EP0162096B1 - Alliages a base d'aluminium contenant du lithium, du magnesium et du cuivre - Google Patents

Alliages a base d'aluminium contenant du lithium, du magnesium et du cuivre Download PDF

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Publication number
EP0162096B1
EP0162096B1 EP85900122A EP85900122A EP0162096B1 EP 0162096 B1 EP0162096 B1 EP 0162096B1 EP 85900122 A EP85900122 A EP 85900122A EP 85900122 A EP85900122 A EP 85900122A EP 0162096 B1 EP0162096 B1 EP 0162096B1
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EP
European Patent Office
Prior art keywords
alloys
alloy
tempering
homogenization
magnesium
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.)
Expired
Application number
EP85900122A
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German (de)
English (en)
French (fr)
Other versions
EP0162096A1 (fr
Inventor
Bruno Dubost
Philippe Meyer
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.)
Cegedur Societe de Transformation de lAluminium Pechiney SA
Original Assignee
Cegedur Societe de Transformation de lAluminium Pechiney SA
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.)
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Publication date
Application filed by Cegedur Societe de Transformation de lAluminium Pechiney SA filed Critical Cegedur Societe de Transformation de lAluminium Pechiney SA
Priority to AT85900122T priority Critical patent/ATE30051T1/de
Publication of EP0162096A1 publication Critical patent/EP0162096A1/fr
Application granted granted Critical
Publication of EP0162096B1 publication Critical patent/EP0162096B1/fr
Expired legal-status Critical Current

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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
    • 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

Definitions

  • the present invention relates to alloys based on AI, containing Li, Mg and Cu and having mechanical characteristics equivalent to those of aluminum alloys with conventional structural hardening at medium strength with a density reduced by at least minus 9% compared to these conventional alloys.
  • lithium alloys It is known to metallurgists that the addition of lithium decreases the density and increases the modulus of elasticity and the mechanical resistance of aluminum alloys. This explains the designers' interest in these alloys for applications in the aeronautical industry, and more particularly, for lithium aluminum alloys containing other addition elements such as magnesium or copper.
  • lithium alloys must imperatively have ductility and toughness at least equivalent, with mechanical strength equal to that of conventional aeronautical alloys such as alloys 2024-T4 or T351, 2214-T6 (51), 7175-T73 (51) or T7652 and 7150-T651 (according to the nomenclature of the Aluminum Association), which is not the case for known lithium alloys.
  • This alloy gives thin sheets and spun products treated in the T6 state (16 h at 170 ° C) moderately high mechanical tensile properties (FRIDLYANDER et al. Met. Science and Heat Treatment n ° 3-4, April 1968, page 212 - Metalov Translator I. Term Obrab Metallov No. 3, page 5052, March 1968) and lower than those of conventional aeronautical alloys.
  • the content of main elements is preferably held individually or in combination between 2.3 to 3.3% for Li, 1.4 and 2.4% for Mg and 0.25 and 1.2% for Cu.
  • the Zr content is preferably between 0.08 and 0.18%.
  • Homogenization can be done in a temperature range between 8 + 10 (° C) and 0 ⁇ 20 (° C); the dissolution is preferably carried out between 0 + - 10 ° C.
  • the optimal durations of heat treatment for homogenization at temperature 0 are 0.5 to 8 hours for alloys produced by rapid solidification (atomization - splat cooling - or any other means) and 12 to 72 hours for molded products or produced in semi-continuous casting.
  • alloys have their optimal mechanical properties after tempering of durations of 8 to 48 hours at temperatures between 170 and 220 ° C and it is preferable to subject the products of adequate shape (sheets, bars, widgets) to work hardening giving rise to plastic deformation of 1 to 5% (preferably 2 to 4%) between quenching and tempering, which further improves the mechanical strength of the products.
  • the alloys according to the invention have a higher mechanical strength than that of the alloy AILiMgMn 01420, which did not make it possible to predict the results of the studies available on the system.
  • the alloys according to the invention have a compromise between mechanical characteristics and density greater than that of the known AILiCuMg alloys (with low magnesium contents). They also have a satisfactory resistance to intergranular or laminating corrosion much higher than that of the known alloys AICuMg, AILiCu, and AILiCuMg.
  • alloys are therefore particularly advantageous for the manufacture of molded or wrought semi-finished products (produced by semi-continuous casting, rapid atomization or solidification, etc.) whether they are, for example, spun, rolled, forged or matrixes used in particular in the aeronautical or space industries.
  • the alloys according to the invention very loaded with Li and Mg, were pourable without major difficulty in semi-continuous casting in the form of billets or trays of industrial format (absence of cracks and porosities).
  • Table 1 gives the chemical compositions of the alloys measured by atomic absorption and spark emission spectrometry, and their characteristics (coefficient K) with respect to the domains according to the invention.
  • Table II gives the mechanical traction characteristics and the density as a function of the chemical composition of the widgets, for the various heat treatments carried out and the rate of work hardening between quenching and tempering.
  • the elastic limit (Rp 0.2), the breaking load (Rm) and the elongation at break (A%) are given.
  • Table III gives the results obtained during the corrosion tests.
  • the alloys according to the invention have mechanical strengths of levels comparable to those of the alloys of the 2000 series without lithium currently used in aeronautics, and greater than those of known AI-Li-Mg alloys. (eg alloy 01420) with the advantage of a significantly lower density than that of conventional alloys and lower than that of the known lithium alloys of the AI-Li-Cu, AI-Li-Cu-Mg systems. They also show the advantage of hardening between quenching and tempering on the mechanical properties.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Conductive Materials (AREA)
  • Laminated Bodies (AREA)
  • Heat Treatment Of Steel (AREA)
  • Powder Metallurgy (AREA)
  • Extrusion Of Metal (AREA)
EP85900122A 1983-11-24 1984-11-22 Alliages a base d'aluminium contenant du lithium, du magnesium et du cuivre Expired EP0162096B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT85900122T ATE30051T1 (de) 1983-11-24 1984-11-22 Legierungen auf aluminiumbasis mit lithium, magnesium und kupfer.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8319070 1983-11-24
FR8319070 1983-11-24

Publications (2)

Publication Number Publication Date
EP0162096A1 EP0162096A1 (fr) 1985-11-27
EP0162096B1 true EP0162096B1 (fr) 1987-09-30

Family

ID=9294664

Family Applications (1)

Application Number Title Priority Date Filing Date
EP85900122A Expired EP0162096B1 (fr) 1983-11-24 1984-11-22 Alliages a base d'aluminium contenant du lithium, du magnesium et du cuivre

Country Status (10)

Country Link
US (1) US4758286A (es)
EP (1) EP0162096B1 (es)
JP (1) JPS60502159A (es)
BR (1) BR8407153A (es)
CA (1) CA1253362A (es)
DE (1) DE3466560D1 (es)
ES (1) ES537895A0 (es)
IL (1) IL73619A (es)
IT (1) IT1209600B (es)
WO (1) WO1985002416A1 (es)

Families Citing this family (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5137686A (en) * 1988-01-28 1992-08-11 Aluminum Company Of America Aluminum-lithium alloys
US4961792A (en) * 1984-12-24 1990-10-09 Aluminum Company Of America Aluminum-lithium alloys having improved corrosion resistance containing Mg and Zn
FR2583776B1 (fr) * 1985-06-25 1987-07-31 Cegedur Produits a base d'al contenant du lithium utilisables a l'etat recristallise et un procede d'obtention
US4915747A (en) * 1985-10-31 1990-04-10 Aluminum Company Of America Aluminum-lithium alloys and process therefor
US4921548A (en) * 1985-10-31 1990-05-01 Aluminum Company Of America Aluminum-lithium alloys and method of making same
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
EP0250656A1 (en) * 1986-07-03 1988-01-07 The Boeing Company Low temperature underaging of lithium bearing alloys
US4795502A (en) * 1986-11-04 1989-01-03 Aluminum Company Of America Aluminum-lithium alloy products and method of making the same
US5122339A (en) * 1987-08-10 1992-06-16 Martin Marietta Corporation Aluminum-lithium welding alloys
US5032359A (en) * 1987-08-10 1991-07-16 Martin Marietta Corporation Ultra high strength weldable aluminum-lithium alloys
US5066342A (en) * 1988-01-28 1991-11-19 Aluminum Company Of America Aluminum-lithium alloys and method of making the same
US5108519A (en) * 1988-01-28 1992-04-28 Aluminum Company Of America Aluminum-lithium alloys suitable for forgings
US4869870A (en) * 1988-03-24 1989-09-26 Aluminum Company Of America Aluminum-lithium alloys with hafnium
US5455003A (en) * 1988-08-18 1995-10-03 Martin Marietta Corporation Al-Cu-Li alloys with improved cryogenic fracture toughness
US5259897A (en) * 1988-08-18 1993-11-09 Martin Marietta Corporation Ultrahigh strength Al-Cu-Li-Mg alloys
US5462712A (en) * 1988-08-18 1995-10-31 Martin Marietta Corporation High strength Al-Cu-Li-Zn-Mg alloys
US5512241A (en) * 1988-08-18 1996-04-30 Martin Marietta Corporation Al-Cu-Li weld filler alloy, process for the preparation thereof and process for welding therewith
US5085830A (en) * 1989-03-24 1992-02-04 Comalco Aluminum Limited Process for making aluminum-lithium alloys of high toughness
FR2646172B1 (fr) * 1989-04-21 1993-09-24 Cegedur Alliage al-li-cu-mg a bonne deformabilite a froid et bonne resistance aux dommages
AU626435B2 (en) * 1989-07-10 1992-07-30 Toyota Jidosha Kabushiki Kaisha Method of manufacture of metal matrix composite material including intermetallic compounds with no micropores
US5211910A (en) * 1990-01-26 1993-05-18 Martin Marietta Corporation Ultra high strength aluminum-base alloys
US5133931A (en) * 1990-08-28 1992-07-28 Reynolds Metals Company Lithium aluminum alloy system
US5198045A (en) * 1991-05-14 1993-03-30 Reynolds Metals Company Low density high strength al-li alloy
EP1788101B8 (en) * 2004-09-06 2009-02-18 Federalnoe Gosudarstvennoe Unitarnoe predpriyatie "Vserossiysky Nauchno-Issledovatelsky Institut Aviatsionnykh Materialov" (FGUP "VIAM") Aluminium-based alloy and a product made thereof
EP2829623B1 (en) 2007-12-04 2018-02-07 Arconic Inc. Improved aluminum-copper-lithium alloys
US8333853B2 (en) * 2009-01-16 2012-12-18 Alcoa Inc. Aging of aluminum alloys for improved combination of fatigue performance and strength
CN107012374A (zh) * 2017-04-07 2017-08-04 安徽省宁国市万得福汽车零部件有限公司 一种耐磨铝合金衬套材料及其制备方法
CN114480922B (zh) * 2022-01-25 2023-04-07 郑州轻研合金科技有限公司 一种超轻铝锂合金及其制备方法和应用

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0142261A1 (en) * 1983-10-12 1985-05-22 Alcan International Limited Stress corrosion resistant aluminium-magnesium-lithium-copper alloy

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1220961A (fr) * 1958-01-13 1960-05-30 Aluminum Co Of America Alliage à base d'aluminium
FR1519021A (fr) * 1967-03-07 1968-03-29 Iosif Naumovich Fridlyander Ni Alliage à base d'aluminium
DE3366165D1 (en) * 1982-02-26 1986-10-23 Secr Defence Brit Improvements in or relating to aluminium alloys
DE3365549D1 (en) * 1982-03-31 1986-10-02 Alcan Int Ltd Heat treatment of aluminium alloys
JPS59118848A (ja) * 1982-12-27 1984-07-09 Sumitomo Light Metal Ind Ltd 電気抵抗を高めた構造用アルミニウム合金

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0142261A1 (en) * 1983-10-12 1985-05-22 Alcan International Limited Stress corrosion resistant aluminium-magnesium-lithium-copper alloy

Also Published As

Publication number Publication date
IL73619A (en) 1987-11-30
BR8407153A (pt) 1985-10-08
CA1253362A (fr) 1989-05-02
IL73619A0 (en) 1985-02-28
ES8600419A1 (es) 1985-09-16
EP0162096A1 (fr) 1985-11-27
ES537895A0 (es) 1985-09-16
DE3466560D1 (en) 1987-11-05
IT1209600B (it) 1989-08-30
IT8423712A0 (it) 1984-11-23
WO1985002416A1 (fr) 1985-06-06
JPS60502159A (ja) 1985-12-12
US4758286A (en) 1988-07-19

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