WO2020127592A1 - 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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Publication number
WO2020127592A1
WO2020127592A1 PCT/EP2019/086106 EP2019086106W WO2020127592A1 WO 2020127592 A1 WO2020127592 A1 WO 2020127592A1 EP 2019086106 W EP2019086106 W EP 2019086106W WO 2020127592 A1 WO2020127592 A1 WO 2020127592A1
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thickness
product
mid
recrystallized
grains
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PCT/EP2019/086106
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English (en)
Inventor
Erembert NIZERY
Ricky WHELCHEL
Jean-Christophe Ehrstrom
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Constellium Issoire
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Application filed by Constellium Issoire filed Critical Constellium Issoire
Priority to US17/415,590 priority Critical patent/US20220081740A1/en
Priority to CN201980083452.1A priority patent/CN113166859A/zh
Priority to CA3121837A priority patent/CA3121837A1/fr
Priority to EP19828721.1A priority patent/EP3899075B1/fr
Priority to BR112021010783-5A priority patent/BR112021010783A2/pt
Publication of WO2020127592A1 publication Critical patent/WO2020127592A1/fr

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Classifications

    • 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
    • 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
    • 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

  • 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 pm), on a mesoscopic scale (100-1000 pm) 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
  • 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 A1— 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 W02004090183 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, Ftf 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 AIZnCuMg 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.
  • 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:
  • the hot rolling starting temperature is controlled to obtain after step f 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.
  • Figure 1 shows the C(T) specimen used for the Fatigue Crack Growth Rate testing.
  • a cone of ⁇ 20° which origin is at the intersection of a line passing through the holes centers and the specimen axis of symmetry used for the criteria of crack deviation is represented as a bold line.
  • Figure 2a is a schematic of the C(T) specimen showing before the fatigue test and the for the criteria of crack deviation.
  • Figure 2b shows a cracked specimen without a tendency to crack deviation: the cracks remains within the cone.
  • Figure 2c shows a specimen with a tendency of crack deviation.
  • Figure 3 shows specimen of alloy A after Fatigue Crack Growth Rate testing.
  • Figure 4 shows specimen of alloy B after Fatigue Crack Growth Rate testing.
  • Figure 5 shows specimen of alloy C after Fatigue Crack Growth Rate testing.
  • 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 Ki C is determined according to ASTM standard E399 (2012).
  • EAC Environmentally Assisted Cracking
  • 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°.
  • L 48 mm
  • W 40 mm
  • Z 50 mm
  • C 22 mm
  • B 10 mm.
  • 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. However, 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. However the Cu content should not exceed 2.30 and preferably 2.25 in particular to avoid quench sensitivity. In an embodiment the Cu maximum content is 2.20. In order to obtain products with low sensitivity to EAC under conditions of high stress and humid environment and avoid quench sensitivity, 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 ° 313 + 20 and preferably at least 145 *Zr ° 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 equivalent time t(eq) at 155°C being defined by the formula :
  • T is the instantaneous temperature in °K during annealing and T ref is a reference temperature selected at 155 °C (428 °K).
  • t(eq) is expressed in 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: a) a minimum life without failure after Environmentally Assisted Cracking (EAC) under conditions of high stress, at a short transverse (ST) stress level of 80% of the product tensile yield strength in ST direction, and humid environment with 85% relative humidity at a temperature of 70°C, of at least 20 days and preferably of at least 30 days, b) a conventional tensile yield strength measured in the L direction at quarter thickness of at least 515 - 0.279 * t MPa and preferably of 525 - 0.279 * t MPa and even more preferably of 535 - 0.279 * t MPa (t being the thickness of the product in mm),
  • EAC Environmentally Assisted Cracking
  • ST short transverse
  • 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.
  • Example 1 Two ingots were cast, one of a product according to the invention (A), and one reference example (B) with the following composition (Table 1) :
  • Table 1 composition (wt. %) of a cast according to the invention and a reference cast.
  • 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 15 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.
  • Example 2 One additional ingot was cast, with a composition according to the invention (C), (Table
  • Table 6 composition (wt. %) of cast C.
  • 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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Abstract

La présente invention concerne un produit d'alliage à base d'aluminium laminé ayant une épaisseur d'au moins 80 mm comprenant (en % en poids) : Zn 6,85 à 7,25, Mg 1,55 à 1,95, Cu 1,90 à 2,30, Zr 0,04 à 0,10, Ti 0 à 0,15, Fe 0 à 0,15, Si 0 à 0,15, autres éléments ≤ 0,05 chacun et ≤ 0,15 au total, le reste étant Al, où, à mi-épaisseur, plus de 75 % des grains sont recristallisés ou, à mi-épaisseur, 30 à 75 % des grains sont recristallisés et les grains non recristallisés ont un rapport d'aspect dans une section transversale L/ST inférieur à 3. L'invention concerne un procédé de fabrication d'un produit d'alliage à base d'aluminium laminé qui comprend les étapes de : (a) coulage d'un lingot fabriqué en un alliage selon l'invention, (b) conduite d'une homogénéisation du lingot (c) conduite d'un laminage à chaud dudit lingot homogénéisé en une ou plusieurs étapes par laminage, (d) conduite d'un traitement thermique de trempe en solution, (e) conduite d'un recuit de détente, et, (f) conduite d'un traitement de vieillissement artificiel. Les produits de l'invention sont appropriés pour la construction d'aéronefs et présentent des propriétés avantageuses de croissance de fissures de fatigue.
PCT/EP2019/086106 2018-12-20 2019-12-18 Alliages al-zn-cu-mg et leur procédé de fabrication WO2020127592A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US17/415,590 US20220081740A1 (en) 2018-12-20 2019-12-18 Al-zn-cu-mg alloys and their manufacturing process
CN201980083452.1A CN113166859A (zh) 2018-12-20 2019-12-18 Al-Zn-Cu-Mg合金及其制备方法
CA3121837A CA3121837A1 (fr) 2018-12-20 2019-12-18 Alliages al-zn-cu-mg et leur procede de fabrication
EP19828721.1A EP3899075B1 (fr) 2018-12-20 2019-12-18 Alliages al-zn-cu-mg et leur procédé de fabrication
BR112021010783-5A BR112021010783A2 (pt) 2018-12-20 2019-12-18 Ligas al-zn-cu-mg e processo de fabricação das mesmas

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP18214960.9A EP3670690A1 (fr) 2018-12-20 2018-12-20 Alliages al-zn-cu-mg et leur procédé de fabrication
EP18214960.9 2018-12-20

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US (1) US20220081740A1 (fr)
EP (2) EP3670690A1 (fr)
CN (1) CN113166859A (fr)
BR (1) BR112021010783A2 (fr)
CA (1) CA3121837A1 (fr)
WO (1) WO2020127592A1 (fr)

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WO2022086997A1 (fr) * 2020-10-20 2022-04-28 Arconic Technologies Llc Alliages d'aluminium 7xxx améliorés

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US20220145439A1 (en) * 2020-11-11 2022-05-12 Kaiser Aluminum Fabricated Products, Llc High Strength and High Fracture Toughness 7xxx Aerospace Alloy Products
CN113201671A (zh) * 2021-04-13 2021-08-03 上海交通大学 一种7系铝合金及提高其耐应力腐蚀能力的方法
CN113604688A (zh) * 2021-06-17 2021-11-05 机械科学研究总院（将乐）半固态技术研究所有限公司 一种大型激光切割机用铝合金横梁的铸造方法
CN114561532A (zh) * 2022-03-30 2022-05-31 中国兵器科学研究院宁波分院 一种7b52叠层铝合金板材的热处理方法

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

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