EP1373591A2 - Procede permettant d'augmenter la solidite et/ou la resistance a la corrosion d'alliages aerospaciaux d'aluminium de la serie 7000 - Google Patents

Procede permettant d'augmenter la solidite et/ou la resistance a la corrosion d'alliages aerospaciaux d'aluminium de la serie 7000

Info

Publication number
EP1373591A2
EP1373591A2 EP02713880A EP02713880A EP1373591A2 EP 1373591 A2 EP1373591 A2 EP 1373591A2 EP 02713880 A EP02713880 A EP 02713880A EP 02713880 A EP02713880 A EP 02713880A EP 1373591 A2 EP1373591 A2 EP 1373591A2
Authority
EP
European Patent Office
Prior art keywords
hours
aging
alloy
aluminum
product
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.)
Withdrawn
Application number
EP02713880A
Other languages
German (de)
English (en)
Inventor
Diana K. Alcoa Technical Center DENZER
Dhruba J. Alcoa Technical Center CHAKRABARTI
John Alcoa Technical Center LIU
LYNN E. Alcoa Technical Center OSWALD
Robert W. Alcoa Inc. WESTERLUND
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.)
Howmet Aerospace Inc
Original Assignee
Alcoa Inc
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 Alcoa Inc filed Critical Alcoa Inc
Publication of EP1373591A2 publication Critical patent/EP1373591A2/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • 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
    • C22F1/053—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 zinc as the next major constituent

Definitions

  • This invention relates to the field of aluminum alloys for aerospace
  • this invention relates to an improved method for
  • the invention may be any material that has strength levels.
  • the invention may be any material that has strength levels.
  • this first artificial aging step is not typically
  • That machined panel is then aligned over a
  • a typical 7xxx age forming practice entails one or two steps. If a two step
  • the first step is usually performed at a lower temperature than the second.
  • That first step is typically about 200-250°F for about 3 to 12 hours.
  • the second step of the first step is typically about 200-250°F for about 3 to 12 hours.
  • two-step practice targets one or more temperatures between about 280-350°F for
  • exfoliation corrosion resistance are critical. In the typical age form practice, exfoliation
  • this invention relates to an improved method for artificially
  • step/stage (second of two or third of three) extends at about 225-
  • the invention especially imparts improved combinations of strength and exfoliation
  • this same invention entails adding a third step to the two-step
  • That third step likewise extends at about 225-275°F for
  • Figures 1 (a) through (c) are graphic representations of three, 2-step aging
  • Figures 2 (a) through (g) are graphic representations of seven representative
  • Figure 3 is a graph depicting the relative improvement in strength
  • Figure 4 is the same graph of Figure 3 through which solid curves A-A and
  • Figure 5 is a graph depicting the numerical increase in tensile yield
  • Figure 6 is a graph depicting the increase in tensile yield strength values
  • Figure 7 is a graph numerically depicting the improvement in electrical
  • Figure 8 is a graph depicting that same improvement in predicted electrical
  • Figures 1 (a) through (c) are graphic representations of three, 2-step aging schemes according to the invention, with
  • FIG. 1(c) schematically depicts a 2-step or staged method with a distinct, fully separated
  • Figures 2 (a) through (g) are graphic representations of seven representative
  • 2(b) illustrates a 3-step method that has a controlled, furnace ramping down to achieve
  • Figure 2(c) represents a
  • Figure 2(e) depicts a variation on 2(b) with a full cool down between steps 1
  • thick 7055 plate were given various combinations of first- and second-step aging
  • EXCO resistance
  • electrical conductivity "EC" serves as an
  • Figure 7 shows the numerical EC improvement predicted
  • Figure 8 predicts that same improvement in strength as a function of electrical conductivity by percentage rather than in actual EC (% IACS) values observed. Note that
  • Such spar members are traditionally made from more corrosion resistant but lower strength temper materials such as those
  • Wing skins are typically made from thinner gauge plates as compared to the
  • main alloying constituents with supporting elements, like Zr, Cr and/or Sc, and grain
  • the method of this invention may just as easily be practiced on an aging operation that
  • steps/stages without having a purposeful cooling off period or quench air, cold water or

Landscapes

  • Chemical & Material Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)
  • Preventing Corrosion Or Incrustation Of Metals (AREA)

Abstract

L'invention concerne un procédé destiné au vieillissement artificiel d'alliages aérospaciaux d'aluminium de la Série 7000 pour les rendre plus solides et/ou plus résistants à la corrosion. Ce procédé consiste à ajouter volontairement un deuxième palier/étape de vieillissement au revenu à un seul palier, ou un troisième palier/étape à une opération de vieillissement à deux paliers, faible et élevé. Le palier/étape ajouté est effectué à une température comprise entre 225-275 °F environ pendant 3 à 24 heures environ. De préférence, le palier supplémentaire est effectué à 250 °F environ pendant au moins 6 heures.
EP02713880A 2001-03-20 2002-03-20 Procede permettant d'augmenter la solidite et/ou la resistance a la corrosion d'alliages aerospaciaux d'aluminium de la serie 7000 Withdrawn EP1373591A2 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US27740301P 2001-03-20 2001-03-20
US277403P 2001-03-20
PCT/US2002/008538 WO2002075010A2 (fr) 2001-03-20 2002-03-20 Procede permettant d'augmenter la solidite et/ou la resistance a la corrosion d'alliages aerospaciaux d'aluminium de la serie 7000

Publications (1)

Publication Number Publication Date
EP1373591A2 true EP1373591A2 (fr) 2004-01-02

Family

ID=23060708

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02713880A Withdrawn EP1373591A2 (fr) 2001-03-20 2002-03-20 Procede permettant d'augmenter la solidite et/ou la resistance a la corrosion d'alliages aerospaciaux d'aluminium de la serie 7000

Country Status (7)

Country Link
US (1) US20030051784A1 (fr)
EP (1) EP1373591A2 (fr)
CN (1) CN1531603A (fr)
AU (1) AU2002245705A1 (fr)
BR (1) BR0208271A (fr)
CA (1) CA2441168A1 (fr)
WO (1) WO2002075010A2 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050006010A1 (en) * 2002-06-24 2005-01-13 Rinze Benedictus Method for producing a high strength Al-Zn-Mg-Cu alloy
US20050034794A1 (en) * 2003-04-10 2005-02-17 Rinze Benedictus High strength Al-Zn alloy and method for producing such an alloy product
DE112004000603B4 (de) 2003-04-10 2022-11-17 Novelis Koblenz Gmbh AI-Zn-Mg-Cu-Legierung
US7666267B2 (en) 2003-04-10 2010-02-23 Aleris Aluminum Koblenz Gmbh Al-Zn-Mg-Cu alloy with improved damage tolerance-strength combination properties
JP5409125B2 (ja) * 2009-05-29 2014-02-05 アイシン軽金属株式会社 耐ｓｃｃ性に優れる７０００系アルミニウム合金押出材及びその製造方法
EP2518173B1 (fr) 2011-04-26 2017-11-01 Benteler Automobiltechnik GmbH Procédé de fabrication d'un composant de structure en tôle ainsi que composant de structure en tôle
JP6344816B2 (ja) * 2013-08-30 2018-06-20 株式会社Uacj 高強度アルミニウム合金押出薄肉形材およびその製造方法
US20180171440A1 (en) * 2016-12-21 2018-06-21 Arconic Inc. High zinc aluminum alloy products

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IL39200A (en) * 1972-04-12 1975-08-31 Israel Aircraft Ind Ltd Method of reducing the susceptibility of alloys,particularly aluminum alloys,to stress-corrosion cracking
US4477292A (en) * 1973-10-26 1984-10-16 Aluminum Company Of America Three-step aging to obtain high strength and corrosion resistance in Al-Zn-Mg-Cu alloys
US4863528A (en) * 1973-10-26 1989-09-05 Aluminum Company Of America Aluminum alloy product having improved combinations of strength and corrosion resistance properties and method for producing the same
FR2409319A1 (fr) * 1977-11-21 1979-06-15 Cegedur Procede de traitement thermique de produits minces en alliages d'aluminium de la serie 7000
US5108520A (en) * 1980-02-27 1992-04-28 Aluminum Company Of America Heat treatment of precipitation hardening alloys
US5221377A (en) * 1987-09-21 1993-06-22 Aluminum Company Of America Aluminum alloy product having improved combinations of properties
CA2069189C (fr) * 1991-08-12 1998-04-14 Aerostructures Corporation Methode d'elaboration de formes complexes pour outils de formage
US5865911A (en) * 1995-05-26 1999-02-02 Aluminum Company Of America Aluminum alloy products suited for commercial jet aircraft wing members
JP3705320B2 (ja) * 1997-04-18 2005-10-12 株式会社神戸製鋼所 耐食性に優れる高強度熱処理型７０００系アルミニウム合金
IL156386A0 (en) * 2000-12-21 2004-01-04 Alcoa Inc Aluminum alloy products and artificial aging method

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO02075010A3 *

Also Published As

Publication number Publication date
WO2002075010A2 (fr) 2002-09-26
CA2441168A1 (fr) 2002-09-26
BR0208271A (pt) 2004-03-09
AU2002245705A1 (en) 2002-10-03
WO2002075010A3 (fr) 2003-03-13
US20030051784A1 (en) 2003-03-20
CN1531603A (zh) 2004-09-22

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