EP0224016A1 - Alliage d'aluminium forgeable du type Al-Cu-Mg à haute résistance dans la gamme des températures entre 0 et 250o C - Google Patents

Alliage d'aluminium forgeable du type Al-Cu-Mg à haute résistance dans la gamme des températures entre 0 et 250o C Download PDF

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Publication number
EP0224016A1
EP0224016A1 EP86114458A EP86114458A EP0224016A1 EP 0224016 A1 EP0224016 A1 EP 0224016A1 EP 86114458 A EP86114458 A EP 86114458A EP 86114458 A EP86114458 A EP 86114458A EP 0224016 A1 EP0224016 A1 EP 0224016A1
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EP
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Prior art keywords
weight
alloy
temperature
mpa
strength
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Granted
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EP86114458A
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German (de)
English (en)
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EP0224016B1 (fr
Inventor
Ian James Prof. Dr. Polmear
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BBC Brown Boveri AG Switzerland
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BBC Brown Boveri AG Switzerland
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    • 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

Definitions

  • the invention is based on a wrought aluminum alloy according to the preamble of claim 1.
  • Aluminum alloys of the Al / Cu / Mg type have been known for decades. Attempts have been made again and again to improve this classic hardenable alloy with further additives and to adapt its properties optimally to the respective intended use. Alloying silver to cast alloys of this type has been proposed, inter alia, to improve strength properties (see, e.g., US-A-3,288,601; US-A-3,475,166; US-A-3,925,067). Similar proposals have also been made in the field of wrought alloys (see GB-A-1 320 271). The alloys have other additives to improve the structure, e.g. Manganese, titanium etc.
  • Al / Cu / Mg wrought alloys with additions of iron and nickel have been developed for operating temperatures up to about 100 ... 150 ° C (see alloy 2618 according to US standard). These alloys are mostly made from corresponding cast alloys with nickel additives. However, since they are above 150 ° C suffer a comparatively pronounced drop in strength, in today's sense, one cannot really speak of "heat-resistant" aluminum alloys. The known alloys do not fully exploit the possibilities of improving the strength properties. In particular, they do not meet the requirements at higher temperatures (up to, for example, 250 ° C.), as are required for numerous technical uses.
  • the invention is based on the object of specifying an aluminum wrought alloy which can be produced by melt metallurgy using simple, conventional methods and which in the temperature range from 0 to 250 ° C. in the hardened state has significantly higher strength properties than conventional alloys.
  • the Brinell hardness as a function of the Ag content of an Al / Cu / Ag or Al / Cu / Mg / Ag alloy is shown diagrammatically in FIG. 1.
  • the Mg content is plotted as a parameter.
  • Curve 1 relates to a Mg-free alloy, curve 2 to a Mg content of 0.3% by weight, curve 3 to 0.4% by weight and curve 4 to 0.5% by weight.
  • the alloy had a constant proportion of 6.3% by weight of Cu; Rest aluminum.
  • the values refer to the state obtained after solution heat treatment, water quenching and heat curing. With increasing content of alloying elements, the Brinell hardness rose to a flat maximum.
  • Fig. 3 the course of the yield point (0.2% limit, corresponding to curve 7) and the tensile strength (corresponding to curve 8) as a function of the test temperature under the assumption of a holding time of 0.5 hours at this temperature for a new alloy in Comparison with two known, commercial alloys.
  • the composition of the new alloy corresponded to that which was described under Fig. 2.
  • the composition of the comparative alloy No. 2618 can be found in the description of FIG. 2.
  • Curve 9 relates to the course of the yield point (0.2% limit) of alloy No. 2618, curve 10 to that of alloy No. 2219.
  • the values of the yield point of the new alloy are significantly higher than those of the known, commercial alloys.
  • FIG. 4 shows a representation of the creep rupture strength at 180 ° C. for a new alloy in comparison to a known, commercial alloy.
  • the new alloy had the composition shown in Fig. 2, while the comparative alloy was No. 2618 described above.
  • Curve 11 relates to the new alloy, while curve 12 applies to the known alloy No. 2618.
  • the achieved values of the new alloy are consistently approx. 20% higher than those of the comparison alloy.
  • the pure elements were melted down as raw materials for the components aluminum, copper, magnesium and silver.
  • the purity of the aluminum was 99.9%.
  • the components manganese, zirconium and vanadium were added as aluminum master alloys, each with 50% by weight of the element in question.
  • the total melted mass was approx. 2 kg.
  • the melt was brought to a casting temperature of 740 ° C. and poured into a slightly conical, water-cooled copper mold.
  • the raw cast ingot had a smallest diameter of approx. 70 mm and a height of approx. 160 mm. After cooling, it was homogenized at a temperature of 485 ° C. for 24 hours.
  • cylindrical pressing bolts 36 mm in diameter and 36 mm high were screwed out of the ingot. These were pressed individually on an extrusion press at a temperature of 420 ° C. to form a round rod with a diameter of 9 mm.
  • the effective reduction ratio was 13: 1. Sections of 50 mm in length were cut off from this bar and further processed individually. At first they were so The test specimen is subjected to solution heat treatment at a temperature of 530 ° C. for a period of 3 hours and then quenched in cold water. The test specimens were then cured for 7 hours at a temperature of 195 ° C. (hot aging).
  • the strength properties were tested both at room and at elevated temperatures after a previous holding time of 0.5 h or 1000 h at the relevant test temperature.
  • the results for the 0.5 hour hold time are shown in the diagrams corresponding to FIGS. 2, 3 and 4. This results in the following values: Brinell hardness HB: Flat maximum of 165 units in the range of approx. 4 to 7h curing time. Curing temperature 195 ° C. Curve 4. Yield point (0.2% limit): curve 6: Test temperature: 20 200 250 ° C Yield strength: 518 393 303 MPa The elongation was 7.5% at 20 ° C and 11.0% at 200 ° C.
  • the specimens of the alloy were solution annealed at a temperature of 533 ° C and quenched in boiling water.
  • the thermosetting was carried out at 175 ° C for a period of 50 hours.
  • the specimens of the alloy were solution annealed at a temperature of 525 ° C and quenched in cold water. The heat curing took place at a tempera at 205 ° C for 2 hours.
  • the melt was brought to a temperature of 700 ° C. and atomized to fine powder in a device using a gas jet.
  • the gas was nitrogen, which was under a pressure of 60 bar.
  • the fine-grained powder produced only the fractions with a particle diameter below 50 ⁇ m were used further.
  • the powder was poured into aluminum cans and degassed at 450 ° C. for 5 hours. Then the filled cans were hot-pressed and the press bolts produced in this way were further processed in an extrusion press at 420 ° C. into bars with a diameter of 9 mm. The material was 100% density. Sections of the bars were then solution annealed at a temperature of 530 ° C for 3 hours and then quenched in cold water. The test specimens were aged at 195 ° C for 7 hours. The maximum strength was reached after about 5 hours. The mechanical properties of the test specimens produced by powder metallurgy were on average still slightly higher than those produced by melt metallurgy.
  • the additional impurities to be accepted in the industrial manufacture of the alloys should remain as low as possible and should not exceed a total of 0.25% by weight for all elements taken together.
  • the silicon content should be kept as low as possible to avoid the formation of low-melting eutectics in the grain boundaries.
  • intermetallic compounds with the magnesium which would mean a loss of the latter metal for its beneficial effect together with silver, should be switched off (see FIG. 1).
  • the silicon content should therefore remain below 0.10% by weight.
  • the transition metals manganese, zircon and vanadium serve to refine the grain and form intermetallic phases, which, in finely divided form, cause dispersion hardening and, above all, contribute to increasing the heat resistance.
  • Solution annealing is preferably carried out in the temperature range from 528 to 533 ° C., the upper temperature limit being local due to the requirement of avoidance melting is given by the appearance of low-melting phases.
  • the heat curing can be carried out in various ways by using the temperature / time relationship. This is preferably done according to the following scheme:
  • the wrought alloys according to the invention have been used to produce light materials which have good strength properties, in particular in the temperature range from room temperature to 250 ° C., and which can be easily produced by conventional melt metallurgical methods.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Manufacture Of Metal Powder And Suspensions Thereof (AREA)
  • Adornments (AREA)
  • Continuous Casting (AREA)
  • Forging (AREA)
EP86114458A 1985-10-31 1986-10-18 Alliage d'aluminium forgeable du type Al-Cu-Mg à haute résistance dans la gamme des températures entre 0 et 250o C Expired EP0224016B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH4696/85A CH668269A5 (de) 1985-10-31 1985-10-31 Aluminium-knetlegierung des typs al/cu/mg mit hoher festigkeit im temperaturbereich zwischen 0 und 250 c.
CH4696/85 1985-10-31

Publications (2)

Publication Number Publication Date
EP0224016A1 true EP0224016A1 (fr) 1987-06-03
EP0224016B1 EP0224016B1 (fr) 1989-09-06

Family

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Application Number Title Priority Date Filing Date
EP86114458A Expired EP0224016B1 (fr) 1985-10-31 1986-10-18 Alliage d'aluminium forgeable du type Al-Cu-Mg à haute résistance dans la gamme des températures entre 0 et 250o C

Country Status (5)

Country Link
US (1) US4772342A (fr)
EP (1) EP0224016B1 (fr)
JP (1) JPS62112748A (fr)
CH (1) CH668269A5 (fr)
DE (1) DE3665487D1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5259897A (en) * 1988-08-18 1993-11-09 Martin Marietta Corporation Ultrahigh strength Al-Cu-Li-Mg alloys
EP0756016A1 (fr) 1995-07-28 1997-01-29 AEROSPATIALE Société Nationale Industrielle Elément de structure d'aéronef, et notamment d'avion supersonique, en alliage d'aluminium présentant une longue durée de vie, une bonne tolerance aux dommages et une bonne résistance à la corrosion sous contrainte
WO1998039494A1 (fr) * 1995-12-26 1998-09-11 Aluminum Company Of America Alliage d'aluminium exempt de vanadium convenant pour des produits a base de feuille ou de tole du domaine aerospatial
EP0989195A1 (fr) * 1998-09-25 2000-03-29 Alusuisse Technology & Management AG Alliage à base d'alumium de type AlCuMg resistant à la chaleur

Families Citing this family (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5032359A (en) * 1987-08-10 1991-07-16 Martin Marietta Corporation Ultra high strength weldable aluminum-lithium alloys
US5122339A (en) * 1987-08-10 1992-06-16 Martin Marietta Corporation Aluminum-lithium welding 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
US5455003A (en) * 1988-08-18 1995-10-03 Martin Marietta Corporation Al-Cu-Li alloys with improved cryogenic fracture toughness
US5085830A (en) * 1989-03-24 1992-02-04 Comalco Aluminum Limited Process for making aluminum-lithium alloys of high toughness
US5211910A (en) * 1990-01-26 1993-05-18 Martin Marietta Corporation Ultra high strength aluminum-base alloys
US5376192A (en) * 1992-08-28 1994-12-27 Reynolds Metals Company High strength, high toughness aluminum-copper-magnesium-type aluminum alloy
US5630889A (en) * 1995-03-22 1997-05-20 Aluminum Company Of America Vanadium-free aluminum alloy suitable for extruded aerospace products
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
US6645321B2 (en) 1999-09-10 2003-11-11 Geoffrey K. Sigworth Method for grain refinement of high strength aluminum casting alloys
US6368427B1 (en) 1999-09-10 2002-04-09 Geoffrey K. Sigworth Method for grain refinement of high strength aluminum casting alloys
US6902699B2 (en) * 2002-10-02 2005-06-07 The Boeing Company Method for preparing cryomilled aluminum alloys and components extruded and forged therefrom
US7435306B2 (en) * 2003-01-22 2008-10-14 The Boeing Company Method for preparing rivets from cryomilled aluminum alloys and rivets produced thereby
BRPI0410713B1 (pt) * 2003-05-28 2018-04-03 Constellium Rolled Products Ravenswood, Llc Membro estrutural de aeronave
US8043445B2 (en) * 2003-06-06 2011-10-25 Aleris Aluminum Koblenz Gmbh High-damage tolerant alloy product in particular for aerospace applications
EP1522600B1 (fr) * 2003-09-26 2006-11-15 Kabushiki Kaisha Kobe Seiko Sho Alliage d' Aluminium forgé à haute résistance en fatigue
US7922841B2 (en) * 2005-03-03 2011-04-12 The Boeing Company Method for preparing high-temperature nanophase aluminum-alloy sheets and aluminum-alloy sheets prepared thereby
CA2707311C (fr) 2007-12-04 2017-09-05 Alcoa Inc. Alliages d'aluminium-cuivre-lithium ameliores
CA2750394C (fr) 2009-01-22 2015-12-08 Alcoa Inc. Alliages ameliores d'aluminium-cuivre contenant du vanadium
US9347558B2 (en) 2010-08-25 2016-05-24 Spirit Aerosystems, Inc. Wrought and cast aluminum alloy with improved resistance to mechanical property degradation
US10266933B2 (en) 2012-08-27 2019-04-23 Spirit Aerosystems, Inc. Aluminum-copper alloys with improved strength
CN103725998A (zh) * 2013-12-20 2014-04-16 合肥工业大学 一种提高Al-Cu-Mg合金强度的方法
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
CN111926226B (zh) * 2020-08-12 2021-12-14 烟台南山学院 一种高强塑性铝合金及其制备方法
US20220170138A1 (en) * 2020-12-02 2022-06-02 GM Global Technology Operations LLC Aluminum alloy for casting and additive manufacturing of engine components for high temperature applications

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3288601A (en) * 1966-03-14 1966-11-29 Merton C Flemings High-strength aluminum casting alloy containing copper-magnesium-silconsilver
US3475166A (en) * 1969-01-15 1969-10-28 Electronic Specialty Co Aluminum base alloy
GB1320271A (en) * 1971-01-29 1973-06-13 Atomic Energy Authority Uk Aluminium alloys
US3925067A (en) * 1974-11-04 1975-12-09 Alusuisse High strength aluminum base casting alloys possessing improved machinability

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS4838282A (fr) * 1971-09-18 1973-06-05
JPS5128562A (ja) * 1974-09-05 1976-03-10 Mitsubishi Heavy Ind Ltd Atsuenkyoatsukasochi
JPS59123735A (ja) * 1982-12-30 1984-07-17 Sumitomo Light Metal Ind Ltd 電気抵抗を高めた構造用低放射化アルミニウム合金

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3288601A (en) * 1966-03-14 1966-11-29 Merton C Flemings High-strength aluminum casting alloy containing copper-magnesium-silconsilver
US3475166A (en) * 1969-01-15 1969-10-28 Electronic Specialty Co Aluminum base alloy
GB1320271A (en) * 1971-01-29 1973-06-13 Atomic Energy Authority Uk Aluminium alloys
US3925067A (en) * 1974-11-04 1975-12-09 Alusuisse High strength aluminum base casting alloys possessing improved machinability

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5259897A (en) * 1988-08-18 1993-11-09 Martin Marietta Corporation Ultrahigh strength Al-Cu-Li-Mg alloys
EP0756016A1 (fr) 1995-07-28 1997-01-29 AEROSPATIALE Société Nationale Industrielle Elément de structure d'aéronef, et notamment d'avion supersonique, en alliage d'aluminium présentant une longue durée de vie, une bonne tolerance aux dommages et une bonne résistance à la corrosion sous contrainte
WO1998039494A1 (fr) * 1995-12-26 1998-09-11 Aluminum Company Of America Alliage d'aluminium exempt de vanadium convenant pour des produits a base de feuille ou de tole du domaine aerospatial
EP0989195A1 (fr) * 1998-09-25 2000-03-29 Alusuisse Technology & Management AG Alliage à base d'alumium de type AlCuMg resistant à la chaleur

Also Published As

Publication number Publication date
EP0224016B1 (fr) 1989-09-06
US4772342A (en) 1988-09-20
CH668269A5 (de) 1988-12-15
DE3665487D1 (en) 1989-10-12
JPS62112748A (ja) 1987-05-23

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