EP0989195A1 - Alliage à base d'alumium de type AlCuMg resistant à la chaleur - Google Patents

Alliage à base d'alumium de type AlCuMg resistant à la chaleur Download PDF

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Publication number
EP0989195A1
EP0989195A1 EP98810967A EP98810967A EP0989195A1 EP 0989195 A1 EP0989195 A1 EP 0989195A1 EP 98810967 A EP98810967 A EP 98810967A EP 98810967 A EP98810967 A EP 98810967A EP 0989195 A1 EP0989195 A1 EP 0989195A1
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EP
European Patent Office
Prior art keywords
weight
aluminum alloy
plate
max
alloy according
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
Application number
EP98810967A
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German (de)
English (en)
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EP0989195B1 (fr
Inventor
Günther Höllrigl
Christophe Jaquerod
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.)
3A Composites International AG
Original Assignee
Alcan Technology and Management Ltd
Alusuisse Lonza Services Ltd
Alusuisse Technology and Management Ltd
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Application filed by Alcan Technology and Management Ltd, Alusuisse Lonza Services Ltd, Alusuisse Technology and Management Ltd filed Critical Alcan Technology and Management Ltd
Priority to ES98810967T priority Critical patent/ES2175647T3/es
Priority to EP98810967A priority patent/EP0989195B1/fr
Priority to AT98810967T priority patent/ATE216737T1/de
Priority to PT98810967T priority patent/PT989195E/pt
Priority to DE59803924T priority patent/DE59803924D1/de
Publication of EP0989195A1 publication Critical patent/EP0989195A1/fr
Application granted granted Critical
Publication of EP0989195B1 publication Critical patent/EP0989195B1/fr
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    • 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
    • C22C21/16—Alloys based on aluminium with copper as the next major constituent with magnesium

Definitions

  • the invention relates to an aluminum alloy of the AlCuMg condition high mechanical strength and high heat resistance, which are used in the solution-annealed quenched, stretched and aged a yield stress at room temperature of Rp0.2> 450 MPa, after a pre-storage of 300 h at 160 ° C a yield stress at 160 ° C of Rp0.2> 340 MPa and after a creep load of 1000 h at 160 ° C below a tensile stress of 260 MPa has an elongation of less than 0.5%.
  • AlCuMg alloys with high mechanical strength and high heat resistance have in practice especially the alloy AA2618 and, due to its good weldability, the alloy AA2219 enforced.
  • a newer alloy of type AA2618 with good Heat resistance is known from EP-A-0756014.
  • the invention has for its object an alloy of the type AlCuMg of the type mentioned with a compared to the known alloys to create increased thermal stability according to the prior art.
  • the alloy for the production of plastic molds i.e. Injection molds for injection molding plastic, at operating temperatures up to about 160 ° C.
  • the preferred copper content is 5.2 to 5.4% by weight.
  • the maximum solubility for copper in this alloy is around 5.2 to 5.3% Cu.
  • Part of the copper is absorbed in the primary intermetallic phases AlFeMnCu, which makes it possible to practically reach the solubility limit.
  • the primary eutectic phase Al 2 Cu forms in the structure, which does not contribute to the strength, but as a local cathodic element, however, reduces the corrosion resistance of the alloy.
  • the alloy according to the invention preferably lies mainly in the phase field of the ⁇ '-precipitation hardening, with the equilibrium phase Al 2 Cu. If the magnesium content rises above 0.6%, there are corresponding proportions of S'-precipitation hardening with the equilibrium phase Al 2 CuMg.
  • the positive effect of a silver additive on precipitation hardening is preferably effective in ⁇ '-precipitation hardening because the silver can form the ⁇ phase together with the magnesium on the (111) lattice planes of the aluminum matrix, which leads to an additional increase in strength . With even higher magnesium contents, the excretion of the ⁇ phase is superimposed by the S 'excretion and reduces the strength-increasing effect of silver.
  • an alloy with higher magnesium contents is sensitive to the speed of the quenching treatment, which leads to a loss of strength in the middle of thick plates.
  • an optimum between achievable strength at room temperature and at elevated temperatures is achieved.
  • the alloy according to the invention is therefore particularly suitable for the production of thick plates.
  • the alloy can be used to further increase strength Contain 0.05 to 0.5 wt .-%, preferably 0.3 to 0.5 wt .-% silver.
  • an isotropic distribution of the internal stresses in the cross section of the plates produced by hot rolling is to be aimed for.
  • the grain size and the grain shape in the plate are of importance for the reduction of the internal stresses.
  • the finer and more uniform the crystal thaw after the recrystallization with the solution annealing preferably carried out in the range from 510 to 525 ° C., the better the internal stresses in the cross-section of the plate can balance.
  • the grain boundaries act as sinks for dislocations when local stress peaks are reduced.
  • a fine grain structure can be achieved in the hot-rolled plate by controlling the heat treatment and the hot rolling temperatures in such a way that the distribution of submicron precipitates of Al 3 Zr in the structure is as homogeneous as possible.
  • the homogenized cast ingots can either be cooled from the homogenization temperature to the holding or hot rolling temperature or heated up to this temperature range.
  • a heterogenization occurs with the elimination of the equilibrium phase Al 2 Cu.
  • the phase interfaces of the Al 2 Cu particles are formed as preferred nucleation sites for the Al 3 Zr precipitates.
  • the hot-rolled plate is subsequently heated to the solution annealing temperature, the Al 2 Cu particles dissolve and what remains is a uniform distribution of the fine, submicron Al 3 Zr precipitates, which are preferably due to the original Al 2 Cu particle boundaries and to sub-grain boundaries and thus one result in homogeneous distribution.
  • These fine Al 3 Zr particles cause a strong growth inhibition during recrystallization during solution treatment and the desired isotropic grain structure results in the plate.
  • the sum of iron and silicon has also proven to be expedient and the sum of zirconium and titanium each to max. 0.25% by weight limit.
  • the preferred content range for manganese is 0.2 to 0.4% by weight.
  • the alloy which is particularly suitable for the production of Plastic molds are suitable, starting from a casting block without kneading operations are further processed, however, the manufacturing process usually includes at least one kneading step. If it is the dimensions of a Allow shape to be produced are preferred as the starting material hot-rolled plates used. In certain cases it can also turn out to be prove expedient, for example a decrease in thickness in a first Direction by hot rolling and in a second direction by forging to create. In particular for the production of inexpensive forms for The production of mass parts can also be extrusion as a processing step be considered. The extrusion process opens up basically also the possibility of certain contours of a later form already preform.
  • Alloys A and B are according to the invention, alloys AA2618 and AA 2219 serve as reference alloys or reference materials.
  • Alloys A and B were used as continuous cast ingots on an industrial scale poured.
  • the homogenization of the cast ingots to compensate for the solidification Crystal segregation was carried out according to the usual procedure for AlCuMg alloys.
  • the ingots cooled after the homogenization annealing were raised to 410 ° C heated, held at this temperature for 3 h and then starting rolled from this temperature to a plate thickness of 70 mm. Subsequently the plates were at a temperature of 520 ° C solution annealed and subsequently in water using a defined convective Heat transfer quenched so that the resulting residual stresses were controllable by the subsequent stretching operation. The stretched Plates were then at a temperature of 180 ° C during Cured warm for 12 hours.
  • the yield stresses Rp 0.2 were determined after 300 h and 500 h pre-storage at a temperature of 160 ° C by tensile tests at room temperature (RT) and at 160 ° C on samples of the thermoset plates and on samples of the reference materials taken from commercially available plates. The results are shown in Tables 2 and 3.
  • the plates used as reference materials had a thickness of 20 mm in the case of alloy AA2618 and a thickness of 90 mm in the case of alloy AA2219.
  • the creep data were determined on round specimens with a measuring length of 160 mm. Out the strain-time diagram in Fig. 1 are the results for the four examined Alloys visible.
  • the load applied to the test bars was 260 MPa, the test temperature was set to 160 ° C.
  • the curves show clearly the improved heat resistance compared to the comparative alloys the alloy according to the invention.

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  • Chemical & Material Sciences (AREA)
  • Organic Chemistry (AREA)
  • Materials Engineering (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Conductive Materials (AREA)
  • Metal Rolling (AREA)
  • Arc Welding In General (AREA)
  • Solid-Phase Diffusion Into Metallic Material Surfaces (AREA)
  • Heat Treatment Of Articles (AREA)
  • Shaping By String And By Release Of Stress In Plastics And The Like (AREA)
  • Superconductors And Manufacturing Methods Therefor (AREA)
  • Insulated Conductors (AREA)
EP98810967A 1998-09-25 1998-09-25 Alliage à base d'alumium de type AlCuMg resistant à la chaleur Revoked EP0989195B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
ES98810967T ES2175647T3 (es) 1998-09-25 1998-09-25 Aleacion de aluminio resistente al calor del tipo alcumg.
EP98810967A EP0989195B1 (fr) 1998-09-25 1998-09-25 Alliage à base d'alumium de type AlCuMg resistant à la chaleur
AT98810967T ATE216737T1 (de) 1998-09-25 1998-09-25 Warmfeste aluminiumlegierung vom typ alcumg
PT98810967T PT989195E (pt) 1998-09-25 1998-09-25 Liga de aluminio resistente ao calor do tigo alcumg
DE59803924T DE59803924D1 (de) 1998-09-25 1998-09-25 Warmfeste Aluminiumlegierung vom Typ AlCuMg

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP98810967A EP0989195B1 (fr) 1998-09-25 1998-09-25 Alliage à base d'alumium de type AlCuMg resistant à la chaleur

Publications (2)

Publication Number Publication Date
EP0989195A1 true EP0989195A1 (fr) 2000-03-29
EP0989195B1 EP0989195B1 (fr) 2002-04-24

Family

ID=8236350

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98810967A Revoked EP0989195B1 (fr) 1998-09-25 1998-09-25 Alliage à base d'alumium de type AlCuMg resistant à la chaleur

Country Status (5)

Country Link
EP (1) EP0989195B1 (fr)
AT (1) ATE216737T1 (fr)
DE (1) DE59803924D1 (fr)
ES (1) ES2175647T3 (fr)
PT (1) PT989195E (fr)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2004018721A1 (fr) * 2002-08-20 2004-03-04 Corus Aluminium Walzprodukte Gmbh Alliage al-cu de grande durete
US6777106B2 (en) 2001-04-24 2004-08-17 Pechiney Rhenalu Metal blocks suitable for machining applications
WO2008003503A2 (fr) * 2006-07-07 2008-01-10 Aleris Aluminum Koblenz Gmbh Produits en alliage d'aluminium série aa2000, et procédé de fabrication correspondant
US7323068B2 (en) 2002-08-20 2008-01-29 Aleris Aluminum Koblenz Gmbh High damage tolerant Al-Cu alloy
CN100469928C (zh) * 2007-03-30 2009-03-18 中南大学 一种高强耐热铝合金及其管材的制备方法
US7604704B2 (en) 2002-08-20 2009-10-20 Aleris Aluminum Koblenz Gmbh Balanced Al-Cu-Mg-Si alloy product
US8043445B2 (en) 2003-06-06 2011-10-25 Aleris Aluminum Koblenz Gmbh High-damage tolerant alloy product in particular for aerospace applications
CN105274408A (zh) * 2015-10-15 2016-01-27 东北轻合金有限责任公司 一种航空航天用铝合金铆钉线材的制造方法
CN109825749A (zh) * 2019-04-10 2019-05-31 上海裕纪金属制品有限公司 一种可冲压铝合金型材耐热耐腐蚀热处理方法及铝合金型材
CN109898000A (zh) * 2019-03-29 2019-06-18 郑州轻研合金科技有限公司 一种超高强耐热铝合金及其制备方法
US10472707B2 (en) 2003-04-10 2019-11-12 Aleris Rolled Products Germany Gmbh Al—Zn—Mg—Cu alloy with improved damage tolerance-strength combination properties
CN115874031A (zh) * 2022-12-07 2023-03-31 东北轻合金有限责任公司 一种航空用2a12铝合金板材的加工方法

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7883591B2 (en) 2004-10-05 2011-02-08 Aleris Aluminum Koblenz Gmbh High-strength, high toughness Al-Zn alloy product and method for producing such product

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0224016A1 (fr) * 1985-10-31 1987-06-03 BBC Brown Boveri AG Alliage d'aluminium forgeable du type Al-Cu-Mg à haute résistance dans la gamme des températures entre 0 et 250o C
WO1995027091A1 (fr) * 1994-03-30 1995-10-12 Reynolds Metals Company Procede de fabrication de pieces extrudees d'alliage d'aluminium
WO1996029440A1 (fr) * 1995-03-21 1996-09-26 Kaiser Aluminum & Chemical Corporation Procede de fabrication de toles d'aluminium pour l'aeronautique
EP0756017A1 (fr) * 1995-07-28 1997-01-29 Pechiney Rhenalu Alliage aluminium-cuivre-magnésium alloy à résistance élevée au fluage
US5630889A (en) * 1995-03-22 1997-05-20 Aluminum Company Of America Vanadium-free aluminum alloy suitable for extruded aerospace products
US5652063A (en) * 1995-03-22 1997-07-29 Aluminum Company Of America Sheet or plate product made from a substantially vanadium-free aluminum alloy
US5800927A (en) * 1995-03-22 1998-09-01 Aluminum Company Of America Vanadium-free, lithium-free, aluminum alloy suitable for sheet and plate aerospace products

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0224016A1 (fr) * 1985-10-31 1987-06-03 BBC Brown Boveri AG Alliage d'aluminium forgeable du type Al-Cu-Mg à haute résistance dans la gamme des températures entre 0 et 250o C
WO1995027091A1 (fr) * 1994-03-30 1995-10-12 Reynolds Metals Company Procede de fabrication de pieces extrudees d'alliage d'aluminium
WO1996029440A1 (fr) * 1995-03-21 1996-09-26 Kaiser Aluminum & Chemical Corporation Procede de fabrication de toles d'aluminium pour l'aeronautique
US5630889A (en) * 1995-03-22 1997-05-20 Aluminum Company Of America Vanadium-free aluminum alloy suitable for extruded aerospace products
US5652063A (en) * 1995-03-22 1997-07-29 Aluminum Company Of America Sheet or plate product made from a substantially vanadium-free aluminum alloy
US5800927A (en) * 1995-03-22 1998-09-01 Aluminum Company Of America Vanadium-free, lithium-free, aluminum alloy suitable for sheet and plate aerospace products
EP0756017A1 (fr) * 1995-07-28 1997-01-29 Pechiney Rhenalu Alliage aluminium-cuivre-magnésium alloy à résistance élevée au fluage

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
ANYALEBECHI P N ET AL: "EFFECT OF SUPEREUTECTIC HOMOGENIZATION ON INCIDENCE OF POROSITY IN ALUMINUM ALLOY 2014 INGOT", METALLURGICAL AND MATERIALS TRANSACTIONS B: PROCESS METALLURGY & MATERIALS PROCESSING SCIENCE, vol. 25B, no. 1, 1 February 1994 (1994-02-01), pages 111 - 122, XP000425868 *
M.J.HAYNES AND R.P.GANGLOFF: "ELEVATED TEMPERATURE FRACTURE TOUGHNESS OF Al-Cu-Mg-Ag SHEET: CHARACTERIZATION AND MODELING", METALLURGICAL AND MATERIALS TRANSACTIONS, vol. 28A, no. 9, pages 1815 - 1829, XP002087749 *

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6777106B2 (en) 2001-04-24 2004-08-17 Pechiney Rhenalu Metal blocks suitable for machining applications
GB2406578A (en) * 2002-08-20 2005-04-06 Corus Aluminium Walzprod Gmbh Al-Cu Alloy with high toughness
GB2406578B (en) * 2002-08-20 2006-04-26 Corus Aluminium Walzprod Gmbh Al-Cu alloy with high toughness
CN1325682C (zh) * 2002-08-20 2007-07-11 克里斯铝轧制品有限公司 具有高韧性的Al－Cu合金
WO2004018721A1 (fr) * 2002-08-20 2004-03-04 Corus Aluminium Walzprodukte Gmbh Alliage al-cu de grande durete
US7323068B2 (en) 2002-08-20 2008-01-29 Aleris Aluminum Koblenz Gmbh High damage tolerant Al-Cu alloy
US7494552B2 (en) 2002-08-20 2009-02-24 Aleris Aluminum Koblenz Gmbh Al-Cu alloy with high toughness
US7604704B2 (en) 2002-08-20 2009-10-20 Aleris Aluminum Koblenz Gmbh Balanced Al-Cu-Mg-Si alloy product
US7815758B2 (en) 2002-08-20 2010-10-19 Aleris Aluminum Koblenz Gmbh High damage tolerant Al-Cu alloy
US10472707B2 (en) 2003-04-10 2019-11-12 Aleris Rolled Products Germany Gmbh Al—Zn—Mg—Cu alloy with improved damage tolerance-strength combination properties
US8043445B2 (en) 2003-06-06 2011-10-25 Aleris Aluminum Koblenz Gmbh High-damage tolerant alloy product in particular for aerospace applications
DE112004000995B4 (de) 2003-06-06 2021-12-16 Corus Aluminium Walzprodukte Gmbh Hoch schadenstolerantes Aluminiumlegierungsprodukt, insbesondere für Luft- und Raumfahrtanwendungen
WO2008003503A2 (fr) * 2006-07-07 2008-01-10 Aleris Aluminum Koblenz Gmbh Produits en alliage d'aluminium série aa2000, et procédé de fabrication correspondant
RU2443798C2 (ru) * 2006-07-07 2012-02-27 Алерис Алюминум Кобленц Гмбх Способ производства продуктов из алюминиевых сплавов серии аа2000
WO2008003503A3 (fr) * 2006-07-07 2008-02-21 Aleris Aluminum Koblenz Gmbh Produits en alliage d'aluminium série aa2000, et procédé de fabrication correspondant
CN100469928C (zh) * 2007-03-30 2009-03-18 中南大学 一种高强耐热铝合金及其管材的制备方法
CN105274408A (zh) * 2015-10-15 2016-01-27 东北轻合金有限责任公司 一种航空航天用铝合金铆钉线材的制造方法
CN109898000A (zh) * 2019-03-29 2019-06-18 郑州轻研合金科技有限公司 一种超高强耐热铝合金及其制备方法
CN109825749A (zh) * 2019-04-10 2019-05-31 上海裕纪金属制品有限公司 一种可冲压铝合金型材耐热耐腐蚀热处理方法及铝合金型材
CN115874031A (zh) * 2022-12-07 2023-03-31 东北轻合金有限责任公司 一种航空用2a12铝合金板材的加工方法
CN115874031B (zh) * 2022-12-07 2023-08-15 东北轻合金有限责任公司 一种航空用2a12铝合金板材的加工方法

Also Published As

Publication number Publication date
EP0989195B1 (fr) 2002-04-24
PT989195E (pt) 2002-08-30
DE59803924D1 (de) 2002-05-29
ATE216737T1 (de) 2002-05-15
ES2175647T3 (es) 2002-11-16

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