EP2449142B1 - Aluminium-kupfer-lithium-legierung mit verbesserten mechanische beständigkeit und zähigkeit - Google Patents

Aluminium-kupfer-lithium-legierung mit verbesserten mechanische beständigkeit und zähigkeit Download PDF

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EP2449142B1
EP2449142B1 EP10734173.7A EP10734173A EP2449142B1 EP 2449142 B1 EP2449142 B1 EP 2449142B1 EP 10734173 A EP10734173 A EP 10734173A EP 2449142 B1 EP2449142 B1 EP 2449142B1
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mpa
weight
yield strength
tensile yield
product
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French (fr)
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EP2449142A1 (de
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Armelle Danielou
Cédric GASQUERES
Christophe Sigli
Timothy Warner
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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
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • 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
    • 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
    • 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

Definitions

  • the invention relates to aluminum-copper-lithium alloy products, more particularly, such products, their manufacturing and use processes, intended in particular for aeronautical and aerospace construction.
  • Products, especially thick rolled products, forged or spun aluminum alloy are developed to produce by cutting, surfacing or mass machining of high strength parts intended especially for the aviation industry, the aerospace industry or mechanical construction.
  • Aluminum alloys containing lithium are very interesting in this respect, since lithium can reduce the density of aluminum by 3% and increase the modulus of elasticity by 6% for each weight percent of lithium added.
  • their performance compared to other properties of use must reach that of commonly used alloys, in particular in terms of a compromise between the static mechanical strength properties (yield strength, resistance to rupture) and the properties of damage tolerance (toughness, resistance to the propagation of fatigue cracks), these properties being in general antinomic.
  • a product is said to be quench sensitive if its static mechanical characteristics, such as its yield strength, decrease as quenching speed decreases.
  • the quenching rate is the average cooling rate of the product during quenching.
  • These alloys must also have sufficient corrosion resistance, be able to be shaped according to the usual methods and have low residual stresses so that they can be machined integrally.
  • the US Patent 5,032,359 discloses a large family of aluminum-copper-lithium alloys in which the addition of magnesium and silver, in particular between 0.3 and 0.5 percent by weight, makes it possible to increase the mechanical strength.
  • the US Patent 5,234,662 describes alloys of composition (in% by weight), Cu: 2.60 - 3.30, Mn: 0.0 - 0.50, Li: 1.30 - 1.65, Mg: 0.0 - 1, 8, elements controlling the granular structure selected from Zr and Cr: 0.0 - 1.5.
  • the US Patent 5,455,003 discloses a process for producing Al-Cu-Li alloys which have improved mechanical strength and toughness at cryogenic temperature, particularly through proper work-hardening and tempering.
  • the problem of aging products for civil aviation applications is not mentioned because the products concerned are essentially cryogenic tanks for rocket launchers or space shuttle.
  • the US Patent 7,438,772 discloses alloys comprising, in weight percent, Cu: 3-5, Mg: 0.5-2, Li: 0.01-0.9 and discourage the use of higher lithium content due to degradation compromise between toughness and mechanical strength.
  • the US Patent 7,229,509 discloses an alloy comprising (% by weight): (2.5-5.5) Cu, (0.1-2.5) Li, (0.2-1.0) Mg, (0.2-0, 8) Ag, (0.2-0.8) Mn, 0.4 max Zr or other grain-refining agents such as Cr, Ti, Hf, Sc, V, especially having a toughness K 1C (L)> 37.4 MPa ⁇ m for an elastic limit R p0.2 (L)> 448.2 MPa (products with a thickness greater than 76.2 mm) and in particular a tenacity K 1C (L)> 38.5 MPa ⁇ m for an elastic limit R p0, 2 (L)> 489.5 MPa (products less than 76.2 mm thick).
  • AA2050 alloy is also known which comprises (% by weight): (3.2-3.9) Cu, (0.7-1.3) Li, (0.20-0.6) Mg, (0 , 20-0.7) Ag, 0.25max. Zn, (0.20-0.50) Mn, (0.06-0.14) Zr and AA2095 (3.7-4.3) Cu, (0.7-1.5) Li, (0.25-0.8) Mg, (0.25-0.6) Ag, 0.25max. Zn, 0.25 max. Mn, (0.04-0.18) Zr.
  • AA2050 alloy products are known for their quality in terms of static strength and toughness.
  • Yet another object of the invention is a structural element comprising a product according to the invention.
  • Yet another object of the invention is the use of a structural element according to the invention for aeronautical construction.
  • alloys are 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 metallurgical states are given in the European standard EN 515.
  • the static mechanical characteristics in other words the ultimate tensile strength R m , the conventional yield stress at 0.2% elongation R p 0.2 ("yield strength") and the elongation at break A%, are determined by a tensile test according to EN 10002-1, the sampling and the direction of the test being defined by the EN 485-1 standard.
  • the stress intensity factor (K Q ) is determined according to ASTM E 399.
  • ASTM E 399 gives the criteria for determining if K Q is a valid value of K 1C .
  • the K Q values obtained for different materials are comparable to each other as long as the elasticity limits of the materials are of the same order of magnitude.
  • the definitions of EN 12258 apply.
  • the thickness of the profiles is defined according to EN 2066: 2001: the cross section is divided into elementary rectangles of dimensions A and B; A being always the largest dimension of the elementary rectangle and B can be considered as the thickness of the elementary rectangle. The sole is the elementary rectangle with the largest dimension A.
  • the MASTMAASIS Modified ASTM Acetic Acid Salt Intermittent Spray test is performed according to ASTM G85.
  • a "structural element” or “structural element” of a mechanical construction is called a mechanical part for which the static and / or dynamic mechanical properties are particularly important for the performance of the structure, and for which a structural calculation is usually prescribed or realized.
  • These are typically elements 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 (stringers or stiffeners), ribs (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 such as wing skin
  • wings such as wing skin
  • stiffeners stringers or stiffeners
  • ribs ribs
  • spars spars
  • 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.
  • a selected class of aluminum alloys which contain specific and critical amounts of lithium, copper and magnesium and zirconium makes it possible to prepare wrought products having an improved compromise between toughness and mechanical strength, and good resistance to corrosion.
  • these products when they undergo an income chosen so as to achieve a yield strength R p0 , 2 close to the yield strength R p0 , 2 at the peak, exhibit excellent thermal stability.
  • the present inventors have found that, surprisingly, it is possible to improve the compromise between the static mechanical strength properties and the damage tolerance properties, in particular of thick products made of aluminum-copper-lithium alloys, such as in particular the alloy. AA2050, by increasing the magnesium content.
  • the choice of copper, magnesium and lithium contents makes it possible to reach a compromise of favorable properties and to obtain a satisfactory thermal stability of the product.
  • the copper content of the products according to the invention is between 3.2 and 3.7% by weight. When the copper content is too high, the toughness is not sufficient especially for income close to the peak and, moreover, the density of the alloy is not advantageous. When the copper content is too low, the minimum static mechanical characteristics are not reached.
  • the lithium content of the products according to the invention is between 0.8 and 1.3% by weight.
  • the lithium content is between 0.9% and 1.2% by weight.
  • the lithium content is at least 0.93% by weight or even at least 0.94% by weight.
  • the magnesium content of the products according to the invention is between 0.6 and 1.0% by weight and preferably between 0.65 or 0.67 and 1.0% by weight.
  • the magnesium content is at most 0.9% by weight and preferably at most 0.8% by weight.
  • the magnesium content is at least 0.7% by weight.
  • the zirconium content is between 0.05 and 0.18% by weight and preferably between 0.08 and 0.14% by weight so as to obtain preferably a fibered or slightly recrystallized grain structure.
  • the manganese content is between 0.0 and 0.5% by weight. In particular for the manufacture of thick plates, a manganese content of between 0.2 and 0.4% by weight makes it possible to improve the toughness without compromising the mechanical strength.
  • the silver content is between 0.0 and 0.5% by weight.
  • the silver content is between 0.15 and 0.35% by weight.
  • the silver content is at most 0.25% by weight.
  • the sum of the iron content and the silicon content is at most 0.20% by weight.
  • the iron and silicon contents are each at most 0.08% by weight.
  • the iron and silicon contents are at most 0.06% and 0.04% by weight, respectively.
  • a controlled and limited iron and silicon content contributes to the improvement of the compromise between mechanical resistance and damage tolerance.
  • the alloy also contains at least one element that can contribute to controlling the grain size selected from Cr, Sc, Hf and Ti, the amount of the element, if selected, being from 0.05 to 0.3 % by weight for Cr and for Sc, 0.05 to 0.5% by weight for Hf and from 0.01 to 0.15% by weight for Ti.
  • Preferably, between 0.02 and 0.10% by weight of titanium is chosen.
  • Zinc is an undesirable impurity.
  • the zinc content is Zn ⁇ 0.15% by weight and preferably Zn ⁇ 0.05% by weight.
  • the zinc content is advantageously less than 0.04% by weight.
  • thinner products are preferred, the thickness of which is between 10 and 30 mm, typically about 20 mm, because the compromise obtained under these conditions between strength and toughness is particularly advantageous.
  • the products according to the invention also have advantageous properties in terms of fatigue behavior both from the point of view of the crack initiation (S / N) and the propagation speed (da / dN).
  • the corrosion resistance of the products of the invention is generally high; thus, the MASTMAASIS test result (ASTMG85 & G34 standards) is at least EA and preferably P for the products according to the invention.
  • the method of manufacturing the products according to the invention comprises stages of preparation, casting, wrought, solution, quenching and tempering.
  • a bath of liquid metal is produced so as to obtain an aluminum alloy of composition according to the invention.
  • the liquid metal bath is then cast in a raw form, such as a billet, a rolling plate or a forging blank.
  • the crude form is then homogenized at a temperature between 450 ° C and 550 ° and preferably between 480 ° C and 530 ° C for a period between 5 and 60 hours.
  • the raw form is generally cooled to room temperature before being preheated for hot deformation.
  • Preheating aims to reach a temperature preferably between 400 and 500 ° C and preferably of the order of 450 ° C allowing the deformation of the raw form.
  • Hot deformation and optionally cold deformation is typically performed by spinning, rolling and / or forging to obtain a spun, rolled and / or forged product preferably having a thickness of at least 30 mm.
  • the product thus obtained is then put in solution by heat treatment between 490 and 530 ° C for 15 min to 8 h, then quenched typically with water at room temperature or preferably cold water.
  • the product then undergoes controlled traction with a permanent deformation of 1 to 6% and preferably of at least 2%.
  • the rolled products preferably undergo controlled pulling with a permanent deformation greater than 3%.
  • the controlled traction is carried out with a permanent deformation of between 3 and 5%.
  • a preferred metallurgical state is the T84 state.
  • Known steps such as rolling, planing, straightening shaping may optionally be performed after solution and quenching and before or after controlled pulling.
  • An income is achieved comprising heating at a temperature between 130 and 170 ° C and preferably between 150 and 160 ° C for 5 to 100 hours and preferably from 10 to 40h so as to achieve a yield strength R p0, 2 close to the elastic limit R p0,2 at the peak.
  • R p0, 2 close to the elastic limit
  • the yield strength increases with the duration of tempering at a given temperature up to a maximum value called the peak of hardening or "peak” then decreases with the duration of income.
  • the yield curve is defined as the evolution of the elastic limit as a function of the equivalent duration of income at 155 ° C.
  • An example of an income curve is presented in FIG. 1.
  • a point N of the income curve, of duration equivalent to 155 ° C t N and yield strength R p0 , 2 (N) is close to the peak by determining the slope P N of the tangent to the income curve at point N. It is considered in the context of the present invention that the elastic limit of a point N of the curve of income is close to the yield strength at the peak if the absolute value of the slope P N is at most 3 MPa / h. As illustrated by FIG. 1, an under-income state is a state for which P N is positive and an over-income state is a state for which P N is negative.
  • the present inventors have found that a satisfactory approximation of P N is generally obtained when the difference t N - t N-1 is between 2 and 15 hours and preferably is of the order of 3 hours.
  • the elastic limit close to the yield strength at the peak is typically at least 90%, generally even at least 95% and frequently at least 97% of the elastic limit R p0,2 at the peak.
  • the yield strength at the peak is generally satisfactorily evaluated by varying the residence time between 10 and 70h for a temperature of 155 ° C after a pull of 3.5%.
  • the clearly underdeveloped states correspond to compromises between the static mechanical resistance (R p0.2 , R m ) and the damage tolerance (toughness, resistance to propagation cracks in fatigue) more interesting than peak and a fortiori that beyond the peak.
  • the present inventors have found that a state under income but close to the peak makes it possible both to obtain a compromise between static mechanical resistance and damage tolerance of interest, but also to improve the performance in terms of corrosion resistance and thermal stability.
  • the use of an under-income state close to the peak makes it possible to improve the robustness of the industrial process: a variation in the income conditions leads to a small variation in the properties obtained.
  • the products according to the invention can advantageously be used in structural elements, in particular aircraft.
  • the use of a structural element incorporating at least one product according to the invention or manufactured from such a product is advantageous, in particular for aeronautical construction.
  • the products according to the invention are particularly advantageous for the production of products machined in the mass, such as in particular intrados or extrados elements whose skin and stiffeners come from the same starting material, spars and ribs, as well as any other use where the present properties could be advantageous
  • the plates were homogenized at about 500 ° C for about 12 hours and then cut and scalped to obtain slugs of size 400 x 335 x 90 mm.
  • the slabs were hot rolled to obtain sheets having a thickness of 20 mm.
  • the sheets were dissolved at 505 ⁇ 2 ° C for 1 h, quenched with water at 75 ° C to obtain a cooling rate of about 18 ° C / sec and thus simulate properties obtained at mid-thickness of sheet of thickness 80 mm.
  • the sheets were then trimmed with a permanent elongation of 3.5%.
  • the sheets were tempered between 10 and 50 hours at 155 ° C. Samples were taken at mid-thickness to measure static mechanical tensile properties as well as toughness K Q.
  • the K Q values obtained from this type of specimen are lower than those obtained from specimens having a greater thickness and width.
  • the products according to the invention have a significantly improved property compromise compared to the reference products.
  • the plates were homogenized and then scalped. After homogenization, the plates were hot-rolled to obtain sheets having a thickness of 50 mm. The sheets were dissolved in cold water and triturated with a permanent elongation of between 3.5% and 4.5%
  • points 8, 9 and 10 have been added to FIG. 2 (slope P N between 0 and 3), although they relate to specimens of different geometry for the measurement of K Q (K 1C ) in order to facilitate the comparison between the invention and the prior art. It is thus confirmed that the products according to the invention have a compromise of significantly improved properties compared to the prior art.
  • the plates were homogenized at about 500 ° C for about 12 hours and then cut and scalped to obtain slugs of size 400 x 335 x 90 mm.
  • the slabs were hot rolled to obtain sheets having a thickness of 20 mm.
  • the sheets were dissolved at 505 +/- 2 ° C for 1h and quenched with cold water. The sheets were then trimmed with a permanent elongation of 3.5%.
  • the products according to the invention have a significantly improved property compromise compared to the reference samples.
  • Alloy plates 12 transformed by the method described in Example 3 up to the excluded revenue stage were tempered at 155 ° C or 143 ° C for increasing times indicated in Table 7. After 34h at 143 ° C and 40h at 155 ° C, the aging was 1000 hours at 85 ° C. Samples were taken at mid-thickness to measure static mechanical tensile characteristics before and after aging.

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Claims (14)

  1. Kneterzeugnis wie ein Strangpress-, Walz- und/oder Schmiedeerzeugnis, aus einer Legierung auf Basis von Aluminium mit (in Gew.-%):
    Cu: 3,2 - 3,7;
    Li: 0,8 - 1,3;
    Mg: 0,6 - 1,0;
    Zr: 0,05 - 0,18;
    Ag: 0,0 - 0,5;
    Mn: 0,0 - 0,5;
    Fe + Si ≤ 0,20;
    Zn ≤ 0,15;
    mindestens einem Element unter
    Ti: 0,01 - 0,15;
    Sc: 0,05 - 0,3;
    Cr: 0,05 - 0,3;
    Hf: 0,05-0,5;
    weitere Elemente jeweils ≤ 0,05 und insgesamt ≤ 0,15, Rest Aluminium.
  2. Erzeugnis nach Anspruch 1, bei dem der Lithium-Gehalt zwischen 0,9 und 1,2 Gew.-% liegt.
  3. Erzeugnis nach irgendeinem der Ansprüche 1 bis 2, bei dem der Magnesium-Gehalt zwischen 0,65 und 1,0 Gew.-% und vorzugsweise zwischen 0,7 und 0,9 Gew.-% liegt.
  4. Erzeugnis nach irgendeinem der Ansprüche 1 bis 3, bei dem der Mangan-Gehalt zwischen 0,2 und 0,4 Gew.-% liegt.
  5. Erzeugnis nach irgendeinem der Ansprüche 1 bis 4, dessen Dicke mindestens 30 mm und vorzugsweise mindestens 50 mm beträgt.
  6. Erzeugnis nach Anspruch 5 in einem gewalzten, lösungsgeglühten, abgeschreckten und ausgelagerten Zustand, derart, dass eine nahezu maximale Streckgrenze erreicht ist, welches Erzeugnis in halber Dicke mindestens eines der folgenden Merkmalspaare bei Dicken zwischen 30 und 100 mm aufweist:
    (i) bei Dicken von 30 bis 60 mm, in halber Dicke, eine Streckgrenze Rp0,2(L) ≥ 525 MPa und vorzugsweise Rp0,2(L) ≥ 545 MPa und eine Bruchzähigkeit KIC(L-T) ≥ 38 MPa√m und vorzugsweise KIC(L-T) ≥ 43 MPa√m,
    (ii) bei Dicken von 60 bis 100 mm, in halber Dicke, eine Streckgrenze Rp0,2(L) ≥ 515 MPa und vorzugsweise Rp0,2(L) ≥ 535 MPa und eine Bruchzähigkeit KIC(L-T) ≥ 35 MPa√m und vorzugsweise KIC(L-T) ≥ 40 MPa√m,
    (iii) bei Dicken von 100 bis 130 mm, in halber Dicke, eine Streckgrenze Rp0,2(L) ≥ 505 MPa und vorzugsweise Rp0,2(L) ≥ 525 MPa und eine Bruchzähigkeit KIC(L-T) ≥ 32 MPa√m und vorzugsweise KIC (L-T) ≥ 37 MPa√m,
    (iv) bei Dicken von 30 bis 100 mm, in halber Dicke, eine Streckgrenze Rp0,2(L) ausgedrückt in MPa und eine Bruchzähigkeit KIC (L-T) ausgedrückt in MPa√m, so dass KIC (L-T) ≥ - 0.217 Rp0,2(L) + 157 und vorzugsweise KIC (L-T) ≥ - 0.217 Rp0,2(L) + 163 und größer als 35 MPa√m,
    (v) nach 1000 Stunden Auslagerung bei 85°C eine Streckgrenze Rp0,2(L) und Bruchdehnung A%(L), die mit der Streckgrenze Rp0,2(L) und Bruchdehnung A%(L) vor Auslagerung eine Differenz von weniger als 10 % und vorzugsweise weniger als 5 % aufweisen.
  7. Erzeugnis nach irgendeinem der Ansprüche 1 bis 4 in einem gewalzten, lösungsgeglühten, abgeschreckten und ausgelagerten Zustand, derart, dass eine nahezu maximale Streckgrenze erreicht ist, welches Erzeugnis in halber Dicke mindestens eines der folgenden Merkmalspaare bei Dicken zwischen 10 und 30 mm aufweist:
    (i) eine Streckgrenze Rp0,2(L) ≥ 525 MPa und vorzugsweise Rp0,2(L) ≥ 545 MPa und eine Bruchzähigkeit KIC (L-T) ≥ 40 MPa√m und vorzugsweise KIC (L-T) ≥ 45 MPa√m,
    (ii) eine Streckgrenze Rp0,2(L) ausgedrückt in MPa und eine Bruchzähigkeit KIC (L-T) ausgedrückt in MPa√m, so dass KIC (L-T) ≥ - 0.4 Rp0,2(L) + 265 und vorzugsweise KIC (L-T) ≥ - 0.4 Rp0,2(L) + 270 und größer als 45 MPa√m,
    (iii) nach 1000 Stunden Auslagerung bei 85 °C eine Streckgrenze Rp0,2(L) und Bruchdehnung A%(L), die mit der Streckgrenze Rp0,2(L) und Bruchdehnung A%(L) vor Auslagerung eine Differenz von weniger als 10 % und vorzugsweise weniger als 5 % aufweisen.
  8. Verfahren zur Herstellung eines Strangpress-, Walz- und/oder Schmiedeerzeugnisses aus Aluminiumlegierung, bei dem
    a) ein Flüssigmetallbad auf Basis von Aluminium hergestellt wird, enthaltend 3,2 - 3,7 Gew.-% Cu, 0,8 - 1,3 Gew.-% Li, 0,6 - 1,0 Gew.-% Mg, 0,05 - 0,18 Gew.-% Zr, 0,0 - 0,5 Gew.-% Ag, 0,0 - 0,5 Gew.-% Mn, höchstens 0,20 Gew.-% Fe + Si, höchstens 0,15 Gew.-% Zn, mindestens ein Element ausgewählt unter Cr, Sc, Hf und Ti, wobei die Menge des Elementes, falls gewählt, 0,05 bis 0,3 Gew.-% für Cr und für Sc, 0,05 - 0,5 Gew.-% für Hf und 0,01 bis 0,15 Gew.-% für Ti beträgt, weitere Elemente jeweils höchstens 0,05 Gew.-% und insgesamt 0,15 Gew.-%, Rest Aluminium;
    b) aus dem Flüssigmetallbad eine Rohform gegossen wird;
    c) die Rohform bei einer Temperatur zwischen 450°C und 550°C und vorzugsweise zwischen 480°C und 530°C für eine Dauer von 5 bis 60 Stunden homogenisiert wird;
    d) die Rohform warm und wahlweise kalt zu einem Strangpress-, Walz-und/oder Schmiedeerzeugnis umgeformt wird;
    e) das Erzeugnis zwischen 490 und 530°C für 15 Minuten bis 8 Stunden lösungsgeglüht und abgeschreckt wird;
    f) das Erzeugnis kontrolliert gereckt wird, mit einer bleibenden Verformung von 1 bis 6 % und vorzugsweise mindestens 2 %;
    g) das Erzeugnis einer Auslagerungsbehandlung unterzogen wird, umfassend eine Erhitzung auf eine Temperatur zwischen 130 und 170°C für 5 bis 100 Stunden und vorzugsweise 10 bis 40 Stunden, derart, dass eine nahezu maximale Streckgrenze erreicht wird, wobei die Auslagerung unter den gleichen Zeit- und Temperaturverhältnissen wie ein Punkt N der Auslagerungskurve bei 155°C durchgeführt wird, so dass die die Auslagerungskurve in diesem Punkt berührende Tangente eine Steigung PN hat, ausgedrückt in MPa/h, die so ist, dass 0 < PN ≤ 3.
  9. Verfahren nach Anspruch 8, bei dem das Warm- und wahlweise Kaltumformen bis auf eine Dicke von mindestens 30 mm durchgeführt wird.
  10. Verfahren nach Anspruch 8 oder Anspruch 9, bei dem das kontrollierte Recken mit einer bleibenden Verformung von 3 bis 5 % durchgeführt wird.
  11. Verfahren nach irgendeinem der Ansprüche 8 bis 10, bei dem 0,2 < PN ≤ 2,5.
  12. Strukturelement umfassend ein Erzeugnis nach irgendeinem der Ansprüche 1 bis 7.
  13. Verwendung eines Strukturelementes nach Anspruch 12 für den Flugzeugbau.
  14. Verwendung nach Anspruch 13, bei der das Strukturelement ein Flügelunterseitenelement bzw. Flügeloberseitenelement ist, dessen Außenhaut und Versteifungen aus demselben Ausgangsprodukt stammen, einem Längsträger bzw. einer Rippe.
EP10734173.7A 2009-06-25 2010-06-22 Aluminium-kupfer-lithium-legierung mit verbesserten mechanische beständigkeit und zähigkeit Active EP2449142B1 (de)

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US22024909P 2009-06-25 2009-06-25
FR0903096A FR2947282B1 (fr) 2009-06-25 2009-06-25 Alliage aluminium cuivre lithium a resistance mecanique et tenacite ameliorees
PCT/FR2010/000455 WO2010149873A1 (fr) 2009-06-25 2010-06-22 Alliage aluminium cuivre lithium a resistance mecanique et tenacite ameliorees

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FR3026747B1 (fr) 2014-10-03 2016-11-04 Constellium France Toles isotropes en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselages d'avion
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EP3072984B2 (de) 2015-03-27 2020-05-06 Otto Fuchs KG Al-cu-mg-li-legierung sowie daraus hergestelltes legierungsprodukt
EP3072985B2 (de) 2015-03-27 2020-08-26 Otto Fuchs KG Ag-freie al-cu-mg-li-legierung
FR3044682B1 (fr) * 2015-12-04 2018-01-12 Constellium Issoire Alliage aluminium cuivre lithium a resistance mecanique et tenacite ameliorees
WO2018037390A2 (en) 2016-08-26 2018-03-01 Shape Corp. Warm forming process and apparatus for transverse bending of an extruded aluminum beam to warm form a vehicle structural component
MX2019004494A (es) 2016-10-24 2019-12-18 Shape Corp Metodo de formacion y procesamiento termico de aleacion de aluminio de multiples etapas para la produccion de componentes de vehiculo.
US20190233921A1 (en) * 2018-02-01 2019-08-01 Kaiser Aluminum Fabricated Products, Llc Low Cost, Low Density, Substantially Ag-Free and Zn-Free Aluminum-Lithium Plate Alloy for Aerospace Application
FR3080861B1 (fr) * 2018-05-02 2021-03-19 Constellium Issoire Procede de fabrication d'un alliage aluminium cuivre lithium a resistance en compression et tenacite ameliorees
CN108754263A (zh) * 2018-07-30 2018-11-06 东北轻合金有限责任公司 一种高强度航天用铝锂合金型材及其制备方法
FR3088935B1 (fr) 2018-11-28 2021-06-04 Irt Antoine De Saint Exupery Procédé de stabilisation des propriétés d’une pièce en alliage d’aluminium, pièce obtenue par un tel procédé et son utilisation dans un aéronef
CN110512125B (zh) * 2019-08-30 2020-09-22 中国航发北京航空材料研究院 一种用于增材制造的直径铝锂合金丝材的制备方法
CN111304503A (zh) * 2020-03-12 2020-06-19 江苏豪然喷射成形合金有限公司 一种航空机轮用低密度耐损伤铝锂合金及其制备方法
CN115821132A (zh) * 2022-11-25 2023-03-21 江苏徐工工程机械研究院有限公司 一种铝合金及其制备方法

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US20110209801A2 (en) 2011-09-01
CA2765382C (fr) 2018-08-07
FR2947282B1 (fr) 2011-08-05
CN102459671B (zh) 2014-03-19
US11111562B2 (en) 2021-09-07
FR2947282A1 (fr) 2010-12-31
DE10734173T1 (de) 2012-12-06
WO2010149873A1 (fr) 2010-12-29
DE10734173T8 (de) 2013-04-25
BRPI1011757A2 (pt) 2018-03-06
EP2449142A1 (de) 2012-05-09
CA2765382A1 (fr) 2010-12-29
CN102459671A (zh) 2012-05-16
BRPI1011757B1 (pt) 2019-04-09
US20110030856A1 (en) 2011-02-10

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