EP1026270B1 - Produkt aus AlCuMg-Legierung für ein Zellenbauteil eines Flugzeuges - Google Patents

Produkt aus AlCuMg-Legierung für ein Zellenbauteil eines Flugzeuges Download PDF

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Publication number
EP1026270B1
EP1026270B1 EP00420020A EP00420020A EP1026270B1 EP 1026270 B1 EP1026270 B1 EP 1026270B1 EP 00420020 A EP00420020 A EP 00420020A EP 00420020 A EP00420020 A EP 00420020A EP 1026270 B1 EP1026270 B1 EP 1026270B1
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EP
European Patent Office
Prior art keywords
mpa
measured
thickness
product
quenched
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
EP00420020A
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English (en)
French (fr)
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EP1026270A1 (de
Inventor
Timothy Warner
Philippe Lassince
Philippe Lequeu
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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First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=26234808&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP1026270(B1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Priority claimed from FR9901468A external-priority patent/FR2789405A1/fr
Application filed by Pechiney Rhenalu SAS filed Critical Pechiney Rhenalu SAS
Publication of EP1026270A1 publication Critical patent/EP1026270A1/de
Application granted granted Critical
Publication of EP1026270B1 publication Critical patent/EP1026270B1/de
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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
    • C22F1/057—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
    • 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

Claims (10)

  1. Walz-, Press- oder Schmiedeerzeugnis aus AlCuMg-Legierung, behandelt durch Homogenisieren, Warmumformen bei einer Austrittstemperatur oberhalb 420°C, um auf einem Viertel der Dicke einen Rekristallisationsgrad von weniger als 20 % zu erhalten, Lösungsglühen, Abschrecken, Kaltrecken und Auslagern, für die Herstellung von Zellenbauteilen eines Flugzeugs, mit der Zusammensetzung (Gew.-%):
    Fe < 0,15   Si < 0,15   Fe + Si < 0,15 %   Cu: 4,0 - 4,3 Mg: 1 - 1,5   Mn: 0,5 - 0,8   Zr: 0,08 - 0,15
    weitere Elemente jeweils < 0,05 und insgesamt < 0,15, mit einem Rm(L)/R0,2(L)-Verhältnis > 1,25 (vorzugsweise > 1,30).
  2. Walzerzeugnis von 6 bis 60 mm Dicke nach Anspruch 1, das im abgeschreckten und gestreckten Zustand eine Bruchfestigkeit Rm(L) > 475 MPa und eine Dehngrenze R0,2(L) > 370 MPa aufweist.
  3. Walzerzeugnis von 6 bis 60 mm Dicke nach einem der Ansprüche 1 oder 2, das im abgeschreckten und gestreckten Zustand einen Verformungsunterschied zwischen Bruchfestigkeit Rm und Dehngrenze R0,2 in Längs- und Längs-Querrichtung > 100 MPa aufweist.
  4. Walzerzeugnis von 6 bis 60 mm Dicke nach einem der Ansprüche 1 bis 3, das im abgeschreckten und gestreckten Zustand einen kritischen Spannungsintensitätsfaktor (längs/quer) Kc > 170 MPa√m und K co > 120 MPa√m aufweist, gemessen nach der Norm ASTM E 561 an angekerbten, auf einem Viertel der Dicke entnommenen Proben mit den Parametern W = 500 mm, B = 5 mm und 2a0 = 165 mm.
  5. Walzerzeugnis von 6 bis 60 mm Dicke nach einem der Ansprüche 1 bis 4, das im abgeschreckten und gestreckten Zustand eine Rissausbreitungsgeschwindigkeit (längs/quer) aufweist, gemessen nach der Norm ASTM E 647 an angekerbten, auf einem Viertel der Dicke entnommenen Proben mit W = 200 mm und B = 5 mm:
    < 10-4 mm/Zyklus bei ΔK = 10 MPa√m
    < 2,5 10-4 mm/Zyklus bei ΔK = 15 MPa√m
    und < 5 10-4 mm/Zyklus bei ΔK = 20 MPa√m.
  6. Walzerzeugnis nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass es eine Durchbiegung f, gemessen in Längs- und Längsquerrichtung nach Bearbeitung auf halber Dicke eines auf zwei, um eine Länge I voneinander beabstandeten Stützen aufliegenden Probestabs, von weniger als (0,14 I2)/e aufweist, wobei f in Mikrometern gemessen ist und die Dicke e des Blechs und die Länge I in mm ausgedrückt sind.
  7. Verfahren zur Herstellung eines Erzeugnisses nach einem der Ansprüche 1 bis 6, mit folgenden Schritten:
    Gießen einer Platte mit der genannten Zusammensetzung
    Homogenisieren dieser Platte zwischen 450 und 500°C
    Warm- und eventuell Kaltumformen durch Walzen, Pressen oder Schmieden, bis sich das gewünschte Erzeugnis ergibt
    Lösungsglühen bei einer Temperatur zwischen 480 und 505°C
    Abschrecken mit kaltem Wasser
    Kaltrecken bis auf mehr als 1,5 % bleibende Verformung
    Kaltauslagerung bei Raumtemperatur.
  8. Verfahren nach Anspruch 7, dadurch gekennzeichnet, dass die Warmumformung bei einer Austrittstemperatur oberhalb 440°C erfolgt.
  9. Verwendung von Blechen nach einem der Ansprüche 2 bis 6 zur Herstellung der Außenhaut für die Tragflügelunterseite eines Flugzeugs.
  10. Verwendung von Profilen nach Anspruch 1 zur Herstellung von Versteifungen für die Tragflügelunterseite und den Rumpf eines Flugzeugs.
EP00420020A 1999-02-04 2000-02-01 Produkt aus AlCuMg-Legierung für ein Zellenbauteil eines Flugzeuges Expired - Lifetime EP1026270B1 (de)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
FR9901468 1999-02-04
FR9901468A FR2789405A1 (fr) 1999-02-04 1999-02-04 PRODUIT EN ALLIAGE AlCuMg POUR ELEMENT DE STRUCTURE D'AVION
FR9910682 1999-08-18
FR9910682A FR2789406B1 (fr) 1999-02-04 1999-08-18 PRODUIT EN ALLIAGE AlCuMg POUR ELEMENT DE STRUCTURE D'AVION

Publications (2)

Publication Number Publication Date
EP1026270A1 EP1026270A1 (de) 2000-08-09
EP1026270B1 true EP1026270B1 (de) 2005-04-27

Family

ID=26234808

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00420020A Expired - Lifetime EP1026270B1 (de) 1999-02-04 2000-02-01 Produkt aus AlCuMg-Legierung für ein Zellenbauteil eines Flugzeuges

Country Status (5)

Country Link
US (2) US6602361B2 (de)
EP (1) EP1026270B1 (de)
DE (1) DE60019655T2 (de)
FR (1) FR2789406B1 (de)
GB (1) GB2346381A (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US8002913B2 (en) 2006-07-07 2011-08-23 Aleris Aluminum Koblenz Gmbh AA7000-series aluminum alloy products and a method of manufacturing thereof
US8608876B2 (en) 2006-07-07 2013-12-17 Aleris Aluminum Koblenz Gmbh AA7000-series aluminum alloy products and a method of manufacturing thereof

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6325869B1 (en) * 1999-01-15 2001-12-04 Alcoa Inc. Aluminum alloy extrusions having a substantially unrecrystallized structure
US7323068B2 (en) * 2002-08-20 2008-01-29 Aleris Aluminum Koblenz Gmbh High damage tolerant Al-Cu alloy
US7604704B2 (en) * 2002-08-20 2009-10-20 Aleris Aluminum Koblenz Gmbh Balanced Al-Cu-Mg-Si alloy product
US7494552B2 (en) * 2002-08-20 2009-02-24 Aleris Aluminum Koblenz Gmbh Al-Cu alloy with high toughness
CN100547098C (zh) 2003-04-10 2009-10-07 克里斯铝轧制品有限公司 一种铝-锌-镁-铜合金
US20050034794A1 (en) * 2003-04-10 2005-02-17 Rinze Benedictus High strength Al-Zn alloy and method for producing such an alloy product
US7666267B2 (en) * 2003-04-10 2010-02-23 Aleris Aluminum Koblenz Gmbh Al-Zn-Mg-Cu alloy with improved damage tolerance-strength combination properties
US20060032560A1 (en) * 2003-10-29 2006-02-16 Corus Aluminium Walzprodukte Gmbh Method for producing a high damage tolerant aluminium alloy
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
CA2750394C (en) 2009-01-22 2015-12-08 Alcoa Inc. Improved aluminum-copper alloys containing vanadium
JP6057855B2 (ja) * 2013-07-31 2017-01-11 株式会社神戸製鋼所 切削用アルミニウム合金押出材
FR3011252B1 (fr) 2013-09-30 2015-10-09 Constellium France Tole d'intrados a proprietes de tolerance aux dommages ameliorees
WO2018206696A1 (en) * 2017-05-11 2018-11-15 Aleris Aluminum Duffel Bvba Method of manufacturing an al-si-mg alloy rolled sheet product with excellent formability
US20190233921A1 (en) * 2018-02-01 2019-08-01 Kaiser Aluminum Fabricated Products, Llc Low Cost, Low Density, Substantially Ag-Free and Zn-Free Aluminum-Lithium Plate Alloy for Aerospace Application
CN108704967A (zh) * 2018-04-25 2018-10-26 南京航空航天大学 一种铝合金电脉冲新淬火成形工艺及装置

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3826688A (en) * 1971-01-08 1974-07-30 Reynolds Metals Co Aluminum alloy system
US4294625A (en) * 1978-12-29 1981-10-13 The Boeing Company Aluminum alloy products and methods
US4336075A (en) * 1979-12-28 1982-06-22 The Boeing Company Aluminum alloy products and method of making same
US5213639A (en) * 1990-08-27 1993-05-25 Aluminum Company Of America Damage tolerant aluminum alloy products useful for aircraft applications such as skin
CA2049840C (en) * 1990-08-27 2002-04-23 Edward L. Colvin Damage tolerant aluminum alloy sheet for aircraft skin
CA2056750A1 (en) * 1990-12-03 1992-06-04 Delbert M. Naser Aircraft sheet
FR2731440B1 (fr) * 1995-03-10 1997-04-18 Pechiney Rhenalu Toles en alliage al-cu-mg a faible niveau de contraintes residuelles
JP3053352B2 (ja) * 1995-04-14 2000-06-19 株式会社神戸製鋼所 破壊靭性、疲労特性および成形性の優れた熱処理型Ａｌ合金
US5863359A (en) * 1995-06-09 1999-01-26 Aluminum Company Of America Aluminum alloy products suited for commercial jet aircraft wing members
US6077363A (en) * 1996-06-17 2000-06-20 Pechiney Rhenalu Al-Cu-Mg sheet metals with low levels of residual stress
US6325869B1 (en) * 1999-01-15 2001-12-04 Alcoa Inc. Aluminum alloy extrusions having a substantially unrecrystallized structure

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US8002913B2 (en) 2006-07-07 2011-08-23 Aleris Aluminum Koblenz Gmbh AA7000-series aluminum alloy products and a method of manufacturing thereof
US8088234B2 (en) 2006-07-07 2012-01-03 Aleris Aluminum Koblenz Gmbh AA2000-series aluminum alloy products and a method of manufacturing thereof
US8608876B2 (en) 2006-07-07 2013-12-17 Aleris Aluminum Koblenz Gmbh AA7000-series aluminum alloy products and a method of manufacturing thereof

Also Published As

Publication number Publication date
GB2346381A (en) 2000-08-09
US20020014288A1 (en) 2002-02-07
GB9924277D0 (en) 1999-12-15
FR2789406A1 (fr) 2000-08-11
EP1026270A1 (de) 2000-08-09
US6602361B2 (en) 2003-08-05
DE60019655T2 (de) 2006-02-02
DE60019655D1 (de) 2005-06-02
US20030217793A1 (en) 2003-11-27
FR2789406B1 (fr) 2001-03-23

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