US20170292180A1 - Wrought product made of a magnesium-lithium-aluminum alloy - Google Patents

Wrought product made of a magnesium-lithium-aluminum alloy Download PDF

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US20170292180A1
US20170292180A1 US15/514,398 US201515514398A US2017292180A1 US 20170292180 A1 US20170292180 A1 US 20170292180A1 US 201515514398 A US201515514398 A US 201515514398A US 2017292180 A1 US2017292180 A1 US 2017292180A1
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product
weight
worked
wrought
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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
Priority claimed from FR1402187A external-priority patent/FR3026410B1/fr
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Assigned to CONSTELLIUM ISSOIRE reassignment CONSTELLIUM ISSOIRE ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: POUGET, Gaëlle, BES, BERNARD
Publication of US20170292180A1 publication Critical patent/US20170292180A1/en
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    • 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
    • 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 wrought products made of aluminum-magnesium-lithium alloy, more particularly such products having an improved balance of properties, in particular an improved balance between the tensile yield strength and the toughness of said products.
  • the invention further relates to a method for manufacturing as well as the use of these products 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.
  • 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 casting the alloy in unprocessed form, hot working optionally cold working of it, solution heat treating then quenching the wrought product, optionally cold working the solution heat treated and quenched product, and finally artificially aging 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 balance 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 relates to a wrought product made of an aluminum alloy having the composition in % by weight, Mg: 4.0-5.0; Li: 1.0-1.8; Mn: 0.3-0.5; Zr: 0.05-0.15; Ag: ⁇ 0.5; Fe: ⁇ 0.1; Ti: ⁇ 0.15; Si: ⁇ 0.05; other elements ⁇ 0.05 each and ⁇ 0.15 in combination; the remainder is aluminum.
  • Another object of the invention is a method for manufacturing said 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; Mn: 0.3-0.5; Zr: 0.05-0.15; 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° C. to 420° C., for 15 minutes to 8 hours;
  • the worked and quenched product 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%;
  • Yet another object of the invention is the use of said wrought product to produce aircraft structural elements.
  • 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.
  • values of K Q are invalid according to standard ASTM E399, in particular in relation to criterion P max /P Q ⁇ 1.10, 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 planes 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 minimizes the risks of a deviation of a crack towards the longitudinal direction during fatigue propagation or under monotonous stress.
  • structure element or “structural element” of a mechanical construction means 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.
  • 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 wrought product made of an aluminum alloy according to the invention has the following particular composition, in % by weight: Mg: 4.0-5.0; Li: 1.0-1.8; Mn: 0.3-0.5; Zr: 0.05-0.15; Ag: ⁇ 0.5; Fe: ⁇ 0.1; Ti: ⁇ 0.15; Si: ⁇ 0.05; other elements ⁇ 0.05 each and ⁇ 0.15 in combination; the remainder is aluminum.
  • the products made of an aluminum alloy having such a composition associated in particular with the particular Mn content selected have improved static mechanical properties as well as a low propensity for delamination.
  • the Mn content, in % by weight is from 0.35 to 0.45, preferably from 0.35 to 0.40.
  • 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 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 casting.
  • it can be advantageous to control the Ti content in order to control the granular structure and in particular the grain size during casting of the alloy.
  • the products according to the invention have a maximum content of 10 ppm of Na, preferably 8 ppm of Na, and/or a maximum content of 20 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 0.3-0.5; preferably from 0.35 to 0.45, preferably from 0.35 to 0.40;
  • Ag ⁇ 0.5; preferably ⁇ 0.25; most preferably ⁇ 0.1;
  • the method for manufacturing products according to the invention comprises the successive steps of preparing a liquid metal bath in such a way as to obtain an Al—Mg—Li alloy having a particular composition, casting said alloy in unprocessed form, optionally homogenizing said unprocessed form as such, hot working said unprocessed form in order to obtain a hot-worked product, optionally separately solution heat treating the hot-worked product, quenching said hot-worked product, optionally straightening/flattening the worked and quenched product, optionally cold working in a controlled manner the worked and quenched 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%, artificially aging said worked and quenched product.
  • the step of artificial aging is carried out before the step of cold working in a controlled manner.
  • the method for manufacturing therefore consists first of all in casting an unprocessed form of Al—Mg—Li alloy having the composition, in % by weight: Mg: 4.0-5.0; Li: 1.0-1.8; Mn: 0.3-0.5; Zr: 0.05-0.15; Ag: ⁇ 0.5; Fe: ⁇ 0.1; Ti: ⁇ 0.15; Si: ⁇ 0.05; other elements ⁇ 0.05 each and ⁇ 0.15 in combination; the remainder is aluminum.
  • a liquid metal bath is therefore prepared and then cast in unprocessed form, typically a rolling ingot, an extrusion billet or a forging blank.
  • 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 starting 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 worked and, optionally, solution heat treated product 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.
  • a 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 is also 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 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 worked, quenched and, optionally straightened/flattened product undergoes a step of artificial aging.
  • the 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 step of artificial aging is carried out after the step of cold working in a controlled manner.
  • the temper obtained for the wrought products correspond in particular to a T8 temper according to standard EN515.
  • the step of artificial aging is carried out before the step of cold working in a controlled manner.
  • the hot-worked and aged product is then 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 method for manufacturing a wrought product does not comprise any step of cold working inducing a permanent 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 aging.
  • the combination of the chosen composition, in particular of the content in Mg, Li and Mn 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 balance of improved properties that is particularly special, in particular the balance 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 plates or thick plates and/or forged products.
  • the wrought products according to the invention have particularly advantageous characteristics in comparison with identical wrought products but having for sole difference their Mn content, in particular a Mn content, in % by weight, less than 0.3% or greater than 0.5%.
  • identical wrought products means products made of an aluminum alloy of the same composition, in % by weight, except for Mn, and obtained according to the same method of manufacturing, in particular wrought products in the same temper according to standard EN515 and having the same percent working in permanent set obtained by stretching in a controlled manner.
  • the wrought products according to the invention have less delamination on the rupture surfaces of the K1c specimens obtained according to standard ASTM E399 than identical wrought products but having for sole difference their Mn content, in particular an Mn content, in % by weight, less than 0.3% or greater than 0.5%.
  • the wrought products according to the invention have at mid-thickness, for a thickness between 0.5 and 15 mm, an ultimate tensile strength Rm (L) greater than that of identical wrought products, having for a difference in their Mn content, in particular a Mn content, in % by weight, less than 0.3% or greater than 0.5%.
  • the wrought products according to the invention have, at mid-thickness, for a thickness between 0.5 and 15 mm, a tensile yield strength Rp0.2 (L) greater than that of identical wrought products but having for difference their Mn content, in particular an Mn content, in % by weight, less than 0.3% or greater than 0.5%.
  • the wrought products in T8 temper advantageously in T8 temper with a permanent cold working set greater than 4%, according to the invention have, at mid-thickness, for a thickness between 0.5 and 15 mm, at least one 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 in T9 temper advantageously in T9 temper with a permanent cold working set greater than 4%, according to the invention have, at mid-thickness, for a thickness between 0.5 and 15 mm, at least one 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):
  • a tensile yield strength Rp0.2 (TL) ⁇ 320 MPa preferably Rp0.2 (TL) ⁇ 335 MPa, more preferably Rp0.2 (TL) ⁇ 340 MPa and, most preferably, Rp0.2 (TL) ⁇ 350 MPa;
  • the wrought products in T8 or T9 temper mentioned hereinabove 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.
  • alloy B has a composition 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 press extrusion 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.
  • 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 particular the mechanical resistance in the direction L, in relation to that of an alloy having a Mn content of about 0.14% by weight (alloy A).
  • the alloy B has a composition according to the invention.
  • 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:
  • 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 particular the mechanical resistance in the direction L, in relation to that of an alloy having a Mn content of about 0.14% by weight (alloy A).
  • T8 ⁇ T9 the best results are generally obtained when the controlled stretching is carried out after the aging
  • 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, K max .
  • the products in T9 have an excellent balance between their static properties, in particular Rp0.2, and their toughness, K Q , or their stress intensity factor corresponding to the maximum force, K max .
  • the products made of alloy B have a lower delamination than the products made of alloy A.

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US15/514,398 2014-09-29 2015-09-29 Wrought product made of a magnesium-lithium-aluminum alloy Abandoned US20170292180A1 (en)

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
FR14/02187 2014-09-29
FR1402186A FR3026411B1 (fr) 2014-09-29 2014-09-29 Procede de fabrication de produits en alliage aluminium magnesium lithium
FR1402187A FR3026410B1 (fr) 2014-09-29 2014-09-29 Produit corroye en alliage aluminium magnesium lithium
FR14/02186 2014-09-29
PCT/FR2015/052580 WO2016051060A1 (fr) 2014-09-29 2015-09-29 Produit corroye en alliage aluminium magnesium lithium

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CN (2) CN107075623A (ko)
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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

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FR3057476B1 (fr) * 2016-10-17 2018-10-12 Constellium Issoire Toles minces en alliage aluminium-magnesium-scandium pour applications aerospatiales
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BR112017006273A2 (pt) 2017-12-12
EP3201371A1 (fr) 2017-08-09
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CN107075623A (zh) 2017-08-18
EP3201370A1 (fr) 2017-08-09
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