US20180363114A1 - Aluminum copper lithium alloy with improved mechanical strength and toughness - Google Patents

Aluminum copper lithium alloy with improved mechanical strength and toughness Download PDF

Info

Publication number
US20180363114A1
US20180363114A1 US15/780,273 US201615780273A US2018363114A1 US 20180363114 A1 US20180363114 A1 US 20180363114A1 US 201615780273 A US201615780273 A US 201615780273A US 2018363114 A1 US2018363114 A1 US 2018363114A1
Authority
US
United States
Prior art keywords
mpa
optionally
product
weight
thicknesses
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
US15/780,273
Other languages
English (en)
Inventor
Ricky WHELCHEL
Alireza Arbab
Bernard Bes
Christophe Sigli
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Constellium Issoire SAS
Original Assignee
Constellium Issoire SAS
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=55862869&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=US20180363114(A1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Constellium Issoire SAS filed Critical Constellium Issoire SAS
Assigned to CONSTELLIUM ISSOIRE reassignment CONSTELLIUM ISSOIRE ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ARBAB, ALIREZA, SIGLI, CHRISTOPHE, BES, BERNARD, WHELCHEL, Ricky
Publication of US20180363114A1 publication Critical patent/US20180363114A1/en
Pending legal-status Critical Current

Links

Images

Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/057—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C22C21/14—Alloys based on aluminium with copper as the next major constituent with silicon
    • 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
    • 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
    • C22C21/18—Alloys based on aluminium with copper as the next major constituent with zinc
    • 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
    • C22F1/002—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working by rapid cooling or quenching; cooling agents used therefor
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M2220/00—Batteries for particular applications
    • H01M2220/20—Batteries in motive systems, e.g. vehicle, ship, plane
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02E60/10—Energy storage using batteries

Definitions

  • the invention relates to aluminum-copper-lithium alloy products, and more particularly such products and methods of manufacturing and use, intended particular for aeronautical and aerospatial construction.
  • Products, and particularly thick rolled and/or forged products made of aluminum alloy, are developed to produce high strength parts intended particularly for the aeronautical industry, the aerospatial industry or mechanical construction, by cutting, surfacing or machining from one block.
  • Aluminum alloys containing lithium are very attractive in this respect because lithium can reduce the density of aluminum by 3% and increase the modulus of elasticity by 6% for each percent by weight of lithium added. If these alloys are to be selected for use in aircraft, their performance in service must be as good as that of currently used alloys, particularly in terms of a balance between static mechanical strength properties (yield stress, ultimate strength) and damage tolerance properties (toughness, resistance to propagation of fatigue cracks), these properties generally being antinomic. For thick products, these products must be obtained particularly at quarter-thickness and at mid-thickness and therefore the products must have low sensitivity to quenching. It is said that a product is sensitive to quenching if its static mechanical properties such as its yield stress decrease as the quenching rate decreases. The quenching rate is the average cooling rate of the product during quenching.
  • U.S. Pat. No. 5,032,359 describes a large family of aluminum-copper-lithium alloys in which the addition of magnesium and silver, particularly between 0.3 and 0.5 percent by weight, can increase the mechanical strength.
  • U.S. Pat. No. 7,229,509 describes an alloy containing (% by weight): (2.5-5.5) of Cu, (0.1-2.5) of Li, (0.2-1.0) of Mg, (0.2-0.8) of Ag, (0.2-0.8) of Mn, 0.4 max of Zr or other grain refining agents such as Cr, Ti, Hf, Sc, V, particularly with toughness K 1C (L)>37.4 MPa ⁇ m for yield stress R p0.2 (L)>448.2 MPa (products thicker than 76.2 mm) and particularly toughness K 1C (L)>38.5 MPa ⁇ m for yield stress R p0.2 (L)>489.5 MPa (products thinner than 76.2 mm).
  • the AA2050 alloy comprises (% by weight): (3.2-3.9) of Cu, (0.7-1.3) of Li, (0.20-0.6) of Mg, (0.20-0.7) of Ag, 0.25max. of Zn, (0.20-0.50) of Mn, (0.06-0.14) of Zr and the AA2095 alloy comprises (3.7-4.3) of Cu, (0.7-1.5) of Li, (0.25-0.8) of Mg, (0.25-0.6) of Ag, 0.25 max. of Zn, 0.25 max. of Mn, (0.04-0.18) of Zr.
  • AA2050 alloy products are known for their quality in terms of static mechanical strength and toughness, particularly for thick rolled products and are selected for some aircraft.
  • Patent application WO2009036953 describes an alloy with composition as a % by weight equal to Cu 3.4 to 5.0, Li 0.9 to 1.7, Mg 0.2 to 0.8, Ag 0.1 to 0.8, Mn 0.1 to 0.9, Zn up to 1.5, and one or several elements chosen from the group composed of: (Zr about 0.05 to 0.3, Cr about 0.05 to 0.3, Ti about 0.03 to 0.3, Sc about 0.05 to 0.4, Hf about 0.05 to 0.4), Fe ⁇ 0.15, Si ⁇ 0.5, normal and inevitable impurities, the remainder being aluminum.
  • Patent application US 2009/142222 A1 describes alloys comprising (% by weight), 3.4 to 4.2% of Cu, 0.9 to 1.4% of Li, 0.3 to 0.7% of Ag, 0.1 to 0.6% of Mg, 0.2 to 0.8% of Zn, 0.1 to 0.6% of Mn and 0.01 to 0.6% of at least one element for controlling the granular structure.
  • Patent application WO2011130180 describes strain hardened aluminum alloy products containing (in % by weight) from 2.75 to 5.0% of Cu, from 0.2 to 0.8% of Mg, in which the copper to magnesium (Cu/Mg) ratio in the aluminum alloy is within the range from about 6.1 to environ 17, from 0.1 to 1.10% of Li, from 0.3 to 2.0% of Ag, from 0.5 to 1.5% of zinc, up to 1.0% of Mn, the remainder being ‘aluminum, optional accessory elements and impurities.
  • Cu copper to magnesium
  • Patent application WO2013169901 describes aluminum alloys containing (in % by weight) from 3.5 to 4.4% of Cu, 0.45 to 0.75% of Mg, from 0.45 to 0.75% of Zn, 0.65-1.15% of Li, 0.1 to 1.0% of Ag, 0.05 to 0.50% of at least one grain structure control element, up to 1.0% de Mn, up to 0.15% of Ti, up to 0.12% of Si, up to 0.15% Fe, up to 0.10% of any other element, with the total of these elements not exceeding 0.35%, the remainder being aluminum.
  • Al—Cu—Li alloys are also known in which the addition of silver is optional or is not mentioned.
  • U.S. Pat. No. 5,455,003 describes a method of manufacturing Al—Cu—Li alloys that have improved mechanical strength and toughness at cryogenic temperatures, particularly due to appropriate strain hardening and ageing.
  • U.S. Pat. No. 5,211,910 describes alloys that may comprise (as a % by weight) from 1 to 7% of Cu, from 0.1 to 4% of Li, from 0.01 to 4% of Zn, from 0.05 to 3% of Mg, from 0.01 to 2% of Ag, from 0.01 to 2% of a grain refiner chosen from among Zr, Cr, Mn, Ti, Hf, V, Nb, B and TiB2, the remainder being Al with accidental impurities.
  • U.S. Pat. No. 5,259,897 describes a method of making aluminum-based alloys with compositions as a % by weight within the following ranges: from 3.5 to 5.0 of Cu, from 0.8 to 1.8 of Li, from 0.25 to 1.0 of Mg, from 0.01 to 1.5 of a grain refiner chosen from among Zr, Cr, Mn, Ti, Hf, V, Nb, B, TiB2 and mixtures thereof, the remainder being essentially Al.
  • Patent application WO2009103899 describes a rolled essentially unrecrystallized product containing the following % by weight: 2.2 to 3.9% by weight of Cu, 0.7 to 2.1% by weight of Li; 0.2 to 0.8% by weight of Mg; 0.2 to 0.5% by weight of Mn; 0.04 to 0.18% by weight of Zr; less than 0.05% by weight of Zn, and optionally 0.1 to 0.5% by weight of Ag, the remainder being aluminum and inevitable impurities, with low propensity to crack bifurcation during a fatigue test in the LS direction.
  • Patent application WO2012112942 describes products at least 12.7 mm thick made of aluminum alloy containing (% by weight) from 3.00 to 3.80% of Cu, from 0.05 to 0.35% of Mg, from 0.975 to 1.385% of Li, in which the Li content is between ⁇ 0.3 Mg-0.15Cu+1.65 and ⁇ 0.3 Mg-0.15Cu+1.55, from 0.05 to 0.50% of at least one element to control the granular structure chosen from the group composed of Zr, Sc, Cr, V, Hf, other rare earth elements and combinations of them up to 1.0% of Zn, up to 1.0% of Mn, up to 0.12% of Si, up to 0.15% of Fe, up to 0.15% of Ti, up to 0.10% of other elements, with the total of these other elements not exceeding 0.35%, the remainder being aluminum.
  • a first purpose of the invention is a rolled and/or forged aluminum-based alloy comprising the following % by weight,
  • V 0.02-0.3, preferably 0.02-0.1;
  • a second purpose of the invention is a method of manufacturing a product according to the invention in which
  • Another purpose of the invention is a structural element of an aircraft comprising a product according to the invention.
  • FIG. 1 represents the balance between the yield stress R p0.2 in the LT direction and the toughness K 1C in the T-L direction for a thickness of 50 mm.
  • FIG. 2 represents the balance between the yield stress R p0.2 in the ST direction and the toughness K 1C in the S-L direction for a thickness of 50 mm.
  • FIG. 3 represents the balance between the yield stress R p0.2 in the LT direction and the toughness K 1C in the T-L direction for a thickness of 102 mm.
  • FIG. 4 represents the balance between the yield stress R p0.2 in the ST direction and the toughness K 1C in the S-L direction for a thickness of 102 mm.
  • FIG. 5 represents the balance between the yield stress R p0.2 in the ST direction and the toughness K 1C in the S-L direction for a thickness of 130 mm.
  • FIG. 6 represents the difference in toughness for quenching conditions as a function of the difference in yield stress for these two quenching conditions for the tests in example 2.
  • static mechanical properties in other words the ultimate strength R m , the conventional yield stress at 0.2% elongation R p0.2 , and elongation at rupture A %, are determined by a tensile test according to standard EN ISO 6892-1: 2009 (formerly EN 10002-1:2001), sampling and the direction of the test being defined by standard EN 485-1 (EN 485-1:2008+A1:2009).
  • K Q The stress intensity factor (K Q ) is determined according to standard ASTM E 399 (ASTM E 399-12e3). Standard ASTM E 399 (ASTM E 399-12e3) gives criteria to determine if K Q is a valid value of K 1C . For a given test piece geometry, the values of K Q obtained for different materials are comparable with each other provided that the yield stresses of the materials are the same order of magnitude.
  • a curve giving the effective stress intensity factor as a function of the effective crack extension, known as the R curve, is determined according to ASTM standard E 561 (ASTM E 561-10e2).
  • the critical stress intensity factor K C in other words the intensity factor that makes the crack unstable, is calculated from the R curve.
  • the stress intensity factor K CO is also calculated by assigning the initial crack length at the beginning of the monotonous load, to the critical load. These two values are calculated for a test piece with the required shape.
  • K app represents the factor K CO corresponding to the test piece that was used to make the R curve test.
  • K eff represents the factor K C corresponding to the test piece that was used to make the R curve test.
  • a selected class of aluminum alloys containing specific and critical quantities of copper, lithium, magnesium, zinc, manganese and zirconium but essentially containing no silver can be used to prepare strain hardened products with an improved balance between toughness and mechanical strength, and good resistance to corrosion.
  • the inventors have observed that, surprisingly, for thick products it is possible to obtain an at least equivalent balance between static mechanical strength properties and damage tolerance properties as that obtained with an aluminum-copper-lithium allow containing silver, particularly such as the AA2050 alloy, by making a narrow selection of quantities of lithium, copper, magnesium, manganese, zinc and zirconium.
  • the copper content of products according to the invention is between 3.2 and 4.0% by weight. In one advantageous embodiment of the invention, the copper content is at least 3.3 or preferably at least 3.4% by weight and/or at most 3.8 and preferably at most 3.7% by weight.
  • the lithium content of products according to the invention is between 0.80 and 0.95% by weight.
  • the lithium content is advantageously between 0.84 and 0.93% by weight.
  • the lithium content is at least 0.86% by weight.
  • the silver content is less than 0.15% by weight, preferably less than 0.10% by weight and more preferably less than 0.05% by weight.
  • the inventors have observed that the advantageous balance between the mechanical strength and the damage tolerance known for alloys typically containing 0.3 to 0.4% by weight of silver can be obtained for alloys containing essentially no silver with the selected composition.
  • the magnesium content of products according to the invention is between 0.15 and 0.7%; and preferably between 0.2 and 0.6% by weight.
  • the magnesium content is at least 0.30% by weight and preferably at least 0.34%, and more preferably at least 0.38% by weight.
  • the inventors have observed that when the magnesium content is less than 0.30% by weight, the advantageous balance between mechanical strength and damage tolerance is not obtained for the highest thicknesses, particularly for thicknesses of more than 76 mm.
  • the inventors have observed that for the lowest contents of magnesium, typically contents of less than 0.5% by weight, preferably less than 0.45% by weight, the presence of a small quantity of silver can be advantageous, preferably the magnesium content is equal to at least (0.3-1.5*Ag). In one embodiment of the invention, the magnesium content is at most (0.55-1.5*Ag).
  • the magnesium content is at most 0.45% by weight and preferably at most 0.43% by weight. In one advantageous embodiment, the magnesium content is at most 0.45% by weight and preferably at most 0.43% by weight and the Ag content is less than 0.15% by weight, and preferably less than 0.10% by weight.
  • the zinc content is between 0.45 and 0.70% by weight.
  • the zinc content is between 0.50 and 0.60% by weight that can contribute to achieving the required balance between toughness and mechanical strength.
  • the zirconium content is between 0.07 and 0.15%; and preferably between 0.09 and 0.12% by weight.
  • the manganese content is between 0.1 and 0.6% by weight.
  • the manganese content is between 0.2 and 0.4% by weight and can improve the toughness without comprising the mechanical strength. If there is no added manganese, the required balance is not achieved.
  • the sum of the iron content and the silicon content is not more than 0.20% by weight.
  • the iron and silicon contents are not more than 0.08% each by weight.
  • the iron and silicon contents are not more than 0.06% and 0.04% by weight respectively.
  • the alloy also contains at least one element that can contribute to controlling the grain size, chosen from among V, Cr, Sc, Hf and Ti, the quantity of the element, if it is chosen, being from 0.02 to 0.3% by weight, preferably from 0.02 to 0.1 by weight for V, Cr; from 0.02 to 0.15% by weight, preferably from 0.02 to 0.1% by weight for Sc; from 0.02 to 0.5% by weight for Hf and from 0.01 to 0.15% by weight for Ti.
  • the quantity of the element if it is chosen, being from 0.02 to 0.3% by weight, preferably from 0.02 to 0.1 by weight for V, Cr; from 0.02 to 0.15% by weight, preferably from 0.02 to 0.1% by weight for Sc; from 0.02 to 0.5% by weight for Hf and from 0.01 to 0.15% by weight for Ti.
  • the alloy according to the invention is intended particularly for the manufacture of thick rolled and/or forged products, and more particularly thick rolled products.
  • thick products means products that are at least 12 mm and preferably at least 40 mm thick.
  • the rolled and/or forged products according to the invention are at least 76 mm thick or even at least 121 mm thick.
  • the thick products according to the invention provide a particularly advantageous balance between mechanical strength and toughness.
  • products according to the invention When in a rolled and/or forged, solution heat treated, quenched, stretched and aged temper, products according to the invention have at least one of the following pairs of characteristics for thicknesses of between 40 and 75 mm:
  • Products according to the invention in which the magnesium content is at least 0.34% by weight and preferably at least 0.38% by weight and the silver content is less than 0.10% by weight, and preferably less than 0.05% by weight, are advantageous and when in a rolled and/or forged, solution heat treated, quenched, stress relieved preferably by stretching, and aged temper, have at least one of the following pairs of characteristics for thicknesses of between 76 and 150 mm:
  • Products according to the invention also have advantageous properties in terms of toughness as measured according to standard ASTM E561 (ASTM E 561-10e2).
  • ASTM E561 ASTM E 561-10e2
  • the resistance of products according to the invention to stress corrosion is generally high; advantageously, the number of days before failure tested according to ASTM standards G47 and G49 (ASTM G47-98(2011) and G49-85(2011)) at mid-thickness for a stress in the ST direction equal to 350 MPa is at least 30 days and preferably, particularly for plates between 40 and 75 mm thick, the number of days before failure for a stress of 450 MPa in the ST direction is at least 30 days.
  • the method of manufacturing products according to the invention includes steps for production, casting, rolling and/or forging, solution heat treatment, quenching, stress relieving and ageing.
  • a liquid metal bath is produced so as to obtain an aluminum alloy with a composition according to the invention.
  • the liquid metal bath is then poured as an unwrought product, typically a rolling slab or as forging stock.
  • the unwrought product is then homogenized at a temperature of between about 450° C. and 550°, and preferably between about 480° C. and 530° C. for a duration of between 5 and 60 hours;
  • the unwrought product is generally cooled to ambient temperature before being preheated to be hot worked.
  • the purpose of preheating is to reach a temperature preferably between 400 and 550° C. and preferably of the order of 500° C. so that the unwrought product can be worked.
  • Hot working is achieved by rolling and/or forging so as to obtain a rolled and/or forged product preferably with a thickness of at least 12 mm and preferably at least 40 mm.
  • the product is then solution heat treated at between 490 and 550° C. for 15 minutes to 8 hours, then quenched typically in water at ambient temperature.
  • the product is then subjected to controlled stress relieving, preferably by tension and/or by compression, with a permanent set of 1 to 7% and preferably at least 2%.
  • the rolled products are preferably subjected to controlled stretching with a permanent set equal to at least 4%.
  • the controlled stretching is done with a permanent set of between 5 and 7%.
  • the preferred metallurgical tempers are the T84 and T86 tempers, and preferably T86.
  • Steps such as rolling, planing, straightening, shaping can be done optionally after solution heat treatment and before or after controlled stretching.
  • a cold rolling step is done to at least 7% and preferably at least 9% before applying controlled stretching with a permanent set of from 1 to 3%.
  • Said product is aged including heating to a temperature of between 130 and 170° C., preferably between 140 and 160° C., and more preferably between 140 and 150° C., for 5 to 100 hours and preferably 10 to 50h.
  • the inventors have observed that the balance between mechanical strength and toughness can be improved by ageing within the preferred range.
  • controlled stretching is applied with a permanent set of between 5 and 7% and ageing is done at a temperature of between 140 and 160° C., preferably between 140 and 150° C., for a duration of 10 to 30 h.
  • Products according to the invention can advantageously be used in structural elements, and particularly in aircraft.
  • a “structure element” or “structural element” in mechanical construction means a mechanical part for which the static and/or dynamic properties are particularly important for performance of the structure, and for which a structural calculation is normally specified or is performed. These are typically elements that, if they fail, could jeopardize the safety of said construction, its users or others.
  • these aircraft structural elements include particularly bulkheads, wings (such as the wing skin), ribs and spars and the tail plane composed particularly of horizontal or vertical stabilizer, and doors.
  • a structure element incorporating at least one product according to the invention or fabricated from such a product is advantageous, particularly for aeronautical construction.
  • Products according to the invention are particularly advantageous for manufacturing products machined from one block, particularly for lower wing skin or upper wing skin elements for which the skin and stiffeners originate from the same initial product, spars and ribs, and also for any other use for which these properties could be advantageous.
  • the slabs were homogenized at about 500° C. for about 12 hours and then scalped. The slabs were then hot rolled to obtain 50 mm, 102 mm or 130 mm thick slabs. The plates were solution heat treated at 527° C. and quenched with cold water. The plates were then stretched to give a permanent elongation of 4% or 6%.
  • the plates were aged at 145° C. or at 150° C. Samples were taken at 1 ⁇ 4-thickness to measure the static mechanical properties in tension and in toughness in the L, LT, L-T and T-L directions at 1 ⁇ 2-thickness to measure the static mechanical properties in tension and in toughness in the ST and S-L directions.
  • the test pieces used for measuring the toughness were test pieces with CT geometry and their dimensions were as defined below:
  • the slabs were machined to a thickness of 100 mm.
  • the slabs were homogenized at about 500° C. for about 12 hours and then scalped. After homogenization, the slabs were hot rolled to obtain 27 mm thick slabs.
  • the plates were solution heat treated and quenched in cold water or in hot water at 90° C. so as to vary the quenching rate and stretched with a permanent set of 3.5%.
  • the plates were aged at between 15 h and 50 h at 155 ° C. Samples were taken at mid-thickness to measure static mechanical properties in tension and the toughness K Q .
  • the width W of the test pieces used to measure the toughness in the T-L direction was 50 mm and their width B was 25 mm. The validity criteria of K 1C were satisfied for all samples.
  • FIG. 6 shows the reduction in properties (mechanical strength, toughness) for quenching in water at 90° C. as a percentage relative to the value with quenching in water at 25° C.
  • Composition 61 is the least sensitive to quenching for toughness
  • composition 58 is the least sensitive to quenching for the yield stress.
  • Plates made of alloy 56 were then aged for 40 hours at 150° C. and plates made of alloy 71 were aged for 20 hours at 150° C.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Heat Treatment Of Steel (AREA)
  • Forging (AREA)
  • Metal Rolling (AREA)
  • Conductive Materials (AREA)
US15/780,273 2015-12-04 2016-12-01 Aluminum copper lithium alloy with improved mechanical strength and toughness Pending US20180363114A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1561852A FR3044682B1 (fr) 2015-12-04 2015-12-04 Alliage aluminium cuivre lithium a resistance mecanique et tenacite ameliorees
FR1561852 2015-12-04
PCT/FR2016/053175 WO2017093680A1 (fr) 2015-12-04 2016-12-01 Alliage aluminium cuivre lithium a resistance mecanique et tenacite ameliorees

Publications (1)

Publication Number Publication Date
US20180363114A1 true US20180363114A1 (en) 2018-12-20

Family

ID=55862869

Family Applications (1)

Application Number Title Priority Date Filing Date
US15/780,273 Pending US20180363114A1 (en) 2015-12-04 2016-12-01 Aluminum copper lithium alloy with improved mechanical strength and toughness

Country Status (7)

Country Link
US (1) US20180363114A1 (fr)
EP (1) EP3384061B1 (fr)
CN (1) CN108291281B (fr)
BR (1) BR112018010380B1 (fr)
CA (1) CA3006871C (fr)
FR (1) FR3044682B1 (fr)
WO (1) WO2017093680A1 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BR112018015112A2 (pt) 2016-02-09 2018-12-18 Aleris Rolled Prod Germany Gmbh produto feito de liga de al-cu-li-mg-mn-zn
FR3080861B1 (fr) * 2018-05-02 2021-03-19 Constellium Issoire Procede de fabrication d'un alliage aluminium cuivre lithium a resistance en compression et tenacite ameliorees
WO2020097169A1 (fr) 2018-11-07 2020-05-14 Arconic Inc. Alliages d'aluminium-lithium de la série 2xxx
WO2020099124A1 (fr) * 2018-11-12 2020-05-22 Aleris Rolled Products Germany Gmbh Procédé de production d'une structure hydroformée à haute énergie à partir d'un alliage de la série 7xxx
FR3101641B1 (fr) * 2019-10-04 2022-01-21 Constellium Issoire Tôles de précision en alliage d’aluminium
FR3103123B1 (fr) * 2019-11-19 2022-07-01 C Tec Constellium Tech Center Procédé de fabrication d'une pièce en alliage d'aluminium
CN110952011B (zh) * 2019-11-22 2021-01-05 天津忠旺铝业有限公司 一种2系高损伤容限铝合金板材及其制备方法
CN111304503A (zh) * 2020-03-12 2020-06-19 江苏豪然喷射成形合金有限公司 一种航空机轮用低密度耐损伤铝锂合金及其制备方法

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040071586A1 (en) * 1998-06-24 2004-04-15 Rioja Roberto J. Aluminum-copper-magnesium alloys having ancillary additions of lithium
US20110247730A1 (en) * 2010-04-12 2011-10-13 Alcoa Inc. 2xxx series aluminum lithium alloys having low strength differential

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5455003A (en) 1988-08-18 1995-10-03 Martin Marietta Corporation Al-Cu-Li alloys with improved cryogenic fracture toughness
US5393357A (en) 1992-10-06 1995-02-28 Reynolds Metals Company Method of minimizing strength anisotropy in aluminum-lithium alloy wrought product by cold rolling, stretching and aging
US8673209B2 (en) 2007-05-14 2014-03-18 Alcoa Inc. Aluminum alloy products having improved property combinations and method for artificially aging same
FR2947282B1 (fr) * 2009-06-25 2011-08-05 Alcan Rhenalu Alliage aluminium cuivre lithium a resistance mecanique et tenacite ameliorees
CN102021457B (zh) 2010-10-27 2012-06-27 中国航空工业集团公司北京航空材料研究院 一种高强韧铝锂合金及其制备方法
CN101967588B (zh) 2010-10-27 2012-08-29 中国航空工业集团公司北京航空材料研究院 一种耐损伤铝锂合金及其制备方法
FR2969177B1 (fr) 2010-12-20 2012-12-21 Alcan Rhenalu Alliage aluminium cuivre lithium a resistance en compression et tenacite ameliorees
RU2587009C2 (ru) * 2011-02-17 2016-06-10 Алкоа Инк. Алюминий-литиевые сплавы серии 2ххх
FR2981365B1 (fr) * 2011-10-14 2018-01-12 Constellium Issoire Procede de transformation ameliore de toles en alliage al-cu-li
US10253404B2 (en) 2014-10-26 2019-04-09 Kaiser Aluminum Fabricated Products, Llc High strength, high formability, and low cost aluminum-lithium alloys

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040071586A1 (en) * 1998-06-24 2004-04-15 Rioja Roberto J. Aluminum-copper-magnesium alloys having ancillary additions of lithium
US20110247730A1 (en) * 2010-04-12 2011-10-13 Alcoa Inc. 2xxx series aluminum lithium alloys having low strength differential

Also Published As

Publication number Publication date
BR112018010380A2 (pt) 2018-12-04
WO2017093680A1 (fr) 2017-06-08
CN108291281A (zh) 2018-07-17
CN108291281B (zh) 2021-08-06
BR112018010380B1 (pt) 2021-09-14
CA3006871A1 (fr) 2017-06-08
FR3044682A1 (fr) 2017-06-09
CA3006871C (fr) 2023-11-07
FR3044682B1 (fr) 2018-01-12
EP3384061A1 (fr) 2018-10-10
EP3384061B1 (fr) 2020-02-05

Similar Documents

Publication Publication Date Title
US20180363114A1 (en) Aluminum copper lithium alloy with improved mechanical strength and toughness
US8277580B2 (en) Al-Zn-Cu-Mg aluminum base alloys and methods of manufacture and use
US11111562B2 (en) Aluminum-copper-lithium alloy with improved mechanical strength and toughness
US11976347B2 (en) Al—Zn—Cu—Mg alloys and their manufacturing process
US11472532B2 (en) Extrados structural element made from an aluminium copper lithium alloy
US8764920B2 (en) Aluminum-copper alloys containing vanadium
US20120152415A1 (en) Aluminum copper lithium alloy with improved resistance under compression and fracture toughness
US20120291925A1 (en) Aluminum magnesium lithium alloy with improved fracture toughness
US11174535B2 (en) Isotropic plates made from aluminum-copper-lithium alloy for manufacturing aircraft fuselages
US20240035138A1 (en) Thick plates made of al-cu-li alloy with improved fatigue properties
US20230012938A1 (en) Al-zn-cu-mg alloys with high strength and method of fabrication
US20210207254A1 (en) Al-Cu-Li-Mg-Mn-Zn ALLOY WROUGHT PRODUCT
US20240287665A1 (en) Aluminum-copper-lithium alloy products
US20210310108A1 (en) Aluminum-copper-lithium alloy having improved compressive strength and improved toughness
US20210388470A1 (en) Metal sheet made of high-strength 2xxx alloy for an aircraft fuselage
CN112105752B (zh) 具有改进的抗压强度和改进的韧性的铝-铜-锂合金的制造方法

Legal Events

Date Code Title Description
AS Assignment

Owner name: CONSTELLIUM ISSOIRE, FRANCE

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:WHELCHEL, RICKY;ARBAB, ALIREZA;BES, BERNARD;AND OTHERS;SIGNING DATES FROM 20180523 TO 20180622;REEL/FRAME:046200/0854

STPP Information on status: patent application and granting procedure in general

Free format text: DOCKETED NEW CASE - READY FOR EXAMINATION

STPP Information on status: patent application and granting procedure in general

Free format text: NON FINAL ACTION MAILED

STPP Information on status: patent application and granting procedure in general

Free format text: RESPONSE TO NON-FINAL OFFICE ACTION ENTERED AND FORWARDED TO EXAMINER

STPP Information on status: patent application and granting procedure in general

Free format text: NON FINAL ACTION MAILED

STPP Information on status: patent application and granting procedure in general

Free format text: RESPONSE TO NON-FINAL OFFICE ACTION ENTERED AND FORWARDED TO EXAMINER

STPP Information on status: patent application and granting procedure in general

Free format text: FINAL REJECTION MAILED

STPP Information on status: patent application and granting procedure in general

Free format text: DOCKETED NEW CASE - READY FOR EXAMINATION

STPP Information on status: patent application and granting procedure in general

Free format text: NON FINAL ACTION MAILED

STPP Information on status: patent application and granting procedure in general

Free format text: RESPONSE TO NON-FINAL OFFICE ACTION ENTERED AND FORWARDED TO EXAMINER

STPP Information on status: patent application and granting procedure in general

Free format text: FINAL REJECTION MAILED

STPP Information on status: patent application and granting procedure in general

Free format text: NON FINAL ACTION MAILED

STPP Information on status: patent application and granting procedure in general

Free format text: RESPONSE TO NON-FINAL OFFICE ACTION ENTERED AND FORWARDED TO EXAMINER

STPP Information on status: patent application and granting procedure in general

Free format text: FINAL REJECTION MAILED

STCV Information on status: appeal procedure

Free format text: NOTICE OF APPEAL FILED