EP0756017B1 - Alliage aluminium-cuivre-magnésium à résistance élevée au fluage - Google Patents

Alliage aluminium-cuivre-magnésium à résistance élevée au fluage Download PDF

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Publication number
EP0756017B1
EP0756017B1 EP96420235A EP96420235A EP0756017B1 EP 0756017 B1 EP0756017 B1 EP 0756017B1 EP 96420235 A EP96420235 A EP 96420235A EP 96420235 A EP96420235 A EP 96420235A EP 0756017 B1 EP0756017 B1 EP 0756017B1
Authority
EP
European Patent Office
Prior art keywords
alloy
alloys
creep
creep resistance
aluminium
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 - Lifetime
Application number
EP96420235A
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German (de)
English (en)
French (fr)
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EP0756017A1 (fr
Inventor
Denis Bechet
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.)
Constellium Issoire SAS
Original Assignee
Pechiney Rhenalu SAS
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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
    • C22C21/06—Alloys based on aluminium with magnesium as the next major constituent
    • C22C21/08—Alloys based on aluminium with magnesium as the next major constituent with silicon
    • 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 aluminum alloys of the 2000 series. according to the designation of the Aluminum Association of the United States, of the AlCuMg type, exhibiting, after spinning transformation, rolling or forging, very little creep deformation and a high breaking time for temperatures between 100 and 150 ° C, while retaining properties of use at less equivalent to that of alloys of this type usually used for similar applications.
  • alloys of the AlCuMgFeNi type have a higher creep resistance than AlCuMg alloys with the same Cu and Mg content.
  • First used in the form of molded, stamped or forged parts, such alloys have been adapted to the manufacture of high-resistance sheets and used in particular for the fuselage of the Concorde supersonic aircraft.
  • patent FR 2279852 by CEGEDUR PECHINEY proposes an alloy with reduced iron and nickel content of the following composition (% by weight): Cu: 1.8 - 3 Mg: 1.2 - 2.7 Si ⁇ 0.3 Fe: 0.1 - 0.4 Ni + Co: 0.1 - 0.4 (Ni + Co) / Fe: 0.9 - 1.3
  • the alloy may also contain Zr, Mn, Cr, V or Mo at contents of less than 0.4%, and optionally Cd, In, Sn or Be of less than 0.2% each, Zn of less than 8% or Ag less than 1%. With this alloy, a significant improvement is obtained in the stress concentration factor K 1c representative of the resistance to the propagation of cracks. On the other hand, the results of the creep tests at temperatures of 100 and 175 ° C are quite comparable to those of 2618.
  • the subject of the invention is therefore an AlCuMg alloy making it possible to obtain, on a product wrought by spinning, rolling or forging, a creep deformation after 1000 h, at 150 ° C. and under a stress of 250 MPa, of less than 0, 3% and a breaking time of at least 2500 h, of composition (% by weight): Cu: 2.5 - 2.75 Mg: 1.5 - 2.1 Mn: 0.3 - 0.7 Zr ⁇ 0.15 If: 0.3 - 0.6 Fe ⁇ 0.3 Ni ⁇ 0.3 Ti ⁇ 0.15 other elements ⁇ 0.05 each and 0.15 in total, remains Al.
  • the alloy can also contain silver with a content of less than 1% and, in this case, this element can partially replace silicon and the sum If + 0.4Ag must be between 0.3 and 0.6%.
  • Mg is preferably between 1.55 and 2.8%.
  • the alloy according to the invention differs from that described in patent FR 2279852 by an even higher content of silicon, optionally partly substituted by silver, and by the compulsory presence of manganese at a content of between 0, 3 and 0.7%. Iron and nickel are kept below 0.3% instead of 0.4% and it is even possible to completely remove nickel, which is a definite advantage for the recycling of manufacturing waste into current second alloys fusion. This reduction was not suggested by the state of the art. Thus, D. ADENIS and R.
  • the alloy according to the invention has a manganese content of between 0.3 and 0.7%. Manganese contributes to increase the mechanical characteristics. Alloy 2618 did not contain manganese (H. MARTINOD mentions in its article a content of 0.014% for an example of industrial alloy) undoubtedly so as not to disturb the formation of intermetallic compounds with iron and nickel Al 9 FeNi.
  • a deformation at 1000 h is obtained of less than 0.3% instead of 1%, a creep rate in secondary regime less than 10 -9 s - 1 instead of 2.5 10 -9 s -1 and a time at failure greater than 2500 h instead of less than 1500 h.
  • the fine-grain recrystallized structure of the thin sheets represents the most unfavorable case for the creep behavior, in particular for the deformation under stress, because of the localized deformation at the grain boundaries. This last result is particularly interesting, although it has rarely been taken into account in previous studies on the creep of aluminum alloys.
  • the alloys according to the invention can be cast in the form of billets or plates by the conventional methods of casting alloys of the 2000 series, and transformed by spinning, hot and possibly cold rolling, stamping or forging, the semi-finished product thus obtained is usually heat treated by dissolution, quenching, optionally controlled traction to reduce residual stresses and tempering, to give it the mechanical characteristics required by the intended application.
  • Alloy A contains manganese, unlike the alloys exemplified in the patent, which allows a better appreciation by comparison of the role of the other elements, in particular silicon.
  • Alloy B contains silver.
  • Alloy F is just below the lower limit for the sum Si + 0.4Ag and, moreover, outside the preferential zone for Mg.
  • Alloy G is slightly above the upper limit for Si + 0.4Ag and alloy H is out of limits for Cu.
  • the plates were then homogenized 24 h at 520 ° C, hot rolled, then cold rolled to the thickness of 1.6 mm, having a recrystallized metallurgical structure with fine grains after dissolving for 40 min at 530 ° C, traction controlled at 1.4% deformation, quenching and tempering from 19 h at 190 ° C. Creep tests were carried out according to standard ASTM E 139 and, for a stress of 250 MPa and a temperature of 150 ° C., the deformation after 1000 h, the minimum creep speed, that is to say, was measured. to say the slope of the curve of strain in creep as a function of time in the secondary zone of creep, as well as the time with rupture, which is representative of the resistance to the damage.
  • Plates were cast of alloy 2618, of alloy A of the previous example and of 3 other alloys according to the invention I, J and K, the chemical composition of which is given in Table 3. These alloys do not contain silver and alloy J does not contain nickel at all. Alloys I and J have a manganese content close to the lower limit of the range, while that of alloy K is close to the upper limit.
  • the plates were homogenized 24 h at 520 ° C, scalped and hot rolled to a thickness of 14 mm. Part of the sheets obtained was left at this thickness, and another part was cold rolled to 1.6 mm.
  • the sheets were dissolved at 530 ° C for 1 h for the 14 mm sheets and 40 min for the 1.6 mm sheets, then towed, quenched and returned 19 h at 190 ° C.
  • the elastic limit at 0.2% R 0.2 , the breaking load Rm and the elongation at break A were measured on these sheets. These results are shown in Table 4. They show that the limit of elasticity and breaking load are practically the same for the 5 alloys, and that the elongation of the sheets of alloys according to the invention is slightly greater than that of the sheets of 2618 or of alloy A.
  • the minimum creep rate was then measured at 150 ° C (for 1.6 mm sheets only) and at 175 ° C at 250 MPa, as in the previous example.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Heat Treatment Of Steel (AREA)
  • Forging (AREA)
EP96420235A 1995-07-28 1996-07-10 Alliage aluminium-cuivre-magnésium à résistance élevée au fluage Expired - Lifetime EP0756017B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9509443A FR2737225B1 (fr) 1995-07-28 1995-07-28 Alliage al-cu-mg a resistance elevee au fluage
FR9509443 1995-07-28

Publications (2)

Publication Number Publication Date
EP0756017A1 EP0756017A1 (fr) 1997-01-29
EP0756017B1 true EP0756017B1 (fr) 2001-08-29

Family

ID=9481669

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96420235A Expired - Lifetime EP0756017B1 (fr) 1995-07-28 1996-07-10 Alliage aluminium-cuivre-magnésium à résistance élevée au fluage

Country Status (5)

Country Link
US (1) US5738735A (ja)
EP (1) EP0756017B1 (ja)
JP (1) JPH09165640A (ja)
DE (1) DE69614788T2 (ja)
FR (1) FR2737225B1 (ja)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0989195B1 (de) * 1998-09-25 2002-04-24 Alcan Technology & Management AG Warmfeste Aluminiumlegierung vom Typ 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
US20030026725A1 (en) * 2001-07-30 2003-02-06 Sawtell Ralph R. Alloy composition for making blister-free aluminum forgings and parts made therefrom
DE10163039C1 (de) * 2001-12-21 2003-07-24 Daimler Chrysler Ag Warm- und kaltumformbares Bauteil aus einer Aluminiumlegierung und Verfahren zu seiner Herstellung
US20050034794A1 (en) * 2003-04-10 2005-02-17 Rinze Benedictus High strength Al-Zn alloy and method for producing such an alloy product
WO2004090185A1 (en) 2003-04-10 2004-10-21 Corus Aluminium Walzprodukte Gmbh An al-zn-mg-cu alloy
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
US20070204937A1 (en) * 2005-07-21 2007-09-06 Aleris Koblenz Aluminum Gmbh Wrought aluminium aa7000-series alloy product and method of producing said product
US20070151636A1 (en) * 2005-07-21 2007-07-05 Corus Aluminium Walzprodukte Gmbh Wrought aluminium AA7000-series alloy product and method of producing said product
US8608876B2 (en) * 2006-07-07 2013-12-17 Aleris Aluminum Koblenz Gmbh AA7000-series aluminum alloy products and a method of manufacturing thereof
US8002913B2 (en) * 2006-07-07 2011-08-23 Aleris Aluminum Koblenz Gmbh AA7000-series aluminum alloy products and a method of manufacturing thereof
EP2149618B1 (en) * 2008-07-30 2011-10-26 Olab S.r.l. Hot pressing process, particularly for providing metal unions for pneumatic, hydraulic and fluid-operated circuits, and metal union obtained thereby
US9347558B2 (en) 2010-08-25 2016-05-24 Spirit Aerosystems, Inc. Wrought and cast aluminum alloy with improved resistance to mechanical property degradation
FR2974118B1 (fr) 2011-04-15 2013-04-26 Alcan Rhenalu Alliages aluminium cuivre magnesium performants a haute temperature
JP5879181B2 (ja) * 2011-06-10 2016-03-08 株式会社神戸製鋼所 高温特性に優れたアルミニウム合金
US10266933B2 (en) 2012-08-27 2019-04-23 Spirit Aerosystems, Inc. Aluminum-copper alloys with improved strength
JP7469072B2 (ja) * 2020-02-28 2024-04-16 株式会社神戸製鋼所 アルミニウム合金鍛造材及びその製造方法
FR3111143B1 (fr) 2020-06-04 2022-11-18 Constellium Issoire Produits en alliage aluminium cuivre magnésium performants à haute température

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE735314C (de) * 1937-06-29 1943-05-12 Ernst Heinkel Flugzeugwerke G Verwendung von Aluminiumlegierungen als Werkstoff fuer Nieten
FR2087439A5 (en) * 1970-05-20 1971-12-31 British Aluminium Co Ltd Aluminium alloys suitable for eloxation - for decorative applications
US4000007A (en) * 1973-02-13 1976-12-28 Cegedur Societe De Transformation De L'aluminium Pechiney Method of making drawn and hemmed aluminum sheet metal and articles made thereby
FR2279852B1 (fr) * 1974-07-23 1977-01-07 Cegedur Transf Aumin Pechiney Alliage d'aluminium de bonne tenue au fluage et de resistance a la propagation des criques amelioree
US4062704A (en) * 1976-07-09 1977-12-13 Swiss Aluminium Ltd. Aluminum alloys possessing improved resistance weldability
US5376192A (en) * 1992-08-28 1994-12-27 Reynolds Metals Company High strength, high toughness aluminum-copper-magnesium-type aluminum alloy

Also Published As

Publication number Publication date
DE69614788T2 (de) 2002-05-23
EP0756017A1 (fr) 1997-01-29
DE69614788D1 (de) 2001-10-04
JPH09165640A (ja) 1997-06-24
FR2737225A1 (fr) 1997-01-31
US5738735A (en) 1998-04-14
FR2737225B1 (fr) 1997-09-05

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