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EP4386097A1 - Produits ecrouis en alliage 7xxx avec un compromis amélioré de propriétés de traction et de ténacité et procédé de production - Google Patents

Produits ecrouis en alliage 7xxx avec un compromis amélioré de propriétés de traction et de ténacité et procédé de production Download PDF

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Publication number
EP4386097A1
EP4386097A1 EP22213912.3A EP22213912A EP4386097A1 EP 4386097 A1 EP4386097 A1 EP 4386097A1 EP 22213912 A EP22213912 A EP 22213912A EP 4386097 A1 EP4386097 A1 EP 4386097A1
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Prior art keywords
product
mpa
hours
wrought
rolled
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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.)
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EP22213912.3A
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German (de)
English (en)
Inventor
Ricky WHELCHEL
Michael M NIEDZINSKI
Kenneth Paul Smith
Timothy Warner
Jean-Christophe Ehrstrom
Armelle Danielou
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Constellium Rolled Products Ravenswood LLC
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Constellium Rolled Products Ravenswood LLC
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Application filed by Constellium Rolled Products Ravenswood LLC filed Critical Constellium Rolled Products Ravenswood LLC
Priority to CN202380083484.8A priority Critical patent/CN120303424A/zh
Priority to EP23821299.7A priority patent/EP4634424A1/fr
Priority to KR1020257022811A priority patent/KR20250126021A/ko
Priority to PCT/EP2023/085062 priority patent/WO2024126341A1/fr
Publication of EP4386097A1 publication Critical patent/EP4386097A1/fr
Withdrawn legal-status Critical Current

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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C22C21/18—Alloys based on aluminium with copper as the next major constituent with zinc
    • 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 disclosure relates to a method for manufacturing 7xxx aluminum wrought product with improved compromise of tensile and toughness properties and excellent cryogenic properties and fatigue resistance in corrosive environment and more particularly to such manufacturing processes and rolled products and use, notably designed for aeronautical and aerospace engineering.
  • High strength 7xxx aluminum alloy products also designated as Al-Zn-Mg-Cu type alloy products, are extensively used in aerospace structure application, in which the material strength, fracture toughness, fatigue resistance, and corrosion resistance are required simultaneously. It is known that these various required properties cannot all be optimized at the same time and independently of each other during the fabrication of semi-finished products and structural elements for aeronautical construction.
  • chemical composition of the alloy or the parameters of product manufacturing processes are modified, several critical properties may tend to change in opposing directions. This is sometimes the case firstly for properties generally referred to as "static mechanical strength” (particularly the ultimate tensile stress UTS and the tensile yield stress TYS), and secondly for properties generally names as "damage tolerance" (particularly the toughness and the resistance to crack propagation).
  • Al-Zn-Mg-Cu alloys with high fracture toughness and high mechanical strength are described in the prior art.
  • US Patent 5,312,498 discloses a method of producing an aluminum-based alloy product having improved exfoliation resistance and fracture toughness which comprises providing an aluminum-based alloy composition consisting essentially of about 5.5-10.0% by weight of zinc, about 1.75-2.6% by weight of magnesium, about 1.8-2.75%) by weight of copper with the balance aluminum and other elements.
  • the aluminum-based alloy is worked, heat treated, quenched and aged to produce a product having improved corrosion resistance and mechanical properties.
  • US Patent 5,560,789 describes AA 7000 series alloys having high mechanical strength and a process for obtaining them.
  • the alloys contain, by weight, 7 to 13.5% Zn, 1 to 3.8% Mg, 0.6 to 2.7% Cu, 0 to 0.5% Mn, 0 to 0.4% Cr, 0 to 0.2% Zr, others up to 0.05% each and 0.15% total, and remainder Al.
  • US Patent No 5,865,911 describes an aluminum alloy consisting essentially of (in weight %) about 5.9 to 6.7% zinc, 1.8 to 2.4% copper, 1.6 to 1.86% magnesium, 0.08 to 0.15% zirconium balance aluminum and incidental elements and impurities.
  • the '911 patent particularly mentions the compromise between static mechanical strength and toughness.
  • US Patent No 6,027,582 describes a rolled, forged or extruded Al-Zn-Mg-Cu aluminum base alloy products greater than 60 mm thick with a composition of (in weight %), Zn: 5.7-8.7, Mg: 1.7-2.5, Cu: 1.2-2.2, Fe: 0.07-0.14, Zr: 0.05-0.15 with Cu + Mg ⁇ 4.1 and Mg>Cu.
  • US Patent No 6,972,110 teaches an alloy, which contains preferably (in weight %) Zn: 7-9.5, Mg: 1.3-1.68 and Cu 1.3-1.9 and encourages keeping Mg +Cu ⁇ 3.5.
  • PCT Patent Application No WO2004090183 discloses an alloy comprising essentially (in weight percent): Zn: 6.0 - 9.5, Cu: 1.3 - 2.4, Mg: 1.5 - 2.6, Mn and Zr ⁇ 0.25 but preferably in a range between 0.05 and 0.15 for higher Zn contents, other elements each less than 0.05 and less than 0.25 in total, balance aluminum, wherein (in weight percent): 0.1 [Cu] + 1.3 ⁇ [Mg] ⁇ 0.2[Cu] + 2.15, preferably 0.2[Cu] + 1.3 ⁇ [Mg] ⁇ 0.1[Cu] + 2.15.
  • US 20050006010 discloses a method for producing a high strength AI-Zn- Cu-Mg alloy with an improved fatigue crack growth resistance and a high damage tolerance, comprising the steps of casting an ingot with the following composition (in weight percent) Zn 5.5-9.5, Cu 1.5-3.5, Mg 1.5-3.5, Mn ⁇ 0.25, Zr ⁇ 0.25, Cr ⁇ 0.10, Fe ⁇ 0.25, Si ⁇ 0.25, Ti ⁇ 0.10, Hf and/or V ⁇ 0.25, other elements each less than 0.05 and less than 0.15 in total, balance aluminum, homogenizing and/or pre-heating the ingot after casting, hot working the ingot and optionally cold working into a worked product of more than 50 mm thickness, solution heat treating, quenching the heat treated product, and artificially aging the worked and heat-treated product, wherein the aging step comprises a first heat treatment at a temperature in a range of 105 ° C. to 135 ° C. for more than 2 hours and less than 8 hours and a second heat treatment at a higher temperature than 135
  • EP 1544315 discloses a product, especially rolled, extruded or forged, made of an AlZnCuMg alloy with constituents having the following percentage weights: Zn 6.7 - 7.3; Cu 1.9 - 2.5; Mg 1.0 - 2.0; Zr 0.07 - 0.13; Fe less than 0.15; Si less than 0.15; other elements not more than 0.05 to at most 0.15 per cent in total; and aluminum the remainder, wherein Mg/Cu ⁇ 1.
  • the product is preferably treated by solution heat treatment, quenching, cold working and artificial aging.
  • US Patent No 8,277,580 teaches a rolled or forged Al-Zn-Cu-Mg aluminum-based alloy wrought product having a thickness from 2 to 10 inches.
  • the product has been treated by solution heat-treatment, quenching and aging, and the product comprises (in weight- %): Zn 6.2-7.2, Mg 1.5-2.4, Cu 1.7-2.1.
  • Fe 0-0.13, Si 0-0.10, Ti 0-0.06, Zr 0.06-0.13, Cr 0-0.04, Mn 0-0.04, impurities and other incidental elements ⁇ 0.05 each.
  • US Patent No 8,673,209 discloses aluminum alloy products about 4 inches thick or less that possesses the ability to achieve, when solution heat treated, quenched, and artificially aged, and in parts made from the products, an improved combination of strength, fracture toughness and corrosion resistance, the alloy consisting essentially of: about 6.8 to about 8.5 wt. % Zn, about 1.5 to about 2.00 wt. % Mg, about 1.75 to about 2.3 wt. % Cu; about 0.05 to about 0.3 wt. % Zr, less than about 0.1 wt. % Mn, less than about 0.05 wt. % Cr, the balance Al, incidental elements and impurities and a method for making same.
  • WO2019/007817 concerns an extruded, rolled and/or forged aluminum-based alloy product having a thickness of at least 25 mm comprising (in weight %): Zn 6.70 -7.40; Mg 1.50 -1.80; Cu 2.20 -2.60, with a Cu to Mg ratio of at least 1.30; Zr 0.04 -0.14; Mn 0 -0.5; Ti 0 -0.15; V 0 -0.15; Cr 0 -0.25; Fe 0 -0.15; Si 0 -0.15; impurities ⁇ 0.05 each and ⁇ 0.15 total.
  • the present invention relates to a method for manufacturing a high strength 7xxx aluminum wrought products by controlling the composition, in particular the quantity of Fe and Si and the fabrication parameters, in particular artificial aging conditions, to provide improved compromise between tensile yield strength and toughness with improved cryogenic fracture toughness, and fatigue resistance in corrosive environment.
  • the invention also concerns a rolled 7xxx product which can be obtained by the method of the invention.
  • cryogenic temperature is defined in accordance with the present invention to include temperatures significantly below room temperature and typically below - 100°C (173 K). Thus, the temperatures at which hydrogen (-253°C/20 K), oxygen (-183°C/90 K) and nitrogen (-196°C/77 K) become liquid at atmospheric pressure are included as cryogenic temperatures. For purposes of experimental evaluation, a temperature of -196°C/77K is considered as a cryogenic temperature.
  • Room temperature is defined in accordance with its common usage and includes temperatures from about 20°C to about 25°C. For purposes of experimental evaluation, a temperature of 22°C is considered to be room temperature.
  • the present invention is directed to a process for the manufacture of a wrought 7xxx aluminum-based alloy product comprising the steps of:
  • the process is advantageously made with a bath of molten alloy comprising Si ⁇ 0.03 wt. % and Fe ⁇ 0.05 wt. %.
  • the sum Fe+Si content is ⁇ 0.07 wt. %, even more preferably ⁇ 0.06 wt. %.
  • the sum Fe+Si content is ⁇ 0.03 wt. %, even more preferably ⁇ 0.04 wt. %.
  • the present invention is directed to a rolled product with a thickness t in millimeter of at least 25 mm, preferentially from 25 mm to 200 mm, comprising (in weight-%)
  • the rolled product according to the invention displays a surprising small drop in both fracture toughness and elongation from room temperature down to liquid nitrogen temperature.
  • the rolled product according to the invention displays a toughness K1c(T-L) in MPa. ⁇ m, at cryogenic temperature, i.e at temperature below 100°C, typically at -196°C, measured according to ASTM standard E399 2020 which is reduced by less than 10 %, preferably by less than 8%, more preferably by less than 7 % in comparison with K1c(T-L) in MPa. ⁇ m, measured at room temperature according to ASTM standard E399 -2020.
  • the rolled product according to the invention displays a toughness K1c(T-L) in MPa. ⁇ m, at cryogenic temperature, i.e at temperature below 100°C, typically at - 196°C, measured according to ASTM standard E399 -2020 higher than -15 ⁇ t +45 MPa.Vm , preferably higher than - 0.15*t+49 MPa.Vm, even more preferably higher than - 0.15*t+55 MPa, where t is the thickness of the rolled product in mm.
  • the rolled product comprises Si ⁇ 0.03 wt. % and Fe ⁇ 0.05 wt. %.
  • the rolled product has a thickness from 70 mm to 160 mm, preferably from 70 mm to 102 mm.
  • the rolled product comprises a sum of Fe+Si content which is ⁇ 0.07 wt. %, even more preferably ⁇ 0.06 wt. %.
  • the product according to the invention is used in structural member used at cryogenic temperature, in particular for cryogenic tanks.
  • Said stress relieved wrought product is then artificially aged with a total equivalent aging time t(eq) at 155°C from 24 hours to 45 hours, preferably from 24 hours to 34 hours, even more preferably from 26 hours to 30 hours
  • Aging treatment is advantageously carried out in two steps, with a first step at a temperature comprised from 110 to 130 °C for 3 to 20 hours, preferably for 3 to 10 hours and a second step at a temperature comprised from 140 to 170 °C for 6 to 90 hours and preferably between 150 and 165 °C for 9 to 50 hours.
  • the product of the invention with his specific composition in particular with a Fe and Si content ⁇ 0.08 wt. %, when combined with an appropriately designed artificial aging treatment, makes it possible to obtain a product with a better compromise between tensile yield strength and toughness, in particular a better compromise between tensile yield strength in the rolling direction (L direction) and toughness in L-T direction.
  • the present alloy according to the invention contains from 6.65 to 7.45 wt. % Zn.
  • a minimum value of Zn content of 6.65 wt. %, preferably 6.90 wt. %, more preferably 7.10 wt. % is needed to obtain sufficient strength; however, Zn should not exceed 7.45 wt. %, preferably 7.30 wt. %, more preferably 7.25 wt. % to obtain the sought balance of properties, in particular toughness and elongation.
  • the present alloy according to the invention contains from 1.35 to 1.75 wt. % Mg.
  • a minimum Mg content of 1.35 wt. % and preferably 1.40 wt. % or 1.50 wt. % or even 1.60 wt. % is needed to obtain sufficient strength.
  • the Mg content should not exceed 1.75 wt. % and preferably 1.70 wt. % to obtain the sought balance of properties in particular toughness and elongation.
  • the alloy of the present invention further contains from 0.04 to 0.14 wt.% Zr, which is typically used for grain size control.
  • the Zr content should preferably comprise at least about 0.07 wt. %, and preferentially about 0.09 wt.% in order to limit the recrystallization, but should advantageously remain below about 0.12 wt.% in order to reduce problems during casting.
  • Manganese up to 0.5 wt.% may be added but it is preferentially avoided and is generally kept below about 0.05 wt.%, preferentially below about 0.04 wt.%. and more preferentially below about 0.03 wt.%.
  • the present alloy may contain iron and silicon which affect fracture toughness properties. It was observed that iron and silicon content (e.g. Fe + Si content) must not exceed about 0.08 wt. %, preferably about 0.07 wt. %, more preferably 0.06 wt. % and even more preferably 0.05 wt. % to achieve a better compromise between tensile yield strength and toughness, small drop (less than 10%) in fracture toughness at cryogenic temperature, and very little increase in fatigue crack growth rate under high humidity conditions when compared to fatigue under ambient lab conditions. The inventors found that for the selected composition and Fe+ Si content below 0.08 wt.
  • iron and silicon content e.g. Fe + Si content
  • iron and silicon content is from 0.03% to 0.08 wt. %, preferably from 0.03% to 0.07 wt. %, more preferably from 0.03% to 0.06 wt. % and even more preferably from 0.03% to 0.05 wt. %.
  • the present alloy may contain an iron and silicon content (e.g. Fe + Si content) from 0.04% to 0.08 wt. %, preferably from 0.04% to 0.07 wt. %, more preferably from 0.04% to 0.06 wt. % and even more preferably 0.04% to 0.05 wt. %.
  • the present alloy may include up to 0.05 wt. % Si, preferentially up to 0.03 wt. %.
  • the present alloy may include up to 0.05 wt. % Fe, preferentially up to 0.03 wt. %.
  • the present alloy may include incidental impurities.
  • incidental impurities can include relatively small amounts, less than 0.05 wt. %, or less than 0.01 wt. % of other elements with a total of less than 0.15 wt% total of the total weight of the 7xxx aluminum alloy product. Incidental impurities can be present without departing from the scope of the invention.
  • the rolled product with a thickness of at least 25 mm, preferentially from 25 mm to 200 mm more preferably from 70 mm to 200 mm, or from 70 to 160 mm, even more preferably from 70 mm to 102 mm according to the invention has advantageously the following properties: A K 1C toughness in the L-T direction at room temperature measured according to ASTM E399-2020 of at least -0.25 *t +65 MPa.Vm, more preferably of at least -0.25 *t +68 MPaVm, and even more preferably of at least -0.25 ⁇ t +72 MPaVm, t being the thickness of the rolled product in mm.
  • the rolled product has advantageously a yield strength of at least 450 MPa in the rolling direction L.
  • a yield strength in the transverse direction LT of at least 410 MPa, even more preferably of at least 420 MPa.
  • the rolled product according to the present invention or the product obtained by the process according to the invention is advantageously used as or incorporated in structural members for the construction of aircraft or spacecraft.
  • the products according to the invention are used in wing ribs, spars and frames.
  • the rolled products according to the present invention are welded with other rolled products to form wing ribs, spars and frames.
  • the rolled product according to the invention the product obtained by the process according to the invention is advantageously used in structural member used at cryogenic temperature, typically cryogenic tank.
  • Tensile and K IC testing was performed both at room temperature (22°C) and at cryogenic temperature, precisely at liquid nitrogen temperature (-196°C). Tensile tests were performed according to ASTM B557. Samples were taken at mid thickness (t/2) and quarter thickness (t/4). Tensile tests were performed in the transverse direction (LT), short transverse direction (ST). [Table 3] Ref. Thickness Test Plane Direct.
  • Figure 1 shows the evolution of toughness K 1c (T-L) at cryogenic temperature versus the thickness of the plate. It can be observed that A1 and B1 specimen display a toughness K1c(T-L) in MPa. ⁇ m, at cryogenic temperature higher than -15*t +45 MPa.Vm , preferably higher than - 0.15*t+49 MPa.Vm, even more preferably higher than - 0.15*t+55 MPa, where t is the thickness of the product in mm.
  • Alloy F composition is according to the invention but sample F1 is processed with a shorter artificial aging which does not permit to obtain the excellent compromise TYS (L) - K 1c (L-T).
  • Table 8 Prior art Reference Prior art Prior art Prior art Prior art Prior art Reference C1 D1 E1 F1 Alloy (Table 7) C D E F Homogenization 15h 479°C 16h 471C-482°C 479°C 479°C Hot rolling Entry hot Rolling temperature 420 °C - 440 °C 416 °C - 438 °C 400°C - 440°C
  • Figure 2 shows the compromise at Room temperature (RT) between tensile yield strength in the rolling direction (L) and toughness in L-T direction, measured respectively at quarter thickness and mid thickness for A1 and C1 plate.
  • RT Room temperature
  • L tensile yield strength in the rolling direction
  • L-T direction toughness in L-T direction
  • Figure 3 shows the compromise between tensile yield strength in the transverse direction (LT) and the toughness in T-L, measured at room temperature and at liquid nitrogen temperature of -196°C. It can be observed that A1 plates exhibits a lower drop in toughness than D1 plate. It is attributed to the chemical composition, in particular the lower Fe + Si content.
  • compositions A, C, G, H, J, K, M were cast and transformed; respective details of composition and process are listed in Tables 14 and 15. All these cast were transformed into plates with thicknesses from 70 to 102 mm.
  • Alloys C, G, H correspond to prior art alloys and J, K and M are compositions according to the invention.
  • Alloy A is similar from example 1.
  • samples having a composition according to the invention and processed according to the invention are represented with a black diamond (A1-a, J1-A, K2-a).
  • Samples having a composition according to the invention but processed differently are represented by an empty diamond (M2-b).
  • a triangle symbol is used to represent compositions which differ from the invention by Fe+Si content above 0.08 wt. % (C1-a and C1-b).
  • a round circle symbol is used to represent compositions which differ from the invention by main alloying elements (G2-a, H2-a).
  • Triangle or round circle symbols are empty if the process differs from the invention, i.e. equivalent time at 155°C below 23 h or with full symbol if the process is according to the invention.

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  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
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  • Metallurgy (AREA)
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EP22213912.3A 2022-12-12 2022-12-15 Produits ecrouis en alliage 7xxx avec un compromis amélioré de propriétés de traction et de ténacité et procédé de production Withdrawn EP4386097A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
CN202380083484.8A CN120303424A (zh) 2022-12-12 2023-12-11 具有改善的拉伸和韧性性能折衷的7xxx锻造产品及其制备方法
EP23821299.7A EP4634424A1 (fr) 2022-12-12 2023-12-11 Produits corroyés 7xxx présentant un compromis amélioré des propriétés de traction et de ténacité et procédé de production
KR1020257022811A KR20250126021A (ko) 2022-12-12 2023-12-11 인장 및 인성 특성의 균형이 개선된 7xxx 가공 제품 및 제조 방법
PCT/EP2023/085062 WO2024126341A1 (fr) 2022-12-12 2023-12-11 Produits corroyés 7xxx présentant un compromis amélioré des propriétés de traction et de ténacité et procédé de production

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US202263387018P 2022-12-12 2022-12-12

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EP4386097A1 true EP4386097A1 (fr) 2024-06-19

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN119307792A (zh) * 2024-09-29 2025-01-14 唐山瑞泰合金制造有限公司 一种高强度铝制品及其制备方法

Citations (14)

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Publication number Priority date Publication date Assignee Title
US5312498A (en) 1992-08-13 1994-05-17 Reynolds Metals Company Method of producing an aluminum-zinc-magnesium-copper alloy having improved exfoliation resistance and fracture toughness
US5560789A (en) 1994-03-02 1996-10-01 Pechiney Recherche 7000 Alloy having high mechanical strength and a process for obtaining it
US5865911A (en) 1995-05-26 1999-02-02 Aluminum Company Of America Aluminum alloy products suited for commercial jet aircraft wing members
US6027582A (en) 1996-01-25 2000-02-22 Pechiney Rhenalu Thick alZnMgCu alloy products with improved properties
WO2004090183A1 (fr) 2003-04-10 2004-10-21 Corus Aluminium Walzprodukte Gmbh Produit d'alliage al-zn a haute resistance et procede de production de ce produit d'alliage al-zn
US20050006010A1 (en) 2002-06-24 2005-01-13 Rinze Benedictus Method for producing a high strength Al-Zn-Mg-Cu alloy
WO2005047557A1 (fr) * 2003-11-12 2005-05-26 Alcoa Inc. Procede de fabrication d'un produit d'alliage pres de la cote desiree
EP1544315A1 (fr) 2003-12-16 2005-06-22 Pechiney Rhenalu Produit corroyé et élément de structure pour aéronef en alliage Al-Zn-Cu-Mg
US6972110B2 (en) 2000-12-21 2005-12-06 Alcoa Inc. Aluminum alloy products having improved property combinations and method for artificially aging same
US8277580B2 (en) 2005-02-10 2012-10-02 Constellium France Al-Zn-Cu-Mg aluminum base alloys and methods of manufacture and use
CN102796973A (zh) * 2012-08-13 2012-11-28 北京有色金属研究总院 一种改善7xxx系铝合金微观组织和综合性能的多级时效处理方法
US8673209B2 (en) 2007-05-14 2014-03-18 Alcoa Inc. Aluminum alloy products having improved property combinations and method for artificially aging same
CN107236883A (zh) * 2017-06-29 2017-10-10 广西南南铝加工有限公司 一种铝合金板材的制备工艺
WO2019007817A1 (fr) 2017-07-03 2019-01-10 Constellium Issoire Alliages al-zn-cu-mg et leur procédé de fabrication

Patent Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5312498A (en) 1992-08-13 1994-05-17 Reynolds Metals Company Method of producing an aluminum-zinc-magnesium-copper alloy having improved exfoliation resistance and fracture toughness
US5560789A (en) 1994-03-02 1996-10-01 Pechiney Recherche 7000 Alloy having high mechanical strength and a process for obtaining it
US5865911A (en) 1995-05-26 1999-02-02 Aluminum Company Of America Aluminum alloy products suited for commercial jet aircraft wing members
US6027582A (en) 1996-01-25 2000-02-22 Pechiney Rhenalu Thick alZnMgCu alloy products with improved properties
EP2322677A1 (fr) * 2000-12-21 2011-05-18 Alcoa Inc. Alliage d'aluminium du groupe 7xxx (Al-Zn-Mg-Cu)
US6972110B2 (en) 2000-12-21 2005-12-06 Alcoa Inc. Aluminum alloy products having improved property combinations and method for artificially aging same
US20050006010A1 (en) 2002-06-24 2005-01-13 Rinze Benedictus Method for producing a high strength Al-Zn-Mg-Cu alloy
WO2004090183A1 (fr) 2003-04-10 2004-10-21 Corus Aluminium Walzprodukte Gmbh Produit d'alliage al-zn a haute resistance et procede de production de ce produit d'alliage al-zn
WO2005047557A1 (fr) * 2003-11-12 2005-05-26 Alcoa Inc. Procede de fabrication d'un produit d'alliage pres de la cote desiree
EP1544315A1 (fr) 2003-12-16 2005-06-22 Pechiney Rhenalu Produit corroyé et élément de structure pour aéronef en alliage Al-Zn-Cu-Mg
US8277580B2 (en) 2005-02-10 2012-10-02 Constellium France Al-Zn-Cu-Mg aluminum base alloys and methods of manufacture and use
US8673209B2 (en) 2007-05-14 2014-03-18 Alcoa Inc. Aluminum alloy products having improved property combinations and method for artificially aging same
CN102796973A (zh) * 2012-08-13 2012-11-28 北京有色金属研究总院 一种改善7xxx系铝合金微观组织和综合性能的多级时效处理方法
CN107236883A (zh) * 2017-06-29 2017-10-10 广西南南铝加工有限公司 一种铝合金板材的制备工艺
WO2019007817A1 (fr) 2017-07-03 2019-01-10 Constellium Issoire Alliages al-zn-cu-mg et leur procédé de fabrication

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN119307792A (zh) * 2024-09-29 2025-01-14 唐山瑞泰合金制造有限公司 一种高强度铝制品及其制备方法

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