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EP2006403B1 - Alliage à base d'aluminium - Google Patents

Alliage à base d'aluminium Download PDF

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Publication number
EP2006403B1
EP2006403B1 EP07747842A EP07747842A EP2006403B1 EP 2006403 B1 EP2006403 B1 EP 2006403B1 EP 07747842 A EP07747842 A EP 07747842A EP 07747842 A EP07747842 A EP 07747842A EP 2006403 B1 EP2006403 B1 EP 2006403B1
Authority
EP
European Patent Office
Prior art keywords
aluminum
temperature
alloy
copper
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.)
Active
Application number
EP07747842A
Other languages
German (de)
English (en)
Other versions
EP2006403A4 (fr
EP2006403A1 (fr
Inventor
Valeriy Ivanovich Popov
Boris Vladimirovich Ovsyannikov
Viktor Mikhailovich Zamyatin
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.)
Otkrytoe Akcionernoe Obschestvo"Kamensk-Uralsky
Original Assignee
Otkrytoe Akcionernoe Obschestvo"Kamensk-Uralsky
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
Application filed by Otkrytoe Akcionernoe Obschestvo"Kamensk-Uralsky filed Critical Otkrytoe Akcionernoe Obschestvo"Kamensk-Uralsky
Publication of EP2006403A1 publication Critical patent/EP2006403A1/fr
Publication of EP2006403A4 publication Critical patent/EP2006403A4/fr
Application granted granted Critical
Publication of EP2006403B1 publication Critical patent/EP2006403B1/fr
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Links

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
    • C22C21/12—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
    • 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
    • C22C21/12—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
    • 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

Definitions

  • An invention covers a field of metallurgy of alloys based on aluminum, in particular to the alloy of aluminum-copper-magnesium-lithium system applied for manufacturing semi-finished products and parts thereof used as structural materials for aerospace engineering.
  • aluminum-lithium alloys possess an unique combination of mechanical properties, namely of low density, increased elasticity modulus, and sufficiently high strength characteristics. Availability of indicated properties enables to use alloys of this system as structural material for aerospace engineering, that allows to improve a number of aircraft performance features of flying vehicles, in particular, reduction of vehicle weight, fuel economy, increase of load capacity.
  • aluminium-lithium alloys have one disadvantage - low ductility on conditions close to maximum strength ( N.I. Fridlyander, K.V. Chuistov, A.L. Berezina, N.I. Kolobnev, Aluminum-lithium alloys. Structure and Properties, Kiev: Nauk. Dumka, 1992, page 177 ).
  • Aluminum-based alloy is known having wt %: Lithium 1.7 - 2.0 Copper 1.6 - 2.0 Magnesium 0.7 - 1.1 Zirconium 0.04 - 0.16 Beryllium 0.02 - 0.2 Titanium 0.01 - 0.07 Nickel 0.02 - 0.15 Manganese 0.01 - 0.4 Aluminum Remainder (Inventor's Certificate of USSR No. 1767916 , IPC C 22 C 21/16, date of publication 1997.08.20).
  • Disadvantages of the indicated alloy are its low processibility, high manufacturing labor intensiveness, and low yields by manufacturing semi-finished products and parts thereof, impossibility to obtain thin sheets, thin-walled sections and die-forgings in it.
  • Aluminum-based alloy is known - 8093, (alloy designation is in conformance with alloy numbers and comply with definitions registered by Aluminum Assosiation, Washington, USA) having wt %: Lithium 1.9 - 2.6 Copper 1.0 - 1.6 Magnesium 0.9 - 1.6 Zirconium 0.04 - 0.14 Titanium Up to 0.1 Manganese Up to 0.1 Zinc Up to 0.25 Aluminum Remainder (International designation of alloys and limits of chemical composition of wrought aluminum and aluminum alloys, Aluminum Association: 2004, pages 12, 13)
  • Disadvantages of the indicated alloy are increased cost of the alloy, its low processibility, high manufacturing labor intensiveness, and low yields by manufacturing semi-finished products and parts thereof, impossibility to obtain thin sheets, thin-walled sections and die-forgings in it.
  • the closest alloy on chemical composition and function to the claimed aluminum-based alloy is the alloy having wt %: Lithium 1.7 - 2.0 Copper 1.6 - 2.0 Magnesium 0.7 - 1.1 Zirconium 0.04 - 0.2 Beryllium 0.02 - 0.2 Titanium 0.01 - 0.1 Nickel 0.01 - 0.15 Manganese 0.001 - 0.05 Gallium 0.001 - 0.05 Zinc 0.01 - 0.3 Sodium 0.0005 - 0.001 Aluminum Remainder (Patent of the Russian Federation No. 2180928 , IPC 7 C 22 C 21/00, C 22 C 21/16, date of publication 2002.03.27; see also EP-A-1 788 101 ).
  • Disadvantages of the indicated alloy taken for a prototype are its relatively low processibility, high manufacturing labor intensiveness, and low yields by manufacturing semi-finished products and parts thereof, impossibility to obtain thin sheets, thin-walled sections and die-forgings in it.
  • the objective which the invention is directed to solve, consists in development of the aluminum-based alloy intended for manufacturing semi-finished products and parts in it for aerospace engineering, free from the above listed disadvantages and inherent to known engineering solutions.
  • a technical result achieved by an embodiment of the invention comprises obtaining an alloy possessing increased ductility, that will allow to improve its processibility, to increase yields by manufacturing semi-finished products and parts thereof, to ensure possibility to produce thin sheets, thin-walled sections and die-forgings by reducing production labor intensiveness, by preservation required strength and operation characteristics of the alloy, and also semi-finished products and parts thereof demanded to structural materials for aerospace engineering.
  • the known aluminum-based alloy containing lithium, copper, magnesium, zirconium, beryllium, titanium, nickel, manganese, gallium, zinc, sodium additionally contains calcium and, at least, one element selected from a group including vanadium and scandium, with the following component ratio, wt %: Lithium 1.6 - 1.9 Copper 1.3 - 1.5
  • Zinc 0.01 - 0.3 Sodium up to 0.0005 Calcium 0.005 - 0.02
  • the aluminum-based alloy used for manufacturing semi-finished products and parts differs from the prior art both quantitatively (reduced contents of copper, gallium, and sodium) and qualitatively (in addition it contains calcium, and, at least, one element selected from a group including vanadium and scandium).
  • Reduction of copper contents in the alloy up to limits of 1.3 - 1.5 wt % allows practically total transfer to solid solution which results in considerable reduction of inclusion volume ratio of coarse intermetallic compounds of copper-bearing phases as determined by electron-microscopical analysis of the alloy, and, consequently, enhancement of alloy ductility. Reduction of copper contents to less than 1.3 wt % will have no enhancing influence on ductility characteristics of the alloy, but will considerably reduce its strength features.
  • gallium and sodium do not form phases with aluminum and accumulate on grain boundaries resulting in brittle fracture along grain boundary in processes of alloy crystallization and its shaping.
  • Calcium in quantity of 0.005 - 0.02 wt % is an additive binding excess sodium and other residual elements of the alloy resulting in formation of a rounder shape of isolated intermetallic compounds and their coagulation resulting in more favorable conditions of shear deformation, and, consequently, in enhancement of alloy process ductility.
  • Alloy No. 1 corresponds to the alloy taken as a prototype, alloys No. 2, 3, 4 correspond to the proposed one.
  • Charge material melting, degassing and ingot casting have been done at temperature of 710 - 730°C.
  • clad sheets have been manufactured from flat ingots in each alloy.
  • the sheets have been manufactured based on one process flow by means of hot rolling at temperature of 430°C up to 6.5 mm of thickness with reeling to coils, and afterwards, after annealing at temperature of 400°C, by means of cols rolling.
  • Sheets in alloys No. 2, 3, 4 have been rolled without ruptures up to 0.5 mm of thickness.
  • Specimens have been cut off lengthwise, crosswise, and at angle of 45° relative to rolling direction.
  • Table 2 shows that the proposed alloy surpasses the known alloy (the prototype) on ductility characteristics with preservation of required strength characteristics.
  • Sections (angles with flange thickness up to 5 mm) have been manufactured from round ingots with diameter of 190 mm in each alloy.
  • Sections in different alloys have been manufactured based on one process flow by means of extruding at temperature of 400°C, with further section water quenching, and ageing at temperature of 150°C within 24 hours.
  • Die-forgings in different alloys have been manufactured on one process flow by means of blanking forging at temperature of 410°C, preliminary forging at temperature of 410°C, and after etching by means of final forging at temperature of 400°C, with further quenching at temperature of 500°C during 2 hours and ageing at temperature of 150 °C during 24 hours.
  • the yield by manufacturing die-forgings in alloy No. 2, 3, 4 has been higher than alloy No. 1 by 10%.
  • the suggested alloy ensures achievement of the posed objective - improvement of alloy ductility characteristics, and, consequently, improvement of its processibility, increase of yields by manufacturing semi-finished products and parts thereof, assurance of possibility to produce thin sheets, thin-walled sections and die-forgings by reducing production labor intensiveness, and preservation of required strength and operation characteristics of the alloy and parts thereof demanded to structural materials for aerospace engineering.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Thermal Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Forging (AREA)
  • Materials For Medical Uses (AREA)
  • Battery Electrode And Active Subsutance (AREA)
  • Laminated Bodies (AREA)
  • Superconductors And Manufacturing Methods Therefor (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)
  • Secondary Cells (AREA)
  • Manufacture And Refinement Of Metals (AREA)

Claims (7)

  1. Alliage à base d'aluminium contenant du lithium, du cuivre, du magnésium, du zirconium, du béryllium, du titane, du nickel, du manganèse, du gallium, du zinc, du sodium, qui diffère par le fait qu'il contient en plus du calcium, et, au moins, un élément choisi parmi un groupe constitué du vanadium et du scandium, les teneurs en composants, exprimées en % en poids, étant les suivantes : lithium 1,6 à 1,9 cuivre 1,3 à 1,5 magnésium 0,7 à 1,1 zirconium 0,04 à 0,2 béryllium 0,02 à 0,2 titane 0,01 à 0,1 nickel 0,01 à 0,15 manganèse 0,01 à 0,2 gallium jusqu'à 0,001 zinc 0,01 à 0,3 sodium jusqu'à 0,0005 calcium 0,005 à 0,02
    et au moins un élément choisi parmi un groupe constitué de : vanadium 0,005 à 0,01 scandium 0,005 à 0,01 aluminium le reste
  2. Produit semi-fini, tel qu'une tôle, une plaque, une pièce forgée par matriçage ou un profilé fabriqué à partir de l'alliage à base d'aluminium selon la revendication 1.
  3. Pièce fabriquée à partir d'un produit semi-fini selon la revendication 2, telle qu'un panneau pour le revêtement d'une structure de fuselage d'avion, un élément d'un cadre de cloison, un réservoir de carburant soudé ou tout autre élément utilisé dans l'aérospatiale.
  4. Procédé de fabrication d'un alliage à base d'aluminium selon la revendication 1, incluant la fusion d'un matériau de charge, le dégazage et la coulée en lingotière effectuée à une température de 710 à 730 °C.
  5. Procédé selon la revendication 4, comportant la fabrication d'une tôle à partir de lingots plats, les tôles étant fabriquées sur la base d'un déroulement de processus au moyen d'un laminage à chaud à une température de 430 °C jusqu'à 6,5 mm d'épaisseur avec rembobiner de bobines, et ensuite, après un recuit à une température de 400 °C, au moyen d'un enroulement de bobines.
  6. Procédé selon la revendication 5 incluant la fabrication de pièces forgées par matriçage ayant une épaisseur de paroi de 40 mm, à partir de lingots ronds ayant un diamètre de 350 mm.
  7. Procédé selon la revendication 5, comportant la fabrication de la pièce forgée par matriçage pendant un déroulement de processus au moyen d'un découpage de la piece forgée à une température de 410 °C, d'un forgeage préliminaire à une température de 410 °C, et après refoulement au moyen d'un forgeage final à une température de 400 °C, avec une trempe supplémentaire à une température de 500 °C pendant deux heures et un vieillissement à une température de 150 °C pendant 24 heures.
EP07747842A 2006-03-27 2007-03-07 Alliage à base d'aluminium Active EP2006403B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
RU2006109658/02A RU2310005C1 (ru) 2006-03-27 2006-03-27 Сплав на основе алюминия и изделие из него
PCT/RU2007/000109 WO2007111529A1 (fr) 2006-03-27 2007-03-07 Alliage à base d'aluminium

Publications (3)

Publication Number Publication Date
EP2006403A1 EP2006403A1 (fr) 2008-12-24
EP2006403A4 EP2006403A4 (fr) 2009-03-18
EP2006403B1 true EP2006403B1 (fr) 2010-01-20

Family

ID=38541383

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07747842A Active EP2006403B1 (fr) 2006-03-27 2007-03-07 Alliage à base d'aluminium

Country Status (8)

Country Link
US (1) US20090068056A1 (fr)
EP (1) EP2006403B1 (fr)
AT (1) ATE455874T1 (fr)
DE (2) DE602007004465D1 (fr)
ES (1) ES2319718T3 (fr)
PT (1) PT2006403E (fr)
RU (1) RU2310005C1 (fr)
WO (1) WO2007111529A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8437332B2 (en) 2009-06-22 2013-05-07 Qualcomm Incorporated Low complexity unified control channel processing
RU2412270C1 (ru) * 2009-10-02 2011-02-20 Открытое акционерное общество "Каменск-Уральский металлургический завод" Сплав на основе алюминия
WO2015181210A1 (fr) * 2014-05-30 2015-12-03 Basf Se Polymère utilisable comme couches de protection et autres composants dans des cellules électrochimiques

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1412280A (en) * 1920-03-29 1922-04-11 Aluminum Co Of America Aluinum alloy
US1767916A (en) 1926-06-23 1930-06-24 Coleman Automatic Transmission Transmission
US4232910A (en) * 1976-04-12 1980-11-11 Motor Wheel Corporation Systems and methods for controlling trailer brakes as a function of trailer wheel rotation
US4832910A (en) * 1985-12-23 1989-05-23 Aluminum Company Of America Aluminum-lithium alloys
RU1584414C (ru) * 1988-02-19 1994-10-15 Всероссийский научно-исследовательский институт авиационных материалов Сплав на основе алюминия
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
AT407404B (de) * 1998-07-29 2001-03-26 Miba Gleitlager Ag Zwischenschicht, insbesondere bindungsschicht, aus einer legierung auf aluminiumbasis
RU2163940C1 (ru) * 1999-08-09 2001-03-10 Государственное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" Сплав на основе алюминия и изделие, выполненное из него
RU2180928C1 (ru) * 2000-09-14 2002-03-27 Государственное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" Сплав на основе алюминия и изделие, выполненное из этого сплава

Also Published As

Publication number Publication date
ES2319718T1 (es) 2009-05-12
WO2007111529A1 (fr) 2007-10-04
US20090068056A1 (en) 2009-03-12
ATE455874T1 (de) 2010-02-15
DE602007004465D1 (de) 2010-03-11
EP2006403A4 (fr) 2009-03-18
EP2006403A1 (fr) 2008-12-24
ES2319718T3 (es) 2010-05-28
RU2310005C1 (ru) 2007-11-10
DE07747842T1 (de) 2009-04-30
PT2006403E (pt) 2010-04-26

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