EP0224016B1 - 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

Info

Publication number
EP0224016B1
EP0224016B1 EP86114458A EP86114458A EP0224016B1 EP 0224016 B1 EP0224016 B1 EP 0224016B1 EP 86114458 A EP86114458 A EP 86114458A EP 86114458 A EP86114458 A EP 86114458A EP 0224016 B1 EP0224016 B1 EP 0224016B1
Authority
EP
European Patent Office
Prior art keywords
weight
gew
alloy
aluminium alloy
temperature
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.)
Expired
Application number
EP86114458A
Other languages
German (de)
English (en)
Other versions
EP0224016A1 (fr
Inventor
Ian James Prof. Dr. Polmear
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.)
BBC Brown Boveri AG Switzerland
Original Assignee
BBC Brown Boveri AG Switzerland
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 BBC Brown Boveri AG Switzerland filed Critical BBC Brown Boveri AG Switzerland
Publication of EP0224016A1 publication Critical patent/EP0224016A1/fr
Application granted granted Critical
Publication of EP0224016B1 publication Critical patent/EP0224016B1/fr
Expired legal-status Critical Current

Links

Images

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

Definitions

  • the invention is based on a wrought aluminum alloy according to the preamble of claim 1.
  • Aluminum alloys of the AUCu / 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 the US standard). These alloys are usually the result of appropriate casting alloys with nickel additives. However, since they suffer a comparatively well-defined drop in strength above 150 ° C, it is not actually possible to speak of "heat-resistant" aluminum alloys in today's sense. 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.
  • 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. First, the test specimens thus obtained were 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 from approx. 4 to 7h curing time. Curing temperature 195 ° C. Curve 4.
  • the alloy specimens 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 temperature of 205 ° C for a period of 2 hours.
  • an aluminum alloy corresponding to this example was melted.
  • 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 given by the requirement to avoid local melting by the occurrence 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 created 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.

Landscapes

  • 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)
  • Continuous Casting (AREA)
  • Adornments (AREA)
  • Forging (AREA)

Claims (4)

1. Alliage d'aluminium forgeable du type AI/Cu/Mg à haute résistance dans le domaine de température compris entre 0 et 250°C, caractérisé en ce qu'il présente la composition pondérale suivante:
Cu = 5,0 à 7,0%
Mg = 0,3 à 0,8%
Ag = 0,2 à 1,0%
Mn = 0,3 à 1,0%
Zr = 0,1 à 0,25%
V = 0,05 à 0,15%
Si < 0,10%
AI = reste, plus maximum 0,25% d'impuretés.
2. Alliage d'aluminium forgeable suivant la revendication 1, caractérisé en ce qu'il présente la composition pondérale suivante:
Cu = 5,5 à 6,5%
Mg = 0,4 à 0,6%
Ag = 0,2 à 0,8%
Mn = 0,3 à 0,8%
Zr=0,1 à 0,2%
V = 0,05 à 0,15%
Si < 0,05%
AI = reste, plus maximum 0,25% d'impuretés.
3. Alliage d'aluminium forgeable suivant la revendication 1, caractérisé en ce qu'il présente la composition pondérale suivante:
Cu = 6,0%
Mg = 0,5%
Ag = 0,4%
Mn = 0,5%
Zr = 0,15%
V=0,10%
Si < 0,05%
AI = reste, plus maximum 0,25% d'impuretés.
4. Alliage d'aluminium forgeable suivant la revendication 1, caractérisé en ce que, dans l'état obtenu après recuit de mise en solution, trempe dans l'eau froide et maintien à chaud pour un durcissement par précipitation, il présente à la température ambiante une limite d'élasticité à 0,2% d'au moins 510 MPa et une charge de rupture d'au moins 575 MPa et à une température de 200°C après un maintien de 0,5 h une limite d'élasticité à 0,2% d'au moins 390 MPa et une charge de rupture d'au moins 405 MPa.
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
CH4696/85 1985-10-31
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.

Publications (2)

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

Family

ID=4280915

Family Applications (1)

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)

Families Citing this family (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5122339A (en) * 1987-08-10 1992-06-16 Martin Marietta Corporation Aluminum-lithium welding alloys
US5032359A (en) * 1987-08-10 1991-07-16 Martin Marietta Corporation Ultra high strength weldable aluminum-lithium alloys
US5259897A (en) * 1988-08-18 1993-11-09 Martin Marietta Corporation Ultrahigh strength Al-Cu-Li-Mg alloys
US5455003A (en) * 1988-08-18 1995-10-03 Martin Marietta Corporation Al-Cu-Li alloys with improved cryogenic fracture toughness
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
US5462712A (en) * 1988-08-18 1995-10-31 Martin Marietta Corporation High strength Al-Cu-Li-Zn-Mg alloys
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
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
US5630889A (en) * 1995-03-22 1997-05-20 Aluminum Company Of America Vanadium-free aluminum alloy suitable for extruded aerospace products
FR2737224B1 (fr) 1995-07-28 1997-10-17 Aerospatiale Element de structure d'aeronef, et notamment d'avion supersonique, en alliage d'aluminium presentant une longue duree de vie, une bonne tolerance aux dommages et une bonne resistance a la corrosion sous contrainte
ES2175647T3 (es) * 1998-09-25 2002-11-16 Alcan Tech & Man Ag Aleacion de aluminio resistente al calor del tipo alcumg.
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
CA2523674C (fr) * 2003-05-28 2015-01-13 Pechiney Rolled Products Alliage al-cu-mg-ag-mn destine a des applications structurales necessitant une resistance et une ductilite ameliorees
US8043445B2 (en) 2003-06-06 2011-10-25 Aleris Aluminum Koblenz Gmbh High-damage tolerant alloy product in particular for aerospace applications
DE60309711T2 (de) * 2003-09-26 2007-09-13 Kabushiki Kaisha Kobe Seiko Sho, Kobe Aluminiumlegierungsschmiedematerial mit ausgezeichneter Hochtemperaturermüdungsfestigkeit
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
US8118950B2 (en) 2007-12-04 2012-02-21 Alcoa Inc. Aluminum-copper-lithium alloys
WO2010085678A1 (fr) 2009-01-22 2010-07-29 Alcoa Inc. Alliages améliorés 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

Family Cites Families (7)

* 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
JPS4838282A (fr) * 1971-09-18 1973-06-05
JPS5128562A (ja) * 1974-09-05 1976-03-10 Mitsubishi Heavy Ind Ltd Atsuenkyoatsukasochi
US3925067A (en) * 1974-11-04 1975-12-09 Alusuisse High strength aluminum base casting alloys possessing improved machinability
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

Also Published As

Publication number Publication date
EP0224016A1 (fr) 1987-06-03
DE3665487D1 (en) 1989-10-12
CH668269A5 (de) 1988-12-15
JPS62112748A (ja) 1987-05-23
US4772342A (en) 1988-09-20

Similar Documents

Publication Publication Date Title
EP0224016B1 (fr) Alliage d&#39;aluminium forgeable du type Al-Cu-Mg à haute résistance dans la gamme des températures entre 0 et 250o C
DE69326838T3 (de) Zähe aluminiumlegierung mit kupfer und magnesium
DE60123065T2 (de) Titanlegierung und wärmebehandlungsverfahren für grossdimensionale, halbfertige materialien aus dieser legierung
AT502310B1 (de) Eine al-zn-mg-cu-legierung
DE2303802C3 (de) Verfahren zum Erhöhen der Festigkeit und Zähigkeit von dispersionsverfestigten Knetlegierungen
EP0918095B1 (fr) Procédé de fabrication d&#39;un élément de structure en alliage d&#39;aluminium moulé sous pression
DE2264997A1 (de) Ausscheidungshaertbare nickel-, eisenlegierung
DE3445767A1 (de) Verfahren zum Schmieden von Superlegierungen auf Nickelbasis sowie ein Gegenstand aus einer Superlegierung auf Nickelbasis mit verbesserter Schmiedbarkeit
DE4436481C2 (de) Verfahren zur Herstellung eines Schmiedestücks aus einer Aluminiumlegierung
DE4103934A1 (de) Fuer kolben geeignete aluminiumlegierung
WO2017182102A1 (fr) Alliage de coulée sous pression
DE69825414T2 (de) Aluminium-Legierung und Verfahren zu ihrer Herstellung
EP0554808B1 (fr) Procédé de fabrication des pièces métalliques
EP1518000A1 (fr) Alliage al-cu-mg-ag avec si, produit semi-fini realise a partir de cet alliage, et procede de realisation d&#39;un produit semi-fini de ce type
EP2236637A2 (fr) Corps coulé sous pression en alliage d&#39;aluminium-silicium-fonte hypereutectrique et son procédé de fabrication
WO2017174185A1 (fr) Alliage d&#39;aluminium destiné notamment à un procédé de coulée, et procédé de fabrication d&#39;une pièce dans un tel alliage d&#39;aluminium
US4732610A (en) Al-Zn-Mg-Cu powder metallurgy alloy
EP1645647B1 (fr) Alliage d&#39;aluminium à vieillissement à froid et procédé de fabrication d&#39;une pièce coulée
WO2003008655A2 (fr) Piece moulee realisee en matiere gamma-ti-al intermetallique
EP0828008B1 (fr) Alliage d&#39;aluminium avec une bonne usinabilité
DE1483228B2 (de) Aluminiumlegierung mit hoher zeitstandfestigkeit
EP0219629A1 (fr) Alliage d&#39;aluminium résistant aux températures élevées et son procédé de préparation
EP0918096A1 (fr) Elément de structure en alliage à aluminium moulé sous pression
EP0702094A1 (fr) Utilisation d&#39;un alliage de cuivre durcissable
EP0042455B1 (fr) Alliages à base de cuivre, contenant de l&#39;aluminium et du cobalt et présentant une bonne résistance à l&#39;usure; procédé pour la fabrication de ces alliages

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): CH DE FR GB LI

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: BBC BROWN BOVERI AG

17P Request for examination filed

Effective date: 19871005

17Q First examination report despatched

Effective date: 19881012

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): CH DE FR GB LI

REF Corresponds to:

Ref document number: 3665487

Country of ref document: DE

Date of ref document: 19891012

ET Fr: translation filed
GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 19990913

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: CH

Payment date: 19990915

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 19990920

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 19990927

Year of fee payment: 14

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20001018

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20001031

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20001031

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20001018

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20010629

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20010703

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST