EP0958393B1 - Aluminiumlegierungsprodukt - Google Patents

Aluminiumlegierungsprodukt Download PDF

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Publication number
EP0958393B1
EP0958393B1 EP97906549A EP97906549A EP0958393B1 EP 0958393 B1 EP0958393 B1 EP 0958393B1 EP 97906549 A EP97906549 A EP 97906549A EP 97906549 A EP97906549 A EP 97906549A EP 0958393 B1 EP0958393 B1 EP 0958393B1
Authority
EP
European Patent Office
Prior art keywords
aluminum alloy
alloy
aerospace part
alloy composition
scandium
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.)
Revoked
Application number
EP97906549A
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English (en)
French (fr)
Other versions
EP0958393A1 (de
Inventor
Stephen F. Baumann
Edward L. Colvin
Robert W. Hyland, Jr.
Jocelyn I. Petit
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.)
Howmet Aerospace Inc
Original Assignee
Aluminum Company of America
Priority date (The priority date 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 date listed.)
Filing date
Publication date
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Priority claimed from US08/381,032 external-priority patent/US5624632A/en
Application filed by Aluminum Company of America filed Critical Aluminum Company of America
Publication of EP0958393A1 publication Critical patent/EP0958393A1/de
Application granted granted Critical
Publication of EP0958393B1 publication Critical patent/EP0958393B1/de
Anticipated expiration legal-status Critical
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Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/06—Alloys based on aluminium with magnesium as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/047—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 magnesium as the next major constituent

Definitions

  • This invention relates to an aluminum alloy product, and more particularly to aluminum alloy products developed for aerospace applications.
  • the base metal, 2024-T3 sheet has the necessary strength and damage tolerance for aerospace applications, but suffers from susceptibility to pitting and/or intergranular corrosion attack. To compensate for that problem, the base metal is effectively isolated from the environment by a cladding layer, a paint or coating system or a combination of both.
  • An alcladding process involves combining a thin layer of an aluminum alloy anodic relative to 2024-T3 on both sides of 2024-T3 sheet. These layers act as a barrier and also afford galvanic protection to the 2024-T3 in case the cladding is damaged. In cases where these layers are intentionally removed by machining or chemical milling to save weight, 2024-T3 sheet may be protected with coatings and/or by anodization.
  • the Alclad layer contributes little with respect to strength, adds weight to the sheet and can act to initiate fatigue cracks.
  • Other coating systems may also add weight and, if damaged, fail to protect 2024-T3 base metal. Surfaces that are anodized are brittle and can act to initiate cracks.
  • Another disadvantage of 2024-T3 sheet is its relatively high density (0.101 lb/in 3 ).
  • V.I. Lukin "Effect of Sc, Mn, Zr alloying elements on the weldability of Al-Mg-Sc-Mn-Zr system alloys," SVAR.PROIZVOD., vol. 6, 1996, discloses an alloy composition comprising 6.3 wt % of magnesium with 0-0.08 wt % scandium which increases the welded joint strength.
  • the alloys of this invention have a relatively low density, good corrosion resistance and a good combination of strength and toughness so as to obviate cladding, painting and/or other base metal protection systems.
  • an aluminum alloy product comprising an alloy composition consisting essentially of 3.5-6 wt % magnesium, 0.03-0.2 wt % zirconium, 0.2-1.2 wt % manganese, up to 0.15 wt % silicon, 0.16-0.34 wt % scandium, 0-0.25 wt % copper, and optionally 0.05-0.5 wt % of a dispersoid-forming element selected from erbium, yttrium, gadolinium, holmium and hafnium, the balance being aluminum and unavoidable impurities.
  • the dispersoid-forming element is scandium.
  • This alloy composition is also preferably zinc-free and lithium-free.
  • substantially free means having no significant amount of that component purposely added to the alloy composition, it being understood that trace amounts of incidental elements and/or impurities may find their way into a desired end product.
  • the alloys of the invention are based on the Al-Mg-Sc system and are of sufficient corrosion resistance so as to obviate cladding or other protection systems. Strength in these alloys is primarily generated through strain hardening of a metal matrix which is generally uniform in composition. Combinations of strength and damage tolerance properties sufficient for fuselage skin applications can be obtained by an appropriate selection of composition, deformation processing and subsequent stabilization treatments.
  • Al-Mg-Sc alloy materials of this invention display adequate tensile strength properties and toughness indicators together with excellent resistance to intergranular (or grain boundary) corrosion. These materials, also demonstrate good resistance to exfoliation attack and excellent stress corrosion cracking ("SCC") resistance during alternate immersion in an NaCl solution tested according to ASTM G-47.
  • SCC stress corrosion cracking
  • a principal alloy used in this invention comprises an alloy composition which includes an aluminum alloy product comprising an alloy composition consisting essentially of 3.5-6 wt % magnesium, 0.03-0.2 wt % zirconium, 0.2-1.2 wt % manganese, up to 0.15 wt % silicon, 0.16-0.34 wt % scandium, 0-0.25 wt % copper, and optionally 0.05-0.5 wt % of a dispersoid-forming element selected from erbium, yttrium, gadolinium, holmium and hafnium, the balance being aluminum and unavoidable impurities.
  • the aluminum alloy composition contains about 3.5-6 wt % magnesium; about 0.06-0.12 wt % zirconium; about 0.4-1 wt % manganese, up to 0.08 wt % silicon and about 0.16-0.34 wt % scandium.
  • the aluminum alloy composition consists essentially of about 3.8-5.2 wt % magnesium; about 0.09-0.12 wt % zirconium, about 0.5-0.7 wt % manganese, up to 0.05 wt % silicon and about 0.2-0.3 wt % scandium.
  • Preferred embodiments of this aluminum alloy are also substantially zinc-free and lithium-free.
  • this invention manages to impart significantly higher strengths and greater corrosion resistance to fuselage skin sheet stock through the addition of certain rare earths or rare earth "act-alikes", such as scandium, by causing rare earth-rich precipitates to form. These precipitates have the ability to store and resist loss of strength arising from plastic deformation. Because of the relatively small size and fine distribution of these particles, recovery and recrystallization of the resulting alloy are also inhibited.
  • the invention alloy is more temperature resistant than the same alloy devoid of scandium or scandium-like additives.
  • temperature resistant it is meant that a large portion of the strength and structure imparted by working this alloy is retained in the fuselage skin sheet end product, even after exposure to one or more higher temperatures, typically above about 232°C (450°F.), such as during subsequent rolling operations or the like.
  • a remainder of substantially aluminum may include some incidental, yet intentionally added elements which may affect collateral properties of the invention, or unintentionally added impurities, neither of which should change the essential characteristics of this alloy.
  • magnesium contributes to strain hardening and strength.
  • Zirconium additions are believed to improve the resistance of scandium precipitates to rapid growth. Scandium and zirconium serve yet another purpose.
  • dispersoids When added to aluminum-magnesium alloys of the type described herein, scandium is believed to precipitate to form a dispersion of fine, intermetallic particles (referred to as "dispersoids"), typically of an Al 3 X stoichiometry, with X being either Sc, Zr or both Sc and Zr.
  • Al 3 (Sc, Zr) dispersoids impart some strength benefit as a precipitation-hardening compound, but more importantly, such dispersoids efficiently retard or impede the process of recovery and recrystallization by a phenomenon sometimes called the "Zener Drag" effect. [See generally, C.S.
  • Scandium dispersoids are very small in size, but also large in number. They generally act as “pinning" points for migrating grain boundaries and dislocations which must bypass them for metal to soften. Recrystallization and recovery are the principal metallurgical processes by which such strain hardenable alloys soften. In order to "soften” an alloy having a large population of Al 3 (Sc, Zr) particles, it is necessary to heat the material to higher temperatures than would be required for an alloy not having such particles. Put another way, when strain-hardened and annealed under identical conditions, a sheet product that contains Al 3 (Sc, Zr) dispersoids will have higher strength levels than a comparable alloy to which no scandium was added.
  • this invention exhibits an ability to resist softening during the high temperature thermal exposures usually needed to roll sheet products.
  • the invention alloy will retain some of the strength acquired through rolling.
  • Other scandium-free alloys would tend to retain less strength through rolling, thus yielding a lower strength final product.
  • An added benefit of zirconium is its ability to limit the growth of these Al 3 X particles to assure that such dispersoids remain small, closely spaced and capable of producing a Zener Drag effect.
  • the alloy of this invention may contain up to 0.15 wt % silicon with up to 0.08 wt % being preferred and 0.05 wt % or less being most preferred.
  • the alloy products described herein may accommodate up to about 0.25 wt % copper or preferably about 0.15 wt % Cu or less.
  • the aluminum alloy product of this invention is especially suited for applications where damage tolerance is required.
  • damage tolerant aluminum products are used for aerospace applications, particularly fuselage skin, and the lower wing sections, stringers or pressure bulkheads of many airplanes.
  • This example refers to the following main additions to an aluminum based alloy of the present invention: Mg Mn Sc Zr Alloy A 4.0 --- 0.23 0.10 Alloy B 4.1 0.62 0.23 0.09 with the balance of each alloy being aluminum, incidental elements and impurities.
  • All of the aforementioned alloys were direct chill (or "DC") cast as 2-1/2 x 12 inch ingots and the rolling surfaces scalped therefrom. Alloy A was not homogenized. Alloy B was homogenized for 5 hours at 287°C (550°F)followed by 5 hours at 427°C (800°F). The scalped ingots were heated to 287°C (550°F) for 30 minutes and cross rolled approximately 50% to a nominal thickness of 1 inch. Alloys A and B were then reheated to 287°C (550°F) and rolled to a final nominal thickness of 0.1 inch. Mechanical properties for each alloy were then evaluated after a stabilization treatment of 5 hours at 287°C (550°F).
  • Table I reports the physical, mechanical property and corrosion data available for the foregoing samples of Alloys A and B, then compares them with typical values for 2024-T3 aluminum, 6013-T6 aluminum and another potential fuselage skin material known commercially as Alcoa's C-188 product as manufactured in accordance with U.S. Patent No. 5,213,639.
  • the materials of this invention display adequate tensile strength properties.
  • the toughness indicators of Alloy A and B, per center notch toughness and fatigue crack growth (or "FCG") data also strongly indicate that these materials will exhibit good inherent toughnesses as well.
  • the resistance to grain boundary corrosion attack of the present invention is also noteworthy.
  • a standard test for measuring such attacks in Al-Mg base alloys is the ASSET (or ASTM G-66) test after a "sensitization" treatment at 100°C (212°F).
  • the subject materials demonstrated good resistance to exfoliation attack in that test with only Alloy B showing any evidence of exfoliation, and even then to just an EA level. By comparison, other materials showed some pitting attack (P) with minimal blistering.
  • the invention materials also showed excellent SCC resistance during alternate immersion testing using an NaCl solution.
  • This aluminum alloy has low density, good corrosion resistance and a good combination of strength and toughness by comparison to conventional fuselage skin materials.

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  • 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)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)
  • Powder Metallurgy (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Claims (19)

  1. Aluminiumlegierungsprodukt, aufweisend eine Aluminiumzusammensetzung, im Wesentlichen bestehend aus: 3,5% -6 Gew.% Magnesium, 0,03% - 0,2 Gew.% Zirconium, 0,2% -1,2 Gew.% Mangan, bis zu 0,15 Gew.% Silicium, 0,16 % - 0,34 Gew.% Scandium, 0%-0,25 Gewichtsprozent Kupfer und wahlweise 0,05% -0,5 Gew.% eines Dispersoid-bildenden Elements, ausgewählt aus: Erbium, Yttrium, Gadolinium, Holmium und Hafnium; wobei der Rest Aluminium sowie unvermeidbare Verunreinigungen sind.
  2. Aluminiumlegierungsprodukt nach Anspruch 1, bei welchem die Legierung 0,2% - 0,3 Gew.% Scandium enthält.
  3. Aluminiumlegierungsprodukt nach Anspruch 1, bei welchem die Legierung im Wesentlichen frei ist von Zink und Lithium.
  4. Schadentolerantes Teil für Luft- und Raumfahrt mit niedriger Dichte, guter Korrosionsbeständigkeit und guter Kombination von Festigkeit und Schlagzähigkeit, wobei das Teil für Luft- und Raumfahrt hergestellt wird aus einer Legierungszusammensetzung, im Wesentlichen bestehend aus: 3,5% - 6 Gew.% Magnesium, 0,03% - 0,2 Gew.% Zirconium, 0,2%- 1,2 Gew.% Mangan, bis zu 0,15 Gew.% Silicium, 0,16% - 0,34 Gew.% Scandium, 0% - 0,25 Gew.% Kupfer und wahlweise 0,05% - 0,5 Gew.% eines Dispersoid-bildenden Elements, ausgewählt aus: Erbium, Yttrium, Gadolinium, Holmium und Hafnium; wobei der Rest Aluminium sowie unvermeidbare Verunreinigungen sind.
  5. Teil für Luft- und Raumfahrt nach Anspruch 4, wobei das Teil ausgewählt wird aus Rumpfschale, einem unteren Tragflächenprofil, einer Längsversteifung und einem Druckspant.
  6. Teil für Luft- und Raumfahrt nach Anspruch 5, bei welchem das Dispersoid-bildende Element im Wesentlichen aus Scandium besteht.
  7. Teil für Luft- und Raumfahrt nach Anspruch 6, bei welchem die Legierungszusammensetzung 0,2% - 0,3 Gew.% Scandium enthält.
  8. Aluminiumlegierungsprodukt oder Teil für Luft- und Raumfahrt nach einem der vorgenannten Ansprüche, bei welchen die Legierungszusammensetzung 3,8% - 5,2 Gew.% Magnesium enthält.
  9. Aluminiumlegierungsprodukt oder Teil für Luft- und Raumfahrt nach einem der vorgenannten Ansprüche, bei welchen die Legierungszusammensetzung maximal 0,25 Gew.% Kupfer enthält.
  10. Aluminiumlegierungsprodukt oder Teil für Luft- und Raumfahrt nach einem der vorgenannten Ansprüche, bei welchen die Legierungszusammensetzung 0,06% - 0,12 Gew.%. Zirconium enthält.
  11. Aluminiumlegierungsprodukt oder Teil für Luft- und Raumfahrt nach einem der vorgenannten Ansprüche, bei welchen die Legierungszusammensetzung 0,09% - 0,12 Gew.% Zirconium enthält.
  12. Aluminiumlegierungsprodukt oder Teil für Luft- und Raumfahrt nach einem der vorgenannten Ansprüche, bei welchen die Legierungszusammensetzung 0,4% - 1 Gew.% Mangan enthält.
  13. Aluminiumlegierungsprodukt oder Teil für Luft- und Raumfahrt nach einem der vorgenannten Ansprüche, bei welchen die Legierungszusammensetzung 0,5% - 0,7 Gew.% Mangan enthält.
  14. Aluminiumlegierungsprodukt oder Teil für Luft- und Raumfahrt nach einem der vorgenannten Ansprüche, bei welchen die Legierungszusammensetzung bis zu 0,08 Gew.% Silicium enthält.
  15. Aluminiumlegierungsprodukt oder Teil für Luft- und Raumfahrt nach einem der vorgenannten Ansprüche, bei welchen die Legierungszusammensetzung bis zu 0,05 Gew.%. Silicium enthält.
  16. Teil für Luft- und Raumfahrt nach Anspruch 5, bei welchem die Legierungszusammensetzung im Wesentlichen frei ist von Zink.
  17. Teil für Luft- und Raumfahrt nach Anspruch 5 oder 6, bei welchem die Legierungszusammensetzung im Wesentlichen frei von Lithium ist.
  18. Aluminiumlegierungsprodukt nach Anspruch 1 oder Teil für Luft- und Raumfahrt nach Anspruch 6, bei welchen die Legierungszusammensetzung enthält: 3,5% - 6 Gew.% Magnesium, 0,06% - 0,12 Gew.% Zirconium, 0,4% - 1 Gew.% Mangan, bis zu 0,08 Gew.% Silicium und 0,16% - 0,34 Gew.% Scandium.
  19. Aluminiumlegierungsprodukt nach Anspruch 1 oder Teil für Luft- und Raumfahrt nach Anspruch 6, bei welchen die Legierungszusammensetzung enthält: 3,8% - 5,2 Gew.% Magnesium, 0,09% - 0,12 Gew.% Zirconium, 0,5% - 0,7 Gew.% Mangan, bis zu 0,05 Gew.% Silicium und 0,2% - 0,3 Gew.% Scandium.
EP97906549A 1995-01-31 1997-02-10 Aluminiumlegierungsprodukt Revoked EP0958393B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US08/381,032 US5624632A (en) 1995-01-31 1995-01-31 Aluminum magnesium alloy product containing dispersoids
PCT/US1997/002117 WO1998035068A1 (en) 1995-01-31 1997-02-10 Aluminum alloy product

Publications (2)

Publication Number Publication Date
EP0958393A1 EP0958393A1 (de) 1999-11-24
EP0958393B1 true EP0958393B1 (de) 2002-12-11

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ID=22260366

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EP97906549A Revoked EP0958393B1 (de) 1995-01-31 1997-02-10 Aluminiumlegierungsprodukt

Country Status (8)

Country Link
EP (1) EP0958393B1 (de)
JP (1) JP4014229B2 (de)
KR (1) KR100469929B1 (de)
AU (1) AU2121197A (de)
CA (1) CA2280191C (de)
DE (1) DE69717858T2 (de)
ES (1) ES2188897T3 (de)
WO (1) WO1998035068A1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2599590C1 (ru) * 2015-05-22 2016-10-10 Открытое акционерное общество "Всероссийский институт легких сплавов" (ОАО "ВИЛС") Конструкционный деформируемый термически неупрочняемый сплав на основе алюминия

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19838015C2 (de) * 1998-08-21 2002-10-17 Eads Deutschland Gmbh Gewalztes, stranggepreßtes, geschweißtes oder geschmiedetes Bauteil aus einer schweißbaren, korrosionsbeständigen hochmagnesiumhaltigen Aluminium-Magnesium-Legierung
DE19838017C2 (de) * 1998-08-21 2003-06-18 Eads Deutschland Gmbh Schweißbare, korrosionsbeständige AIMg-Legierungen, insbesondere für die Verkehrstechnik
DE19838018C2 (de) * 1998-08-21 2002-07-25 Eads Deutschland Gmbh Geschweißtes Bauteil aus einer schweißbaren, korrosionsbeständigen hochmagnesiumhaltigen Aluminium-Magnesium-Legierung
US20040156739A1 (en) 2002-02-01 2004-08-12 Song Shihong Gary Castable high temperature aluminum alloy
US7998402B2 (en) † 2005-08-16 2011-08-16 Aleris Aluminum Koblenz, GmbH High strength weldable Al-Mg alloy
US7584778B2 (en) 2005-09-21 2009-09-08 United Technologies Corporation Method of producing a castable high temperature aluminum alloy by controlled solidification
CA2811754C (en) 2010-10-04 2019-01-15 Gkn Sinter Metals, Llc Aluminum powder metal alloying method
DE112011104398T5 (de) 2010-12-15 2013-09-12 Aleris Rolled Products Germany Gmbh Verfahren zur Herstellung einer geformten Verkleidung aus einer Al-Legierung für Anwendungen in der Luft- und Raumfahrt
US9551050B2 (en) * 2012-02-29 2017-01-24 The Boeing Company Aluminum alloy with additions of scandium, zirconium and erbium
JP6726058B2 (ja) * 2016-08-12 2020-07-22 本田技研工業株式会社 Ａｌ合金鋳造物の製造方法
ES2878315T3 (es) 2019-01-17 2021-11-18 Aleris Rolled Prod Germany Gmbh Procedimiento de fabricación de un producto de aleación de la serie AlMgSc

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2056750A1 (en) * 1990-12-03 1992-06-04 Delbert M. Naser Aircraft sheet
RU2048576C1 (ru) * 1993-12-17 1995-11-20 Центральный научно-исследовательский институт конструкционных материалов "Прометей" Сплав на основе алюминия
FR2717827B1 (fr) * 1994-03-28 1996-04-26 Jean Pierre Collin Alliage d'aluminium à hautes teneurs en Scandium et procédé de fabrication de cet alliage.

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2599590C1 (ru) * 2015-05-22 2016-10-10 Открытое акционерное общество "Всероссийский институт легких сплавов" (ОАО "ВИЛС") Конструкционный деформируемый термически неупрочняемый сплав на основе алюминия

Also Published As

Publication number Publication date
AU2121197A (en) 1998-08-26
WO1998035068A1 (en) 1998-08-13
KR20000070878A (ko) 2000-11-25
KR100469929B1 (ko) 2005-02-02
DE69717858T2 (de) 2003-07-31
CA2280191A1 (en) 1998-08-13
JP2001511847A (ja) 2001-08-14
JP4014229B2 (ja) 2007-11-28
CA2280191C (en) 2007-07-31
DE69717858D1 (de) 2003-01-23
EP0958393A1 (de) 1999-11-24
ES2188897T3 (es) 2003-07-01

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