EP2010689B1 - Herstellungsprozess eines strukturelements für die flugzeigkonstruktion, welcher differentialfestwalzen enthält - Google Patents

Herstellungsprozess eines strukturelements für die flugzeigkonstruktion, welcher differentialfestwalzen enthält Download PDF

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EP2010689B1
EP2010689B1 EP07731300.5A EP07731300A EP2010689B1 EP 2010689 B1 EP2010689 B1 EP 2010689B1 EP 07731300 A EP07731300 A EP 07731300A EP 2010689 B1 EP2010689 B1 EP 2010689B1
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mpa
preferentially
dimension
thickness
transformation
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French (fr)
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EP2010689A1 (de
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Philippe Lequeu
Fabrice Heymes
Armelle Danielou
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Constellium Issoire SAS
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Constellium Issoire SAS
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/057—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C22C21/14—Alloys based on aluminium with copper as the next major constituent with silicon
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C22C21/16—Alloys based on aluminium with copper as the next major constituent with magnesium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C22C21/18—Alloys based on aluminium with copper as the next major constituent with zinc
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21B—ROLLING OF METAL
    • B21B2205/00—Particular shaped rolled products
    • B21B2205/02—Tailored blanks

Definitions

  • the present invention relates to wrought products and structural elements, in particular for aircraft construction, made of aluminum alloy.
  • the wrought 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.
  • Structural monolithic metal elements with variable properties in space are of considerable interest in the current context of the aeronautical industry. Indeed, the structural elements are subject to a set of contradictory constraints that require particular choices on materials and processing conditions, which can lead to unsatisfactory compromises.
  • the replacement of the long and costly mechanical assembly steps by more economical steps of integral machining of monolithic elements is limited by the possibility of obtaining within a monolithic element the most advantageous properties in a monolithic element. each geometric area. It would therefore be very interesting to produce monolithic structural elements having variable properties in space so as to obtain in each zone an optimal compromise of properties while enjoying the economic advantages of integral machining processes.
  • no method of manufacturing monolithic metal structural element with variable properties in space has been industrialized to date because many problems of cost and reliability are encountered.
  • a first proposed solution is to achieve, during the income, a different heat treatment between the ends of the structural element.
  • FR 2 707 092 discloses a method for producing structurally curable products having continuously variable properties in at least one direction in which the feed is made by carrying one end of the product at a temperature T and the other end at a temperature of temperature t in a specific furnace comprising a hot chamber and a cold room connected by a heat pump.
  • WO 2005/098072 (Pechiney Rhenalu) describes a manufacturing process in which at least one stage of the treatment of income is carried out in a controlled thermal profile oven comprising at least two zones or groups of zones Z 1 and Z 2 with initial temperatures T 1 and T 2 in which the length of the two zones is at least one meter.
  • the problem is partly solved by locally varying the thickness of structural elements with homogeneous properties in space so as to allow them to withstand the local level of stress.
  • the variation in thickness is generally obtained by assembly or by machining.
  • CA 2,317,366 Airbus GmbH describes, for example, the manufacture of fuselage elements by welding plates of various thicknesses. It is also conceivable to directly obtain by rolling sheets of varying thickness so as to avoid the assembly steps and the associated technical and economic problems. Thickness variations can be envisaged in the longitudinal direction or in the transverse direction (see for example R. Kopp, C. Wiedner and A. Meyer, International Sheet Metal Review, July / August 2005, p20-24 ).
  • JP 11-192502 (Nippon Steel) and describes a method for obtaining a steel strip, whose thickness and static mechanical characteristics vary in width.
  • EP 0 062 469 A1 (Sumitomo) describes a process comprising a step of transformation by cold plastic deformation with several cold reductions followed by a heat treatment solubilization also called dissolution.
  • WO 00/21695 (Thyssen Krupp) describes a method for obtaining sections of variable thickness in the rolling direction within a metal strip, these sections having different mechanical properties.
  • the problem addressed by the present invention is to develop a process for the manufacture of wrought products and monolithic alloy structural elements. of aluminum, in particular for aircraft construction, having variable use properties in space while having geometrical characteristics identical to those of current products and elements, which is sufficiently economical and controllable, which makes it possible to vary in the space the properties of use of structural elements whose manufacturing process does not necessarily require income and which allows to vary the properties of employment of structural elements at different positions of their length.
  • a first object of the present invention is a method for manufacturing a wrought product or a monolithic multi-functional structural element made of aluminum alloy comprising a hot transformation step characterized in that after the hot conversion it also comprises at least one step of transformation by cold plastic deformation in which at least two zones of the structural element of the average generalized plastic deformations different from at least 2% and preferably different by at least 3% are imposed. .
  • a second object of the invention is a wrought product or a 2XXX alloy structure element in the T3X state that can be obtained by the method according to the invention.
  • a third object of the invention is a wrought product or a structural element made of 2XXX alloy containing lithium in the T8X state that can be obtained by the process 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.
  • K 1C toughness is measured according to ASTM E 399.
  • the definitions of the European standard EN 12258-1 apply, in particular without heat treatment, an alloy which can not be substantially hardened by heat treatment and alloy with heat treatment an alloy that can be hardened by a suitable heat treatment.
  • sheet metal is used here for rolled products of any thickness.
  • cold plastic deformation plastic deformation for which the metal is deliberately heated neither before being deformed nor during the deformation.
  • cold plastic deformations including cold rolling, controlled pulling (planing), drawing, drawing, stamping, stamping, bending, compression and cold forging.
  • hot transformation is meant a deformation step for which the initial temperature of the metal is at least 200 ° C.
  • the average generalized plastic deformation is the average of the generalized plastic deformation in a given volume.
  • 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.
  • wrought product refers to a semi-finished product (i.e., an intermediate product) ready to be processed, in particular by sawing, machining and / or forming a structural element. In some cases the wrought product can be used directly as a structural element.
  • the wrought 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.
  • the method of manufacturing the wrought product comprises a controlled pulling step, the ends of the workpiece which are under the grip of the jaws of the traction bench are sawed so as to render the workpiece usable in mechanical engineering.
  • 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 and spars) and the empennage composed in particular of horizontal and vertical stabilizers (horizontal or vertical stabilizers), as well as the floor beams, the seat tracks and the doors.
  • fuselage such as fuselage skin (fuselage skin in English), stiffeners or stringers, bulkheads, fuselage (circumferential frames), wings (such as wing skin), stiffeners (stiffeners), ribs and spars
  • empennage composed in particular of horizontal and vertical stabilizers (horizontal or vertical stabilizers), as well as the floor beams, the seat tracks and the 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.
  • multi-functional structural element refers here primarily to the functions conferred by the metallurgical characteristics of the product and not by its geometric form.
  • the problem is solved by a method of manufacturing a wrought aluminum alloy product or a monolithic multi-functional aluminum alloy structural element which comprises at least one step of plastic deformation to cold after the hot transformation, in which at least two zones of the wrought product or of the structural element undergo different average generalized plastic deformations of at least 2%, preferably at least 3% and even more preferentially at least 4% or even 5%.
  • the areas considered have a significant volume relative to the total volume of the structural element.
  • the volume of the zones considered represents at least 5%, preferably at least 10% and more preferably at least 15% of the total volume of the wrought product or the structural element.
  • all zones of the wrought product or the structural element undergo minimum generalized plastic deformation of at least 1% and preferably at least 1.5%.
  • the process according to the invention comprises at least two stages of transformation by cold plastic deformation after the hot transformation.
  • the methods according to the invention make it possible to produce wrought products and structural elements having a main dimension or final length L f in the principal direction or direction of the length L and a final section in the plane perpendicular to this direction S f .
  • the section S f is substantially constant at all points of the wrought product.
  • the thickness e f it is advantageous for the thickness e f to be substantially constant at all points.
  • Machining may be one of the last step of the method according to the invention so as to obtain a final section and / or a final thickness of the wrought product substantially constant at any point.
  • the process according to the invention can be used to produce wrought products, preferably sheets and profiles, and structural elements of any wrought aluminum alloy.
  • the invention can be used with alloys without heat treatment such as alloys 1XXX, 3XXX, 5XXX and some alloys of the 8XXX series, and particularly advantageously with 5XXX alloys containing scandium, at a preferred content of 0.001 to 5% by weight and even more preferably 0.01 to 0.3% by weight.
  • the differences in mechanical properties resulting from the differences in workmanship obtained by the process according to the invention give the structural elements obtained from wrought products of alloy without heat treatment according to the invention a multi-functional character.
  • a heat-treated aluminum alloy is used, and between the hot conversion and the first cold plastic deformation transformation, a solution step, a quenching step and optionally a step of income posterior to the transformation steps by cold plastic deformation.
  • the invention can be used to develop wrought products or aluminum alloy structural members of the 2XXX, 4XXX, 6XXX and 7XXX series, as well as 8XXX series-containing structural alloy containing lithium.
  • alloy containing lithium an alloy whose lithium content is greater than 0.1% by weight.
  • an income can be used to obtain for example a T8X state or, on the contrary, to use a natural aging to a T3X state.
  • the invention is particularly advantageous for producing wrought products or structural elements made of 2XXX alloy in the T3X state.
  • the cold plastic deformation carried out after the solution and quenching steps makes it possible to modify the kinetics of income.
  • the zones undergoing different average generalized plastic deformations will reach different metallurgical states during the income, which will give the structural element a multi-functional character.
  • the tempering is carried out in a furnace having a temperature gradient so as to amplify the differences in properties between the ends of the heat sink element. structure.
  • the at least two zones of the wrought product or of the structural element undergoing different average generalized plastic deformations of at least 2% are located at a different position in the main direction or in length. L.
  • the zones considered advantageously have a section S Z in the plane perpendicular to the direction L equal to the section of the product wrought in this plane.
  • the wrought product is substantially constant section S Z is advantageously substantially equal to S f .
  • the length of said zones in the direction L is preferably at least 1m and preferably at least 5m.
  • the method according to the invention comprises in the first variant at least one cold plastic deformation step by controlled traction.
  • Controlled traction is usually used to perform planing or straightening and to release residual stresses.
  • a controlled traction step in which one of the ends of the intermediate product on which the controlled traction is carried out significantly exceeds the jaws of the traction bench, can also be used to generate average generalized plastic deformations. between two areas of the wrought product.
  • the figure 1 illustrates an embodiment of the invention in which 3 controlled traction steps are performed successively.
  • At least one of the jaws (1) of the traction bench is then moved as indicated on the figure 1 , so that one of the ends of the piece significantly exceeds the jaws and the length of the part between the jaws is L 1 .
  • a second controlled traction step B is then performed on the zone of the part located between the jaws so as to obtain a second useful intermediate length L i2 of the element and thus to pass the zone (22) between the jaws of the length L 1 to the length L i2 - L i1 + L 1 .
  • at least one of the jaws can be moved again so as to perform at least a third pulling step on a portion of length L 2 .
  • a fourth step D the ends of the part which were under the grip of the jaws of the traction bench during step A are sawn.
  • the method using successive pulls described by the figure 1 can be applied to sheet metal as well as to spun products.
  • the figure 2 describes another embodiment of the first variant of the invention.
  • an intermediate product having a variable section in the direction of the length L.
  • the intermediate product thus obtained has an initial length L 0 and three different sectional areas S 1 , S 2 and S 3 .
  • the deformations undergone by these zones are different.
  • At least one cold plastic deformation step is performed by compression. This embodiment is illustrated by the figure 5 .
  • the method according to the invention comprises a cold rolling step in which the thickness of the sheet is variable. at the entrance of the rolling mill and substantially constant at the exit of the rolling mill.
  • the figure 3 illustrates an embodiment in which a sheet having three zones Z31 , Z32 and Z33 of respective thicknesses e 1 , e 2 and e 3 and an initial length L 0 undergoes a cold rolling step between two rolls (5) leading to a final thickness e f .
  • the sheet having a variable thickness in the direction L required in the embodiment described by the figure 3 can be obtained for example by modifying in the course of hot rolling the thickness target.
  • this sheet of variable thickness can be obtained by machining a sheet of constant thickness resulting from the hot rolling step.
  • the figure 3 describes an embodiment in which the thickness variation is obtained on one side, the other face remaining flat. It is also possible to vary the thickness on both sides and not to keep a plane face.
  • the method according to the invention comprises a cold rolling step in which the thickness of the sheet is substantially constant at the input of the rolling mill and variable in the direction L at the exit of the rolling mill and a subsequent machining step which makes it possible to obtain a substantially constant thickness at all points.
  • the areas of the structural element undergoing different mean generalized plastic deformations of at least 2% are located at a different position in the transverse direction l .
  • the zones considered advantageously have a thickness e Z in the direction of the thickness e equal to the thickness of the wrought product.
  • the thickness e Z is advantageously substantially equal to e f .
  • the width of said zones is preferably at least 0.2 m and preferably at least 0.4 m.
  • the method according to the invention comprises a cold rolling step in which the thickness of the sheet is variable in the transverse direction 1 at the inlet of the rolling mill and is substantially constant at the exit of the rolling mill.
  • the thickness variation of the sheet may in particular be obtained by hot rolling, by machining at the end of the hot rolling or by forging.
  • This embodiment is illustrated on the figure 4 where a sheet whose thickness is e 1 for the areas at the ends of the element in direction 1 is e 2 for the centrally located area in the direction 1 is laminated in the direction L to a thickness substantially homogeneous e f .
  • the embodiment in which the zones Z41 and Z43 have the same initial thickness is advantageous, however an embodiment in which the thicknesses are different is also possible.
  • the method according to the invention comprises a cold rolling step in which the thickness of the sheet is substantially constant at the input of the rolling mill and variable in the direction l at the output of the rolling mill and a subsequent machining step that provides a substantially constant thickness at any point.
  • the figure 5 describes another embodiment in which a compression is performed using a tool (6) moving in the direction symbolized by an arrow.
  • the thickness is reduced from e 0 to e 1 , then in a second step from e 1 to e 2 on a part of the structural element, then finally during a third step of e 2 to e 3 , which defines three zones Z51 , Z52 and Z53 .
  • a final machining step allows to obtain a final thickness e f substantially equal at any point. It is also possible to machine the sheet to different thicknesses and then compress it so as to obtain a constant thickness at all points.
  • a sheet 30 meters long, 2.5 meters wide and 28.2 mm thick was manufactured by hot rolling a rolling plate.
  • composition of the alloy used is given in Table 1 below: Table 1: composition of the alloy rolling plate AA2023 (% by weight) Yes Fe Cu mg Ti Zr sc 0.06 0.07 3.81 1.36 0,024 0.11 0.03
  • the rolling plate was homogenized for 12 hours at 500 ° C.
  • the inlet temperature of the hot rolling was 460 ° C.
  • the sheet was then dissolved at 500 ° C. and quenched.
  • the sheet was then cold-rolled, so as to obtain a substantially constant thickness of 25.5 mm over the entire sheet, then underwent a controlled pull with a permanent elongation of about 2% at the end of which ends of the piece which were under the grip of the jaws of the traction bench were sawn
  • the rolling step led the zone Z31 to reach a length of about 11 meters
  • Table 2 The deformations performed in the different zones are summarized in Table 2 below: Table 2.
  • Zoned Work hardening rate Tensile strain rate Total work hardening rate Generalized deformation by rolling Generalized deformation by traction Total generalized deformation Z31 10.2% 2.0% 12.4% 11.2% 2.0% 13.2% Z32 3.1% 2.0% 5.2% 3.6% 2.0% 5.6% Z33 0.0% 2.0% 2.0% 0.0% 2.0% 2.0% 2.0% 2.0% 2.0% 2.0% 2.0% 2.0%
  • zone Z31 is characterized by a high mechanical strength, to the detriment of a limited elongation while zone Z33 is distinguished by a significant elongation but for a lower static mechanical resistance.
  • a sheet 30 meters long, 2.5 meters wide and 16.8 mm thick was manufactured by hot rolling a rolling plate.
  • composition of the alloy used is given in Table 4 below: Table 4: composition of the alloy rolling plate AA2024A (% by weight) Yes Fe Cu mn mg Ti 0.04 0.07 3.96 0.38 1.29 0,013
  • the rolling plate was homogenized and then hot rolled.
  • the sheet was then dissolved at 500 ° C. and quenched.
  • the sheet was then cold-rolled, so as to obtain a substantially constant thickness of 15.3 mm over the entire sheet, then underwent a controlled pull with a permanent elongation of about 2% at the end of which ends of the piece which were under the grip of the jaws of the traction bench were sawed.
  • Zoned Work hardening rate Tensile strain rate Total work hardening rate Generalized deformation by rolling Generalized deformation by traction Total generalized deformation Z31 9.2% 2% 11.3% 10.1% 2.0% 12.1% Z32 3.9% 2% 6.0% 4.4% 2.0% 6.4% Z33 0.0% 2% 2.0% 0.0% 2% 2.0%
  • zone Z31 is characterized by a high mechanical strength, to the detriment of a limited elongation while zone Z33 is distinguished by a significant elongation but for a lower static mechanical resistance.
  • composition of the alloy used is given in Table 7 below: Table 7: composition of the alloy rolling plate AA2027 (% by weight) Yes Fe Cu mn mg Zn Ti Zr 0.05 0.11 4.2 0.6 1.3 0.06 0.02 0.11
  • the spinning billet was homogenized at 490 ° C and extruded while hot.
  • Table 8 The deformations performed in the zones are summarized in Table 8 below: Table 8. Work hardening rate and general deformation in zones Z11, Z12 and Z13.
  • Tensile strain rate Generalized deformation rate Zoned Step 1 2nd step 3rd step Total Step 1 2nd step 3rd step Total Z11 2.8% 5.6% 2.4% 11.2% 2.8% 5.4% 2.4% 10.6% Z12 2.8% 5.6% 8.6% 2.8% 5.4% 8.2% Z13 2.8% 2.8% 2.8% 2.8%
  • zone Z11 is characterized by high mechanical strength, to the detriment of limited elongation and toughness, while zone Z13 is distinguished by a significant elongation and tenacity but for a lower static mechanical strength.
  • a sheet 30 meters long, 2.5 meters wide and 33 mm thick was manufactured by hot rolling a rolling plate.
  • composition of the alloy used is given in Table 10 below: Table 10: Composition of rolling plate alloy AA2195 (% by weight) Yes Fe Cu Li mg Zr Ag 0.03 0.06 4.3 1.17 0.39 0.12 0.35
  • the rolling plate was homogenized and then hot rolled.
  • the sheet was then dissolved at 510 ° C. and quenched.
  • zone G One half of the sheet (zone G) was then cold-rolled to 30 mm thickness while the other half underwent a controlled pull with 2.5% offset jaws (zone H).
  • the sheet was then machined, so as to obtain a substantially constant thickness of 30 mm over the entire sheet, then underwent a controlled pull with a permanent elongation of about 1.5% at the end of which the ends of the piece that were under the grip of the jaws of the traction bench were sawn
  • Table 11 The deformations made in the different zones are summarized in Table 11 below: Table 11. Work hardening rate and generalized deformation in zones G and H. Zoned Work hardening rate Tensile strain rate Total work hardening rate Deformations generalized by rolling Generalized deformation by traction Total generalized deformation BOY WUT 10% 1,5% 11.3% 11% 1,5% 11.5% H 0% 2.5 + 1.5% 4.0% 0% 2.5 + 1.5% 4.0%
  • the method according to the invention makes it possible to obtain compromises of different properties in the zones G and H.
  • the zone G is characterized by a high mechanical resistance, to the detriment of a limited elongation and tenacity whereas the zone H is distinguished by greater elongation and toughness but for lower static strength.

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  • Organic Chemistry (AREA)
  • Metallurgy (AREA)
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  • Crystallography & Structural Chemistry (AREA)
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Claims (14)

  1. Verfahren zur Herstellung eines Kneterzeugnisses aus Aluminiumlegierung ohne Wärmebehandlung, wobei das Verfahren umfasst:
    - einen Warmumformschritt,
    - mindestens einen Umformschritt durch plastische Kaltverformung, bei dem in wenigstens zwei Bereichen des Kneterzeugnisses mittlere generalisierte plastische Verformungen durchgeführt werden, die um mindestens 2% und vorzugsweise um mindestens 3% voneinander verschieden sind,
    dadurch gekennzeichnet, dass die Umformung durch plastische Kaltverformung nach der Warmumformung durchgeführt wird.
  2. Verfahren zur Herstellung eines Kneterzeugnisses aus Aluminiumlegierung mit Wärmebehandlung, wobei das Verfahren umfasst:
    - einen Warmumformschritt,
    - einen Lösungsglühschritt und einen Abschreckschritt,
    - mindestens einen Umformschritt durch plastische Kaltverformung, bei dem in wenigstens zwei Bereichen des Kneterzeugnisses mittlere generalisierte plastische Verformungen durchgeführt werden, die um mindestens 2 % und vorzugsweise um mindestens 3 % voneinander verschieden sind,
    dadurch gekennzeichnet, dass die Umformung durch plastische Kaltverformung nach der Warmumformung und dem Lösungsglüh- und Abschreckschritt durchgeführt wird.
  3. Verfahren nach Anspruch 1 oder 2, welches mindestens zwei Umformschritte durch plastische Kaltverformung nach der Warmumformung umfasst.
  4. Verfahren nach irgendeinem der Ansprüche 1 bis 3, bei dem das Kneterzeugnis ein Haupt- oder Längenmaß in der Richtung L aufweist und bei dem sich die wenigstens zwei Bereiche an einer unterschiedlichen Position in der Hauptrichtung L befinden.
  5. Verfahren nach Anspruch 4, bei dem mindestens ein plastischer Kaltverformungsschritt ein kontrolliertes Ziehen ist und bei dem eines der Enden in Hauptrichtung des Zwischenerzeugnisses, an dem das kontrollierte Ziehen durchgeführt wird, bei diesem kontrollierten Ziehschritt deutlich aus den Klemmbacken der Ziehmaschine herausragt.
  6. Verfahren nach Anspruch 4, bei dem mindestens ein plastischer Kaltverformungsschritt ein kontrolliertes Ziehen ist und bei dem dieser kontrollierte Ziehschritt an einem Zwischenerzeugnis durchgeführt wird, das in der Ebene senkrecht zur Richtung L einen variablen Querschnitt hat.
  7. Verfahren nach Anspruch 4, bei dem das Kneterzeugnis ein Blech ist, das ein Haupt- oder Längenmaß in Richtung L, ein Quer- oder Breitenmaß in Richtung l und ein Dickenmaß in Richtung e aufweist, und bei dem mindestens ein Umformschritt durch plastische Kaltverformung mittels Kaltwalzen so durchgeführt wird, dass die Dicke des Blechs am Eingang des Walzwerks variabel und am Ausgang des Walzwerks im Wesentlichen konstant ist.
  8. Verfahren nach Anspruch 7, bei dem die Dickenvariation des Blechs am Eingang des Kaltwalzwerks während des Warmwalzschritts bzw. durch Bearbeitung eines aus dem Warmwalzschritt hervorgehenden Blechs konstanter Dicke erzeugt wird.
  9. Verfahren nach Anspruch 4, bei dem das Kneterzeugnis ein Blech ist, das ein Haupt- oder Längenmaß in Richtung L, ein Quer- oder Breitenmaß in Richtung l und ein Dickenmaß in Richtung e aufweist,
    und bei dem mindestens ein Umformschritt durch plastische Kaltverformung mittels Kaltwalzen so durchgeführt wird, dass die Dicke des Blechs am Eingang des Walzwerks im Wesentlichen konstant und am Ausgang des Walzwerks variabel ist,
    und bei dem mit einem nachfolgenden Bearbeitungsschritt eine an allen Stellen im Wesentlichen konstante Enddicke erhalten werden kann.
  10. Verfahren nach irgendeinem der Ansprüche 1 bis 3, bei dem das Kneterzeugnis ein Blech ist, das ein Haupt- oder Längenmaß in Richtung L, ein Quer- oder Breitenmaß in Richtung l und ein Dickenmaß in Richtung e aufweist, und bei dem sich die wenigstens zwei Bereiche an einer unterschiedlichen Position in der Querrichtung l befinden.
  11. Verfahren nach Anspruch 10, bei dem mindestens ein Umformschritt durch plastische Kaltverformung mittels Kaltwalzen so durchgeführt wird, dass die Dicke des Blechs am Eingang des Walzwerks im Wesentlichen konstant und am Ausgang des Walzwerks variabel ist,
    und bei dem mit einem nachfolgenden Bearbeitungsschritt eine an allen Stellen im Wesentlichen konstante Enddicke erhalten werden kann.
  12. Kneterzeugnis aus einer Legierung 2XXX im Zustand T3X, herstellbar durch das Verfahren nach irgendeinem der Ansprüche 1 bis 11, dadurch gekennzeichnet, dass die wenigstens zwei Bereiche Z1 und Z2 Festigkeitseigenschaften aufweisen, die ausgewählt sind aus der Gruppe bestehend aus
    (i) Z1: Rm(L) > 500 MPa und vorzugsweise Rm(L) > 520 MPa
    und Z2 : A(L)(%) > 16% und vorzugsweise A(L)(%) > 18%
    (ii) Z1: Rm(L) > 450 MPa und vorzugsweise Rm(L) > 470 MPa
    und Z2 : A(L)(%) > 18% und vorzugsweise A(L)(%) > 20%
    (iii) Z1: Rm(L) > 550 MPa und vorzugsweise Rm(L) > 590 MPa
    und Z2 : A(L)(%) > 10% und vorzugsweise A(L)(%) > 14%
    (iv) Z1: Rm(L) > 550 MPa und vorzugsweise Rm(L) > 590 MPa
    und Z2 : K1c(L-T) > 45MPa√m und vorzugsweise K1c(L-T) > 45MPa√m.
  13. Kneterzeugnis aus einer Legierung 2XXX im Zustand T3X, herstellbar durch das Verfahren nach irgendeinem der Ansprüche 1 bis 11, dadurch gekennzeichnet, dass die wenigstens zwei Bereiche Z1 und Z2 Festigkeitseigenschaften aufweisen, bei denen
    (i) Rp0,2, gemessen in L-Richtung oder in LT-Richtung, eine Abweichung Rp0,2(Z1) - Rp0,2(Z2) von mindestens 50 MPa und vorzugsweise mindestens 70 MPa aufweist, und/oder
    (ii) Rm, gemessen in L-Richtung oder in LT-Richtung, eine Abweichung Rm(Z1) - Rm(Z2) von mindestens 20 MPa und vorzugsweise mindestens 30 MPa aufweist.
    (iii) K1c, gemessen in L-T-Richtung, weist eine Abweichung K1c (Z1) - K1c (Z2) von mindestens 5MPa√m und vorzugsweise mindestens 15MPa√m auf.
  14. Kneterzeugnis aus einer Lithium enthaltenden Legierung 2XXX im Zustand T8X, herstellbar durch das Verfahren nach irgendeinem der Ansprüche 1 bis 11, dadurch gekennzeichnet, dass die wenigstens zwei Bereiche Z1 und Z2 Festigkeitseigenschaften aufweisen, die ausgewählt sind aus der Gruppe bestehend aus
    (i) Z1 : Rm(L) > 630 MPa und vorzugsweise Rm(L) > 640 MPa
    und Z2 : A(L)(%) > 8% und vorzugsweise A(L)(%) > 9%
    (ii) Z1: Rm(L) > 640 MPa und vorzugsweise Rm(L) > 650 MPa
    und Z2 : A(L)(%) > 7% und vorzugsweise A(L)(%) > 8%
    (iii) Z1: Rm(L) > 630 MPa und vorzugsweise Rm(L) > 640 MPa
    und Z2 : K1c(L-T) > 25MPa√m und vorzugsweise K1c(L-T) > 30MPa√m.
EP07731300.5A 2006-04-21 2007-04-16 Herstellungsprozess eines strukturelements für die flugzeigkonstruktion, welcher differentialfestwalzen enthält Active EP2010689B1 (de)

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FR0603567A FR2900160B1 (fr) 2006-04-21 2006-04-21 Procede de fabrication d'un element de structure pour construction aeronautique comprenant un ecrouissage differentiel
US80355306P 2006-05-31 2006-05-31
PCT/FR2007/000633 WO2007122314A1 (fr) 2006-04-21 2007-04-16 Procede de fabrication d'un element de structure pour construction aeronautique comprenant un ecrouissage differentiel

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CN101426945A (zh) 2009-05-06
JP2009534191A (ja) 2009-09-24
FR2900160A1 (fr) 2007-10-26
RU2440438C2 (ru) 2012-01-20
EP2010689A1 (de) 2009-01-07
FR2900160B1 (fr) 2008-05-30
CA2649571A1 (fr) 2007-11-01
BRPI0711263A2 (pt) 2011-08-30
US10144998B2 (en) 2018-12-04
CN101426945B (zh) 2015-04-15
WO2007122314A1 (fr) 2007-11-01
RU2008145888A (ru) 2010-05-27
US20070246137A1 (en) 2007-10-25
CA2649571C (fr) 2014-03-25

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