-MG-CU ALLOYS", METALLURGICAL TRANSACTIONS A PHYSICAL METALLURGY AND MATERIALS SCIENCE., vol. 22, no. 11, November 1991 (1991-11-01), NEW YORK US, pages 2809 - 2817, XP000270489 * |
S.R. LAMPMAN ET AL: "METALS HANDBOOK, VOL.2", 1990, ASM INTERNATIONAL, METALS PARK, OHIO, US, XP002015076 * |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6726878B1 (en) | 1999-10-05 | 2004-04-27 | Federalnoe Gosudarstvennoe Unitarnoe Predpriyatie “Vserossiisky Nauchno-Issle-Dovatelsky Institut Aviatsionnykh Materialov” | High strength aluminum based alloy and the article made thereof |
US7776167B2 (en) | 2002-12-06 | 2010-08-17 | Alcan Rhenalu, Inc. | Edge-on stress-relief of aluminum plates |
EP1544316A2 (fr) * | 2003-12-16 | 2005-06-22 | Pechiney Rhenalu | Tôle épaisse en alliage Al-Zn-Cu-Mg recristallisée à faible teneur en Zr |
EP1544316A3 (fr) * | 2003-12-16 | 2007-05-09 | Pechiney Rhenalu | Tôle épaisse en alliage Al-Zn-Cu-Mg recristallisée à faible teneur en Zr |
US7520945B2 (en) | 2003-12-16 | 2009-04-21 | Alcan Rhenalu | Recrystallized Al-Zn-Cu-Mg plate with low zirconium |
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 |
RU2484169C2 (ru) * | 2006-09-04 | 2013-06-10 | Алюминиум Ленд Гезельшафт М.Б.Х. | Алюминиевый сплав и способ его получения |
Also Published As
Publication number | Publication date |
---|---|
CA2244148A1 (fr) | 1997-07-31 |
FR2744136B1 (fr) | 1998-03-06 |
FR2744136A1 (fr) | 1997-08-01 |
DE876514T1 (de) | 1999-05-06 |
EP0876514A1 (fr) | 1998-11-11 |
EP0876514B1 (fr) | 1999-07-14 |
JP4235260B2 (ja) | 2009-03-11 |
DE69700330T2 (de) | 2000-01-13 |
DE69700330D1 (de) | 1999-08-19 |
CA2244148C (fr) | 2005-01-04 |
JP2000504068A (ja) | 2000-04-04 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP0876514B1 (fr) | PRODUITS EPAIS EN ALLIAGE A1ZnMgCu A PROPRIETES AMELIOREES | |
EP1838891B1 (fr) | TOLES FORTES EN ALLIAGE Al-Zn-Cu-Mg A FAIBLES CONTRAINTES INTERNES | |
US6027582A (en) | Thick alZnMgCu alloy products with improved properties | |
EP1809779B1 (fr) | Produits en alliage d ' aluminium a haute tenacite et procede d ' elaboration | |
FR2907466A1 (fr) | Produits en alliage d'aluminium de la serie aa7000 et leur procede de fabrication | |
FR2907796A1 (fr) | Produits en alliage d'aluminium de la serie aa7000 et leur procede de fabrication | |
CA2907854C (fr) | Toles minces en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselages d'avion | |
EP1231290A1 (fr) | Procédé de fabrication d'un produit corroyé à haute résistance en alliage AIZnMgCu | |
EP1114877A1 (fr) | Element de structure d'avion en alliage Al-Cu-Mg | |
EP3384061B1 (fr) | Alliage aluminium cuivre lithium à resistance mécanique et tenacité ameliorées | |
EP3201372A1 (fr) | Tôles isotropes en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselages d'avion | |
EP3526358A1 (fr) | Toles minces en alliage aluminium-magnesium-scandium pour applications aerospatiales | |
FR3004196A1 (fr) | Toles en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselages d'avion. | |
EP4038214A1 (fr) | Toles de precision en alliage d'aluminium | |
EP3728667A1 (fr) | Procede de fabrication ameliore de toles en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselage d'avion | |
EP0731185B1 (fr) | Tôles en alliage Al-Cu-Mg à faible niveau de contraintes résiduelles | |
WO2021111069A1 (fr) | Tôles minces en alliage d'aluminium-cuivre-lithium à tenacite ameliorée et procédé de fabrication d'une tôle mince en alliage d'aluminium-cuivre-lithium | |
WO2022129806A1 (fr) | Produits corroyes en alliage 2xxx presentant une resistance a la corrosion optimisee et procede d'obtention | |
WO2024018147A1 (fr) | Procédé de fabrication d'une tôle en alliage d'aluminium 7xxx et tôle en alliage d'aluminium 7xxx | |
WO2023233090A1 (fr) | Toles pour elements de chambres a vide en alliage d'aluminium | |
FR3082210A1 (fr) | Toles minces en alliage d’aluminium-cuivre-lithium pour la fabrication de fuselages d’avion |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AK | Designated states |
Kind code of ref document: A1 Designated state(s): CA JP US |
|
AL | Designated countries for regional patents |
Kind code of ref document: A1 Designated state(s): AT BE CH DE DK ES FI FR GB GR IE IT LU MC NL PT SE |
|
ENP | Entry into the national phase |
Ref country code: US Ref document number: 1997 836473 Date of ref document: 19970825 Kind code of ref document: A Format of ref document f/p: F |
|
DFPE | Request for preliminary examination filed prior to expiration of 19th month from priority date (pct application filed before 20040101) | ||
121 | Ep: the epo has been informed by wipo that ep was designated in this application | ||
WWE | Wipo information: entry into national phase |
Ref document number: 1997901668 Country of ref document: EP |
|
ENP | Entry into the national phase |
Ref document number: 2244148 Country of ref document: CA Ref country code: CA Ref document number: 2244148 Kind code of ref document: A Format of ref document f/p: F |
|
WWP | Wipo information: published in national office |
Ref document number: 1997901668 Country of ref document: EP |
|
WWG | Wipo information: grant in national office |
Ref document number: 1997901668 Country of ref document: EP |
|
WWW | Wipo information: withdrawn in national office |
Ref document number: 1997901668 Country of ref document: EP |