US20170218493A1 - Method for manufacturing products made of magnesium-lithium-aluminum alloy - Google Patents

Method for manufacturing products made of magnesium-lithium-aluminum alloy Download PDF

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US20170218493A1
US20170218493A1 US15/514,802 US201515514802A US2017218493A1 US 20170218493 A1 US20170218493 A1 US 20170218493A1 US 201515514802 A US201515514802 A US 201515514802A US 2017218493 A1 US2017218493 A1 US 2017218493A1
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mpa
product
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Gaëlle Pouget
Bernard Bes
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Constellium Issoire SAS
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Constellium Issoire SAS
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Priority claimed from FR1402186A external-priority patent/FR3026411B1/fr
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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
    • C22C21/06—Alloys based on aluminium with magnesium as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/047—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with magnesium as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/06—Alloys based on aluminium with magnesium as the next major constituent
    • C22C21/08—Alloys based on aluminium with magnesium as the next major constituent with silicon
    • 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

Definitions

  • the invention relates to a method for manufacturing a wrought product made of aluminum-magnesium-lithium alloy, more particularly a method for manufacturing such a product having an improved compromise of properties, in particular an improved compromise between the tensile yield strength and the toughness of said products.
  • the invention has also for object a product able to be obtained by said method for manufacturing and its use, said product being intended in particular for aeronautical and aerospace construction.
  • Wrought products made of an aluminum alloy are developed to produce high-resistance parts intended in particular for the aeronautical industry and the aerospace industry.
  • Aluminum alloys containing lithium are very interesting in this respect, as lithium can reduce the density of the aluminum by 3% and increase the elastic modulus by 6% for each percentage in weight of lithium added.
  • aluminum alloys containing simultaneously magnesium and lithium make it possible to reach particularly low densities and therefore have been studied extensively.
  • Patent GB 1.172.736 discloses an alloy containing, in percentage by weight, 4 to 7% of Mg, 1.5-2.6% of Li, 0.2-10 of Mn and/or 0.05-0.3% of Zr, the remainder is aluminum. This alloy is useful for the elaboration of products that have a high mechanical resistance, good corrosion resistance, low density and a high elastic modulus. Said products are obtained by a method comprising an optional quenching then an artificial aging. By way of example, the products coming from the method according to GB 1.172.736 have a ultimate tensile strength ranging from about 440 MPa to about 490 MPa, a tensile yield strength ranging from about 270 MPa to about 340 MPa and an elongation to fracture of about 5-8%.
  • This document also discloses a method for obtaining said alloy comprising the steps of: a) casting an ingot which has the composition described hereinabove, b) removing the residual stresses from said ingot by thermal treatment, c) homogenizing by heating and maintaining at temperature then cooling the ingot, d) hot rolling said ingot to its final thickness, e) solution heat treated then quenching the product rolled as such, f) stretching the product and g) carrying out an artificial aging of said product by heating and maintaining at temperature.
  • U.S. Pat. No. 5,431,876 discloses a ternary group of alloys of aluminum lithium and magnesium or copper, including at least one additive such as zirconium, chromium and/or manganese.
  • the alloy is prepared according to methods known to those skilled in the art comprising, by way of example, an extrusion, a solution heat treatment, a quenching, a stretching of the product from 2 to 7% then an artificial aging.
  • U.S. Pat. No. 6,551,424 describes a method for manufacturing rolled products made of aluminum-magnesium-lithium alloy having the composition (in % by weight) Mg: 3.0-6.0; Li: 0.4-3.0; Zn up to 2.0; Mn up to 1.0; Ag up to 0.5; Fe up to 0.3; Si up to 0.3; Cu up to 0.3; 0.02-0.5 of an element selected from the group comprising Sc, Hf, Ti, V, Nd, Zr, Cr, Y, Be, said method including a cold rolling lengthwise and widthwise.
  • U.S. Pat. No. 6,461,566 describes an alloy having the composition (in % by weight) Li: 1.5-1.9; Mg: 4.1-6.0; Zn 0.1-1.5; Zr 0.05-0.3; Mn 0.01-0.8; H 0.9 ⁇ 10 ⁇ 5 -4.5 ⁇ 10 ⁇ 5 and at least one element selected from the group of Be 0.001-0.2; Y 0.001-0.5 and Sc 0.01-0.3.
  • Patent application WO 2012/16072 describes a wrought product made of an aluminum alloy having the composition in % by weight, Mg: 4.0-5.0; Li: 1.0-1.6; Zr: 0.05-0.15; Ti: 0.01-0.15; Fe: 0.02-0.2; Si: 0.02-0.2; Mn: ⁇ 0.5; Cr ⁇ 0.5; Ag: ⁇ 0.5; Cu ⁇ 0.5; Zn ⁇ 0.5; Sc ⁇ 0.01; other elements ⁇ 0.05; the remainder is aluminum.
  • Said product is in particular obtained according to a method for manufacturing comprising in particular successively the casting of the alloy in unprocessed form, hot working optionally cold working of it, solution heat treatment then the quenching the wrought product, optionally the cold working of the solution heat treated and quenched product as such and finally the artificial aging of the wrought product at a temperature less than 150° C.
  • the temper obtained for rolled products is advantageously a T6 or T6X or T8 or T8X temper and for extruded products advantageously a T5 or T5X temper in the case of press quenching or a T6 or T6X or T8 or T8X temper.
  • the wrought products made of aluminum-magnesium-lithium alloy have a low density and are therefore particularly interesting in the extremely demanding field of aeronautics.
  • their performance has to be significantly improved in relation to that of existing products, in particular their performance in terms of a compromise between the static mechanical resistance properties (in particular tensile and compression yield strength, ultimate tensile strength) and damage tolerance properties (toughness, resistance to fatigue crack propagation), with these properties being mutually exclusive in general.
  • These alloys must also have sufficient corrosion resistance, in order to be formed according to the usual methods and have low residual stresses so as to be able to be machined without substantial distortion during said machining.
  • a first object of the invention is a method for manufacturing a wrought product wherein:
  • an unprocessed form of aluminum alloy is cast, which has the composition, in % by weight: Mg: 4.0-5.0; Li: 1.0-1.8; Zr: 0.05-0.15; Mn: ⁇ 0.6; Ag: ⁇ 0.5; Fe: ⁇ 0.1; Ti: ⁇ 0.15; Si: ⁇ 0.05; other elements ⁇ 0.05 each and ⁇ 0.15 in association; the remainder is aluminum;
  • said hot-worked product is solution heat treated at a temperature from 360° C. to 460° C., preferably from 380 to 420° C., for 15 minutes to 8 hours;
  • said hot-worked and quenched product is straightened or flattened
  • the hot-worked product artificially aged as such is cold worked in a controlled manner in order to obtain a permanent cold working set from 1 to 10%, preferably from 2 to 6%, most preferably from 3 to 5% and, most preferably from 4 to 5%.
  • the invention further has for objects, a wrought product able to be obtained according to the method of the invention as well as the use of said wrought product in order to carry out an aircraft structural element.
  • FIG. 1 Profile for circumferential frame of example 1
  • FIG. 2 Tensile yield strength, Rp0.2, according to the toughness, K Q * for a flat bar 10 mm thick (* all of the values of K Q are invalid due to the P max /P Q ⁇ 1.10 criterion of standard ASTM E399)
  • FIG. 3 Tensile yield strength, Rp0.2, according to the stress intensity factor corresponding to the maximum force, K max (evaluated according to standard ASTM E399) for a flat bar 10 mm thick
  • the expression 1.4 Cu means that the copper content expressed in % by weight is multiplied by 1.4.
  • the designation of the alloys is carried out 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 tempers are indicated in European standard EN 515.
  • the tensile static mechanical characteristics in other terms the ultimate tensile strength R m , the conventional tensile yield strength at 0.2% R p0.2 , and the elongation to fracture A %, are determined by a tensile test according to standard NF EN ISO 6892-1, the sampling and the direction of the test are defined by standard EN 485-1.
  • the toughness is determined by toughness test K1c according to standard ASTM E399.
  • a curve providing the effective stress intensity factor according to the effective crack growth is determined according to standard ASTM E399.
  • the results were also presented in K max (stress intensity factor corresponding to the maximum force P max ).
  • delamination also “crack delamination” and/or “crack divider” means a cracking in the planes orthogonal to the front of the main crack. The orientation of these plans corresponds to that of the seals of the non-recrystallized grains after deformation via working.
  • Low delamination is the sign of lesser fragility of the planes concerned and minimized the risks of a deviation of a crack towards the longitudinal direction during fatigue propagation or under monotonous stress.
  • structural element or “structural element” of a mechanical construction a mechanical part for which the static and/or dynamic mechanical properties are particularly substantial for the performance of the structure and for which a calculation structure is usually prescribed or carried out. This is typically elements of which the failure is able to jeopardize the safety of said construction, of its users or of other persons.
  • these structural elements include in particular the elements that comprise the fuselage (such as the fuselage skin, fuselage stringers, bulkheads, circumferential frames, wings (such as the upper or lower wing skin, stringers or stiffeners, ribs, spars, floor beams and seat tracks) and tail plane comprised in particular of horizontal or vertical stabilizers, as well as the doors.
  • the method for manufacturing products according to the invention comprises the successive steps of elaborating a liquid metal bath in such a way as to obtain an Al—Mg—Li alloy having a particular composition, the casting of said alloy in unprocessed form, optionally the homogenization of said unprocessed form cast as such, the hot working of said unprocessed form in order to obtain a hot-worked product, optionally the separate solution heat treatment of the product hot worked as such, the quenching of said hot-worked product, optionally the straightening/flattening of the worked and quenched product, the artificial aging of said worked and quenched product and the cold working in a controlled manner of the aged product in order to obtain a permanent cold working set from 1 to 10%, preferably from 2 to 6%, most preferably from 3 to 5% and most preferably from 4 to 5%.
  • the method for manufacturing therefore consists first of all in the casting of an unprocessed form of Al—Mg—Li alloy having the composition, in % by weight: Mg: 4.0-5.0; Li: 1.0-1.8; Zr: 0.05-0.15; Mn: ⁇ 0.6; Ag: ⁇ 0.5; Fe: ⁇ 0.1; Ti: ⁇ 0.15; Si: ⁇ 0.05; other elements ⁇ 0.05 each and ⁇ 0.15 in association; the remainder is aluminum.
  • a liquid metal bath is therefore carried out then cast in unprocessed form, typically a rolling ingot, an extrusion billet or a forging blank.
  • the Al—Mg—Li alloy has a Mn content, in % by weight, from 0.2 to 0.6%, preferably from 0.35 to 0.5%, more preferably from 0.35 to 0.45% and most preferably from 0.35 to 0.40%.
  • the products made of an alloy such as described hereinabove and having the advantageous Mn content have in particular improved static mechanical properties as well as a low propensity for delamination.
  • the unprocessed form made of aluminum alloy has a silver content less than or equal to 0.25% by weight, more preferably a silver content from 0.05% to 0.1% by weight. This element contributes in particular to the static mechanical properties.
  • the unprocessed form made of aluminum alloy has a total Ag and Cu content less than 0.15% by weight, preferably less than or equal to 0.12%. Controlling the maximum content in these two elements in association makes it possible in particular to improve the intergranular corrosion resistance of the wrought product.
  • the unprocessed form has a zinc content, in % by weight, less than 0.04%, preferably less than or equal to 0.03%.
  • a zinc content in % by weight, less than 0.04%, preferably less than or equal to 0.03%.
  • the unprocessed form made of aluminum alloy has an Fe content, in % by weight, less than 0.08%, preferably less than or equal to 0.07%, most preferably less than or equal to 0.06%.
  • Fe content in % by weight, less than 0.08%, preferably less than or equal to 0.07%, most preferably less than or equal to 0.06%.
  • the lithium content of the products according to the invention is between 1.0 and 1.8% by weight.
  • the unprocessed form made of aluminum alloy has a Li content, in % by weight, less than 1.6%, preferably less than or equal to 1.5%, most preferably less than or equal to 1.4%.
  • a minimum lithium content of 1.1% by weight and preferably from 1.2% by weight is advantageous.
  • the unprocessed form made of aluminum alloy has a Zr content, in % by weight, from 0.10 to 0.15%.
  • the inventors indeed observed that such a Zr content makes it possible to obtain an alloy that has a fiber structure favorable for improved static mechanical properties.
  • the unprocessed form made of aluminum alloy has a Mg content, in % by weight, from 4.5 to 4.9%. Excellent results were obtained for alloys according to this embodiment in particular regarding the static mechanical properties.
  • the Cr content of the products according to the invention is less than 0.05% by weight, preferably less than 0.01% by weight.
  • Such a limited Cr content in association with the other elements of the alloy according to the invention makes it possible in particular to limit the forming of primary phases during the casting.
  • the Ti content of the products according to the invention is less than 0.15% by weight, preferably between 0.01 and 0.05% by weight.
  • the Ti content is limited in the particular alloy of this invention in particular to prevent the forming of primary phases during the casting.
  • the products according to the invention have a maximum content of 10 ppm of Na, preferably from 8 ppm of Na, and/or a maximum content of ppm of Ca.
  • the unprocessed form made of aluminum alloy is substantially free of Sc, Be, Y, more preferably said unprocessed form comprises less than 0.01% by weight of these elements taken in combination.
  • the unprocessed form made of aluminum alloy has a composition, in % by weight:
  • Mg 4.0-5.0, preferably 4.5-4.9;
  • Li 1.1-1.6, preferably 1.2-1.5;
  • Zr 0.05-0.15, preferably 0.10-0.15;
  • Fe 0.02-0.1, preferably 0.02-0.06;
  • Mn ⁇ 0.6, preferably 0.2-0.6, most preferably 0.35-0.5;
  • Ag ⁇ 0.5; preferably ⁇ 0.25; most preferably ⁇ 0.1;
  • the method for manufacturing optionally comprises a step of homogenizing the unprocessed form in such a way as to reach a temperature between 450° C. and 550° C. and, preferably, between 480° C. and 520° C. for a period of time between 5 and 60 hours.
  • the homogenization treatment can be carried out in one or several steps. According to a preferred embodiment of the invention, the hot working is carried out directly following a simple heating without carrying out any homogenization.
  • the unprocessed form is then hot worked, typically by extrusion, rolling and/or forging, in order to obtain a worked product.
  • This hot working is carried out at an inlet temperature greater than 400° C. and, advantageously, from 420° C. to 450° C.
  • the hot working is a working via extrusion of the unprocessed form.
  • step of cold rolling which then constitutes a first optional step of cold working
  • intermediate thermal treatments typically carried out at a temperature between 300 and 420° C., before or during the cold rolling.
  • the hot-worked and optionally cold-worked, product is optionally subjected to a separate solution heat treatment at a temperature from 360° C. to 460° C., preferably from 380° C. to 420° C., for 15 minutes to 8 hours.
  • the hot-worked product and, optionally, solution heat treated is then quenched.
  • the quenching is carried out with water and/or with air. It is advantageous to carry out the quenching with air as the intergranular corrosion properties are improved.
  • the press quenching or quenching using the extrusion heat
  • this can also be a water press quenching.
  • the product is solution heat treated using the extrusion heat.
  • the hot-worked and quenched product can possibly be subjected to a step of straightening or flattening according to whether it is a profile or plate.
  • straightening/flattening means a step of cold working without permanent set or with permanent set less than 1%.
  • the hot-worked, quenched and, optionally straightened/flattened product then undergoes a step of artificial aging.
  • the artificial aging is carried out by heating, in one or several steps, at a temperature less than 150° C., preferably at a temperature from 70° C. to 140° C., for 5 to 100 hours.
  • the hot-worked product aged as such is cold worked in a controlled manner in order to obtain a permanent cold working set from 1 to 10%, preferably from 2 to 6%, most preferably from 3 to 5% and, most preferably from 4 to 5%.
  • the permanent cold working set is from 2 to 4%.
  • the cold working can in particular be carried out by stretching, compression and/or rolling. According to a preferred embodiment, the cold working is carried out by stretching.
  • the temper obtained for the wrought products corresponds in particular a T9 temper according to standard EN515.
  • the method for manufacturing a wrought product does not comprise any step of cold working inducing a permanent working set of at least 1% between the step of hot working or, if this step is present, of solution heat treatment and the step of artificial aging.
  • the combination of the chosen composition, in particular of the content in Mg, Li and Mn if the latter is present, and of the transformation parameters, in particular the order of the steps of the method of manufacturing, advantageously makes it possible to obtain wrought products having a compromise of improved properties that is entirely particular, in particular the compromise between the mechanical resistance and the damage tolerance, while still having a low density and a good corrosion performance.
  • the wrought products according to the invention are preferably extruded products such as profiles, rolled products such as plate or thick plate and/or forged products.
  • the invention also has for object wrought products able to be obtained according to the method described hereinabove, advantageously such cold-worked products with a permanent cold working set greater than 4%. Indeed, such products have entirely new and particular characteristics.
  • the wrought products able to be obtained by the method according to the invention advantageously said products with a permanent cold working set greater than 4%, have, in particular at mid-thickness, for a thickness between 0.5 and 15 mm, at least a static mechanical resistance property chosen from the properties (i) to (iii) and at least one damage tolerance property chosen from the properties (iv) to (v):
  • the wrought products able to be obtained by the method according to the invention have, for a thickness between 0.5 and 15 mm, at mid-thickness at least two static mechanical resistance properties chosen from the properties (i) to (iii) and at least one damage tolerance properties chosen from the properties (iv) to (v).
  • the extruded products according to the invention have particularly advantageous characteristics.
  • the extruded products preferably have a thickness between 0.5 mm and 15 mm, but products with a thickness greater than 15 mm, up to 50 mm or even 100 mm or more can also have advantageous properties.
  • the thickness of the extruded products is defined according to standard EN 2066: 2001: the transversal section is divided into elementary rectangles with dimensions A and B; with A always being the greatest dimension of the elementary rectangle and B able to be considered as the thickness of the elementary rectangle. The bottom is the elementary rectangle that has the greatest dimension A.
  • the wrought products according to the invention are advantageously used to carry out aircraft structural elements, in particular of planes.
  • Preferred aircraft structural elements are in particular a fuselage skin, a circumferential frame, a fuselage stiffener or stringer or a wing skin, a wing stiffener, a rib or a spar.
  • alloys A and B both have a composition suitable for the implementation of the method according to the invention.
  • the density of alloys A and B calculated in conformity with the procedure of The Aluminum Association described in pages 2-12 and 2-13 of “Aluminum Standards and Data”, is 2.55.
  • Billets 358 mm in diameter were carried out in the unprocessed forms. They were heated to 430-440° C. then hot worked by extrusion on a press in the form of a profile for circumferential frame such as shown in FIG. 1 . The products extruded as such were quenched with air (press quenching). They were then subjected to:
  • results obtained are given in tables 2 (direction L) and 3 (direction TL) hereinbelow. These results are the averages of 4 measurements taken on full thickness samples sampled on 4 positions on the circumferential frame (positions referenced as a, b, c and d in FIG. 1 ) for the direction L and of 2 measurements taken on full thickness samples sampled on 1 single position, referenced as c in FIG. 1 , for the direction TL.
  • the mechanical properties, in particular the maximum stress that can be withstood by the product or ultimate tensile strength, Rm, and the tensile yield strength Rp0.2 (strain value for a plastic deformation of 0.2%) of the products in T9 temper are globally significantly higher than those of the products in T8 or T6 tempers. Moreover, the mechanical properties, in particular Rp0.2, increase with the controlled stretching (T6 ⁇ T8-3% ⁇ T8-5% ⁇ T9-3% ⁇ T9-5%).
  • a Mn content of the Al—Mg—Li alloy of about 0.4% by weight makes it possible to significantly improve the mechanical resistance (Rp0.2 and Rm), in particular in the direction L, of the alloy in relation to that of an alloy having a Mn content of about 0.14% by weight (alloy A).
  • Billets 358 mm in diameter were carried out in the unprocessed forms. They were heated to 430-440° C. then hot worked by extrusion on a press in the form of a flat bar (100 mm ⁇ 10 mm). The products extruded as such were quenched with air (press quenching). They were then subjected to:
  • the tensile yield strength (strain value for a plastic deformation of 0.2%, Rp0.2) of the products in T9 temper is significantly higher than those of the products in T8 or T6 tempers. Moreover, Rp0.2 increases with the increase in the controlled stretching stress (T6 ⁇ T8-3% ⁇ T8-5% ⁇ T9-3% ⁇ T9-5%).
  • a Mn content of the Al—Mg—Li alloy of about 0.4% by weight makes it possible to significantly improve the mechanical resistance of the alloy (Rp0.2 and Rm) in relation to that of an alloy having a Mn content of about 0.14% by weight (alloy A).
  • the toughness of the products was characterized by the K1c test according to standard ASTM E399.
  • the values of K Q were still invalid according to standard ASTM E399, in particular in relation to criterion P max /P Q ⁇ 1.10.
  • the results are presented in K max (stress intensity factor corresponding to the maximum force P max ).
  • the results are reported in tables 6 and 7 and illustrated in FIGS. 2 and 3 (specimens L-T and T-L respectively). These results are the averages of at least two 2 values.
  • the products according to the invention have a satisfactory toughness regardless of the Mn content of the alloy.
  • FIG. 2 shows the tensile yield strength, Rp0.2, of the products of this example according to the toughness, K Q (all of the values of K Q are invalid due to the criterion P max /P Q ⁇ 1.10).
  • FIG. 3 shows the tensile yield strength, Rp0.2, of the products of this example according to the stress intensity factor corresponding to the maximum stress, Kmax.
  • the products in T9 have an excellent compromise between their static properties, in particular Rp0.2, and their toughness, K Q , or their stress intensity factor corresponding to the maximum force, Kmax.
  • Tables 8 and 9 summarize the scores assigned to the various specimens (specimens L-T and T-L respectively).
  • the products made of alloy B have a lower delamination than the products made of alloy A.

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US15/514,802 2014-09-29 2015-09-29 Method for manufacturing products made of magnesium-lithium-aluminum alloy Abandoned US20170218493A1 (en)

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FR14/02187 2014-09-29
FR14/02186 2014-09-29
FR1402187A FR3026410B1 (fr) 2014-09-29 2014-09-29 Produit corroye en alliage aluminium magnesium lithium
FR1402186A FR3026411B1 (fr) 2014-09-29 2014-09-29 Procede de fabrication de produits en alliage aluminium magnesium lithium
PCT/FR2015/052581 WO2016051061A1 (fr) 2014-09-29 2015-09-29 Procédé de fabrication de produits en alliage aluminium, magnésium, lithium

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CN112410691A (zh) * 2020-11-10 2021-02-26 中国航发北京航空材料研究院 一种铝锂合金材料退火工艺
WO2021126665A1 (en) * 2019-12-17 2021-06-24 Novelis Inc. Suppression of stress corrosion cracking in high magnesium alloys through the addition of calcium
US11072844B2 (en) 2016-10-24 2021-07-27 Shape Corp. Multi-stage aluminum alloy forming and thermal processing method for the production of vehicle components
CN114054531A (zh) * 2021-11-18 2022-02-18 西南铝业（集团）有限责任公司 一种高均匀性2196铝锂合金型材的挤压方法

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3057476B1 (fr) * 2016-10-17 2018-10-12 Constellium Issoire Toles minces en alliage aluminium-magnesium-scandium pour applications aerospatiales
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
WO2020206161A1 (en) * 2019-04-05 2020-10-08 Arconic Technologies Llc Methods of cold forming aluminum lithium alloys
CN112226656A (zh) * 2020-09-25 2021-01-15 西南铝业（集团）有限责任公司 一种Al-Mg-Mn-Er系铝合金挤压制品的生产工艺

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4790884A (en) * 1987-03-02 1988-12-13 Aluminum Company Of America Aluminum-lithium flat rolled product and method of making
US6551424B1 (en) * 1998-12-18 2003-04-22 Corus Aluminium Walzprodukte Gmbh Method for the manufacturing of an aluminium-magnesium-lithium alloy product
US20120291925A1 (en) * 2011-05-20 2012-11-22 Constellium France Aluminum magnesium lithium alloy with improved fracture toughness

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1519021A (fr) * 1967-03-07 1968-03-29 Iosif Naumovich Fridlyander Ni Alliage à base d'aluminium
SU1367517A1 (ru) * 1986-01-16 1995-07-25 И.Н. Фридляндер Сплав на основе алюминия
CA1337747C (en) * 1986-12-01 1995-12-19 K. Sharvan Kumar Ternary aluminium-lithium alloys
BR8807653A (pt) * 1987-08-10 1990-06-12 Martin Marietta Corp Ligas de aluminio-litio soldaveis de resistencia ultra elevada
CA1338007C (en) * 1988-01-28 1996-01-30 Roberto J. Rioja Aluminum-lithium alloys
RU2256720C1 (ru) * 2004-04-02 2005-07-20 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") Способ термомеханической обработки полуфабрикатов из алюминиевых сплавов
ES2373054T5 (es) * 2005-08-16 2018-12-05 Aleris Aluminum Koblenz Gmbh Aleación de Al-Mg soldable de alta resistencia
FR2894985B1 (fr) * 2005-12-20 2008-01-18 Alcan Rhenalu Sa Tole en aluminium-cuivre-lithium a haute tenacite pour fuselage d'avion
CN101896631B (zh) * 2007-11-15 2015-11-25 阿勒里斯铝业科布伦茨有限公司 Al-Mg-Zn锻造合金产品及其制造方法
CN103045975A (zh) * 2012-12-29 2013-04-17 湖南工程学院 一种改善Al-Mg-Li系合金易轧制开裂的方法

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4790884A (en) * 1987-03-02 1988-12-13 Aluminum Company Of America Aluminum-lithium flat rolled product and method of making
US6551424B1 (en) * 1998-12-18 2003-04-22 Corus Aluminium Walzprodukte Gmbh Method for the manufacturing of an aluminium-magnesium-lithium alloy product
US20120291925A1 (en) * 2011-05-20 2012-11-22 Constellium France Aluminum magnesium lithium alloy with improved fracture toughness

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10835942B2 (en) 2016-08-26 2020-11-17 Shape Corp. Warm forming process and apparatus for transverse bending of an extruded aluminum beam to warm form a vehicle structural component
US11072844B2 (en) 2016-10-24 2021-07-27 Shape Corp. Multi-stage aluminum alloy forming and thermal processing method for the production of vehicle components
WO2021126665A1 (en) * 2019-12-17 2021-06-24 Novelis Inc. Suppression of stress corrosion cracking in high magnesium alloys through the addition of calcium
CN112410691A (zh) * 2020-11-10 2021-02-26 中国航发北京航空材料研究院 一种铝锂合金材料退火工艺
CN114054531A (zh) * 2021-11-18 2022-02-18 西南铝业（集团）有限责任公司 一种高均匀性2196铝锂合金型材的挤压方法

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CN107075623A (zh) 2017-08-18
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BR112017006273B1 (pt) 2021-06-08
WO2016051060A1 (fr) 2016-04-07
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CA2960942A1 (fr) 2016-04-07
CA2960947A1 (fr) 2016-04-07
BR112017006131A2 (pt) 2017-12-19
US20170292180A1 (en) 2017-10-12
EP3201371A1 (fr) 2017-08-09
WO2016051061A1 (fr) 2016-04-07

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