EP3899075B1 - Alliages al-zn-cu-mg et leur procédé de fabrication - Google Patents

Alliages al-zn-cu-mg et leur procédé de fabrication Download PDF

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EP3899075B1
EP3899075B1 EP19828721.1A EP19828721A EP3899075B1 EP 3899075 B1 EP3899075 B1 EP 3899075B1 EP 19828721 A EP19828721 A EP 19828721A EP 3899075 B1 EP3899075 B1 EP 3899075B1
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alloy
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EP3899075A1 (fr
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Erembert NIZERY
Ricky WHELCHEL
Jean-Christophe Ehrstrom
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Constellium Issoire SAS
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    • 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
    • C22C21/10—Alloys based on aluminium with zinc 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
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
    • C21D9/46—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for sheet metals

Definitions

  • the present invention relates generally to aluminum base alloys and more particularly, Al-Zn-Cu-Mg aluminum base alloys, in particular for aerospace applications.
  • Al-Zn-Cu-Mg aluminum base alloys have been used extensively in the aerospace industry for many years. With the evolution of airplane structures and efforts directed towards the goal of reducing both weight and cost, an optimum compromise between properties such as strength, toughness and corrosion resistance is continuously sought. Also, process improvement in casting, rolling and heat treatment can advantageously provide further control in the composition diagram of an alloy and property compromise.
  • Thick rolled, forged or extruded products made of Al-Zn-Cu-Mg aluminum base alloys are used in particular to produce integrally machined high strength structural parts for the aeronautic industry, for example wing elements such as wing ribs, spars, frames and the like, which are typically machined from thick wrought sections.
  • Crack deviation, crack turning or also crack branching are terms used to express propensity for crack propagation to deviate from the expected fracture plane perpendicular to the loading direction during a fatigue or toughness test. Crack deviation happens on a microscopic scale ( ⁇ 100 ⁇ m), on a mesoscopic scale (100-1000 ⁇ m) or on a macroscopic scale (>1 mm) but it is considered detrimental only if the crack direction remains stable after deviation (macroscopic scale). The phenomenon is a particular concern for fatigue trials in L-S direction.
  • the term crack branching is used herein for macroscopic deviation of cracks in L-S fatigue or toughness tests from the S direction towards the L direction which occurs for rolled products with a thickness of 30 mm or higher. Crack branching may occur in relation to the rolled product composition and microstructure and to the test conditions.
  • US Patent 5,560,789 describes AA 7000 series alloys having high mechanical strength and a process for obtaining them.
  • the alloys contain, by weight, 7 to 13.5% Zn, 1 to 3.8% Mg, 0.6 to 2.7% Cu, 0 to 0.5% Mn, 0 to 0.4% Cr, 0 to 0.2% Zr, others up to 0.05% each and 0.15% total, and remainder Al, corrosion properties are however not mentioned.
  • US Patent No 5,865,911 describes an aluminum alloy consisting essentially of (in weight %) about 5.9 to 6.7% zinc, 1.8 to 2.4% copper, 1.6 to 1.86% magnesium, 0.08 to 0.15% zirconium balance aluminum and incidental elements and impurities.
  • the '911 patent particularly mentions the compromise between static mechanical strength and toughness.
  • US Patent application N° US20050167016A1 discloses in particular an Al-Zn-Cu-Mg product comprising (in weight %) : 5.8-6.8% Zn, 1.5-2.5% Cu, 1.5-2.5% Mg, 0.04-0.09% Zr remainder aluminum and incidental impurities, wherein said product possesses a recrystallization rate greater than about 35% at a quarter thickness location, with improved fatigue crack growth resistance.
  • US Patent No 6,027,582 describes a rolled, forged or extruded Al-Zn-Mg-Cu aluminum base alloy products greater than 60 mm thick with a composition of (in weight %), Zn : 5.7-8.7, Mg : 1.7-2.5, Cu : 1.2-2.2, Fe : 0.07-0.14, Zr : 0.05-0.15 with Cu + Mg ⁇ 4.1 and Mg>Cu.
  • the '582 patent also describes improvements in quench sensitivity.
  • US Patent No 6,972,110 teaches an alloy, which contains preferably (in weight %) Zn : 7-9.5, Mg : 1.3-1.68 and Cu 1.3-1.9 and encourages keeping Mg +Cu ⁇ 3.5.
  • the '110 patent discloses using a three step aging treatment in order to improve resistance to stress corrosion cracking. A three step aging is long and difficult to master and it would be desirable to obtain high corrosion resistance without necessarily requiring such a thermal treatment.
  • PCT Patent application No WO2004090183 discloses an alloy comprising essentially (in weight percent): Zn: 6.0 - 9.5, Cu: 1.3 - 2.4, Mg: 1.5 - 2.6, Mn and Zr ⁇ 0.25 but preferably in a range between 0.05 and 0.15 for higher Zn contents, other elements each less than 0.05 and less than 0.25 in total, balance aluminium, wherein (in weight percent): 0.1[Cu] + 1.3 ⁇ [Mg] ⁇ 0.2[Cu] + 2.15, preferably 0.2[Cu] + 1.3 ⁇ [Mg] ⁇ 0.1[Cu] + 2.15.
  • US Patent application No 2005/006010 a method for producing a high strength Al-Zn-Cu-Mg alloy with an improved fatigue crack growth resistance and a high damage tolerance, comprising the steps of casting an ingot with the following composition (in weight percent) Zn 5.5-9.5, Cu 1.5-3.5, Mg 1.5-3.5, Mn ⁇ 0.25, Zr ⁇ 0.25, Cr ⁇ 0.10, Fe ⁇ 0.25, Si ⁇ 0.25, Ti ⁇ 0.10, Hf and/or V ⁇ 0.25, other elements each less than 0.05 and less than 0.15 in total, balance aluminum, homogenizing and/or pre-heating the ingot after casting, hot rolling the ingot and optionally cold rolling into a worked product of more than 50 mm thickness, solution heat treating, quenching the heat treated product, and artificially ageing the worked and heat-treated product, wherein the ageing step comprises a first heat treatment at a temperature in a range of 105 ° C to 135 ° C for more than 2 hours and less than 8 hours and a second heat treatment at a higher temperature than 135
  • EP Patent 1 544 315 discloses a product, especially rolled, extruded or forged, made of an AlZnCuMg alloy with constituents having the following percentage weights: Zn 6.7 - 7.3; Cu 1.9 - 2.5; Mg 1.0 - 2.0; Zr 0.07 - 0.13; Fe less than 0.15; Si less than 0.15; other elements not more than 0.05 to at most 0.15 per cent in total; and aluminum the remainder.
  • the product is preferably treated by solution heat treatment, quenching, cold rolling and artificial aging.
  • US Patent No 8,277,580 teaches a rolled or forged Al-Zn-Cu-Mg aluminum-based alloy wrought product having a thickness from 2 to 10 inches.
  • the product has been treated by solution heat-treatment, quenching and aging, and the product comprises (in weight-%): Zn 6.2-7.2, Mg 1.5-2.4, Cu 1.7-2.1.
  • Fe 0-0.13, Si 0-0.10, Ti 0-0.06, Zr 0.06-0.13, Cr 0-0.04, Mn 0-0.04, impurities and other incidental elements ⁇ 0.05 each.
  • US Patent No 8,673,209 discloses aluminum alloy products about 4 inches thick or less that possesses the ability to achieve, when solution heat treated, quenched, and artificially aged, and in parts made from the products, an improved combination of strength, fracture toughness and corrosion resistance, the alloy consisting essentially of: about 6.8 to about 8.5 wt. % Zn, about 1.5 to about 2.00 wt. % Mg, about 1.75 to about 2.3 wt. % Cu; about 0.05 to about 0.3 wt. % Zr, less than about 0.1 wt. % Mn, less than about 0.05 wt. % Cr, the balance Al, incidental elements and impurities and a method for making same.
  • a problem that the present invention addresses is to obtain thick rolled products of the 7XXX alloy series with improved fatigue crack growth rate without increased tendency of crack deviation, while maintaining a good balance between mechanical strength, fracture toughness, resistance to corrosion, quench sensitivity, fatigue resistance, and level of residual stress.
  • thick rolled products it is meant products with a thickness of at least 80 mm or even of at least 100 mm.
  • An object of the invention was to provide an Al-Zn-Cu-Mg alloy having a specific composition range and manufacturing process that enables, for thick rolled products, an improved fatigue crack growth rate without increased tendency of crack deviation.
  • Another object of the invention was the provision of a manufacturing process of wrought aluminum products which enables an improved compromise improved fatigue crack growth rate without increased tendency of crack deviation.
  • the present invention is directed to a rolled product having a thickness of at least 80 mm comprising (in weight %) :
  • the present invention is directed the present invention is directed to a process for the manufacture of a rolled aluminum-based alloy product comprising the steps of:
  • static mechanical characteristics i.e., the ultimate tensile strength UTS, the tensile yield stress TYS and the elongation at fracture E, are determined by a tensile test according to standard NF EN ISO 6892-1 (2016), the location at which the pieces are taken and their direction being defined in standard EN 485 (2016).
  • the fracture toughness K 1C is determined according to ASTM standard E399 (2012).
  • EAC Environmentally Assisted Cracking
  • the tendency to crack deviation is observed using a L-S Compact Tension C(T) fatigue specimen as defined in ASTM E647.
  • the term "deviation" in is not meant herein as described in ASTM E647-15 (which definition is focused on the precision of measurement of fatigue crack growth rate), but is meant as the crack remaining within a cone of ⁇ 20°and preferably of ⁇ 15°, which origin is at the intersection of a line passing through the holes centers and a specimen axis of symmetry, illustrated by the line A-A in Figure 1 .
  • a representation of the specimen used is shown in Figure 1 which also illustrates with a bold line the cone of ⁇ 20°.
  • Figure 2a shows schematically the CT specimen before the fatigue test.
  • Figure 2b shows a cracked specimen without a tendency to crack deviation: the cracks remains with the cone illustrated by bolded lines.
  • Figure 2c shows a specimen with a tendency of crack deviation.
  • structural member is a term well known in the art and refers to a component used in mechanical construction for which the static and/or dynamic mechanical characteristics are of particular importance with respect to structure performance, and for which a structure calculation is usually prescribed or undertaken. These are typically components the rupture of which may seriously endanger the safety of the mechanical construction, its users or third parties.
  • structural members comprise members of the fuselage (such as fuselage skin), stringers, bulkheads, circumferential frames, wing components (such as wing skin, stringers or stiffeners, ribs, spars), empennage (such as horizontal and vertical stabilizers), floor beams, seat tracks, and doors.
  • the alloy of the invention has a specific composition and microstructure which makes possible to obtain products which have a very low fatigue crack growth rate and do not have a tendency to crack deviation.
  • a minimum Zn content of 6.85 and preferably 6.90 or even 6.90 is needed to obtain sufficient strength.
  • the Zn content should not exceed 7.25 and preferably 7.20 or even 7.15 to obtain the sought balance of properties, in particular toughness and elongation.
  • a minimum Mg content of 1.55 and preferably 1.60 or even 1.65 is needed to obtain sufficient strength.
  • the Mg content should not exceed 1.95 and preferably 1.90 or even 1.85 to obtain the sought balance of properties in particular toughness and elongation and avoid quench sensitivity.
  • a minimum Cu content of 1.90 and preferably 1.95 or 2.00, or even 2.05 is needed to obtain sufficient strength and also to obtain sufficient EAC performance.
  • the Cu content should not exceed 2.30 and preferably 2.25 in particular to avoid quench sensitivity.
  • the Cu maximum content is 2.20.
  • the sum Cu + Mg is preferably controlled between 3.8 and 4.2.
  • the alloys of the present invention further contains 0.04 to 0.10 wt.% zirconium, which is typically used for grain size control.
  • the control of the zirconium content in combination with the hot rolling conditions is important to obtain the desired microstructural properties of the invention which are at mid-thickness more than 75 % of recrystallized grains or at mid-thickness 30 to 75 % of recrystallized grains and non-recrystallized grains with an aspect ratio in a L/ST cross section less than 3.
  • the Zr content should preferably comprise at least about 0.05 wt. %, but should advantageously remain below about 0.08 or even 0.07 wt.%.
  • Titanium associated with incidental elements such as boron or carbon can usually be added if desired during casting in order to limit the as-cast grain size.
  • the present invention may typically accommodate up to about 0.15 wt. % and preferably up to about 0.06 wt.% Ti.
  • the Ti content is about 0.02 wt.% to about 0.06 wt.% and preferentially about 0.03 wt.% to about 0.05 wt.%.
  • the present alloy can further contain other elements to a lesser extent and in some embodiments, on a less preferred basis.
  • Iron and silicon typically affect fracture toughness properties. Iron and silicon content should generally be kept low, with a content of at most 0.15 wt.%, and preferably not exceeding about 0.13 wt.% or preferentially about 0.10 wt.% for iron and preferably not exceeding about 0.10 wt.% or preferentially about 0.08 wt.% for silicon. In one embodiment of the present invention, iron and silicon content are ⁇ 0.07 wt.%.
  • Other elements are impurities or incidental elements which should have a maximum content of 0.05 wt.% each and ⁇ 0.15 wt.% total, preferably a maximum content of 0.03 wt.% each and ⁇ 0.10 wt. total.
  • a suitable process for producing rolled products according to the present invention comprises: (a) casting an ingot made in an alloy according to the invention, (b) conducting an homogenization of the ingot preferably with at least one step at a temperature from about 460 to about 510 °C or preferentially from about 470 to about 500 °C typically for 5 to 30 hours, (c) conducting hot rolling of said homogenized ingot in one or more stages by rolling, with an entry temperature preferably comprised from about 280 to about 420 °C, to a rolled product with a final thickness of at least 80 mm, (d) conducting a solution heat treatment preferably at a temperature from 460 to about 510 °C or preferentially from about 470 to about 500 °C typically for 1 to 10 hours depending on thickness and conducting a quench, preferentially with room temperature water, (e) conducting stress relieving by controlled stretching or compression with a permanent set of preferably less than 5% and preferentially from 1 to 4%, and, (f) conducting an artificial aging treatment.
  • the hot rolling entry temperature is controlled in order to obtain the desired microstructural properties of the invention which are at mid-thickness more than 75 % of recrystallized grains or at mid-thickness 30 to 75 % of recrystallized grains and non-recrystallized grains with an aspect ratio in a L/ST cross section less than 3.
  • the hot rolling starting temperature is at least 145 ⁇ Zr -0.313 - 20 and preferably at least 145 ⁇ Zr -0.313 - 10.
  • the hot rolling starting temperature is at most 145 ⁇ Zr -0.313 + 20 and preferably at least 145 ⁇ Zr -0.313 + 10.
  • Zr is the weight percent concentration of Zirconium in the alloy.
  • a rolled product of the present invention is a plate having a thickness from 80 to 200 mm, or advantageously from 100 to 180 mm comprising an alloy according to the present invention.
  • "Over-aged" tempers (“T7 type") are advantageously used in order to improve corrosion behavior in the present invention.
  • Tempers that can suitably be used for the products according to the invention, include, for example T6, T651, T73, T74, T76, T77, T7351, T7451, T7452, T7651, T7652 or T7751, the tempers T7351, T7451 and T7651 being preferred.
  • Aging treatment is advantageously carried out in two steps, with a first step at a temperature comprised between 110 and 130 °C for 3 to 20 hours and preferably for 4 or 5 to 12 hours and a second step at a temperature comprised between 140 and 170 °C and preferably between 150 and 165 °C for 5 to 30 hours.
  • the equivalent aging time t(eq) at 155°C is comprised between 8 and 35 or 30 hours and preferentially between 12 and 25 hours.
  • the narrow composition range of the alloy from the invention selected mainly for a strength versus toughness compromise provided rolled products with unexpectedly high EAC performance under conditions of high stress and humid environment.
  • a product according to the invention also preferably has preferably one, more preferably two and most preferably three of the following properties:
  • Rolled products according to the present invention are advantageously used as or incorporated in structural members for the construction of aircraft.
  • the products according to the invention are used in wing ribs, spars and frames.
  • the rolled products according to the present invention are welded with other rolled products to form wing ribs, spars and frames.
  • the ingots were then scalped and homogenized at about 475 °C.
  • the ingots were hot rolled to a plate of thickness of 102 mm (alloy A) or 110 mm (alloys B).
  • Hot rolling entry temperature was 350 °C for alloy A and 440 °C for alloy B.
  • the plates were solution heat treated with a soak temperature of about 475 °C.
  • the plates were quenched and stretched with a permanent elongation comprised between 2.0 and 2.5 %.
  • the reference plates were submitted to a two-step aging of 4 hours at 120 °C followed by approximately 15 hours at 155°C for a total equivalent time at 155 °C of 17 hours, to obtain a T7651 temper.
  • the plates made of alloy A had at mid-thickness more than 75 % of recrystallized grains and the plates of alloy B were substantially unrecrystallized, with a volume fraction of recrystallized grains lower than 35% at mid-thickness.
  • EAC under conditions of high stress and humid environment was measured with ST direction tensile specimens which are described in ASTM G47. Testing stress and environment were different from ASTM G47 and used a load of about 80% of ST direction TYS at t/2, under 85% relative humidity, and at a temperature of 70°C. The number of days to failure is provided for 3 specimens for each plate,
  • the plate made of alloy A resisted in average 33 days under a stress of 350 MPa for SCC testing under ASTM G47.
  • the L-S fatigue crack growth rate is reduced up to a factor at least 3 on CT specimens for the invention alloy A vs alloy B.
  • the ingot was then scalped and homogenized at 475 °C.
  • the ingot was hot rolled to a plate of thickness of 152 mm.
  • Hot rolling entry temperature was 420 °C.
  • the plate was solution heat treated with a soak temperature of 475 °C.
  • the plate was quenched and stretched with a permanent elongation comprised between 2.0 and 2.5 %.
  • the plate microstructure was not according to the invention, the plate made had at mid-thickness less than 20% of recrystallized grains.

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Claims (11)

  1. Produit laminé d'alliage à base d'aluminium ayant une épaisseur d'au moins 80 mm comprenant, (en % en poids) :
    Zn de 6,85 à 7,25,
    Mg de 1,55 à 1,95,
    Cu de 1,90 à 2,30,
    Zr de 0,04 à 0,10,
    Ti de 0 à 0,15,
    Fe de 0 à 0,15,
    Si de 0 à 0,15,
    d'autres éléments ≤ 0,05 chacun et ≤ 0,15 au total, le reste étant Al,
    dans lequel, à mi-épaisseur, plus de 75 % des grains sont recristallisés ou à mi-épaisseur, de 30 à 75 % des grains sont recristallisés et les grains non recristallisés possèdent un facteur de forme dans une section transversale L/ST inférieur à 3.
  2. Produit selon la revendication 1 dans lequel Cu de 1,95 à 2,25 et de préférence Cu : de 2,00 à 2,20.
  3. Produit selon la revendication 1 ou la revendication 2 dans lequel pendant un test de vitesse de propagation de fissure de fatigue selon la norme ASTM E647, la fissure reste au sein d'un cône de ± 20° et de préférence de ± 15°, dont l'origine est à l'intersection d'une ligne passant par des centres de trous d'éprouvette et un axe de symétrie d'éprouvette et da/dN à ΔK = 15 MPa√m est inférieur à 2,0 10-4 mm/cycle, de préférence inférieur à 1,0 10-4 mm/cycle et plus préférentiellement inférieur à 0,9 10-5 mm/cycle, sur une éprouvette de fatigue L-S C(T) à mi-épaisseur avec W = 40 mm et B = 10 mm.
  4. Produit selon l'une quelconque des revendications 1 à 3, dans lequel ledit produit possède au moins l'une des propriétés suivantes :
    a) une durée de vie minimale sans rupture après fissuration assistée par l'environnement (EAC) sous des conditions de contrainte élevée, à un niveau de contrainte transversale courte (ST) de 80 % de la limite d'élasticité en traction du produit dans la direction ST, et un environnement humide avec 85 % d'humidité relative à une température de 70 °C, d'au moins 30 jours et de préférence d'au moins 40 jours,
    b) une limite conventionnelle d'élasticité en traction mesurée dans la direction L au quart de l'épaisseur d'au moins 515 - 0,279 ∗ t MPa et de préférence 525 - 0,279 ∗ t MPa et encore plus préférentiellement 535 - 0,279 ∗ t MPa, t étant l'épaisseur du produit en mm,
    c) une ténacité K1C dans la direction L-T mesurée au quart de l'épaisseur d'au moins 32 - 0,1∗t MPa√m et de préférence 34-0,1 ∗ t MPa√m et encore plus préférentiellement 36 - 0,1 ∗ t MPa√m, t étant l'épaisseur du produit en mm.
  5. Produit selon l'une quelconque des revendications 1 à 4 dans lequel l'épaisseur de celui-ci est de 80 à 200 mm, ou avantageusement de 100 à 180 mm.
  6. Organe structurel approprié pour la construction d'aéronefs dans lequel ledit organe structurel est utilisé dans des nervures, des longerons et des armatures d'aile, comprenant un produit selon l'une quelconque des revendications 1 à 5.
  7. Procédé pour la fabrication d'un produit laminé d'alliage à base d'aluminium comprenant les étapes de :
    a) la coulée d'un lingot comprenant, (en % en poids)
    Zn de 6,85 à 7,25,
    Mg de 1,55 à 1,95,
    Cu de 1,90 à 2,30,
    Zr de 0,04 à 0,10,
    Ti de 0 à 0,15,
    Fe de 0 à 0,15,
    Si de 0 à 0,15,
    d'autres éléments ≤ 0,05 chacun et ≤ 0,15 au total, le reste étant Al ;
    b) l'homogénéisation du lingot ;
    c) le laminage à chaud dudit lingot homogénéisé en un produit laminé ayant une épaisseur finale d'au moins 80 mm ;
    d) le traitement thermique de mise en solution et la trempe du produit ;
    e) la relaxation des contraintes du produit mis en solution et trempé ;
    f) le vieillissement artificiel du produit relaxé ;
    dans lequel la température de début de laminage à chaud est régulée pour obtenir après l'étape f à mi-épaisseur, plus de 75 % de grains recristallisés ou à mi-épaisseur, de 30 à 75 % de grains recristallisés et des grains non recristallisés ayant un facteur de forme dans une section transversale L/ST inférieur à 3.
  8. Procédé selon la revendication 7 dans lequel la température de début de laminage à chaud est d'au moins 145∗Zr-0,313- 20 et de préférence d'au moins 145∗Zr-0,313- 10.
  9. Procédé selon la revendication 7 ou la revendication 8 dans lequel la température de début de laminage à chaud est d'au plus 145∗Zr-0,313 + 20 et de préférence d'au moins 145∗ Zr-0,313 + 10.
  10. Procédé selon l'une quelconque des revendications 7 à 9 dans lequel le temps de vieillissement équivalent t(eq) est compris entre 8 et 30 heures et de préférence entre 12 et 25 heures,
    le temps équivalent t(eq) à 155 °C étant défini par la formule : t eq = ∫ exp − 16000 / T dt exp − 16000 / T ref
    Figure imgb0004
     où T est la température instantanée en °K pendant un recuit et
    Tref est une température de référence sélectionnée à 155 °C (428 °K). t(eq) est exprimé en heures.
  11. Procédé selon l'une quelconque des revendications 7 à 10 dans lequel la température de traitement thermique de mise en solution est de 460 à environ 510 °C ou de préférence d'environ 470 à environ 500 °C.
EP19828721.1A 2018-12-20 2019-12-18 Alliages al-zn-cu-mg et leur procédé de fabrication Active EP3899075B1 (fr)

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EP18214960.9A EP3670690A1 (fr) 2018-12-20 2018-12-20 Alliages al-zn-cu-mg et leur procédé de fabrication
PCT/EP2019/086106 WO2020127592A1 (fr) 2018-12-20 2019-12-18 Alliages al-zn-cu-mg et leur procédé de fabrication

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EP4232613A4 (fr) * 2020-10-20 2024-10-09 Arconic Technologies LLC Alliages d'aluminium 7xxx améliorés
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CN116815083A (zh) * 2023-06-30 2023-09-29 中国航发北京航空材料研究院 一种提高高强韧铝合金应力腐蚀性能的方法
CN121344492B (zh) * 2025-12-19 2026-03-24 中南大学 一种降低铝锂合金剥落腐蚀敏感性的组织调控方法及铝锂合金

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BR112021010783A2 (pt) 2021-08-31
CN113166859A (zh) 2021-07-23

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