EP3411508B1 - Dicke bleche aus al- cu - li legierung mit verbesserten ermüdungseigenschaften - Google Patents

Dicke bleche aus al- cu - li legierung mit verbesserten ermüdungseigenschaften Download PDF

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EP3411508B1
EP3411508B1 EP17707940.7A EP17707940A EP3411508B1 EP 3411508 B1 EP3411508 B1 EP 3411508B1 EP 17707940 A EP17707940 A EP 17707940A EP 3411508 B1 EP3411508 B1 EP 3411508B1
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EP3411508A1 (de
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Jean-Christophe Ehrstrom
Carla DA FONSECA BARBATTI
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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

Definitions

  • the present invention generally relates to thick sheets of Al-Cu-Li alloy and in particular to such products used in the aeronautical and aerospace industry.
  • Products, in particular thick rolled products, the thickness of which is typically at least 50 mm, made of aluminum alloy are developed to produce by cutting, surfacing or machining in the mass of high resistance parts intended in particular for the aeronautical industry. , the aerospace industry or mechanical engineering.
  • Aluminum alloys containing lithium are very interesting in this regard, 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.
  • the patent US 7,229,509 describes 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, having in particular a toughness K 1C (L)> 37.4 MPa ⁇ m for a limit elasticity R p0.2 (L)> 448.2 MPa (products thicker than 76.2 mm) and in particular a toughness 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).
  • the AA2050 alloy includes (% 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 the alloy 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 mechanical strength and toughness, especially for thick rolled products and are selected in certain aircraft.
  • the interval between two operations of control of the structure depends on the speed and the way in which the cracks propagate in the materials used for the structure and it is advantageous to use products for which the cracks spread slowly and predictably.
  • the improvement of the propagation properties of fatigue cracks therefore relates in particular to the speed of propagation and the direction of propagation.
  • the patent application WO2009103899 thus describes an essentially non-recrystallized laminated product comprising in% by weight: 2.2 to 3.9% by weight of Cu, 0.7 to 2.1% by weight of Li; 0.2 to 0.8% by weight of Mg; 0.2 to 0.5% by weight of Mn; 0.04 to 0.18% by weight of Zr; less than 0.05% by weight of Zn and, optionally, 0.1 to 0.5% by weight of Ag, the remainder being aluminum and unavoidable impurities, having a low propensity for crack bifurcation during a fatigue test in the direction of LS.
  • Bifurcation of cracks, crack deflection, rotation of cracks or branching of cracks are terms used to express the propensity for the propagation of a crack to deviate from the expected plane of fracture perpendicular to the load applied during a stress test. tiredness or tenacity.
  • the crack bifurcation occurs on the microscopic scale ( ⁇ 100 ⁇ m), on the mesoscopic scale (100-1000 ⁇ m) or on the macroscopic scale (> 1 mm), but it is only considered harmful if the direction of the crack remains stable after bifurcation (macroscopic scale).
  • the term crack bifurcation is used here for the macroscopic bifurcation of cracks during fatigue or toughness tests in the LS direction, from the S direction to the L direction which occurs for rolled products whose thickness is at least minus 50 mm.
  • a first object of the invention is a laminated product with a thickness of at least 50 mm made of aluminum alloy comprising in% by weight 2.2 to 3.9% of Cu, 0.7 to 1.8% of Li, 0.1 to 0.8% Mg, 0.1 to 0.6% Mn; 0.01 to 0.15% of Ti, at least one element chosen from Zn and Ag, the quantity of said element if it is chosen being 0.2 to 0.8% for Zn and 0.1 to 0.5% for Ag, optionally at least one element chosen from Zr, Cr, Sc, Hf, and V, the amount of said element if it is chosen being 0.04 to 0.18% for Zr, 0.05 to 0.3% for Cr and for Sc, 0.05 to 0.5% for Hf and for V, less than 0.1% of Fe, less than 0.1% of Si remains aluminum and unavoidable impurities, of a content less than 0 , 05% each and 0.15% in total; characterized in that its granular structure is mainly recrystallized between 1 ⁇ 4 and 1 ⁇ 2 thickness.
  • Yet another object of the invention is the use of a sheet according to the invention for the production of an aircraft wing spar or an aircraft wing rib.
  • the static mechanical characteristics in other words the tensile strength R m , the conventional yield strength at 0.2% elongation R p0.2 and the elongation at break A, are determined by a tensile test according to standard EN 10002-1, the sampling and the direction of the test being defined by standard EN 485-1. Unless otherwise stated, the definitions of standard EN 12258-1 apply.
  • the cracking speed (da / dN) is determined according to ASTM E 647.
  • the stress intensity factor (K 1C ) is determined according to standard ASTM E 399.
  • the present inventors have surprisingly found that laminated products with a thickness of at least 50 mm made of an aluminum - copper - lithium - magnesium - manganese alloy have advantageous properties when the granular structure is mainly recrystallized between 1 ⁇ 4 and 1 ⁇ 2 thickness.
  • the resistance to fatigue crack propagation is improved while the compromise between mechanical strength and toughness is not significantly degraded.
  • granular structure predominantly recrystallized between 1 ⁇ 4 and 1 ⁇ 2 thickness is meant a granular structure whose recrystallization rate is at least 50% between 1 ⁇ 4 and 1 ⁇ 2 thickness, that is to say of which at least 50% of the grains between 1 ⁇ 4 and 1 ⁇ 2 thickness are recrystallized.
  • the recrystallization rate between 1 ⁇ 4 and 1 ⁇ 2 thickness is at least 55%.
  • the thickness of the products according to the invention is between 80 and 130 mm.
  • the products according to the invention have a copper content of between 2.2 and 3.9% by weight.
  • the copper content is at least 2.8% by weight and preferably at least 3.2% by weight.
  • the maximum copper content is 3.8% by weight.
  • the products according to the invention have a lithium content of between 0.7 and 1.8% by weight.
  • the lithium content is at least 0.8% by weight and preferably at least 0.9% by weight.
  • the maximum lithium content is 1.5% by weight, preferably 1.1% and preferably 0.95% by weight.
  • the products according to the invention have a magnesium content of between 0.1 and 0.8% by weight.
  • the magnesium content is at least 0.2% by weight and preferably at least 0.3% by weight.
  • the maximum magnesium content is 0.7% by weight and preferably 0.6% by weight.
  • the products according to the invention have a manganese content of between 0.1 and 0.6% by weight.
  • the manganese content is at least 0.2% by weight and preferably at least 0.3% by weight.
  • the maximum manganese content is 0.5% by weight and preferably 0.4% by weight.
  • the products according to the invention contain at least one element chosen from Zn and Ag, the amount of said element if it is chosen being 0.2 to 0.8% for Zn and 0.1 to 0.5% for Ag, these elements being particularly useful for hardening of the alloy. Preferably, only one of these elements is added, the second being maintained at a content of less than 0.05% by weight.
  • the products according to the invention contain at least one element chosen from Zr, Cr, Sc, Hf, and V, the amount of said element if it is chosen being 0.04 to 0.18% and preferably 0.04 to 0.15% for Zr, 0.05 to 0.3% for Cr and for Sc, 0.05 to 0.5% for Hf and for V.
  • These elements contribute to the control of the granular structure.
  • the granular structure mainly recrystallized according to the invention is obtained by means of a selection of the processing parameters, in particular the conditions for homogenization and hot rolling.
  • the sum of the content of the elements Zr, Cr, Sc, Hf, and V is preferably at least 0.08% by weight.
  • the Zr content in this first embodiment is from 0.08 to 0.10% by weight.
  • the mainly recrystallized granular structure according to the invention is obtained by limiting the content of elements acting on the control of the granular structure.
  • the sum of the content of the elements Zr, Cr, Sc, Hf, and V is less than 0.08% by weight.
  • the Zr content is from 0.04 to 0.07% by weight and preferably 0.05 to 0.07% by weight.
  • there is no addition of Zr the Zr content is less than 0.05% by weight, preferably less than 0.04% by weight and more preferably still less at 0.02% by weight. It is also possible in certain cases to combine these two embodiments.
  • the products according to the invention also have advantageous properties in terms of propensity to crack bifurcation.
  • the macroscopic bifurcation of cracks during fatigue tests in the LS direction, from the S direction to the L direction was evaluated in two ways.
  • the figure 5c shows an example of evaluation of this distance: when the crack deviates, it does not immediately join the direction L and one can thus measure the distance d.
  • One considers that the crack is in direction S or direction L when it does not deviate from this direction by more than 10 °.
  • the process for manufacturing a mainly recrystallized granular sheet with a thickness of at least 50 mm comprises the steps of casting, homogenization, hot rolling, dissolution, quenching, controlled traction and tempering.
  • An alloy containing controlled quantities according to the invention of alloying elements is cast in the form of a plate.
  • the plate is homogenized at a temperature of at least 490 ° C.
  • Preferably the homogenization time is at least 12 hours. Homogenization can be carried out in one or more stages.
  • the homogenization comprises at least one step whose temperature is at least 520 ° C and preferably at least 530 ° C, the period during which the temperature is above 520 ° C being at least 20 hours and preferably at least 30 hours.
  • a hot rolling step is carried out after reheating if necessary to obtain sheets whose thickness is at least 50 mm.
  • the hot rolling outlet temperature is less than 390 ° C, preferably less than 380 ° C.
  • the combination in particular of the conditions of the homogenization step and of the hot rolling step of the first embodiment makes it possible to obtain a final structure after mostly recrystallized tempering, in particular for products whose sum of the content of the elements Zr , Cr, Sc, Hf, and V is at least 0.08% by weight.
  • the inventors have found that the conditions according to this first embodiment make it possible to reduce the propensity for crack bifurcation.
  • the sum of the content of the elements Zr, Cr, Sc, Hf, and V is less than 0.08% by weight and the outlet temperature from hot rolling is preferably at least 400 ° C and preferably at least 420 ° C.
  • the sheets are dissolved by heating between 490 and 540 ° C, preferably for 15 minutes to 4 hours, the dissolution parameters depending on the thickness of the product.
  • Cold water quenching is carried out after dissolution.
  • the product then undergoes controlled traction with a permanent deformation of between 1% and 7% and preferably between 2% and 6%.
  • Tempering is carried out at a temperature between 130 ° C and 170 ° C and preferably at a temperature between 140 ° C and 160 ° C for a period of 5 to 60 hours, which results in a T8 state. In certain cases, and in particular for certain preferred compositions, the tempering is carried out preferably between 140 and 160 ° C. for 12 to 50 hours.
  • the products according to the invention are advantageously used in aeronautical construction.
  • the use of the products according to the invention for producing an aircraft wing spar or an aircraft wing rib is particularly advantageous.
  • the use of the products according to the invention for the production of an aircraft wing spar is preferred, advantageously for the lower part, that is to say in connection with the lower surface of the wing, d '' a welded beam.
  • Plate A was homogenized in two stages of 36 hours at 504 ° C and then 48 hours at 530 ° C. Plates B and C were homogenized in two steps of 8 hours at 496 ° C and then 34 hours at 530 ° C. Plate D was homogenized for 12 hours at 505 ° C. Plate E was homogenized in two stages 8 h at 500 ° C and then 36 hours at 527 ° C.
  • Plate A was hot rolled to a 100 mm thick sheet, the hot rolling inlet temperature was 410 ° C and the hot rolling outlet temperature was 361 ° C.
  • Plate B was hot rolled to a 102 mm thick sheet, the hot rolling inlet temperature was 406 ° C and the hot rolling outlet temperature was 350 ° C.
  • Plate C was hot rolled to a 102 mm thick sheet, the hot rolling inlet temperature was 410 ° C and the hot rolling outlet temperature was 360 ° C.
  • Plate D was hot rolled to a 100 mm thick sheet, the hot rolling inlet temperature was 505 ° C and the hot rolling outlet temperature was 520 ° C.
  • Plate E was hot rolled to a 100 mm thick sheet, the hot rolling inlet temperature was 481 ° C and the hot rolling outlet temperature was 460 ° C.
  • the sheets thus obtained were dissolved for 2 hours at 525 ° C and quenched with cold water.
  • the sheets thus dissolved and quenched were pulled in a controlled manner, with a permanent elongation of 4% and underwent an 18 hour tempering at 155 ° C (A, B, C and E) or 24 h at 155 ° C (D).
  • Fatigue crack propagation tests on L-S test pieces were carried out on samples from sheets C and E. The tests were carried out according to standard ASTM E647. These tests are carried out on CCT specimens, with central crack, of width 100 mm and thickness 6.35 mm.
  • the marks 84A2 and A2, B2 and C2 were tested at 3000 N of maximum force rather than 4000 N.
  • the conditions make it possible during the test to cover the range of ⁇ K ranging from 10 at 40 MPa ⁇ m, where ⁇ K is the variation of the stress intensity factor in a charge cycle.
  • the figures 3a and 3b show, respectively, the samples from sheets A and D after the fatigue test.
  • the samples from sheet A according to the invention exhibit a progressive crack bifurcation with in 4 out of 6 cases (C1, C2, B1, A2) a rupture by the rear face of the test piece.
  • the distance d over which the crack is neither in the initial S direction, nor in the L direction is at least 15 mm for all samples from sheet A, because in none of the cases does the crack join the direction L.
  • the figure 4 shows the propagation speed results measured by the crack opening method, during tests on CT specimens. These tests also show that the propagation speed is significantly slower, in the LS direction, for sheet A according to the invention.
  • the mainly recrystallized product according to the invention has a particularly advantageous propagation of fatigue cracks.
  • Samples of format 14 mm x 50 mm x 56 mm were machined at half-width (L / 2) and quarter-thickness (T / 4) of the casting plates.
  • the figure 6 presents such samples of thickness C 14 mm and width B 50 mm.
  • the samples were homogenized in two stages of 5 hours at 505 ° C and then 12 hours at 525 ° C.
  • the samples were hot deformed by double punching using a "Servotest" ® type machine, the temperature and the speed of deformation were 400 ° C and 1s -1 respectively .
  • the figure 6 illustrates such a deformation by double-punching.
  • Such a deformation is representative of an industrial deformation by hot rolling of a foundry plate of approximately 400 mm to a final thickness of approximately 100 mm.
  • the samples F and G are mainly recrystallized.

Claims (10)

  1. Walzprodukt mit einer Dicke von mindestens 50 mm aus einer Aluminiumlegierung aufweisend - in Gew.-% - 2,2 bis 3,9 % Cu, 0,7 bis 1,8 % Li, 0,1 bis 0,8 % Mg, 0,1 bis 0,6 % Mn; 0,01 bis 0,15% Ti, mindestens ein Element ausgewählt aus Zn und Ag, wobei die Menge des Elements, falls ausgewählt, 0,2 bis 0,8 % für Zn und 0,1 bis 0,5 % für Ag beträgt, optional mindestens ein Element ausgewählt aus Zr, Cr, Sc, Hf und V, wobei die Menge des Elements, falls ausgewählt, 0,04 bis 0,18 % für Zr, 0,05 bis 0,3 % für Cr und für Sc, 0,05 bis 0,5 % für Hf und für V beträgt, weniger als 0,1 % Fe, weniger als 0,1% Si, Rest Aluminium und die unvermeidbaren Verunreinigungen mit einem Gehalt von jeweils weniger als 0,05 % und insgesamt 0,15 %; dadurch gekennzeichnet, dass sein Korngefüge überwiegend zwischen einem Viertel und der halben Dicke rekristallisiert ist.
  2. Walzprodukt nach Anspruch 1, dadurch gekennzeichnet, dass seine Dicke zwischen 80 und 130 mm beträgt.
  3. Walzprodukt nach Anspruch 1 oder Anspruch 2, dadurch gekennzeichnet, dass der maximale Gehalt an Li 1,5 Gew.-% beträgt.
  4. Walzprodukt nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die Summe des Gehalts an den Elementen Zr, Cr, Sc, Hf und V weniger als 0,08 Gew.-% beträgt.
  5. Walzprodukt nach einem der Ansprüche 1 bis 4, aufweisend
    (i) bei einer Dicke zwischen 50 und 75 mm, in 1/4 Dicke, eine Streckgrenze Rp0,2(TL) ≥ 435 MPa und vorzugsweise Rp0,2(TL) ≥ 455 MPa und eine Bruchzähigkeit KIC (T-L) ≥ 28 MPa√m und vorteilhaft eine solche Bruchzähigkeit, dass KIC (T-L) ≥ 30 MPa√m,
    (ii) bei einer Dicke zwischen 76 und 102 mm, in 1/4 Dicke, eine Streckgrenze Rp0,2(TL) ≥ 435 MPa und vorzugsweise Rp0,2(TL) ≥ 455 MPa und eine Bruchzähigkeit KIC (T-L) ≥ 25 MPa√m und vorteilhaft eine solche Bruchzähigkeit, dass KIC (T-L) ≥ 27 MPa√m,
    (iii) bei einer Dicke zwischen 103 und 130 mm, in 1/4 Dicke, eine Streckgrenze Rp0,2(TL) ≥ 428 MPa und vorzugsweise Rp0,2(TL) ≥ 448 MPa und eine Bruchzähigkeit KIC (T-L) ≥ 23 MPa√m und vorteilhaft eine solche Bruchzähigkeit, dass KIC (T-L) ≥ 25 MPa√m,
    (iv) bei einer Dicke größer als 130 mm, in 1/4 Dicke, eine Streckgrenze Rp0,2(TL) ≥ 428 MPa und vorzugsweise Rp0,2(TL) ≥ 448 MPa und eine Bruchzähigkeit KIC (T- L) ≥ 21 MPa√m und vorteilhaft eine solche Bruchzähigkeit, dass KIC (T-L) ≥ 23 MPa√m,
    und aufweisend eine Rissausbreitungsgeschwindigkeit gemessen nach ASTM E647 an in halber Dicke in L-S-Richtung entnommenen CCT-Proben mit zentralem Riss von 100 mm Breite und 6,35 mm Dicke von weniger als 10-4 mm/Zyklus bei ΔK = 20 MPa√m.
  6. Walzprodukt nach irgendeinem der Ansprüche 1 bis 5 mit geringer Neigung zur Rissverzweigung, dadurch gekennzeichnet, dass der Bruch bei einem Ermüdungstests in L-S-Richtung bei einer maximalen Belastung von mindestens 3000 N, R = 0,1, an einem Satz von mindestens 6 CT-Proben von 10 mm Dicke und 50 mm Gesamtbreite überwiegend über die Rückseite (1) erfolgt.
  7. Walzprodukt nach irgendeinem der Ansprüche 1 bis 6 mit geringer Neigung zur Rissverzweigung, dadurch gekennzeichnet, dass bei einem Ermüdungstest in L-S-Richtung bei einer maximalen Belastung von mindestens 3000 N, R = 0,1, an einer CT-Probe von 10 mm Dicke und 50 mm Gesamtbreite die Strecke d, auf der sich der Riss weder in der ursprünglichen Richtung S noch in der Richtung L erstreckt, mindestens 5 mm und vorzugsweise mindestens 10 mm beträgt.
  8. Verfahren zur Herstellung eines Blechs nach irgendeinem der Ansprüche 1 bis 7, umfassend die Schritte:
    a) Gießen einer Platte aus einer Aluminiumlegierung aufweisend - in Gew.-% - 2,2 bis 3,9 % Cu, 0,7 bis 1,8 % Li, 0,1 bis 0,8 % Mg, 0,1 bis 0,6 % Mn; 0,01 bis 0,15% Ti, mindestens ein Element ausgewählt aus Zn und Ag, wobei die Menge des Elements, falls ausgewählt, 0,2 bis 0,8 % für Zn und 0,1 bis 0,5 % für Ag beträgt, optional mindestens ein Element ausgewählt aus Zr, Cr, Sc, Hf und V, wobei die Menge des Elements, falls ausgewählt, 0,04 bis 0 18 % für Zr, 0,05 bis 0,3 % für Cr und für Sc, 0,05 bis 0,5 % für Hf und für V beträgt, weniger als 0,1 % Fe, weniger als 0,1% Si, Rest Aluminium und die unvermeidbaren Verunreinigungen mit einem Gehalt von jeweils weniger als 0,05 % und insgesamt 0,15;
    b) Homogenisieren der Platte bei einer Temperatur von mindestens 490°C,
    c) Warmwalzen der Platte, um ein Blech von mindestens 50 mm Dicke zu erhalten,
    d) Lösungsglühen bei 490°C bis 540°C,
    e) Abschrecken mit kaltem Wasser,
    f) kontrolliertes Recken des Blechs mit einer bleibenden Verformung von 1 bis 7%,
    g) Auslagern des Blechs durch Erwärmen bei 130°C bis 170°C für 5 bis 60 Stunden,
    dadurch gekennzeichnet, dass die Summe der Gehalte an den Elementen Zr, Cr, Sc, Hf und V kleiner als 0,08 Gew.-% ist und/oder dass in Schritt b) die Homogenisierung mindestens eine Stufe umfasst, bei der die Temperatur mindestens 520°C beträgt, wobei der Zeitraum, in dem die Temperatur über 520 °C liegt, mindestens 20 Stunden beträgt, und in Schritt c) die Austrittstemperatur des Warmwalzvorgangs unter 390°C liegt.
  9. Verwendung eines Blechs nach irgendeinem der Ansprüche 1 bis 7 zur Herstellung eines Flugzeugflügellängsträgers oder einer Flugzeugflügelrippe.
  10. Verwendung nach Anspruch 9 für den unteren Teil eines geschweißten Längsträgers.
EP17707940.7A 2016-02-03 2017-02-03 Dicke bleche aus al- cu - li legierung mit verbesserten ermüdungseigenschaften Active EP3411508B1 (de)

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FR1650850A FR3047253B1 (fr) 2016-02-03 2016-02-03 Toles epaisses en alliage al - cu - li a proprietes en fatigue ameliorees
PCT/FR2017/050255 WO2017134405A1 (fr) 2016-02-03 2017-02-03 Tôles épaisses en alliage al–cu–li à propriétés en fatigue améliorées

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EP3411508B1 true EP3411508B1 (de) 2020-04-08

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US (2) US20190040508A1 (de)
EP (1) EP3411508B1 (de)
CN (1) CN108603253B (de)
BR (1) BR112018014770B1 (de)
CA (1) CA3012956C (de)
FR (1) FR3047253B1 (de)
WO (1) WO2017134405A1 (de)

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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
CN113943880A (zh) * 2021-10-15 2022-01-18 西南铝业（集团）有限责任公司 一种Al-Cu-Li-Mg-V-Zr-Sc-Ag合金及其制备方法
CN115433888B (zh) * 2022-08-18 2023-06-13 哈尔滨工业大学（深圳） 一种铝锂合金中厚板的形变热处理方法

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CN108603253B (zh) 2021-03-19
EP3411508A1 (de) 2018-12-12
BR112018014770B1 (pt) 2022-11-16
FR3047253A1 (fr) 2017-08-04
US20190040508A1 (en) 2019-02-07
CA3012956A1 (fr) 2017-08-10
US20240035138A1 (en) 2024-02-01
FR3047253B1 (fr) 2018-01-12
BR112018014770A2 (pt) 2018-12-18
WO2017134405A1 (fr) 2017-08-10
CN108603253A (zh) 2018-09-28

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