CA2508534A1 - Method for making structural elements by machining thick plates - Google Patents

Method for making structural elements by machining thick plates Download PDF

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Publication number
CA2508534A1
CA2508534A1 CA002508534A CA2508534A CA2508534A1 CA 2508534 A1 CA2508534 A1 CA 2508534A1 CA 002508534 A CA002508534 A CA 002508534A CA 2508534 A CA2508534 A CA 2508534A CA 2508534 A1 CA2508534 A1 CA 2508534A1
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CA
Canada
Prior art keywords
sheet
machined
alloy
machining
traction
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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.)
Granted
Application number
CA002508534A
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French (fr)
Other versions
CA2508534C (en
Inventor
Fabrice Heymes
David Godard
Timothy Warner
Julien Boselli
Raphaeel Muzzolini
Sjoerd Van Der Veen
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Constellium Issoire SAS
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Individual
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Priority claimed from FR0215997A external-priority patent/FR2848480B1/en
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Publication of CA2508534A1 publication Critical patent/CA2508534A1/en
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Publication of CA2508534C publication Critical patent/CA2508534C/en
Anticipated expiration legal-status Critical
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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
    • 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
    • C22F1/047—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 magnesium as the next major constituent
    • 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

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  • 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)
  • Metal Rolling (AREA)
  • Heat Treatment Of Articles (AREA)
  • Mounting, Exchange, And Manufacturing Of Dies (AREA)

Abstract

The invention concerns a method for making a machined metal part comprising making a metal plate, pre-machining said plate on one or both sides to obtain a pre-machined blank, solution heat-treating said pre-machined blank, hardening, optionally followed by controlled traction. Such a part can be used as structural element in aeronautics.

Claims (27)

1) Procédé de fabrication d'une pièce métallique usinée, comportant a) la fabrication d'une tôle métallique en alliage à traitement thermique par un procédé
comportant a1) la coulée d'une plaque de laminage, suivie éventuellement d'une homogénéisation, a2) une ou plusieurs opérations de laminage à chaud ou à froid, éventuellement séparées d'une ou plusieurs opérations de réchauffage, pour obtenir une tôle, a3) éventuellement une ou plusieurs opérations de découpe ou finition de la tôle, b) le préusinage de ladite tôle sur l'une ou les deux faces pour obtenir une ébauche préusinée, c) un traitement de mise en solution de ladite ébauche préusinée, d) un traitement de trempe. 1) Process for manufacturing a machined metal part, comprising a) the manufacture of an alloy metal sheet with heat treatment by a method comprising a1) the casting of a rolling plate, possibly followed by a homogenization a2) one or more hot or cold rolling operations, possibly separated from one or more reheating operations, to obtain a sheet, a3) possibly one or more operations of cutting or finishing the sheet, b) the pre-machining of said sheet on one or both sides to obtain a draft Pre-Machined, c) a solution treatment of said pre-machined blank, d) quenching treatment. 2) Procédé selon la revendication 1, comportant en plus, après le traitement de trempe, une ou plusieurs des étapes suivantes:
e) traction contrôlée, f) revenu, g) découpe. 2) Method according to claim 1, further comprising, after treatment quenching, one or more of the following steps:
e) controlled traction, f) income, g) cutting. 3) Procédé selon la revendication 1, caractérisé en ce que la tôle est en alliage d' aluminium. 3) Method according to claim 1, characterized in that the sheet is in alloy aluminum. 4) Procédé selon la revendication 3, caractérisé en ce que l'alliage d'aluminium est un alliage de la série 2xxx, 6xxx ou 7xxx. 4) Method according to claim 3, characterized in that the alloy aluminum is a alloy from the 2xxx, 6xxx or 7xxx series. 5) Procédé selon une quelconque des revendications 1 à 3, caractérisé en ce que l'alliage comprend entre 5,5 et 11 % (massiques) de zinc (préférentiellement au moins 8 %), entre 1,5 et 3 % de magnésium, et entre 1,0 et 3,0 de cuivre. 5) Method according to any one of claims 1 to 3, characterized in that that the alloy contains between 5.5 and 11% (mass) of zinc (preferably at least 8 %) between 1.5 and 3% magnesium, and between 1.0 and 3.0 copper. 6) Procédé selon une quelconque des revendications 1 à 5, caractérisée en ce que le profil est constitué d'un ou plusieurs canaux parallèles au sens de laminage. 6) Method according to any one of claims 1 to 5, characterized in that that the profile consists of one or more channels parallel to the rolling direction. 7) Procédé selon la revendication 6, caractérisé en ce que le profil est sensiblement constant sur sa longueur. 7) Method according to claim 6, characterized in that the profile is sensibly constant over its length. 8) Procédé selon une quelconque des revendications 1 à 7, caractérisé en ce que l'usinage est effectué avec une vitesse d'au moins 5000 tours par minute, et préférentiellement supérieur à 10 000 tours par minute. 8) Method according to any one of claims 1 to 7, characterized in that than the machining is carried out with a speed of at least 5000 revolutions per minute, and preferably greater than 10,000 revolutions per minute. 9) Procédé selon une quelconque des revendications 1 à 8, caractérisé que la pièce obtenue est soumise à une ou plusieurs nouvelles opérations d'usinage ou de perçage après la trempe ou après la traction contrôlée. 9) Method according to any one of claims 1 to 8, characterized in that the room obtained is subjected to one or more new machining operations or drilling after quenching or after controlled traction. 10) Procédé selon une quelconque des revendications 1 à 9, caractérisé en ce que la traction contrôlée est effectuée de façon à conduire à un allongement permanent compris entre 0,5 % et 5 %. 10) Method according to any one of claims 1 to 9, characterized in that that the controlled traction is carried out so as to lead to an elongation permanent between 0.5% and 5%. 11) Procédé selon une quelconque des revendications 1 à 10, caractérisé en ce que la découpe est effectuée mécaniquement par cisaillage ou sciage, par faisceau laser ou par jet liquide. 11) Method according to any one of claims 1 to 10, characterized in that that the cutting is carried out mechanically by shearing or sawing, by beam laser or by liquid jet. 12) Procédé selon une quelconque des revendications 1 à 11, caractérisé en ce que le lit de fusion est constitué d'au moins 5 % et préférentiellement d' au moins 15 %
de copeaux d'usinage. 12) Method according to any one of claims 1 to 11, characterized in that that the bed of fusion consists of at least 5% and preferably at least 15%
of machining chips. 13) Procédé selon une quelconque des revendications 1 à 12, caractérisé en ce que une longueur comprise entre 50 mm et 1000 mm, et préférentiellement comprise entre mm et 500 mm en début et à la fin de la tôle ne comporte pas de profil et a une épaisseur sensiblement constante. 13) Method according to any one of claims 1 to 12, characterized in that that a length between 50 mm and 1000 mm, and preferably between mm and 500 mm at the beginning and at the end of the sheet does not have a profile and has a substantially constant thickness. 14) Procédé selon la revendication 13, caractérisé en ce que la tôle comporte entre les talons dépourvus de canaux usinés et la zone centrale possédant des canaux usinés une zone de transition dont l'épaisseur décroît du talon dépourvu de canaux usinés vers la zone centrale possédant des canaux usinés. 14) Method according to claim 13, characterized in that the sheet comprises between the heels without machined channels and the central area with channels machined one transition zone whose thickness decreases from the heel without machined channels around the central area with machined channels. 15) Procédé selon une quelconque des revendications 1 à 14, caractérisé en ce que la tôle a une largeur supérieure à 60 cm et préférentiellement supérieure à 120 cm. 15) Method according to any one of claims 1 to 14, characterized in that that the sheet has a width greater than 60 cm and preferably greater than 120 cm. 16) Procédé selon une quelconque des revendications 1 à 15, caractérisé en ce que la tôle a une longueur supérieure à 200 cm et préférentiellement supérieure à 500 cm. 16) Method according to any one of claims 1 to 15, characterized in that that the sheet has a length greater than 200 cm and preferably greater than 500 cm. 17) Procédé selon une quelconque des revendications 1 à 16, caractérisée en ce que la tôle à, avant usinage, une épaisseur supérieure à 15 mm et préférentiellement supérieure à 30 mm. 17) Method according to any one of claims 1 to 16, characterized in that that the sheet metal, before machining, a thickness greater than 15 mm and preferably higher at 30 mm. 18) Procédé selon une quelconque des revendications 1 à 17, caractérisé en ce que le talon non usiné et la zone de transition sont éboutés après la traction contrôlée. 18) Method according to any one of claims 1 to 17, characterized in that that the non-machined heel and transition zone are trimmed after traction controlled. 19) Procédé selon une quelconque des revendications 1 à 18, caractérisé en ce qu'en effectue la traction contrôlée entre deux mors jusqu'à un allongement permanent contrôlé de plus de 0.5% et de préférence de plus de 1%, et qu'on maintient, pendant au moins une partie de la durée de la traction, un appui transversal sur l'une au moins des faces de la tôle. 19) Method according to any one of claims 1 to 18, characterized in that that performs controlled traction between two jaws until elongation permanent controlled by more than 0.5% and preferably by more than 1%, and which is maintained, during at less part of the duration of the traction, a transverse support on one at less sheet metal faces. 20) Procédé selon la revendication 19, caractérisée en ce que l'allongement permanent est supérieur à 1,5%. 20) Method according to claim 19, characterized in that the elongation permanent is greater than 1.5%. 21) Procédé selon une quelconque de revendications 19 ou 20, caractérisé en ce que l'appui sur la face ou les faces de la tôle est réalisé par un ou plusieurs rouleaux soumis à un effort d'application sur la tôle. 21) Method according to any one of claims 19 or 20, characterized in that than support on the face or faces of the sheet is made by one or more rollers subject to an application force on the sheet. 22 22) Procédé selon la revendication 21, caractérisé en ce que les rouleaux sont mobiles longitudinalement sur la face de la tôle. 22 22) Method according to claim 21, characterized in that the rollers are mobile longitudinally on the face of the sheet. 23) Pièce métallique usinée susceptible d'être obtenue par le procédé selon une quelconque des revendications 1 à 22. 23) Machined metal part capable of being obtained by the process according to a any of claims 1 to 22. 24) Pièce métallique usinée selon la revendication 23, caractérisée en ce que ladite tôle est en alliage 7449 et montre au fond d'un canal usiné
- une valeur de K app(L-T) de 90 MPa.sqroot.m, et préférentiellement même de 90 MPa.sqroot.m (éprouvette de type CT avec W = 75 mm selon ASTM E561-98), et - une valeur de R m(L) mesurée en traction supérieure à 550 MPa. 24) Machined metal part according to claim 23, characterized in that said sheet is made of 7449 alloy and shows at the bottom of a machined channel - a value of K app (LT) of 90 MPa.sqroot.m, and preferably even of 90 MPa.sqroot.m (CT type test piece with W = 75 mm according to ASTM E561-98), and - a value of R m (L) measured in tension greater than 550 MPa. 25) Utilisation d'une pièce métallique susceptible d'être obtenue par le procédé selon une quelconque des revendications 1 à 22 comme élément de structure dans la construction aéronautique. 25) Use of a metal part capable of being obtained by the process according any one of claims 1 to 22 as a structural element in the aeronautical construction. 26) Utilisation d'une pièce métallique en alliage d'aluminium susceptible d'être obtenue par le procédé selon une quelconque des revendications 1 à 22 comme panneau de voilure, élément de fuselage, longeron, nervure ou caisson central d'aile. 26) Use of a metallic piece of aluminum alloy susceptible to be obtained by the method according to any one of claims 1 to 22 as a panel wing, fuselage element, spar, rib or central wing box. 27) Elément de structure en alliage d'aluminium pour construction aéronautique susceptible d'être obtenu par le procédé selon une quelconque des revendications 1 à 22. 27) Aluminum alloy structural element for aeronautical construction likely to be obtained by the process according to any one of claims 1 to 22.
CA2508534A 2002-12-17 2003-12-17 Method for making structural elements by machining thick plates Expired - Fee Related CA2508534C (en)

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
FR02/15997 2002-12-17
FR0215997A FR2848480B1 (en) 2002-12-17 2002-12-17 METHOD OF MANUFACTURING STRUCTURAL ELEMENTS BY MACHINING THICK TOLES
US44699303P 2003-02-13 2003-02-13
US60/446,993 2003-02-13
PCT/FR2003/003753 WO2004056501A2 (en) 2002-12-17 2003-12-17 Method for making structural elements by machining thick plates

Publications (2)

Publication Number Publication Date
CA2508534A1 true CA2508534A1 (en) 2004-07-08
CA2508534C CA2508534C (en) 2011-06-21

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CA2508534A Expired - Fee Related CA2508534C (en) 2002-12-17 2003-12-17 Method for making structural elements by machining thick plates

Country Status (7)

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EP (1) EP1573080B1 (en)
JP (1) JP2006510808A (en)
AU (1) AU2003300632A1 (en)
BR (1) BR0317336B1 (en)
CA (1) CA2508534C (en)
RU (1) RU2341585C2 (en)
WO (1) WO2004056501A2 (en)

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FR2900160B1 (en) * 2006-04-21 2008-05-30 Alcan Rhenalu Sa METHOD FOR MANUFACTURING A STRUCTURAL ELEMENT FOR AERONAUTICAL CONSTRUCTION COMPRISING A DIFFERENTIAL NUT
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CN102282284A (en) * 2009-01-16 2011-12-14 阿勒里斯铝业科布伦茨有限公司 Method for the manufacture of an aluminium alloy plate product having low levels of residual stress
US9314826B2 (en) 2009-01-16 2016-04-19 Aleris Rolled Products Germany Gmbh Method for the manufacture of an aluminium alloy plate product having low levels of residual stress
CN102179422B (en) * 2010-12-29 2013-03-27 山东华盛荣镁业科技有限公司 Method for preparing metal plane plate
CN102303064A (en) * 2011-09-13 2012-01-04 王辉 Trapezoidal teeth dual-roller extrusion steel plate forming machine device
FR2997706B1 (en) * 2012-11-08 2014-11-07 Constellium France METHOD FOR MANUFACTURING A VARIABLE THICKNESS STRUCTURE ELEMENT FOR AERONAUTICAL CONSTRUCTION
JP6093192B2 (en) * 2013-01-25 2017-03-08 三菱航空機株式会社 Aircraft fuselage panel, aircraft wing
WO2016182794A1 (en) * 2015-05-08 2016-11-17 Novelis Inc. Shock heat treatment of aluminum alloy articles
RU2621499C2 (en) * 2015-11-17 2017-06-06 Федеральное государственное автономное образовательное учреждение высшего образования "Национальный исследовательский технологический университет "МИСиС" Method for producing castings of high-strength aluminium-based alloys
WO2018075353A1 (en) 2016-10-17 2018-04-26 Novelis Inc. Metal sheet with tailored properties
FR3059578B1 (en) 2016-12-07 2019-06-28 Constellium Issoire METHOD FOR MANUFACTURING A STRUCTURE ELEMENT
WO2021029925A1 (en) 2019-06-03 2021-02-18 Novelis Inc. Ultra-high strength aluminum alloy products and methods of making the same
RU2771167C1 (en) * 2021-06-10 2022-04-27 Акционерное общество "Государственный Рязанский приборный завод" (АО "ГРПЗ") Method for manufacturing an aluminum wrought alloy casing

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Also Published As

Publication number Publication date
WO2004056501A3 (en) 2004-08-19
BR0317336A (en) 2005-11-08
BR0317336B1 (en) 2013-07-09
JP2006510808A (en) 2006-03-30
EP1573080A2 (en) 2005-09-14
EP1573080B1 (en) 2010-10-27
RU2005122471A (en) 2006-02-10
WO2004056501A2 (en) 2004-07-08
RU2341585C2 (en) 2008-12-20
AU2003300632A8 (en) 2004-07-14
CA2508534C (en) 2011-06-21
AU2003300632A1 (en) 2004-07-14

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