EP2006403A1 - Alliage à base d'aluminium - Google Patents
Alliage à base d'aluminium Download PDFInfo
- Publication number
- EP2006403A1 EP2006403A1 EP07747842A EP07747842A EP2006403A1 EP 2006403 A1 EP2006403 A1 EP 2006403A1 EP 07747842 A EP07747842 A EP 07747842A EP 07747842 A EP07747842 A EP 07747842A EP 2006403 A1 EP2006403 A1 EP 2006403A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- alloy
- aluminum
- copper
- magnesium
- finished products
- 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.)
- Granted
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).
- 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
- Sodium up to 0.0005 Calcium 0.005 - 0.02 At least, one element selected from a group including: Vanadium 0.005 - 0.01 Scandium 0.005 - 0.01 Aluminum Remainder
- 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)
- Manufacture And Refinement Of Metals (AREA)
- Secondary Cells (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
- Superconductors And Manufacturing Methods Therefor (AREA)
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 true EP2006403A1 (fr) | 2008-12-24 |
| EP2006403A4 EP2006403A4 (fr) | 2009-03-18 |
| EP2006403B1 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) | DE07747842T1 (fr) |
| ES (1) | ES2319718T3 (fr) |
| PT (1) | PT2006403E (fr) |
| RU (1) | RU2310005C1 (fr) |
| WO (1) | WO2007111529A1 (fr) |
Families Citing this family (3)
| 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 |
| JP6676861B2 (ja) * | 2014-05-30 | 2020-04-08 | シオン・パワー・コーポレーション | 電気化学セルにおける保護層および他の構成要素として使用するためのポリマー |
Family Cites Families (10)
| 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 |
-
2006
- 2006-03-27 RU RU2006109658/02A patent/RU2310005C1/ru active
-
2007
- 2007-03-07 ES ES07747842T patent/ES2319718T3/es active Active
- 2007-03-07 DE DE07747842T patent/DE07747842T1/de active Pending
- 2007-03-07 EP EP07747842A patent/EP2006403B1/fr active Active
- 2007-03-07 PT PT07747842T patent/PT2006403E/pt unknown
- 2007-03-07 WO PCT/RU2007/000109 patent/WO2007111529A1/fr not_active Ceased
- 2007-03-07 DE DE602007004465T patent/DE602007004465D1/de active Active
- 2007-03-07 AT AT07747842T patent/ATE455874T1/de active
- 2007-03-07 US US11/920,090 patent/US20090068056A1/en not_active Abandoned
Non-Patent Citations (2)
| Title |
|---|
| No further relevant documents disclosed * |
| See also references of WO2007111529A1 * |
Also Published As
| Publication number | Publication date |
|---|---|
| ATE455874T1 (de) | 2010-02-15 |
| US20090068056A1 (en) | 2009-03-12 |
| EP2006403A4 (fr) | 2009-03-18 |
| RU2310005C1 (ru) | 2007-11-10 |
| PT2006403E (pt) | 2010-04-26 |
| EP2006403B1 (fr) | 2010-01-20 |
| DE07747842T1 (de) | 2009-04-30 |
| WO2007111529A1 (fr) | 2007-10-04 |
| ES2319718T1 (es) | 2009-05-12 |
| ES2319718T3 (es) | 2010-05-28 |
| DE602007004465D1 (de) | 2010-03-11 |
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