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US20050271543A1 - Aluminum-based alloy and method of fabrication of semiproducts thereof - Google Patents

Aluminum-based alloy and method of fabrication of semiproducts thereof Download PDF

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Publication number
US20050271543A1
US20050271543A1 US10/343,712 US34371203A US2005271543A1 US 20050271543 A1 US20050271543 A1 US 20050271543A1 US 34371203 A US34371203 A US 34371203A US 2005271543 A1 US2005271543 A1 US 2005271543A1
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Prior art keywords
alloy
hours
aging
aluminum
billet
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Abandoned
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US10/343,712
Inventor
Thomas Pfannen-Mueller
Rainer Rauh
Peter-Juergen Winkler
Roland Lang
Iosif Fridlyander
Evgeny Kablov
Vladimir Sandler
Svetlana Borovskikh
Valentin Davydov
Valery Zakharov
Marina Samarina
Viktor Elagin
Leonid Ber
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Airbus Defence and Space GmbH
All Russian Scientific Research Institute of Aviation Materials
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Individual
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Assigned to ALL RUSSIAN INSTITUTE OF AVIATION MATERIALSVIAM, EADS DEUTSCHLAND GMBH reassignment ALL RUSSIAN INSTITUTE OF AVIATION MATERIALSVIAM ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: WINKLER, PETER-JUERGEN, LANG, ROLAND, RAUH, RAINER, PFANNEN-MUELLER, THOMAS, ELAGIN, VIKTOR IGNATOVITCH, KABLOV, EVGENY NIKOLAEVITCH, ZAKHAROV, VALERY VLADIMIROVITCH, BER, LEONID BORISOVITCH, BOROVSKIKH, SVETLANA NIKOLAEVNA, DAVYDOV, VALENTIN GEORGIEVITCH, FRIDLYANDER, IOSIF NAUMOVITCH, SAMARINA, MARINA VLADIMIROVNA, SANDLER, VLADIMIR SOLOMONOVITCH
Publication of US20050271543A1 publication Critical patent/US20050271543A1/en
Priority to US12/010,326 priority Critical patent/US7597770B2/en
Abandoned 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
    • 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
    • C22F1/057—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 copper 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
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C22C21/14—Alloys based on aluminium with copper as the next major constituent with silicon
    • 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
    • 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

Definitions

  • This invention relates to the field of metallurgy, in particular to high strength weldable alloys with low density, of aluminium-copper-lithium system, said invention can be used in air- and spacecraft engineering.
  • the aluminium-based alloy comprising (mass %): copper 2.6-3.3 lithium 1.8-2.3 zirconium 0.09-0.14 magnesium ⁇ 0.1 manganese ⁇ 0.1 chromium ⁇ 0.05 nickel ⁇ 0.003 cerium ⁇ 0.005 titanium ⁇ 0.02-0.06 silicon ⁇ 0.1 iron ⁇ 0.15 beryllium 0.008-0.1 aluminium balance (OST 1-90048-77)
  • the disadvantage of this alloy is its low weldability, reduced resistance to impact loading and low stability of mechanical properties in case of prolonged low-temperature heating.
  • the aluminium-based alloy with the following composition has been chosen as a prototype: (mass %) copper 1.4-6.0 lithium 1.0-4.0 zirconium 0.02-0.3 titanium 0.01-0.15 boron 0.0002-0.07 cerium 0.005-0.15 iron 0.03-0.25 at least one element from the group including: neodymium 0.0002-0.1 scandium 0.01-0.35 vanadium 0.01-0.15 manganese 0.05-0.6 magnesium 0.6-2.0 aluminium balance (RU patent 1584414, C22C21/12, 1988)
  • the disadvantage of this alloy is its reduced thermal stability, not high enough crack resistance, high anisotropy of properties, especially of elongation.
  • the shortcoming of this method is the low thermal stability of semiproducts' properties because of the residual supersaturation of the solid solution and its subsequent decomposition with precipitation of fine particles of hardening phases, and also the low elongation and crack resistance, all of which increases the danger of fracture in the course of service life.
  • the disadvantage of this method is the wide range of mechanical properties' values due to wide interval of deformation temperatures and low thermal stability because of the residual supersaturation of solid solution after ageing.
  • the suggested aluminium-based alloy comprises (mass %): copper 3.0-3.5 lithium 1.5-1.8 zirconium 0.05-0.12 scandium 0.06-0.12 silicon 0.02-0.15 iron 0.02-0.2 beryllium 0.0001-0.02 at least one element from the group including magnesium 0.1-0.6 zinc 0.01-1.0 manganese 0.05-0.5 germanium 0.02-0.2 cerium 0.05-0.2 yttrium 0.005-0.02 titanium 0.005-0.05 aluminium balance
  • the Cu/Li ratio is in the range 1.9-2.3.
  • the suggested method differs from the prototype in that the billet prior to deformation process, is heated to 460-500° C., the deformation temperature is not less than 400° C., and the artificial ageing process is performed in three stages: first at 155-165° C. for 10-12 hours, then at 180-190° C. for 2-5 hours and lastly at 155-165° C. for 8-10 hours; then is performed cooling to 90-100° C. with cooling rate of 2-5° C./hour and subsequent air cooling to room temperature.
  • the task of the present invention is the weight reduction of aircraft structures, the increase in their reliability and service life.
  • the technical result of the invention is the increase in plasticity, crack resistance, including the impact loading resistance, and also the increase in stability of mechanical properties in case of prolonged low-temperature heating.
  • the suggested composition of the alloy and the method of fabrication of semiproducts from said alloy ensure the necessary and sufficient saturation of the solid solution, allowing to achieve the high hardening effect at the expense of mainly fine T 1 -phase (Al 2 CuLi) precipitates without residual supersaturation of the solid solution with Li, and that results in practically complete thermal stability of the alloy in case of prolonged low—temperature heating.

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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)
  • Metal Rolling (AREA)
  • Heat Treatment Of Steel (AREA)

Abstract

This invention relates to the field of metallurgy, in particular to high strength weldable alloy with low density, of aluminium-copper-lithium system. Said invention can be used in air- and spacecraft engineering. The suggested alloy comprises copper, lithium, zirconium, scandium, silicon, iron, beryllium, and at least one element from the group including magnesium, zinc, manganese, germanium, cerium, yttrium, titanium. Also there is suggested the method for fabrication of semiproducts' which method comprising heating the as-cast billet prior to rolling, hot rolling, solid solution treatment and water quenching, stretching and three-stage artificial ageing.

Description

  • This invention relates to the field of metallurgy, in particular to high strength weldable alloys with low density, of aluminium-copper-lithium system, said invention can be used in air- and spacecraft engineering.
  • Well-known is the aluminium-based alloy comprising (mass %):
    copper 2.6-3.3
    lithium 1.8-2.3
    zirconium 0.09-0.14
    magnesium ≦0.1
    manganese ≦0.1
    chromium ≦0.05
    nickel ≦0.003
    cerium ≦0.005
    titanium ≦0.02-0.06   
    silicon ≦0.1
    iron ≦0.15
    beryllium 0.008-0.1 
    aluminium balance

    (OST 1-90048-77)
  • The disadvantage of this alloy is its low weldability, reduced resistance to impact loading and low stability of mechanical properties in case of prolonged low-temperature heating.
  • The aluminium-based alloy with the following composition has been chosen as a prototype: (mass %)
    copper  1.4-6.0
    lithium  1.0-4.0
    zirconium 0.02-0.3
    titanium  0.01-0.15
    boron 0.0002-0.07 
    cerium 0.005-0.15
    iron  0.03-0.25
    at least one element from the group including:
    neodymium 0.0002-0.1 
    scandium  0.01-0.35
    vanadium  0.01-0.15
    manganese 0.05-0.6
    magnesium  0.6-2.0
    aluminium balance

    (RU patent 1584414, C22C21/12, 1988)
  • The disadvantage of this alloy is its reduced thermal stability, not high enough crack resistance, high anisotropy of properties, especially of elongation.
  • Well-known is the method of fabrication of semiproducts from alloys of Al—Cu—Li system, which method comprises heating of the billet at 470-537° C., hot rolling (temperature of the metal at the end of the rolling process is not specified), hardening from 549° C., stretching (ε=2-8%) and artificial ageing at 149° C. for 8-24 hours or at 162° C. for 36-72 hours, or at 190° C. for 18-36 hours.
    • U.S. Pat. No. 4,806,174, C22F Jan. 4, 1989
  • The shortcoming of this method is the low thermal stability of semiproducts' properties because of the residual supersaturation of the solid solution and its subsequent decomposition with precipitation of fine particles of hardening phases, and also the low elongation and crack resistance, all of which increases the danger of fracture in the course of service life.
  • The well-known method of fabrication of products from the alloy of Al—Cu—Li system is chosen as a prototype, which method comprising: heating the as-cast billet prior to deformation at 430-480° C., deformation at rolling finish temperature of not less than 375° C., hardening from 525°±5 C., stretching (ε=1.5-3.0%) and artificial ageing 150°±5 C. for 20-30 hours.
  • (Technological Recommendation for fabrication of plates from 1440 and 1450 alloys, TR 456-2/31-88, VILS, Moscow, 1988).
  • The disadvantage of this method is the wide range of mechanical properties' values due to wide interval of deformation temperatures and low thermal stability because of the residual supersaturation of solid solution after ageing.
  • The suggested aluminium-based alloy comprises (mass %):
    copper  3.0-3.5
    lithium  1.5-1.8
    zirconium  0.05-0.12
    scandium  0.06-0.12
    silicon  0.02-0.15
    iron 0.02-0.2
    beryllium 0.0001-0.02 
    at least one element from the group including
    magnesium  0.1-0.6
    zinc 0.01-1.0
    manganese 0.05-0.5
    germanium 0.02-0.2
    cerium 0.05-0.2
    yttrium 0.005-0.02
    titanium 0.005-0.05
    aluminium balance
  • The Cu/Li ratio is in the range 1.9-2.3.
  • Also is suggested the method for fabrication of semiproducts, comprising heating of as-cast billet to 460-500° C., deformation at temperature ≧400° C., water quenching from 525° C., stretching (ε=1.5-3.0%), three-stage artificial ageing including:
      • I—155-165° C. for 10-12 hours,
      • II—180-190° C. for 2-5 hours,
      • III—155-165° C. for 8-10 hours,
        with subsequent cooling in a furnace to 90-100° C. with cooling rate 2-5° C./hours and air cooling to room temperature.
  • The suggested method differs from the prototype in that the billet prior to deformation process, is heated to 460-500° C., the deformation temperature is not less than 400° C., and the artificial ageing process is performed in three stages: first at 155-165° C. for 10-12 hours, then at 180-190° C. for 2-5 hours and lastly at 155-165° C. for 8-10 hours; then is performed cooling to 90-100° C. with cooling rate of 2-5° C./hour and subsequent air cooling to room temperature.
  • The task of the present invention is the weight reduction of aircraft structures, the increase in their reliability and service life.
  • The technical result of the invention is the increase in plasticity, crack resistance, including the impact loading resistance, and also the increase in stability of mechanical properties in case of prolonged low-temperature heating.
  • The suggested composition of the alloy and the method of fabrication of semiproducts from said alloy ensure the necessary and sufficient saturation of the solid solution, allowing to achieve the high hardening effect at the expense of mainly fine T1-phase (Al2CuLi) precipitates without residual supersaturation of the solid solution with Li, and that results in practically complete thermal stability of the alloy in case of prolonged low—temperature heating.
    Figure US20050271543A1-20051208-C00001

Claims (12)

1-2. (canceled)
3. An aluminum-based alloy comprising, 3.0-3.5% copper, 1.5-1.8% lithium, 0.05-0.12% zirconium, 0.06-0.12% scandium, 0.02-0.15% silicon, 0.02-0.2% iron, 0.0001-0.02% beryllium; at least one element selected from the group consisting of 0.1-0.6% magnesium, 0.02-1.0% zinc, 0.05-0.5% manganese, 0.02-0.2% germanium, 0.05-0.2% cerium, 0.005-0.02% yttrium and 0.005-0.05% titanium; and aluminum which makes up the balance, wherein the ratio between copper/lithium (Cu/Li) is in the between about 1.9 and about 2.3.
4. The aluminum-based alloy of claim 3, wherein the Cu/Li is 2.26.
5. The aluminum-based alloy of claim 4, consisting of 3.4% Cu, 1.5% Li, 0.08% Zr, 0.09% Sc, 0.04% Si, 0.02% Fe, 0.07% Be, 0.3% Mg, 0.15% Mn, 0.001% Y and 94.349% Al.
6. The aluminum-based alloy of claim 3, wherein the Cu/Li is 1.98.
7. The aluminum-based alloy of claim 6, consisting of 3.48% Cu, 1.76% Li, 0.11% Zr, 0.069% Sc, 0.05% Si, 0.02% Fe, 0.06% Be, 0.28% Mg, 0.31% Mn, 0.02% Zn, 0.02% Ti, 0.001% Y and 93.82% Al.
8. The aluminum-based alloy of claim 3, wherein the Cu/Li is 1.90.
9. The aluminum-based alloy of claim 8, consisting of 3.1% Cu, 1.63% Li, 0.07% Zr, 0.1% Sc, 0.1% Si, 0.2% Fe, 0.0001% Be, 0.56% Mg, 0.3% Mn, 0.1% Ce, 0.02% Ti, and 93.8579% Al.
10. A method for producing a semi-product from the alloy of claim 3, the method comprising
heating a billet of the alloy to 460-500° C.,
deforming at a temperature of not less than 400° C.,
aging at 155-165° C. for 10-12 hours, aging at 180-190° C. for 2-5 hours and aging at 155-165° C. for 8-10 hours;
cooling the billet to 90-100° C. with cooling rate of 2-5° C./hour, and
air cooling to room temperature.
11. A method for fabricating a sheet of the alloy of claim 5, comprising heating a billet of the alloy to 490° C., rolling the billet such that the temperature of the alloy at rolling finish is 420° C., and aging the alloy at 160° C. for 10 hours, aging the alloy at 180° C. for 3 hours, and aging the alloy at 160° C. for 10 hours.
12. A method for fabricating a sheet of the alloy of claim 7, comprising heating a billet of the alloy to 460° C., rolling the billet such that the temperature of the alloy at rolling finish is 410° C., and aging the alloy at 160° C. for 12 hours, aging the alloy at 180° C. for 4 hours, and aging the alloy at 160° C. for 10 hours.
13. A method for fabricating a sheet of the alloy of claim 9, comprising heating a billet of the alloy to 460° C., rolling the billet such that the temperature of the alloy at rolling finish is 410° C., and aging the alloy at 160° C. for 10 hours, aging the alloy at 180° C. for 3 hours, and aging the alloy at 160° C. for 8 hours.
US10/343,712 2000-08-01 2001-07-30 Aluminum-based alloy and method of fabrication of semiproducts thereof Abandoned US20050271543A1 (en)

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CN112853172B (en) * 2020-12-28 2022-04-15 郑州轻研合金科技有限公司 A kind of ultra-low density aluminum-lithium alloy and preparation method thereof

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4806174A (en) * 1984-03-29 1989-02-21 Aluminum Company Of America Aluminum-lithium alloys and method of making the same
US5066342A (en) * 1988-01-28 1991-11-19 Aluminum Company Of America Aluminum-lithium alloys and method of making the same
US5076859A (en) * 1989-12-26 1991-12-31 Aluminum Company Of America Heat treatment of aluminum-lithium alloys
US5211910A (en) * 1990-01-26 1993-05-18 Martin Marietta Corporation Ultra high strength aluminum-base alloys
US5882449A (en) * 1997-07-11 1999-03-16 Mcdonnell Douglas Corporation Process for preparing aluminum/lithium/scandium rolled sheet products

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4816087A (en) * 1985-10-31 1989-03-28 Aluminum Company Of America Process for producing duplex mode recrystallized high strength aluminum-lithium alloy products with high fracture toughness and method of making the same
JPS62297433A (en) * 1986-06-18 1987-12-24 Sumitomo Light Metal Ind Ltd Structural al alloy excellent in hardenability
RU1584414C (en) * 1988-02-19 1994-10-15 Всероссийский научно-исследовательский институт авиационных материалов Aluminium-based alloy
SU1785286A1 (en) * 1991-01-18 1994-08-15 Научно-производственное объединение "Всесоюзный институт авиационных материалов" Aluminium-base alloy
GB9424970D0 (en) * 1994-12-10 1995-02-08 British Aerospace Thermal stabilisation of Al-Li alloy

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4806174A (en) * 1984-03-29 1989-02-21 Aluminum Company Of America Aluminum-lithium alloys and method of making the same
US5066342A (en) * 1988-01-28 1991-11-19 Aluminum Company Of America Aluminum-lithium alloys and method of making the same
US5076859A (en) * 1989-12-26 1991-12-31 Aluminum Company Of America Heat treatment of aluminum-lithium alloys
US5211910A (en) * 1990-01-26 1993-05-18 Martin Marietta Corporation Ultra high strength aluminum-base alloys
US5882449A (en) * 1997-07-11 1999-03-16 Mcdonnell Douglas Corporation Process for preparing aluminum/lithium/scandium rolled sheet products

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040211498A1 (en) * 2003-03-17 2004-10-28 Keidel Christian Joachim Method for producing an integrated monolithic aluminum structure and aluminum product machined from that structure
US7610669B2 (en) * 2003-03-17 2009-11-03 Aleris Aluminum Koblenz Gmbh Method for producing an integrated monolithic aluminum structure and aluminum product machined from that structure
RU2556179C2 (en) * 2013-06-18 2015-07-10 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Самарский государственный аэрокосмический университет имени академика С.П. Королева (национальный исследовательский университет)" (СГАУ) Heat-resistant electroconductive alloy based on aluminium (versions) and method of production of deformed semi-finished product out of aluminium alloy
US12305267B2 (en) 2017-02-22 2025-05-20 Ut-Battelle, Llc Rapidly solidified aluminum-rare earth element alloy and method of making the same
WO2019055872A1 (en) * 2017-09-15 2019-03-21 Orlando Rios Aluminum alloys with improved intergranular corrosion resistance properties and methods of making and using the same
US11761061B2 (en) 2017-09-15 2023-09-19 Ut-Battelle, Llc Aluminum alloys with improved intergranular corrosion resistance properties and methods of making and using the same
CN108103372A (en) * 2018-02-23 2018-06-01 北京工业大学 Al-Zn-Mg-Cu-Mn-Er-Zr aluminium alloy three-step aging techniques
WO2020150056A1 (en) * 2019-01-18 2020-07-23 Divergent Technologies, Inc. Aluminum alloys
US12378643B2 (en) 2019-01-18 2025-08-05 Divergent Technologies, Inc. Aluminum alloys
US11986904B2 (en) 2019-10-30 2024-05-21 Ut-Battelle, Llc Aluminum-cerium-nickel alloys for additive manufacturing
US12247272B2 (en) 2019-10-30 2025-03-11 Ut-Battelle, Llc Aluminum-cerium-copper alloys for metal additive manufacturing
US11608546B2 (en) 2020-01-10 2023-03-21 Ut-Battelle Llc Aluminum-cerium-manganese alloy embodiments for metal additive manufacturing
US12365965B2 (en) 2021-07-01 2025-07-22 Divergent Technologies, Inc. Al—Mg—Si based near-eutectic alloy composition for high strength and stiffness applications
CN114033591A (en) * 2021-11-16 2022-02-11 苏州星波动力科技有限公司 Aluminum alloy oil rail, forming method and manufacturing method thereof, engine and automobile

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