EP0008996B1 - Procédé de traitement thermique des alliages aluminium-cuivre-magnésium-silicium - Google Patents

Procédé de traitement thermique des alliages aluminium-cuivre-magnésium-silicium Download PDF

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Publication number
EP0008996B1
EP0008996B1 EP79420041A EP79420041A EP0008996B1 EP 0008996 B1 EP0008996 B1 EP 0008996B1 EP 79420041 A EP79420041 A EP 79420041A EP 79420041 A EP79420041 A EP 79420041A EP 0008996 B1 EP0008996 B1 EP 0008996B1
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Prior art keywords
temperature
temper
main
complementary
process according
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EP79420041A
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German (de)
English (en)
French (fr)
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EP0008996A1 (fr
Inventor
Bruno Dubost
Jean Bouvaist
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Cegedur Societe de Transformation de lAluminium Pechiney SA
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Cegedur Societe de Transformation de lAluminium Pechiney SA
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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

Definitions

  • the present invention relates to a process for heat treatment of wrought products of aluminum alloys of the 2000 series (aluminum - copper - magnesium - silicon) intended to improve their resistance to intercrystalline corrosion and to corrosion under stress.
  • the process is applicable to all wrought aluminum alloy products having, in particular, 3.5% to 5% copper, 0.2% to 1.0% magnesium and 0.25 weight contents. % to 1.2% in silicon, such that the ratio of the Si / Mg content by weight is greater than 0.8.
  • These alloys can also contain weight contents less than or equal to 1% manganese, 0.5% chromium and 0.3% zirconium.
  • the most characteristic aluminum alloy in this field of compositions is the alloy known as 2014 according to the designations of the Aluminum Association.
  • This alloy and its variants, 2X14 (2214 etc 7), which differ from 2014 by lower iron contents, are widely used in the aeronautical industry.
  • the current practice of heat treatment of these alloys includes dissolving at a temperature generally below 510 ° C, as rapid quenching as possible, maturing for several days at room temperature (state T4) and simple tempering at a temperature generally between 150 ° C and 190 ° C for an isothermal holding time between 4 hours and 48 hours (state T6).
  • This range of heat treatment is notably that of stamped products.
  • the known practice of heat treatment of rolled, forged or extruded products also includes work hardening by plastic deformation of 1 to 5% of the raw quenching products before maturation and tempering, intended to stress the quenched products. This work hardening can be obtained by controlled traction or leveling of long products (states T351 after maturation or T651 after isothermal tempering) and by compression of forged products (states T352 or T625).
  • the resistance to intercrystalline corrosion is evaluated after immersion for a period of 6 hours in NaCI-H 2 0 2 reagent according to the French aeronautical standard AIR 9050 C of 1/12/1964.
  • the resistance to corrosion under stress is evaluated in the short-cross direction after air-immersion-emersion test in buffered NaCl solution, the composition of which appears in French standard NF 91-411 of October 1966 -reactive said A3-. It is characterized by the non-breaking stress in 30 days of testing ( Q NR 30), often given as a percentage of the elastic limit Rp 0.2 in the short-cross direction.
  • the 2014 alloy has, in the T6 (or T651) state, a non-breaking constraint in the cross-short direction of less than 100 MPa in 30 days of testing, and even in the absence of a constraint applied, is very sensitive to intercrystalline corrosion after the NaCI-H 2 0 2 test .
  • the holding time above 225 ° C is shorter the higher the temperature reached.
  • the rate of temperature rise and the rate of cooling of the product to be treated must be fast enough. In particular, between 175 ° C and 225 ° C, they must be higher on average than 1 ° C / min.
  • the product After the main tempering, the product must be cooled, either to room temperature or to the temperature of the supplementary tempering. It can then undergo work hardening by plastic deformation of 1 to 5% intended for its stress relieving, if this operation has not already been carried out between the quenching and the main tempering.
  • the temperature of the additional income will preferably be at least 70 ° C. lower than that of the main income.
  • the work hardening can be carried out at an intermediate temperature between that of the main tempering and the ambient temperature.
  • An advantage of the present invention is the good reproducibility of the conditions of the main income, obtained by simple control of the temperature development, in the coldest part, of a control room.
  • the main income may not include an isothermal bearing, at a temperature above 225 ° C. It can therefore be produced on products of all thicknesses and by means of the most diverse techniques allowing a sufficiently rapid rise in temperature, for example, a ventilated oven, passage oven, high frequency oven, oil, salt or of molten metal, or by Joule effect, depending on the nature of the products to be treated.
  • the method according to the invention applies to the thermal treatment of rolled, forged, stamped, extruded or other products, whatever the homogenization or solution treatment carried out before quenching and whatever the method of stress relieving by work hardening after quenching.
  • the alloy, before working has been homogenized at a temperature between the starting melting temperature of the metastable eutectics and the temperature of the equilibrium solidus of the alloy, as described in French patent no. 2,278,785.
  • the combination of such homogenization and of an income according to the invention gives the alloy, without the need to modify its composition, a set of improved characteristics since the elastic limit Rp 0.2 is at least equal to 95% of that obtained on an alloy of the same composition having undergone the same work hardening and the treatment of tempering T6 or T651 with an elongation (A%) greater than that of the current state T6.
  • the Applicant has found that the modification of the alloy by increasing the content of Cu and / or Mg and / or Si up to their limit of solubility in aluminum at the homogenization temperature (according to the certificate of addition no. 2,293,497 to French patent no. 2,278,785), associated with a homogenization carried out at a temperature between the starting melting temperature of the metastable eutectics and the temperature of the solidus balance of the alloy (as described in French patent no. 2,278,785) and a tempering treatment according to the invention makes it possible to achieve a compromise between mechanical properties of traction and resistance to corrosion under tension quite exceptional for alloys of the 2000 series and impossible to reach by other means in the current state of the art.
  • the 2014 alloy products with modified composition have, after special homogenization and tempering according to the invention, mechanical tensile characteristics (Rm and Rp 0.2) superior to those of the classic 2014 alloy, treated with state T6 (or T651 ° or T652) without reduction in elongation or toughness, with, in addition, a much higher corrosion resistance: the non-breaking stress is greater than 75% of the elastic limit Rp 0 , 2 and the alloy treated according to the invention is not sensitive to intercrystalline corrosion according to the AIR 9050C standard.
  • the main income was carried out in a nitrites-nitrates salt bath.
  • Table 1 below indicates the duration of keeping the part at temperature above 225 ° C and the maximum temperature reached by the product.
  • the products were cooled with water after main tempering, and the complementary tempering (R.C.) was carried out in a ventilated stationary oven.
  • Table 1 gives the mechanical tensile characteristics in the cross-long and cross-short direction, the stress at NR 30 of non-rupture in corrosion under tension in the cross-short direction (imposed stresses 100, 200 and 300 MPa) in reagent A3, and resistance to intercrystalline corrosion according to AIR 9050C standard.
  • Table II below gives the Vickers hardness (under load 3 kg) and the sensitivity to intercrystalline corrosion (NaCI-H 2 0 2 test ) on the surface of sheets.
  • the wire table below gives the mechanical tensile characteristics and the stress ⁇ NR 30 of non-rupture in 30 days of corrosion test under tension in reagent A3 (constraints imposed 100, 200, 300 MPa) in the cross direction. short.
  • Table IV gives the holding time of the blanks at a temperature above 225 ° C. and the maximum temperature reached by the blanks, measured by a mid-thickness thermocouple.
  • the table shows that the conditions of main income and additional income according to the invention make it possible to obtain good resistance to corrosion under tension with mechanical tensile characteristics (Rp 0.2 in particular) at least equal to 90% of those of the current T6 state.

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  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Heat Treatment Of Nonferrous Metals Or Alloys (AREA)
  • Heat Treatment Of Articles (AREA)
  • Conductive Materials (AREA)
  • Contacts (AREA)
EP79420041A 1978-09-08 1979-09-05 Procédé de traitement thermique des alliages aluminium-cuivre-magnésium-silicium Expired EP0008996B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR7826371A FR2435535A1 (fr) 1978-09-08 1978-09-08 Procede de traitement thermique des alliages aluminium, cuivre, magnesium, silicium
FR7826371 1978-09-08

Publications (2)

Publication Number Publication Date
EP0008996A1 EP0008996A1 (fr) 1980-03-19
EP0008996B1 true EP0008996B1 (fr) 1981-10-07

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP79420041A Expired EP0008996B1 (fr) 1978-09-08 1979-09-05 Procédé de traitement thermique des alliages aluminium-cuivre-magnésium-silicium

Country Status (10)

Country Link
US (1) US4323399A (xx)
EP (1) EP0008996B1 (xx)
JP (3) JPS5541996A (xx)
BE (1) BE878673A (xx)
CA (1) CA1139645A (xx)
DE (1) DE2960938D1 (xx)
ES (1) ES483945A1 (xx)
FR (1) FR2435535A1 (xx)
IL (1) IL58190A (xx)
IT (1) IT1122979B (xx)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0164114B1 (en) * 1984-06-06 1988-12-28 Toyota Jidosha Kabushiki Kaisha Door window regulator
EP0164121B1 (en) * 1984-06-06 1989-12-27 Toyota Jidosha Kabushiki Kaisha Door window regulator
US4808248A (en) * 1986-10-10 1989-02-28 Northrop Corporation Process for thermal aging of aluminum alloy plate
JPH0373375U (xx) * 1989-11-20 1991-07-24
US5076859A (en) * 1989-12-26 1991-12-31 Aluminum Company Of America Heat treatment of aluminum-lithium alloys
US5098490A (en) * 1990-10-05 1992-03-24 Shin Huu Super position aluminum alloy can stock manufacturing process
US5718780A (en) * 1995-12-18 1998-02-17 Reynolds Metals Company Process and apparatus to enhance the paintbake response and aging stability of aluminum sheet materials and product therefrom
US6325869B1 (en) * 1999-01-15 2001-12-04 Alcoa Inc. Aluminum alloy extrusions having a substantially unrecrystallized structure
IL156386A0 (en) 2000-12-21 2004-01-04 Alcoa Inc Aluminum alloy products and artificial aging method
US8083871B2 (en) * 2005-10-28 2011-12-27 Automotive Casting Technology, Inc. High crashworthiness Al-Si-Mg alloy and methods for producing automotive casting
US7854809B2 (en) * 2007-04-10 2010-12-21 Siemens Energy, Inc. Heat treatment system for a composite turbine engine component
US8840737B2 (en) * 2007-05-14 2014-09-23 Alcoa Inc. Aluminum alloy products having improved property combinations and method for artificially aging same
US8673209B2 (en) * 2007-05-14 2014-03-18 Alcoa Inc. Aluminum alloy products having improved property combinations and method for artificially aging same
US8357250B2 (en) * 2008-07-29 2013-01-22 GM Global Technology Operations LLC Recovery heat treatment to improve formability of magnesium alloys
US8206517B1 (en) 2009-01-20 2012-06-26 Alcoa Inc. Aluminum alloys having improved ballistics and armor protection performance
CN107490519B (zh) * 2017-08-07 2019-08-13 天津重型装备工程研究有限公司 合金锻件的力学性能的测试方法及应力松弛数值模拟方法
FR3118065B1 (fr) 2020-12-18 2023-11-10 Constellium Issoire Produits corroyés en alliage 2xxx présentant une résistance à la corrosion optimisée et procédé d’obtention

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3305410A (en) * 1964-04-24 1967-02-21 Reynolds Metals Co Heat treatment of aluminum
US3726725A (en) * 1971-03-22 1973-04-10 Philco Ford Corp Thermal mechanical processing of aluminum alloys (a)
US3947297A (en) * 1973-04-18 1976-03-30 The United States Of America As Represented By The Secretary Of The Air Force Treatment of aluminum alloys

Also Published As

Publication number Publication date
ES483945A1 (es) 1980-04-16
IL58190A (en) 1982-09-30
JPS6326191B2 (xx) 1988-05-28
EP0008996A1 (fr) 1980-03-19
BE878673A (fr) 1980-03-07
JPS5541996A (en) 1980-03-25
JPS6246621B2 (xx) 1987-10-02
IT1122979B (it) 1986-04-30
JPS59145765A (ja) 1984-08-21
JPS59145766A (ja) 1984-08-21
IT7925497A0 (it) 1979-09-05
CA1139645A (fr) 1983-01-18
FR2435535B1 (xx) 1981-07-03
IL58190A0 (en) 1979-12-30
FR2435535A1 (fr) 1980-04-04
JPS6362581B2 (xx) 1988-12-02
DE2960938D1 (en) 1981-12-17
US4323399A (en) 1982-04-06

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