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WO2007111529A1 - Alliage à base d'aluminium - Google Patents

Alliage à base d'aluminium Download PDF

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Publication number
WO2007111529A1
WO2007111529A1 PCT/RU2007/000109 RU2007000109W WO2007111529A1 WO 2007111529 A1 WO2007111529 A1 WO 2007111529A1 RU 2007000109 W RU2007000109 W RU 2007000109W WO 2007111529 A1 WO2007111529 A1 WO 2007111529A1
Authority
WO
WIPO (PCT)
Prior art keywords
mass
alloy
copper
magnesium
lithium
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.)
Ceased
Application number
PCT/RU2007/000109
Other languages
English (en)
Russian (ru)
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 Metallurgichesky Zavod'
Borovichsky Kombinat Ogneuporov OAO
Original Assignee
Otkrytoe Akcionernoe Obschestvo 'kamensk-Uralsky Metallurgichesky Zavod'
Borovichsky Kombinat Ogneuporov OAO
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 Metallurgichesky Zavod', Borovichsky Kombinat Ogneuporov OAO filed Critical Otkrytoe Akcionernoe Obschestvo 'kamensk-Uralsky Metallurgichesky Zavod'
Priority to EP07747842A priority Critical patent/EP2006403B1/fr
Priority to AT07747842T priority patent/ATE455874T1/de
Priority to DE07747842T priority patent/DE07747842T1/de
Priority to US11/920,090 priority patent/US20090068056A1/en
Priority to DE602007004465T priority patent/DE602007004465D1/de
Publication of WO2007111529A1 publication Critical patent/WO2007111529A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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

  • the invention relates to the field of metallurgy of aluminum-based alloys, in particular to an alloy of the aluminum-copper-magnesium-lithium system used for the manufacture of semi-finished products and articles thereof used as structural materials for aerospace engineering.
  • aluminum - lithium alloys have a unique combination of mechanical properties, namely low density, high modulus of elasticity and sufficiently high strength characteristics.
  • the presence of these properties makes it possible to use the alloys of this system as a structural material for aerospace engineering, which makes it possible to improve a number of flight technical characteristics of aircraft, in particular, reducing the mass of vehicles, saving fuel, increasing load capacity.
  • Titanium up to 0.1
  • Manganese up to 0.1
  • the closest alloy in chemical composition and purpose to the claimed aluminum-based alloy is an alloy containing, wt.%:
  • the reasons for the occurrence of the above disadvantages when using the known alloy adopted for the prototype include the fact that the known alloy is characterized by an increased copper content, which negatively affects the heat resistance and ductility during pressure treatment, which leads to increased crack formation, increased rejection by clamps and non-flatness during finishing operations, namely when ironing and dressing semi-finished products, moreover, the high content of sodium and gallium leads to a significant the magnitude of the heat capacity of the alloy, an even greater decrease in its plastic characteristics (A. V Kurdyumov, S.V. Inkin, V. S. Chulkov, G. G. Shadrin., Metallic impurities in aluminum alloys., M.:, Metallurgy. 1988, p.
  • the problem to which the invention is directed is to develop an alloy based on aluminum, intended for the manufacture of semi-finished products and products for aerospace engineering from it, free from the disadvantages of the above and inherent in known technical solutions.
  • the technical result achieved by the implementation of the invention is to obtain an alloy having increased ductility, which will increase its manufacturability, increase the yield in the manufacture of semi-finished products and products, provide the ability to produce thin sheets, thin-walled profiles and stampings while reducing the complexity of production, while maintaining the required strength and operational characteristics of the alloy, as well as semi-finished products and products from it, presented to structural materials la aerospace engineering.
  • the problem with the achievement of the aforementioned technical result in the implementation of the invention is solved by the fact that 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 the group consisting of vanadium and scandium, in the following ratio, May. %: Lithium 1.6 - 1.9
  • Calcium 0.005 - 0.02 At least one element selected from the group consisting of: Vanadium 0.005 - 0.01
  • the aluminum-based alloy used for the manufacture of semi-finished products and products differs from the prototype both quantitatively (low content of copper, gallium and sodium), and qualitatively
  • a decrease in the copper content in the alloy to the limits of 1.3 - 1.5 wt.% Allows it to be almost completely converted into a solid solution, which leads to a significant decrease in the volume fraction of coarse intermetallic compounds of copper-containing phases, which was established by electron microscopic examination of the alloy, and as a result increase the ductility of the alloy.
  • a decrease in the copper content below 1.3 wt.% Will not affect the increase in the ductility characteristics of the alloy, but will significantly reduce its strength characteristics.
  • gallium and sodium do not form phases with aluminum and accumulate at the grain boundary, which leads to brittle fracture along the grain boundary during crystallization of the alloy and its processing by pressure.
  • Alloy W 1 corresponds to the alloy adopted as a prototype, alloys N 9 2,3,4 correspond to the proposed. Melting of the charge, refining and casting of ingots was carried out at a temperature of 710 - 730 0 C.
  • Example 1
  • clad sheets were made from the flat ingots of each alloy. Sheets were made according to one technological scheme by hot rolling at a temperature of 430 0 C to a thickness of 6.5 mm. rolled up and then after annealing at a temperature of 400 0 C by cold rolling.
  • the sheet of alloy W 1 managed to be rolled only to a thickness of 0.9 mm. and further rolling was stopped due to the presence of flaws on the side edges of the sheet with a depth of more than 30 mm. and the presence of two cliffs in a roll.
  • Sheets of alloys N 1 - 2,3,4 were rolled without breaks to a thickness of 0.5 mm.
  • Samples were cut along, across and at an angle of 45 ° relative to the rolling direction.
  • Profiles from different alloys were made according to one technological scheme by pressing at a temperature of 400 0 C, followed by quenching of the profiles in water, and aging at a temperature of 150 0 C for 24 hours.
  • Stampings from different alloys were made according to one technological scheme by means of blank stamping at a temperature of 410 0 C, preliminary stamping at a temperature of 410 0 C, and after etching by final stamping at a temperature of 400 0 C, followed by quenching at a temperature of 500 0 C for 2 hours and aging at a temperature of 150 0 C for 24 hours.
  • the proposed alloy ensures the achievement of the goal - improving the ductility of the alloy, and as a result, increasing its manufacturability, increasing the yield in the production of semi-finished products and products from it, making it possible to produce thin sheets, thin-walled profiles and stampings while reducing the complexity of production and maintaining the required strength and performance characteristics of the alloy, as well as semi-finished products and products from it, presented to structural materials for I aerospace engineering.

Landscapes

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

Abstract

L'invention concerne la métallurgie des alliages à base d'aluminium du système aluminium / cuivre / magnésium / lithium, utilisés dans la fabrication de produits semi-finis et d'articles correspondants, qui sont utilisés comme matériaux de construction en industrie aérospatiale. L'invention vise à atteindre de plus grandes plasticité et technicité des alliages du système aluminium / cuivre / magnésium / lithium, à augmenter le rendement en terme de produits utiles et d'articles correspondants, à assurer la production de feuilles minces, de profilés à parois minces et de pièces embouties tout en réduisant le coefficient de main d'oeuvre nécessaire à la fabrication et en préservant les caractéristiques de résistance et d'usage, applicables aux matériaux de construction en industrie aérospatiale. Selon l'invention, l'alliage comprend un rapport de composants suivant, en % en poids : 1,6-1,9 de lithium, 1,3-1,5 de cuivre, 0,7-1,1 de magnésium, 0,04-0,2 de zirconium, 0,02-0,2 de béryllium, 0,01-0,1 de titane, 0,01-0,15 de nickel, 0,01-0,2 de manganèse, jusqu'à 0,001 de gallium, 0,01-0,3 de zinc, jusqu'à 0,0005 de sodium, 0,005-0,02 de calcium et au moins un élément choisi dans le groupe contenant du vanadium 0,005-0,01 et du scandium 0,005-0,01, le reste étant constitué d'aluminium.
PCT/RU2007/000109 2006-03-27 2007-03-07 Alliage à base d'aluminium Ceased WO2007111529A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP07747842A EP2006403B1 (fr) 2006-03-27 2007-03-07 Alliage à base d'aluminium
AT07747842T ATE455874T1 (de) 2006-03-27 2007-03-07 Legierung auf aluminiumbasis
DE07747842T DE07747842T1 (de) 2006-03-27 2007-03-07 Legierung auf aluminiumbasis
US11/920,090 US20090068056A1 (en) 2006-03-27 2007-03-07 Aluminum-based alloy
DE602007004465T DE602007004465D1 (de) 2006-03-27 2007-03-07 Legierung auf aluminiumbasis

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
RU2006109658 2006-03-27
RU2006109658/02A RU2310005C1 (ru) 2006-03-27 2006-03-27 Сплав на основе алюминия и изделие из него

Publications (1)

Publication Number Publication Date
WO2007111529A1 true WO2007111529A1 (fr) 2007-10-04

Family

ID=38541383

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/RU2007/000109 Ceased WO2007111529A1 (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) DE07747842T1 (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

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
JPH02294448A (ja) * 1989-04-21 1990-12-05 Cegedur Pechiney Rhenalu 低温変形性がすぐれかつ耐損傷性がすぐれたＡｌ―Ｌｉ―Ｃｕ―Ｍｇ合金
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

Family Cites Families (5)

* 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
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
AT407404B (de) * 1998-07-29 2001-03-26 Miba Gleitlager Ag Zwischenschicht, insbesondere bindungsschicht, aus einer legierung auf aluminiumbasis

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
JPH02294448A (ja) * 1989-04-21 1990-12-05 Cegedur Pechiney Rhenalu 低温変形性がすぐれかつ耐損傷性がすぐれたＡｌ―Ｌｉ―Ｃｕ―Ｍｇ合金
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

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
N.I. FRIDLYANDER ET AL., ALUMINUM-LITHIUM ALLOYS. STRUCTURE AND PROPERTIES, 1992, pages 177

Also Published As

Publication number Publication date
ATE455874T1 (de) 2010-02-15
US20090068056A1 (en) 2009-03-12
EP2006403A4 (fr) 2009-03-18
EP2006403A1 (fr) 2008-12-24
ES2319718T3 (es) 2010-05-28
RU2310005C1 (ru) 2007-11-10
PT2006403E (pt) 2010-04-26
ES2319718T1 (es) 2009-05-12
DE602007004465D1 (de) 2010-03-11
EP2006403B1 (fr) 2010-01-20
DE07747842T1 (de) 2009-04-30

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