EP1727921B1 - Element de structure pour construction aeronautique presentant une variation des proprietes d"emploi - Google Patents

Element de structure pour construction aeronautique presentant une variation des proprietes d"emploi Download PDF

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Publication number
EP1727921B1
EP1727921B1 EP05743083A EP05743083A EP1727921B1 EP 1727921 B1 EP1727921 B1 EP 1727921B1 EP 05743083 A EP05743083 A EP 05743083A EP 05743083 A EP05743083 A EP 05743083A EP 1727921 B1 EP1727921 B1 EP 1727921B1
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EP
European Patent Office
Prior art keywords
mpa
structural member
zones
sub
length
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EP05743083A
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German (de)
English (en)
French (fr)
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EP1727921A2 (fr
Inventor
Philippe Lequeu
David Dumont
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Constellium Issoire SAS
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Alcan Rhenalu SAS
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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
    • C22F1/053—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with zinc as the next major constituent
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F27—FURNACES; KILNS; OVENS; RETORTS
    • F27B—FURNACES, KILNS, OVENS, OR RETORTS IN GENERAL; OPEN SINTERING OR LIKE APPARATUS
    • F27B9/00—Furnaces through which the charge is moved mechanically, e.g. of tunnel type; Similar furnaces in which the charge moves by gravity
    • F27B9/30—Details, accessories, or equipment peculiar to furnaces of these types
    • F27B9/40—Arrangements of controlling or monitoring devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F27—FURNACES; KILNS; OVENS; RETORTS
    • F27D—DETAILS OR ACCESSORIES OF FURNACES, KILNS, OVENS, OR RETORTS, IN SO FAR AS THEY ARE OF KINDS OCCURRING IN MORE THAN ONE KIND OF FURNACE
    • F27D19/00—Arrangements of controlling devices

Definitions

  • the present invention relates to wrought products and structural elements, especially for aircraft construction, heat-treated aluminum alloy. It relates in particular to so-called long products, ie products having a length significantly greater than the other dimensions, typically at least twice as long as they are wide, and of a length typically of at least 5 meters. . These products can be rolled products (such as thin sheets, medium sheets, thick sheets), spun products (such as bars, profiles, tubes or wires), and forged products.
  • Very large aircraft have unique construction problems.
  • the assembly of structural elements becomes increasingly critical, firstly as a cost factor (riveting is a very expensive process), secondly as a generator of discontinuities in the properties of assembled parts.
  • structural elements can be prepared by integral machining in thick plates; these structural elements can then integrate into a single piece (called monolithic) different functions such as the wing skin function and the stiffener function. It is also possible, and at the same time, to enlarge the dimension of the monolithic structural elements. This poses new manufacturing problems of these parts by rolling, spinning, forging or molding, because it is more difficult to ensure homogeneous properties in very large parts.
  • the patent EP 0 630 986 discloses a method of manufacturing structurally hardened aluminum alloy sheets having a continuous variation of the use properties, wherein the final income is made in a specific structure furnace comprising a hot chamber and a cold room, connected by a heat pump. This process made it possible to obtain small pieces with a length of about one meter in alloy 7010, one end of which is in the T651 state and the other in the T7451 state, by an isochronous tempering treatment.
  • the problem addressed by the present invention is to develop a method for the manufacture of structural elements, in particular for aircraft construction, having a variation of the use properties, which allows the production of very long parts, and which is sufficiently controllable, stable and reproducible under the stringent quality assurance and process control conditions that are commonly required by the aviation industry.
  • Yet another object of the present invention is an aircraft comprising at least one wing which integrates at least one structural element according to the present invention, characterized in that the segment P 1 is located close to the fuselage, and the segment P 2 close to the geometric end of the wing, opposite the fuselage.
  • the figure 1 schematically shows the evolution of the static mechanical properties (curve 1), for example the tensile or compressive strength, and dynamic (curve 2), for example the damage tolerance, in the length of a panel of wing according to the invention.
  • curve 2 shows the mechanical strength in a structural element with a length of 34 meters according to the invention.
  • the static mechanical characteristics ie the breaking strength R m , the yield stress R p0,2, and the elongation at break A, are determined by a tensile test according to EN 10002-1 standard, the location and direction of specimen collection being defined in EN 485-1.
  • the tenacity K IC was measured according to the ASTM E 399 standard.
  • the curve R is determined according to ASTM standard 561. From the curve R, the critical stress intensity factor K C is calculated, that is to say the intensity factor that causes the instability of the crack.
  • the stress intensity factor K CO is also calculated by assigning to the critical load the initial length of the crack at the beginning of the monotonic loading.
  • K app denotes the K CO corresponding to the test piece used to perform the R curve test.
  • the resistance to exfoliating corrosion was determined according to the EXCO test described in the ASTM G34 standard. Unless otherwise specified, the definitions of the standard European EN 12258-1 apply.
  • sheet metal is used here for rolled products of any thickness.
  • machining includes any material removal process such as turning, milling, drilling, reaming, tapping, EDM, grinding, polishing, chemical machining.
  • spun product also includes products that have been drawn after spinning, for example by cold drawing through a die. It also includes drawn products.
  • structural element refers to an element used in mechanical engineering for which the static and / or dynamic mechanical characteristics are of particular importance for the performance and integrity of the structure, and for which a calculation of the structure is usually prescribed or performed. It is typically a mechanical part whose failure is likely to endanger the safety of said construction, its users, its users or others.
  • these structural elements include the elements that make up the fuselage (such as fuselage skin (fuselage skin in English), stiffeners or stringers, bulkheads, fuselage (circumferential frames), wings (such as wing skin), stiffeners (stiffeners), ribs (ribs) and spars) and empennage including horizontal stabilizers and vertical stabilizers horizontal or vertical stabilizers, as well as floor beams, seat tracks and doors.
  • fuselage such as fuselage skin (fuselage skin in English
  • stiffeners or stringers such as fuselage skin
  • bulkheads fuselage (circumferential frames)
  • wings such as wing skin
  • stiffeners stiffeners (stiffeners), ribs (ribs) and spars
  • empennage including horizontal stabilizers and vertical stabilizers horizontal or vertical stabilizers, as well as floor beams, seat tracks and doors.
  • monolithic structural element refers to a structural element which has been obtained from a single piece of semi-finished product, rolled, forged or molded, without assembly, such as riveting, welding, gluing, with another room.
  • the problem is solved by a method in which in an oven which preferably has an internal length greater than the length of the workpiece, the temperature is kept substantially constant over at least two furnace zones of a furnace. length of at least one meter.
  • a temperature profile can be obtained by subdividing the oven along its length into several thermal zones.
  • the invention is applicable to all long metal products, that is to say having a dimension (called length) significantly larger than the other two (width, thickness).
  • the length is the largest dimension of the product. Typically, in the context of the present invention, the length is at least twice as large as the other two dimensions. In particularly advantageous embodiments, it is five or even ten times larger than the other two dimensions. It usually coincides with the long direction of manufacture (rolling or spinning direction); in some cases, it may be different.
  • the products according to the invention may be rolled products (such as sheets or plates), spun products (such as bars, tubes or profiles), forged products; these products can be raw or machined.
  • extreme property segments of a product is understood to mean the two segments showing the greatest difference in properties. Depending on the embodiments chosen, these segments may be close to the two “geometric ends” (or “geometrical ends") of the product, or elsewhere: the present invention also makes it possible to manufacture parts in which at least one of the two segments showing the greatest difference in properties are closer to the geometric medium than to the geometrical end of the part.
  • zone of an oven means the smallest thermal unit over the length of the oven characterized by a substantially constant temperature, that is to say by a temperature variation parallel to the axis of the oven which is low. compared to the temperature difference that characterizes the temperature profile of the oven over its entire length.
  • Such an oven zone is characterized by heating and control means which make it possible to maintain the temperature at a substantially constant value within said zone.
  • the variation of the temperature around the set temperature must not exceed ⁇ 5 ° C, and preferably does not exceed. ⁇ 4 ° C. In a preferred embodiment, this difference does not exceed ⁇ 3 ° C.
  • the difference should not exceed ⁇ 2 ° C.
  • the temperature should be as constant as possible. In any case, the variation of the temperature around the set temperature inside a zone must be lower than the temperature difference between the hottest oven zone and the coldest oven zone. .
  • zones can form a "zone group", that is, a thermal unit within which the temperature is substantially constant, or follows a controlled thermal profile.
  • a zone group that is, a thermal unit within which the temperature is substantially constant, or follows a controlled thermal profile.
  • two groups of thermal zones can be formed, each comprising three furnace zones (having the successive numbers 1, 2, 3, 7, 8 and 9), separated by a central zone group comprising a controlled thermal profile and obtained via three oven zones (bearing the successive numbers 4, 5 and 6).
  • a group of zones may have only one oven zone.
  • the minimum temperature difference that leads to differences in industrially exploitable properties between two segments with extreme properties of the product according to the invention is five degrees.
  • a difference of at least ten degrees is preferred.
  • the difference in temperature can be much greater, up to 80 ° C, or even up to 100 ° C, or even more, but this can cause problems of temperature control and its profile parallel to the axis of the oven, and this especially in the case of relatively small parts. If one wants to obtain returned states, the difference in temperature will not exceed typically fifty degrees.
  • a temperature difference greater than fifty degrees can advantageously be used to manufacture a part of which one of the segments with extreme properties is in a state close to a state T3 or T4.
  • an oven having a plurality of contiguous furnace zones is used in the present invention.
  • plurality is meant at least two, and preferably at least three furnace zones.
  • a partition between two contiguous zones, as proposed in the patent EP 0 630 986 is neither necessary nor useful. It does not allow to exercise sufficient control over the temperature between two zones.
  • the use of a heat pump that connects the cold room to the hot room, as proposed in EP 0 630 986 makes the thermal profile inside the oven too unstable.
  • a good control of the thermal profile inside the furnace is essential to be able to manufacture structural elements in a manner compatible with the requirements of quality assurance of aeronautical products.
  • the furnace comprises at least three furnace zones with a unit length of at least one meter.
  • the inventors use a furnace with a total length of thirty-six meters with thirty oven zones of substantially identical length, adjustable independently of each other.
  • these thirty furnace zones are grouped so as to form a reduced number of groups of thermal zones, for example three to five.
  • the method according to the invention comprises the preparation of a corrected piece of aluminum alloy with a hardening, a dissolution, quenching, possibly traction with a permanent elongation of at least 0.5%, a treatment of income in a controlled thermal profile oven.
  • Said tempering treatment in a thermal profile furnace may comprise, for at least one of the groups of thermal zones that make up the controlled thermal profile, one or more, typically two or three, temperature stages, or a more or less continuous ramp of no net temperature.
  • the tempering treatment in the controlled thermal profile oven is preceded or followed by another step of treatment of income in a homogeneous oven (which can be the same oven, adjusted so as to obtain a uniform temperature in all its zones , or another oven).
  • Such a final homogenous furnace income is particularly useful when aiming to obtain a state suitable for an income shaping operation; in this case, the homogeneous final income allows the formation of income.
  • a room may incur an income in the controlled thermal gradient oven, then at least one shaping or machining operation, and then a treatment step in a homogeneous oven.
  • the process according to the invention can be used to form semi-finished products of any structurally hardened alloy, such as 2xxx, 4xxx, 6xxx and 7xxx series aluminum alloys, as well as 8xxx series hardening alloys. containing lithium.
  • the method according to the invention can, in the case of Al-Zn-Cu-Mg alloys (series 7xxx), be used to have one of the segments with extreme properties in a state close to T6, and another segment with properties extremes close to T74 or T73.
  • the method according to the invention can be used to obtain on one of the segments with extreme properties a state close to T3 or T4, and on the other segment with extreme properties a state close to T6 or T8.
  • the alloy comprises between 6 and 15% of zinc, between 1 and 3% of copper and between 1.5 and 3.5% of magnesium.
  • the zinc content is at least 7%, and is preferably between 8 and 13%, and even more preferably between 8.5 and 11%.
  • the copper content is advantageously between 1.3 and 2.1%, and the magnesium content between 1.8 and 2.7%.
  • alloys including 7449, 7349 and 7056, make it possible to obtain both a very high mechanical strength (for example in the T651 or T7951 state) and a very high toughness (for example in the T76 state, T7651 or T74, or in the T7451, T73 or T7351 state), while maintaining in the two states corresponding to the two extreme property segments of the product, as well as in the intermediate zones, a compromise between acceptable strength and toughness and resistance to exfoliating corrosion (EXCO test) maintained at a good level (EA).
  • EXCO test acceptable strength and toughness and resistance to exfoliating corrosion
  • a product made of 2xxx alloy (such as 2024 or 2023) on one segment or a geometrical end (P 1 ) is tempered at about 120 ° C, and on another segment or the other geometric end (P 2 ) a peak income of mechanical strength (T851 state) at about 190 ° C.
  • the segment or geometric end that is not worn at the peak of mechanical strength (ie P 1 ) is tempered at about 100 ° C (or 80 ° C); it is an under-income state.
  • an income at peak strength (state T651) at about 120 ° C. is carried out. and on another segment or the other geometric end an overflow (state T7651, T7451 or T7351) in two stages at 120 ° C and 150 ° C - 165 ° C.
  • a 6xxx alloy product (such as 6056 or 6156) is made on a segment or a geometrical end. returned to the peak of mechanical strength (T651 state) at about 190 ° C, and on another segment or the other end geometric over-income (T7851 state) in two stages.
  • the metal parts obtained by the process according to the invention can be used as a structural element in the aeronautical construction.
  • These structural elements can be bi-functional or multi-functional, that is to say, bring together in a single piece of monolithic different functionalities that the methods according to the prior art could only bring together the assembly of different parts.
  • These structural elements may also allow a simpler and lighter construction and manufacture of aircraft, particularly aircraft of very large cargo or passenger capacity.
  • a specific advantage of the process according to the invention is that in each segment with extreme properties, the optimal properties targeted in a well-controlled length of the product are obtained.
  • the designer of the aircraft knows exactly how long the product will have the optimal properties recommended and guaranteed.
  • the method according to the invention is used to manufacture structural elements which do not have a continuous variation of properties over their entire length, but which have at least two zones in which the mechanical properties ( or some of them) are constant over a certain length of the product.
  • this zone has a length of at least one meter, and preferably at least two meters.
  • Another specific advantage of the method according to the invention is the precise control of the properties in the transition segment P 1,2 between two groups of segments P 1 and P 2 (there may be two or more, depending on the number of groups of thermal zones), P 1 and P 2 being segments with extreme properties.
  • the designer of the aircraft does not need, in the transition segment, maximum properties for one or other of the properties (or groups of properties) to be optimized, for example the breaking strength. in the long direction R m (L) and the toughness K IC (LT) . But it does require a certain compromise between these properties or groups of properties, because in this transition segment, the structural element plays a structural role and must meet precise specifications.
  • the method according to the invention makes it possible to heat-treat long structural parts or elements. Most often, their section perpendicular to the length is substantially constant along their length, but it may be otherwise. Similarly, the parts can be straight or not; for example, slightly curved forged structural elements can be processed. The method could be used also for processing molded parts, but long molded parts are very rare and difficult to manufacture.
  • the length of the piece is at least 5 meters or better still at least 7 meters, but a length of at least 15 meters or even at least 25 meters is preferred to take full advantage of possibilities to create several functionalized segments distributed over the length of the room.
  • Structural elements with at least two segments P 1 and P 2 have thus been produced in which the length F P1 and F P2 (expressed as a percentage of the total length of the workpiece L) of the at least two segments P 1 and P 2 is such that F P1 > 25% and F P2 > 25% and preferably F P1 > 30% and F P2 > 30%. In other embodiments, F P1 > 35% and F P2 > 30%, or F P1 > 40% and F P2 > 30%.
  • Structural elements according to the invention can be advantageously used in aeronautical construction.
  • a large-capacity airplane comprising at least one wing comprising at least one structural element according to the invention, characterized in that the segment P 1 is located close to the fuselage, and the segment P 2 close to the geometrical end of the wing (see figure 1 ).
  • said wing panels have a length of at least 15 meters, and preferably at least 25 meters. As described in the example below, the inventors made wing panels more than 30 meters long.
  • Said parts and structural elements may be monolithic.
  • the method according to the invention also makes it possible to heat-treat parts or structural elements that are not monolithic but assembled from at least two rolled or forged pieces or semi-finished products (preferably in hardening aluminum alloys). structural), for example by welding, riveting or gluing. It is also conceivable that in such an assembly, one or more of the parts are made from a base material that is not an aluminum alloy.
  • the sheets and profiles are in the T351 state, and the assembly is performed by laser welding (Laser Beam Welding, LBW), friction welding (Friction Stir Welding, FSW) or Electron Beam Welding (EBW).
  • the Applicant has found that it may be preferable to treat such a welded assembly after welding by the method according to the invention, instead of treating the semi-finished products (sheets and profiles) intended to constitute said assembly before welding, because an improvement in the mechanical strength and the corrosion resistance of the welded joint is obtained.
  • This effect is significant when the welded joint is spread over a large length of the structural element (for example substantially parallel to the long direction of the product).
  • a sheet 36 meters long, 2.5 meters wide and 30 mm thick was manufactured by hot rolling a rolling plate.
  • the composition of the alloy was: Zn 9.1%, Mg 1.89%, Cu 1.57%, Fe 0.06%, Si 0.03%, Ti 0.03%, Zr 0.11%, other items ⁇ 0.01 each.
  • the rolling plate was homogenized for 14 hours at 475 ° C.
  • the inlet temperature to the hot mill was 428 ° C
  • the outlet temperature of the hot rolled sheet was 401 ° C.
  • the sheet was put into solution, quenched and quenched under the following conditions: hold for 6 hours at 471 ° C, quench in water at a temperature between about 15 and 16 ° C, then controlled pull with permanent elongation about 2.5%
  • the sheet was trimmed to give a sheet of 34 meters long. It was positioned in length in an oven consisting of 30 zones with a unit length of 1200 mm. For all tempering temperatures, the variation around the setpoint did not exceed ⁇ 3 ° C.
  • the treatment of income consisted of a first step of homogeneous treatment at 120 ° C for 6 hours ("first step"), immediately followed by a second step during which a geometric end of 18 meters (called Z 1 , corresponding to 15 furnace zones) was treated for 15 hours at 155 ° C ("second stage", preceded by an adjustment period of about 1 hour), while the other geometric end of 10.8 meters (called Z 2 , corresponding to 9 furnace zones) was maintained for 16 hours at 120 ° C.
  • the transition zone between these two ends corresponded to 7.2 meters (called Z 1.2 , corresponding to 6 furnace zones).
  • the sheet was subjected to a third step of income, namely a homogeneous income consisting of a rise in temperature at 148 ° C for 1:30, followed by maintenance at 150 ° C for 15h hours.
  • This third step was intended to simulate an income shaping operation or income after shaping the structural element.
  • Table 1 summarizes the static mechanical characteristics obtained by a tensile test. These are averages obtained from measurements made at mid-thickness and at different locations spread across the width of the sheet. There was no significant variation in properties in the width of the sheet. It should be noted that for R p0.2 in the L and TL directions, the values were also measured by a compression test; they are shown in Table 1 in parentheses.
  • K IC and K app toughness results are shown in Table 2.
  • Such a sheet of 34 meters length can be used as a wing panel for cargo or passenger planes of very large capacity.
  • the geometric end X of the sheet (corresponds to high K IC toughness, the static mechanical resistance being lower) is positioned on the fuselage side, and the geometric end Z of the sheet (corresponds to a high static mechanical resistance , toughness K IC being lower) corresponds to the geometrical end of the wing.
  • the set-point, sheet and air temperatures in the furnace zones for the second tempering stage are shown in Table 3.
  • the temperature profile is shown during the tempering step at 120 ° C. and 155 ° C. ° C in the stationary thermal state.
  • the temperature of the sheet was measured using forty thermocouples; the values given in Table 3 were measured at mid-width.
  • Table 3 Oven area Set temperature [° C] Sheet temperature [° C] Air temperature [° C] 1 120 3 120 120.5 6 120 120.8 120.8 9 120 124.4 124.3 10 123 125.9 126.7 11 129 129.9 129.7 14 147 147.7 148.3 16 155 157.2 156.6 17 155 156.8 156.6 18 155 155.3 154.9 22 155 155.1 154.8 30 155

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Organic Chemistry (AREA)
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  • Metal Rolling (AREA)
EP05743083A 2004-03-23 2005-03-21 Element de structure pour construction aeronautique presentant une variation des proprietes d"emploi Not-in-force EP1727921B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0402971A FR2868084B1 (fr) 2004-03-23 2004-03-23 Element de structure pour construction aeronautique presentant une variation des proprietes d'emploi
PCT/FR2005/000681 WO2005098072A2 (fr) 2004-03-23 2005-03-21 Element de structure pour construction aeronautique presentant une variation des proprietes d’emploi

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EP1727921A2 EP1727921A2 (fr) 2006-12-06
EP1727921B1 true EP1727921B1 (fr) 2008-05-14

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EP (1) EP1727921B1 (pt)
CN (1) CN100507066C (pt)
AT (1) ATE395444T1 (pt)
BR (1) BRPI0507940B1 (pt)
CA (1) CA2560672C (pt)
DE (1) DE602005006764D1 (pt)
ES (1) ES2307180T3 (pt)
FR (1) FR2868084B1 (pt)
WO (1) WO2005098072A2 (pt)

Cited By (3)

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Publication number Priority date Publication date Assignee Title
US11180839B2 (en) 2017-10-26 2021-11-23 Ut-Battelle, Llc Heat treatments for high temperature cast aluminum alloys
US11220729B2 (en) 2016-05-20 2022-01-11 Ut-Battelle, Llc Aluminum alloy compositions and methods of making and using the same
US11242587B2 (en) 2017-05-12 2022-02-08 Ut-Battelle, Llc Aluminum alloy compositions and methods of making and using the same

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FR2894857B1 (fr) 2005-12-16 2009-05-15 Alcan Rhenalu Sa Procede de fabrication de demi-produits comportant deux alliages a base d'aluminium
WO2007106772A2 (en) * 2006-03-13 2007-09-20 Alcoa Inc. Method and process of non-isothermal aging for aluminum alloys
FR2900160B1 (fr) * 2006-04-21 2008-05-30 Alcan Rhenalu Sa Procede de fabrication d'un element de structure pour construction aeronautique comprenant un ecrouissage differentiel
EP2193214B1 (en) 2007-10-04 2018-01-10 Aleris Rolled Products Germany GmbH A method for manufacturing a wrought metal plate product having a gradient in engineering properties
FR2945464B1 (fr) * 2009-05-13 2012-03-23 Alcan Rhenalu Procede d'assemblage par soudage de pieces en alliage d'aluminium.
ES2445323T3 (es) 2010-01-29 2014-03-03 Tata Steel Nederland Technology B.V. Proceso para el tratamiento térmico de material en tiras de metal, y material en tiras producido de esa manera
DE102010000292B4 (de) * 2010-02-03 2014-02-13 Thyssenkrupp Steel Europe Ag Metallband hergestellt aus Stahl mit unterschiedlichen mechanischen Eigenschaften
JP5776874B2 (ja) * 2011-02-14 2015-09-09 住友電気工業株式会社 マグネシウム合金圧延材、およびマグネシウム合金部材、ならびにマグネシウム合金圧延材の製造方法
FR2997706B1 (fr) * 2012-11-08 2014-11-07 Constellium France Procede de fabrication d'un element de structure d'epaisseur variable pour construction aeronautique

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US4518351A (en) * 1982-03-22 1985-05-21 Mellen Sr Robert H Method of providing a dynamic temperature gradient
FR2707092B1 (fr) * 1993-06-28 1995-08-25 Pechiney Rhenalu Produit métallurgique en alliage d'Al à durcissement structural présentant une variation continue des propriétés d'emploi suivant une direction donnée et un procédé et dispositif d'obtention de celui-ci.

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11220729B2 (en) 2016-05-20 2022-01-11 Ut-Battelle, Llc Aluminum alloy compositions and methods of making and using the same
US11242587B2 (en) 2017-05-12 2022-02-08 Ut-Battelle, Llc Aluminum alloy compositions and methods of making and using the same
US11180839B2 (en) 2017-10-26 2021-11-23 Ut-Battelle, Llc Heat treatments for high temperature cast aluminum alloys

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FR2868084B1 (fr) 2006-05-26
WO2005098072A3 (fr) 2006-05-04
FR2868084A1 (fr) 2005-09-30
ATE395444T1 (de) 2008-05-15
WO2005098072A2 (fr) 2005-10-20
ES2307180T3 (es) 2008-11-16
CA2560672A1 (fr) 2005-10-20
BRPI0507940A (pt) 2007-07-17
CN100507066C (zh) 2009-07-01
CA2560672C (fr) 2012-07-17
DE602005006764D1 (de) 2008-06-26
CN1930317A (zh) 2007-03-14
BRPI0507940B1 (pt) 2018-04-17
EP1727921A2 (fr) 2006-12-06

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