EP2836620B1 - Aluminium-kupfer-lithium-legierung mit verbesserter schlagzähigkeit - Google Patents

Aluminium-kupfer-lithium-legierung mit verbesserter schlagzähigkeit Download PDF

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EP2836620B1
EP2836620B1 EP13722480.4A EP13722480A EP2836620B1 EP 2836620 B1 EP2836620 B1 EP 2836620B1 EP 13722480 A EP13722480 A EP 13722480A EP 2836620 B1 EP2836620 B1 EP 2836620B1
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mpa
thickness
extruded product
product according
weight
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EP2836620A1 (de
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Armelle Danielou
Mathieu MARQUETTE
Jérome PIGNATEL
Gaëlle POUGET
Timothy Warner
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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
    • C22C21/12—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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
    • B21C23/00—Extruding metal; Impact extrusion
    • B21C23/002—Extruding materials of special alloys so far as the composition of the alloy requires or permits special extruding methods of sequences
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
    • B21C23/00—Extruding metal; Impact extrusion
    • B21C23/02—Making uncoated products
    • B21C23/04—Making uncoated products by direct extrusion
    • B21C23/14—Making other products
    • B21C23/142—Making profiles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
    • B21C29/00—Cooling or heating work or parts of the extrusion press; Gas treatment of work
    • B21C29/003—Cooling or heating of work
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
    • B21C35/00—Removing work or waste from extruding presses; Drawing-off extruded work; Cleaning dies, ducts, containers, or mandrels
    • B21C35/02—Removing or drawing-off work
    • B21C35/023—Work treatment directly following extrusion, e.g. further deformation or surface treatment
    • 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
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals

Definitions

  • the invention relates to spun products made of aluminum-copper-lithium alloys, more particularly, such products, their manufacturing and use processes, intended in particular for aeronautical and aerospace construction.
  • Aluminum alloy spun products are developed to produce high strength parts for the aerospace industry and the aerospace industry in particular.
  • Aluminum alloy spun products are used in the aerospace industry for many applications, such as stiffeners or fuselage rails, fuselage frames, wing stiffeners, floor profiles or beams, as well as track rails. seat.
  • Ductile aluminum alloys have a significant ability to absorb impact energy during impact, in particular because they deform plastically.
  • the specific energy absorption capacity during a shock of an aluminum alloy profile can be connected to the curve obtained during a tensile test of the material in question, in particular to the area under the curve deformation force. It can thus be evaluated by the product R m x A% or R p0.2 x A% in the direction L and in the direction TL.
  • AlCuLi alloys are known.
  • the patent US 5,032,359 discloses a large family of aluminum-copper-lithium alloys in which the addition of magnesium and silver, in particular between 0.3 and 0.5 percent by weight, makes it possible to increase the mechanical strength.
  • the patent US5,455,003 discloses a process for manufacturing Al-Cu-Li alloys which have improved mechanical strength and toughness at cryogenic temperature, particularly through proper work-hardening and tempering.
  • the patent US7,438,772 discloses alloys comprising, in weight percent, Cu: 3-5, Mg: 0.5-2, Li: 0.01-0.9 and discourage the use of higher lithium contents due to degradation compromise between toughness and mechanical strength.
  • the patent US 7,229,509 discloses an alloy comprising (% by weight): (2.5-5.5) Cu, (0.1-2.5) Li, (0.2-1.0) Mg, (0.2-0, 8) Ag, (0.2-0.8) Mn, 0.4 max Zr or other grain refining agents such as Cr, Ti, Hf, Sc, V.
  • the patent application US 2009/142222 A1 discloses alloys comprising (in% by weight), 3.4 to 4.2% Cu, 0.9 to 1.4% Li, 0.3 to 0.7% Ag, 0.1 to 0, 6% Mg, 0.2 to 0.8% of Zn, 0.1 to 0.6% Mn and 0.01 to 0.6% of at least one element for controlling the granular structure. This application also describes a process for manufacturing spun products.
  • the patent application WO 2009/036953 discloses an alloy for structural elements comprising (in% by weight) 3.4 to 6.0% Cu, 0.9 to 1.7% Li, about 0.2 to 0.8% Mg, about 0 , 1 to 0.8% Ag, about 0.1 to 0.8% Mn, up to 1.5% Zn and one or more members selected from the group consisting of Zr, Cr, Ti, Sc and Hf, with Fe ⁇ 0.15 and Si ⁇ 0.15.
  • AA2195 alloy comprising (in% by weight) 3.7 to 4.3% Cu, 0.8 to 1.2% Li, 0.25 to 0.8% Mg, O, is also known.
  • Yet another object of the invention is the use of a product according to the invention for the aeronautical construction as a stiffener or smooth fuselage, fuselage frame, wing stiffener, profile or beam floor or seat rail.
  • alloys are in accordance with the regulations of The Aluminum Association, known to those skilled in the art. The density depends on the composition and is determined by calculation rather than by a method of measuring weight. The values are calculated in accordance with the procedure of The Aluminum Association, which is described on pages 2-12 and 2-13 of "Aluminum Standards and Data". The definitions of the metallurgical states are given in the European standard EN 515 .
  • the static mechanical characteristics in tension in other words the tensile strength R m , the conventional yield stress at 0.2% elongation R p0.2 , and the elongation at break A% are determined by a tensile test according to standard NF EN ISO 6892-1, the sampling and the direction of the test being defined by the EN 485-1 standard.
  • the stress intensity factor (K Q ) is determined according to ASTM E399.
  • ASTM E399 gives the criteria to determine if K Q is a valid K 1C value .
  • the thickness of the spun products is defined according to EN 2066: 2001: the cross section is divided into elementary rectangles of dimensions A and B; A being always the largest dimension of the elementary rectangle and B can be considered as the thickness of the elementary rectangle. The sole is the elementary rectangle with the largest dimension A.
  • a selected class of aluminum-copper-lithium alloys makes it possible to manufacture spun products having improved properties with respect to those of known products, in particular in terms of energy absorption during impact, static mechanical strength properties, corrosion resistance and low density.
  • the simultaneous addition of manganese, titanium, zirconium, magnesium and silver allows for the selected copper and lithium contents, to obtain a compromise between a representative parameter of the energy absorption during a shock and the yield point particularly advantageous.
  • the copper content is at least 4.2% by weight, preferably at least 4.3% and most preferably at least 4.35% by weight. In one embodiment of the invention, the copper content is at least 4.50% by weight.
  • the copper content is at most 4.8 wt.%, Preferably at most 4.7 wt.% And most preferably 4.55 wt.%.
  • the selected copper content improves in particular the static mechanical properties.
  • a high copper content is, however, unfavorable especially for the density of the alloy.
  • the lithium content is at least 0.9% by weight and preferably at least 0.95% by weight.
  • the lithium content is at most 1.1% by weight and preferably at most 1.05% by weight. In one embodiment of the invention, the lithium content is at most 1.04% by weight.
  • the selected lithium content improves in particular the energy absorbed during an impact.
  • An excessively low lithium content is however unfavorable, especially for the density of the alloy.
  • the addition of manganese is an important aspect of the present invention.
  • the manganese content is at least 0.2% by weight and preferably at least 0.3% by weight.
  • the manganese content is at most 0.6% by weight and preferably at most 0.5% by weight. In one embodiment of the invention, the manganese content is at most 0.40% by weight.
  • the addition of manganese in these amounts improves in particular the compromise between the desired properties.
  • the magnesium content is at least 0.2% by weight and preferably at least 0.30% by weight.
  • the magnesium content is at most 0.6% by weight and preferably at most 0.50% by weight.
  • the magnesium content is at most 0.40% by weight.
  • the silver content is at least 0.15% by weight.
  • Content silver is at most 0.25% by weight.
  • the present inventors have found that surprisingly silver addition of more than 0.25% by weight could have an adverse effect on the energy absorption during an impact. It is important to combine the silver content from 0.15% to 0.25% by weight to a controlled pull after dissolution and quenching with a permanent deformation of 2 to 4%, in particular because a controlled pull of less than 2% does not then allow to obtain the desired mechanical strength.
  • the addition of magnesium and silver is necessary to achieve the favorable compromise between static mechanical strength, absorbed energy, density and toughness.
  • the zirconium content is at least 0.07% by weight and preferably at least 0.10% by weight.
  • the zirconium content is at most 0.15% by weight and preferably at most 0.13% by weight.
  • the addition of zirconium is in particular necessary to maintain the essentially non-recrystallized structure desired for the spun products according to the invention.
  • the titanium content is between 0.01 and 0.15% by weight and preferably between 0.02 and 0.05% by weight.
  • the addition of titanium makes it possible in particular to obtain a controlled granular structure of the raw form obtained after casting.
  • the amount of Fe and Si is less than or equal to 0.1% by weight each. Preferably, the content of Fe and Si is less than 0.08% by weight each.
  • the Zn content is less than 0.2% by weight, preferably less than 0.15% by weight and preferably less than 0.1% by weight.
  • the presence of Zn can have an adverse effect on the compromise between static mechanical resistance, absorbed energy, density and toughness, especially since this element adversely affects the density of the alloy without having a favorable effect on the static mechanical resistance, absorbed energy and toughness.
  • the unavoidable impurities are maintained at a content of less than or equal to 0.05% by weight each and 0.15% by weight in total.
  • the products according to the invention preferably have, for a thickness of between 5 and 16 mm, a tenacity K 1C (LT) of at least 24 MPa m and preferably at least 25 MPa m and for a thickness of between 17 and 30 mm a tenacity K 1C (LT) of at least 21 MPa m and preferably at least 22 22 MPa m .
  • LT tenacity K 1C
  • the products according to the invention have an excellent resistance to corrosion.
  • the spun products according to the invention have a resistance of at least 30 days when a stress corrosion test according to ASTM G44 and ASTM G49 standards on specimens taken in the TL direction for a voltage of 450 MPa.
  • the spun products according to the invention are particularly advantageous for aircraft construction.
  • the products according to the invention are used for aeronautical construction as a stiffener or smooth fuselage, fuselage frame, wing stiffener, profile or beam floor or seat rail.
  • the products according to the invention are used as a floor beam, in particular as a beam of the lower floor of the aircraft, or cargo floor, this floor being particularly important during the impact.
  • the raw forms were homogenized at a temperature of 490 ° C to 520 ° C adapted according to their composition, spun as spun product described in FIG. Figure 1 whose thickness of the elementary rectangles is between 17 and 22 mm, with an initial hot deformation temperature of about 460 ° C.
  • the spun products obtained were dissolved at a temperature suitable for the alloy of between 500 ° C. and 520 ° C., quenched, triturated for about 3% and recovered for 30 hours at 155 ° C.
  • the figure 2 presents the trade-off between the elastic limit and the EA parameter.
  • the alloy according to the invention makes it possible to reach a particularly advantageous compromise.
  • the alloy spun product A according to the invention underwent a stress corrosion test according to ASTM G44 and ASTM G49 standards for a tension of 450 MPa on specimens taken in the TL direction. No rupture was observed after 30 days of testing.
  • the alloys A and B presented in Example 1 were spun as a spun product of a different shape and having lower elementary rectangles thicknesses between 5 and 12 mm.
  • the crude forms were homogenized 15h at 500 ° C and then 20-25 h at 510 ° C, spun as I-spun product with an initial hot deformation temperature of about 460 ° C.
  • the spun products obtained were dissolved at a temperature of approximately 510 ° C., quenched, triturated approximately 3.5% and returned for 30 hours at 155 ° C.
  • the mechanical properties in the longitudinal direction were measured on "full thickness” specimens taken from the various elementary rectangles of the spun product (thicknesses 5, 7 and 12 mm) and averaged for the different sections obtained.
  • the "full thickness” measurement underestimates the real value measured at mid-thickness on machined specimens, because of the effect of the different microstructure close to the surface.
  • a correction factor was introduced to account for this bias, however, the factor was chosen such that the actual machined test specimen value would likely be greater than the indicated corrected value.
  • the mechanical properties in the transverse direction were measured on machined specimens taken from the zone of smaller thickness, the only possible zone for this type of measurement because of the length of the specimens necessary for this measurement.
  • the toughness properties were measured on specimens taken from the thickest zone.
  • the structure of the spun products obtained was essentially non-recrystallized. The degree of recrystallized granular structure between 1 ⁇ 4 and 1 ⁇ 2 thickness was less than 10%.
  • the spun product according to the invention achieves a more favorable compromise than the spun product of reference between the mechanical strength and the EA parameter.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
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  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
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  • Crystallography & Structural Chemistry (AREA)
  • Heat Treatment Of Steel (AREA)
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Claims (12)

  1. Strangpresserzeugnis, bei dem die gemäß EN 2066:2001 bestimmte Dicke wenigstens eines elementaren Rechtecks zwischen 1 mm und 30 mm beträgt, aus einer Legierung auf Aluminiumbasis, enthaltend
    4,2 bis 4,8 Gew.-% Cu,
    0,9 bis 1,1 Gew.-% Li,
    0,15 bis 0,25 Gew.-% Ag,
    0,2 bis 0,6 Gew.-% Mg,
    0,07 bis 0,15 Gew.-% Zr,
    0,2 bis 0,6 Gew.-% Mn,
    0,01 bis 0,15 Gew.-% Ti,
    Zn in einer Menge von weniger als 0,2 Gew.-%, Fe und Si jeweils in einer Menge von 0,1 Gew.-% oder weniger, und unvermeidbare Verunreinigungen mit einem Gehalt von jeweils höchstens 0,05 Gew.-% und insgesamt höchstens 0,15 Gew.-%.
  2. Strangpresserzeugnis nach Anspruch 1, enthaltend 4,3 bis 4,7 Gew.-% Cu, vorzugsweise 4,35 bis 4,55 Gew.-% Cu.
  3. Strangpresserzeugnis nach Anspruch 1 oder 2, enthaltend 0,95 bis 1,05 Gew.-% Li.
  4. Strangpresserzeugnis nach irgendeinem der Ansprüche 1 bis 3, enthaltend 0,30 bis 0,50 Gew.-% Mg und/oder 0,10 bis 0,13 Gew.-% Zr.
  5. Strangpresserzeugnis nach irgendeinem der Ansprüche 1 bis 4, enthaltend 0,3 bis 0,5 Gew.-% Mn.
  6. Strangpresserzeugnis nach irgendeinem der Ansprüche 1 bis 5, enthaltend weniger als 0,15 % Zn, vorzugsweise weniger als 0,1 % Zn.
  7. Strangpresserzeugnis nach irgendeinem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass es ein Strangpressprofil ist, bei dem die Dicke wenigstens eines elementaren Rechtecks zwischen 2 und 20 mm und vorzugsweise zwischen 5 und 16 mm beträgt.
  8. Strangpresserzeugnis nach irgendeinem der Ansprüche 1 bis 7, bei dem der Rekristallisationsgrad zwischen einem Viertel und der halben Dicke eines elementaren Rechtecks weniger als 30 % und vorzugsweise weniger als 10 % beträgt.
  9. Strangpresserzeugnis nach irgendeinem der Ansprüche 1 bis 8, das in halber Dicke
    bei einer Dicke zwischen 5 und 16 mm
    eine mittlere Dehngrenze Rp0,2 in L-Richtung von mindestens 630 MPa und vorzugsweise mindestens 635 MPa und
    eine mittlere Dehngrenze Rp0,2 in TL-Richtung von mindestens 625 MPa und vorzugsweise mindestens 630 MPa und
    einen Faktor EA EA = Rm L + Rp 0,2 L / 2 * A ⁢ % L + Rm TL + Rp 0,2 TL / 2 * A ⁢ % TL
    Figure imgb0014
     von mindestens 14000 und vorzugsweise mindestens 14500 aufweist,
    und/oder
    bei einer Dicke zwischen 17 und 30 mm
    eine mittlere Dehngrenze Rp0,2 in L-Richtung von mindestens 655 MPa und vorzugsweise mindestens 660 MPa und
    eine mittlere Dehngrenze Rp0,2 in TL-Richtung von mindestens 600 MPa und vorzugsweise mindestens 605 MPa und
    einen Faktor EA EA = Rm L + Rp 0,2 L / 2 * A ⁢ % L + Rm TL + Rp 0,2 TL / 2 * A ⁢ % TL
    Figure imgb0015
     von mindestens 9500 und vorzugsweise mindestens 9800 aufweist.
  10. Erzeugnis nach Anspruch 9,
    das bei einer Dicke zwischen 5 und 16 mm eine Bruchzähigkeit KIC(L-T) von mindestens 24 MPa m
    Figure imgb0016
     und vorzugsweise mindestens 25 MPa m
    Figure imgb0017
     aufweist und bei einer Dicke zwischen 17 und 30 mm eine Bruchzähigkeit KIC(L-T) von mindestens 21 MPa m
    Figure imgb0018
     und vorzugsweise mindestens 22 MPa m
    Figure imgb0019
     aufweist.
  11. Verfahren zur Herstellung eines Strangpresserzeugnisses nach irgendeinem der Ansprüche 1 bis 10, bei dem
    (a) eine Rohform aus einer Legierung nach einem der Ansprüche 1 bis 6 gegossen wird,
    (b) die Rohform bei einer Temperatur von 490°C bis 520°C für 8 bis 48 Stunden homogenisiert wird,
    (c) die Rohform mit einer anfänglichen Warmumformtemperatur von 420°C bis 480°C durch Strangpressen warmumgeformt wird, um ein Strangpresserzeugnis zu erhalten,
    (d) das Strangpresserzeugnis bei einer Temperatur von 500°C bis 520°C für 15 Minuten bis 8 Stunden lösungsgeglüht wird,
    (e) ein Abschrecken erfolgt,
    (f) das Strangpresserzeugnis mit einer bleibenden Verformung von 2 bis 4 % kontrolliert gereckt wird,
    (g) das Strangpresserzeugnis optional gerichtet wird,
    (h) eine Auslagerungsbehandlung des Strangpresserzeugnisses durch Erwärmen auf eine Temperatur von 100°C bis 170°C für 5 bis 100 Stunden durchgeführt wird.
  12. Verwendung eines Erzeugnisses nach irgendeinem der Ansprüche 1 bis 10 für den Flugzeugbau als Rumpfversteifung oder Stringer, Rumpfrahmen, Flügelversteifung, Bodenprofil oder -träger oder Sitzschiene.
EP13722480.4A 2012-04-11 2013-04-10 Aluminium-kupfer-lithium-legierung mit verbesserter schlagzähigkeit Active EP2836620B1 (de)

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US201261622774P 2012-04-11 2012-04-11
FR1201063A FR2989387B1 (fr) 2012-04-11 2012-04-11 Alliage aluminium cuivre lithium a resistance au choc amelioree
PCT/FR2013/000096 WO2013153292A1 (fr) 2012-04-11 2013-04-10 Alliage aluminium cuivre lithium à résistance au choc améliorée

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FR3014904B1 (fr) * 2013-12-13 2016-05-06 Constellium France Produits files pour planchers d'avion en alliage cuivre lithium
RU2560485C1 (ru) * 2014-06-10 2015-08-20 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") Высокопрочный сплав на основе алюминия и изделие, выполненное из него
CN109890663B (zh) 2016-08-26 2023-04-14 形状集团 用于横向弯曲挤压成形铝梁从而温热成型车辆结构件的温热成型工艺和设备
JP7433905B2 (ja) 2016-10-24 2024-02-20 シェイプ・コープ 車両構成要素を製造するための多段アルミニウム合金成形及び熱処理方法
CN107964641B (zh) * 2017-10-18 2021-02-05 中国航发北京航空材料研究院 一种改善铝锂合金蠕变成形性能的热处理方法
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
FR3080860B1 (fr) * 2018-05-02 2020-04-17 Constellium Issoire Alliage aluminium cuivre lithium a resistance en compression et tenacite ameliorees
CN110423927A (zh) * 2019-07-17 2019-11-08 中南大学 一种超高强铝锂合金及其制备方法
CN110952010A (zh) * 2019-12-18 2020-04-03 东北轻合金有限责任公司 一种火箭槽体用耐高温铝合金板材的制造方法
CN116287913A (zh) * 2023-02-10 2023-06-23 南京航空航天大学 一种增材制造用微量元素改性铝锂合金粉末及其制备方法

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DE13722480T1 (de) 2015-06-25
WO2013153292A1 (fr) 2013-10-17
US20130269840A1 (en) 2013-10-17
FR2989387A1 (fr) 2013-10-18
EP2836620A1 (de) 2015-02-18
CA2869733C (fr) 2021-07-20
CN104220616B (zh) 2017-12-15
CA2869733A1 (fr) 2013-10-17
US9945010B2 (en) 2018-04-17
CN104220616A (zh) 2014-12-17
FR2989387B1 (fr) 2014-11-07
BR112014025110B1 (pt) 2019-04-24

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