EP1544315B1 - Knetprodukt in Form eines gewalzten Bleches und Strukturbauteil für Flugzeug aus Al-Zn-Cu-Mg-Legierung - Google Patents

Knetprodukt in Form eines gewalzten Bleches und Strukturbauteil für Flugzeug aus Al-Zn-Cu-Mg-Legierung Download PDF

Info

Publication number
EP1544315B1
EP1544315B1 EP04356196A EP04356196A EP1544315B1 EP 1544315 B1 EP1544315 B1 EP 1544315B1 EP 04356196 A EP04356196 A EP 04356196A EP 04356196 A EP04356196 A EP 04356196A EP 1544315 B1 EP1544315 B1 EP 1544315B1
Authority
EP
European Patent Office
Prior art keywords
mpa
alloy
anyone
product according
product
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP04356196A
Other languages
English (en)
French (fr)
Other versions
EP1544315A1 (de
Inventor
Bernard Bes
David Dumont
Jean-Christophe Ehrstrom
Timothy Warner
Vic Dangerfield
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Constellium Issoire SAS
Constellium Rolled Products Ravenswood LLC
Original Assignee
Constellium France SAS
Constellium Rolled Products Ravenswood LLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Constellium France SAS, Constellium Rolled Products Ravenswood LLC filed Critical Constellium France SAS
Publication of EP1544315A1 publication Critical patent/EP1544315A1/de
Application granted granted Critical
Publication of EP1544315B1 publication Critical patent/EP1544315B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • 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
    • C22C21/10—Alloys based on aluminium 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
    • 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

Definitions

  • the invention relates to Al-Zn-Cu-Mg alloy rolled products treated by dissolving, quenching, cold working and tempering, and in particular structural elements made from such products and intended for the construction of aircraft. .
  • 7xxx alloys are used for the structural elements (except for the undersides) of the wing.
  • the patent application WO 02/052053 discloses three Al-Zn-Cu-Mg type alloys of composition (a) Zn 7.3 + Cu 1.6; (b) Zn 6.7 + Cu 1.9; (c) Zn 7.4 + Cu 1.9; each of these three alloys also containing Mg 1.5 + Zr 0.11. It also describes thermomechanical treatment processes suitable for the manufacture of structural elements for aircraft.
  • Also known alloy 7040 whose standardized chemical composition is: Zn 5.7 - 6.7 Mg 1.7 - 2.4 Cu 1,5 - 2,3 Zr 0.05 - 0.12 If ⁇ 0.10 Fe ⁇ 0.13 Ti ⁇ 0.06 Mn ⁇ 0.04 other elements ⁇ 0.05 each and ⁇ 0.15 in total.
  • Alloy 7475 is also known whose standardized chemical composition is: Zn 5.2 - 6.2 Mg 1.9-2.6 Cu 1.2-1.9 Cr 0.18-0.25 If ⁇ 0.10 Fe ⁇ 0.12 Ti ⁇ 0.06 Mn ⁇ 0.06 other elements ⁇ 0.05 each and ⁇ 0.15 in total.
  • alloys of the 2xxx series for example alloy 2324 are commonly used.
  • the alloys conventionally used for the fuselage structure elements belong to the 2xxx series, for example the alloy 2024.
  • the object of the present invention is to obtain elements of aircraft structure, and in particular fuselage elements, made of Al-Zn-Cu-Mg alloy, having, compared to the prior art, improved mechanical strength, for comparable damage tolerance and sufficient formability.
  • the subject of the invention is a wrought product as defined in claim 1.
  • the subject of the invention is also a structural element for aircraft construction, in particular an aircraft fuselage element, or an aircraft wing-bottom element, or an integral aircraft structural element, manufactured from a wrought product, and especially from such a rolled or spun product.
  • the static mechanical characteristics ie the ultimate tensile strength R m , the yield strength R p0,2 and the elongation at break A, are determined by a tensile test according to the standard EN 10002-1, the location and direction of specimen collection being defined in EN 485-1.
  • the fatigue strength is determined by a test according to ASTM E 466, and the fatigue crack growth rate (so-called da / dn test) according to ASTM E 647.
  • the curve R is determined according to ASTM standard E 561. From the curve R, the critical stress intensity factor K c is calculated, ie the intensity factor which 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. These two values are calculated for a specimen of the desired shape. K app means the Kco corresponding to the test piece used for the R curve test.
  • the size of the crack at the end of the fatigue pre-cracking step is W / 4 for the test pieces of the type M (T), and W / 2 for CT type specimens, where W is the specimen width as defined in ASTM E 561.
  • spun product includes so-called “stretched” products, i.e., products that are made by spinning followed by stretching.
  • structural element or “structural element” of a mechanical construction 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.
  • integral structure refers to the structure of a portion of an aircraft that has been designed to provide as much continuity as possible over as large a dimension as possible to reduce the number of assembly points mechanical.
  • An integral structure can be manufactured either by machining in the mass, or by using shaped parts obtained for example by spinning, forging or molding, or by welding structural elements made of weldable alloys. This results in structure elements of larger size and in one piece, without mechanical assembly or with a reduced number of mechanical assembly points compared to an assembled structure in which sheets, thin or strong depending on the destination of the structural element (for example: fuselage element or wing element), are fixed, usually by riveting, on stiffeners and / or frames (which can be manufactured by machining from spun or rolled products).
  • the present invention applies to an aluminum alloy containing between 6.7% and 7.3% zinc.
  • the zinc content must be high enough to ensure good mechanical properties, but if it is too high, the sensitivity of the alloy to the quenching increases, which risks, in particular for thick products, to degrade the compromise properties referred.
  • the product is a strong sheet with a thickness greater than 20 mm.
  • the chemical composition of the Al-Zn-Cu-Mg alloy has been chosen so that the Mg / Cu ratio of the alloy which is the subject of the invention is less than 1. Preferably, this ratio is maintained at a value less than 0.9. A value of less than 0.85 or even about 0.8 is preferred.
  • the Applicant has found that a zirconium content of between 0.07 and 0.12% gives access for this composition to Al-Zn-Cu-Mg major elements, to a better compromise between R p0.2 , toughness ( at ambient or cold temperature) and fatigue resistance (in particular speed of propagation of fatigue cracks). Above 0.12%, there is a significant risk of forming Al 3 Zr type primary phases, unless the cooling is sufficiently rapid; in the case of semi-continuous casting, such a sufficient speed can be achieved, especially when casting billets.
  • the Zr content must be less than 0.12%, and the best results have been obtained with a content of between 0.07 and 0.09%.
  • the silicon and iron contents must be maintained each below 0.15%, and preferably below 0.10%, to have good toughness.
  • the iron content does not exceed 0.07%, and the silicon content does not exceed 0.06%.
  • the alloy according to the invention can be cast according to one of the techniques known to those skilled in the art to obtain a raw form, such as a rolling plate.
  • This raw form optionally after scalping, is then homogenized, typically for a period of 15 to 16 hours at a temperature between 470 and 485 ° C.
  • the raw form is then hot processed to form hot-rolled sheets.
  • the hot rolling of thick products according to the invention can be carried out at a temperature of about 350 ° C, much lower than that traditionally practiced for this type of product (which is about 415 to 440 ° C), without affecting the compromise of properties required for thick products used in aircraft structures.
  • the hot transformation can optionally be followed by a cold transformation. It is also possible to carry out one or more cold rolling passes.
  • This dissolution can be done in any suitable oven, such as air oven (horizontal or vertical), or salt bath oven. This dissolution is carried out at a temperature between 470 and 480 ° C, and preferably between 475 and 480 ° C for a period of at least 4 hours.
  • the products are quenched, preferably in a liquid medium such as water, said liquid preferably having a temperature not exceeding 40 ° C.
  • the products are then generally subjected to controlled traction with a permanent elongation of the order of 1 to 5%, and preferably 1.5 to 3%.
  • the products are subjected to a treatment of income, which influences in a big way on the final properties of the product.
  • income which influences in a big way on the final properties of the product.
  • the product according to the invention leads to new products which have particularly interesting characteristics for aeronautical construction.
  • These products are in the form of sheets, including fuselage sheets, thick sheets for intrados or integral structures.
  • K app LT
  • the value of K app (LT) is stable, or even higher, cold compared to its temperature value. room. More specifically, this value is slightly increased from room temperature when measured at -54 ° C. This is particularly interesting since -54 ° C is about the typical temperature reached by the structural elements during the flight of a civilian jet aircraft.
  • the products according to the invention advantageously replace the alloy structure elements known in alloys 2x24, for example alloy 2024 or 2324.
  • alloys 2x24 for example alloy 2024 or 2324.
  • laminated products with a thickness greater than about 40 mm can be used for the fabrication of structural elements by integral machining, as described below.
  • Rolled products with a thickness greater than about 60 mm can be used for the manufacture of stiffeners or frames, especially for high capacity aircraft.
  • the products according to the invention can be plated on at least one face according to the methods and with the alloys usually used for plating the products of Al-Zn-Cu-Mg type alloys. This is particularly interesting for the plates used for the manufacture of aircraft fuselage elements, which must resist corrosion.
  • a useable plating alloy is 7072.
  • a particularly advantageous use of the products according to the invention is related to the concept of the integral structure in aeronautical construction.
  • a large part of the aircraft structures are dimensioned according to a compromise between the damage tolerance and the resistance to static loads.
  • the requirements of tolerance to damage are specified for example in the article "Damage Tolerance Certification of Commercial Aircraft” by T. Swift, ASM Handbook vol. 19 (1996), pp 566-576 .
  • Sizing under static loadings is explained for example in the book “Airframe Stress Analysis and Sizing” by Niu, Hong Kong Conmilit Press Ltd, 1999, in particular pages 607-654 . From the point of view of the material, it is known that, generally, the damage tolerance of the 7xxx series alloys, and in particular their toughness, decreases when their yield strength increases.
  • the damage tolerance is the sizing parameter for a part essentially stressed in compression and vice versa.
  • a toughness gain of x% to constant yield strength as with the alloy according to the invention can result in a weight gain of the same level, or even higher if the fact of allowing a higher load on the part in question also allows the lightening of other components.
  • a yield strength gain of x%, with a constant damage tolerance can result in a weight gain of the order of x / 3% to x%.
  • x is typically between 15 and 30%.
  • the continuity between the stiffeners and the skin means that the damage tolerance becomes more critical than in a component assembled by riveting. Indeed, given stress, the stress intensity factor increases sharply when the stiffener is crossed by a crack, since it must be admitted that this stiffener will necessarily be cracked.
  • the present inventors have found that products with high tenacity, for a given elastic limit, are particularly well suited to the manufacture of integral structures.
  • fuselage barge panels or wing covers are manufactured by integral machining of products according to one of the preceding embodiments, given that said products, and in particular the plates for machining advantageously have a thickness of at least 40 mm; this value also depends on the type of aircraft, and especially its size.
  • the product according to the invention with a yield strength R p0.2 (L) at half thickness of at least 540 MPa and a K app toughness (LT) measured on a specimen of type M (T).
  • the Applicant has found that refining the grain at a reduced level compared to the usual practice during casting provides a compromise of properties, including a level of tenacity, particularly interesting.
  • a TiC refining agent for example adding A13% Ti0.15% C thread
  • the solidification germ obtained with this approach having a different germination-growth compromise germs obtained by refining for example with A15% Ti1% B (ie a seed type TiB 2 ).
  • the level of this refining can be quantified by the amount of C added, since it corresponds indirectly to the amount of added solidification nuclei, as well as by the amount of free Ti (not combined with C) in the alloy.
  • the stoichiometry of the seed is not definitively quantified, it can be considered that the seed is composed of TiC, each C atom combining with a Ti atom to form said seeds.
  • Al - x% Ti - y% C affinants There are different types of Al - x% Ti - y% C affinants, usually Ti being added in excess of C.
  • the amount of sprouts added is proportional to the amount of refining (in kilograms) added per ton. of liquid metal multiplied by y%, that is to say proportional to A (number of kilograms of affine added per tonne of metal) xy%.
  • the addition of seeds can thus be quantified by specifying 3 g / t of added C (2 ⁇ 0, 0015 kg / t).
  • a refining agent containing titanium and carbon is thus added, so that the amount of carbon added is between 0.4 and 3 g / t of carbon, preferentially between 0, 6 and 2 g / t, and so that the total content of Ti in the final product is between 50 and 500 ppm (by weight), preferably between 150 and 300 ppm.
  • N-alloy was developed whose chemical composition corresponds to that of a product according to the invention.
  • the liquid metal was first treated in a gas injection holding furnace using an Irma® type rotor, and then in a pocket type Alpur ®, these two brands belonging to the plaintiff.
  • the refining was done online, ie in the channel between the holding oven and the Alpur ® bag, at a rate of 1.1 kg / ton of Al-3% Ti-0.15 yarn. % C (diameter 9.5 mm).
  • An industrial-sized plate was cast. It was relaxed for 10 hours at 350 ° C.
  • the product thus cast was homogenized after scalping for 15 hours at a temperature of between 471 ° C and 482 ° C (880 ° F to 900 ° F), and then hot rolled to a thickness of 5 mm (0. 2 inches) (thickness outside the invention).
  • the start-up temperature was 450 ° C (840 ° F)
  • the end-of-rolling temperature was 349 ° C (660 ° F).
  • Sheets of width 178 mm (7 inches) and length 508 mm (20 inches) were taken. These coupons were dissolved in a salt bath oven for 1 hour at 472 ° C, then quenched with water, and triturated until a permanent deformation of 2%.
  • the coupons thus obtained then underwent a two-stage artificial aging treatment, the first bearing being 6 hours at 105 ° C., the second bearing being 18 hours at 155 ° C., in order to reach the peak of mechanical properties.
  • the alloy was cast by treating the liquid metal first in a gas injection holding furnace using an Irma ® type rotor, and then in an Alpur ® type pouch.
  • the refining was done online, that is to say in the channel between the holding furnace and the Alpur ® pocket, at a rate of 0.7 kg / tonne of AT5B wire (diameter 9.5 mm).
  • the plates were relaxed for 10h at 350 ° C. These plates were homogenized for 12 hours at 500 ° C. and then hot rolled (end of rolling temperature between 230 and 255 ° C.) to a thickness of 6 mm (thickness outside the invention).
  • a solution bath treatment was then carried out in a salt bath oven for 1 hour at 500 ° C on 600 mm by 200 mm coupons. This operation was followed by quenching with cold water at about 20 ° C. and pulling until a permanent deformation of 2% (state T351).
  • 7xxx alloy plates according to the prior art were also cast (reference G) in the same foundry device as the 2xxx alloy sheets described above.
  • a plate was obtained which was then homogenized for 24 hours at 470 ° C and then 24 hours at 495 ° C and then hot rolled (rolling end temperature between 230 and 255 ° C) to a thickness of 6. mm (thickness outside the invention).
  • a solution treatment of 1 hour at 450 ° C. in a salt bath oven was then carried out on a coupon of 600 mm by 200 mm. This operation was followed by quenching with water and traction to obtain a permanent deformation of 2%.
  • the coupon was then subjected to an artificial aging treatment of 5 hours at 100 ° C. and then 6 hours at 155 ° C., in order to reach the peak of mechanical properties (state T6).
  • An AA7475 alloy plate was also cast (reference H) according to the conventional methods of the prior art.
  • the plate thus obtained was homogenized for 9 hours at 480.degree. C. and then co-laminated at a temperature of about 270.degree. C., with a 7072 sheet, until a thickness of plated plate 4.5 was obtained. mm (thickness outside the invention).
  • the 7072 plating was about 2% of the final thickness.
  • the product thus obtained was dissolved in a salt bath oven for 45 minutes at 478 ° C, then quenched with water at a temperature of about 20 ° C, and then it was pulled to obtain a deformation permanent 2%. He then suffered a double-stage income operation for 4 hours at 120 ° C, then 24 hours at 162 ° C (condition T76).
  • Table 1 Chemical Composition Alloy Yes Fe Cu mn mg Zn Zr Cr NOT 0.05 0.06 2.05 - 1.64 7.08 0.08 - Y 0.04 0.05 2.16 - 1.80 6.76 0.09 - E (2024A) ⁇ 0.06 0.06 4.12 0.4 1.37 - - - BOY WUT 0.05 0.08 1.47 - 1.56 4.27 0.11 - H (7475) 0.03 0.06 1.5 - 2.22 5.73 - 0.21 Plating (7072) 0.15 0.35 ⁇ 0.02 ⁇ 0.05 ⁇ 0.10 1.05 ⁇ 0.03 ⁇ 0.03
  • the tensile strength R m (in MPa), the conventional yield stress at 0.2% elongation R p0.2 (in MPa) and the elongation at break A (in%) were measured by a tensile test according to EN 10002-1.
  • Table 2 Static mechanical characteristics sheet metal Thickness [mm] Meaning L TL direction R m [MPa] R p0.2 [MPa] AT [%] R m [MPa] R p0.2 [MPa] AT [%] NOT 5.08 539 508 13.9 541 495 13.9 Y 6 557 530 13.9 555 519 13.6 E 6.35 482 365 22.8 466 319 23.5 BOY WUT 6.35 435 373 15.1 436 366 14.8 H 4.6 475 414 13.3 484 414 12.5
  • the sheet whose composition corresponds to that of a product according to the invention has in both directions measured a breaking strength and a yield strength much higher than those of 2xxx alloy sheets.
  • the elongation of the sheet whose composition corresponds to that of a product according to the invention is lower than that of the sheet E, but sufficient compared to the intended applications.
  • the alloy whose composition corresponds to that of a product according to the invention has in both directions measured a significantly improved resistance to fracture and yield strength. , for comparable lengthening.
  • the sheet whose composition corresponds to that of a product according to the invention has a Kapp much greater than the alloy sheets 7xxx of the prior art, and of the same order of magnitude as 2xxx alloy sheets.
  • Fatigue behavior according to ASTM E 647 was also tested by measuring the crack growth rate in sheet N in comparison with sheets E, F and G.
  • the test pieces used were of type C (T), with W 76.2 mm (3 inches).
  • the comparative results are shown in Table 4.
  • the sheet Y had a thickness of 6 mm.
  • the sheet whose composition corresponds to that of a product according to the invention behaves at least as well in fatigue as the sheets according to the prior art.
  • a 3.2 mm thick Y sheet had da / dN (10) TL of 1.7 10 -4 mm / cycles, da / dN (30) TL of 10 -4 mm / cycles, and ⁇ K at 100 ⁇ inch. / cycle of 28.3 MPa ⁇ m.
  • An alloy M was prepared whose chemical composition was in accordance with that of a product according to the invention.
  • an alloy plate 2324 according to the prior art (reference I) was developed according to a conventional casting process.
  • the chemical compositions of alloys M and I measured on a spectrometric counter taken from the casting channel, are collated in the table: Table 5: Chemical Composition Alloy Yes Fe Cu mn mg Zn Zr M 0.05 0.06 2.05 - 1.64 7.08 0.08 I (AA2324) ⁇ 0.10 ⁇ 0.12 3.8-4.4 0.3-0.9 1.2-1.8 ⁇ 0.20 ⁇ 0.05
  • the M alloy plates were homogenized for 15 hours at 479 ° C, then slowly cooled to 420-440 ° C and rolled to a thickness of 25.4 mm.
  • the output temperature of the hot rolling mill was 354 ° C, which is significantly lower than that usually used for this type of product.
  • the sheets thus obtained were then subjected to solution treatment at 479 ° C. for 4 hours (total time, about 1/3 of which was spent at the temperature rise), then quenched, and triturated so that the permanent deformation resulting therefrom that is 2%.
  • the sheets were then artificially treated for 8 hours at 160 ° C.
  • the alloy 1 (AA2324) was subjected to a conventional range until an alloy sheet AA 2324, thickness 25.4 mm in the T39 state, that is to say a homogenization step, was obtained. hot rolling, followed by dissolution and quenching, followed by cold working by about 9%, and controlled pulling to obtain a permanent deformation of between 1.5 and 3 %.
  • Table 6 Static mechanical characteristics sheet metal Thickness [mm] Meaning L R m [MPa] R p0.2 [MPa] AT [%] M 25.4 570 540 12.3 I 25.4 490 470 14
  • the tensile strength and yield strength of the sheet according to the invention are substantially higher than those of the sheet I generally used for these applications, and for quite comparable elongations.
  • the alloy whose composition corresponds to that of a product according to the invention has under all conditions a toughness better than the conventional alloy 1. Moreover, and surprisingly, the alloy whose composition corresponds to that of a product according to the invention has a Kapp (LT) at -54 ° C which is of the same order as at room temperature.
  • Table 8 Fatigue Results sheet metal Number of cycles (Log average over 5 tests) Notched test tube Number of cycles (Log average over 5 tests) Double-hole test tube M 299213 330737 I 181402 337730
  • the fatigue behavior according to ASTM E 647 was also tested by measuring the crack growth rate in sheet M compared to sheet I.
  • the test pieces used were of type C (T), with B equal to 9 , 52 mm (0.375 inches), and W equal to 101.6 mm (4 inches).
  • the exfoliating corrosion behavior of the plates of this test was evaluated according to the ASTM G34 standard; this test was made at the surface, and at mid-thickness, under the conditions adapted to the alloys 7xxx for the sheet metal M according to the invention, and under the conditions adapted to the alloys 2xxx for the sheet I.
  • the sample M according to the The invention has been classified EA, both at the surface and at mid-thickness, while the sample I according to the prior art has been classified EA at the surface, and EB at mid-thickness.
  • the sheet according to the invention is therefore at least as powerful, if not more efficient, in resistance to exfoliating corrosion, than the sheet according to the prior art.
  • the sheet M is better for each of the following physical parameters: static mechanical characteristics, K app , fatigue resistance, crack propagation speed.
  • a P alloy similar to the M alloy of Example 2 was produced. From this alloy, using a manufacturing range similar to that of Example 2, hot-rolled plates (FIG. inlet temperature: 420 - 440 ° C) with a thickness of 75 mm.
  • Table 10 summarizes the mechanical characteristics obtained: Table 10: Process R p0.2 (L) [MPa] R m (L) [MPa] A (L) [%] K IC (LT) [MPa ⁇ m] K app (LT) [MPa ⁇ m] AT 542 561 9.7 30.1 57.1 B 525 549 10.2 32.8 63.2 VS 507 537 11.3 34.6 72.5

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Metal Rolling (AREA)
  • Heat Treatment Of Steel (AREA)

Claims (10)

  1. Kneterzeugnis in Form eines gewalzten Blechs mit einer Dicke größer als 20 mm aus AlZnCuMg-Legierung,
    dadurch gekennzeichnet, dass es enthält (Gew.-%):
    Zn: 6,7-7,3 % Cu: 2,0-2,3 % Mg: 1,5-1,8 % Zr: 0,07-0,12 % Fe<0,15% Si<0,15%
    weitere Elemente nicht mehr als jeweils 0,05 % und insgesamt 0,15 %,
    Rest Aluminium,
    wobei das Erzeugnis durch Lösungsglühen, Abschrecken, Kaltumformung und Auslagerung behandelt ist, und
    wobei das Erzeugnis folgende Eigenschaften aufweist:
    (a) Rm(L) > 540 MPa;
    (b) Rp0,2(L) > 535 MPa;
    (c) Kapp(L-T) > 100 MPa√m (gemessen bei Raumtemperatur an einer C(T)-Probe mit W = 127 mm und B = 7,6 mm);
    (d) ΔK bei einer Rissausbreitungsgeschwindigkeit von 2,54 µm / Zyklus > 28 MPa√m;
    (e) KIC(L-T) > 28 MPa√m.
  2. Erzeugnis nach Anspruch 1, dadurch gekennzeichnet, dass Zr 0,07 - 0,09 %.
  3. Erzeugnis nach irgendeinem der Ansprüche 1 bis 2, dadurch gekennzeichnet, dass Mg / Cu ≤ 0,80.
  4. Erzeugnis nach irgendeinem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die Legierung zwischen 50 und 500 ppm Titan, vorzugsweise zwischen 150 und 300 ppm Titan enthält.
  5. Erzeugnis nach irgendeinem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass es aus einem Metall hergestellt ist, das mit einem Raffinationsmittel, das Ti und C enthält, raffiniert wurde.
  6. Erzeugnis nach irgendeinem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass es aus einem flüssigen Metall hergestellt ist, dem ein Raffinationsmittel, das Titan und Kohlenstoff enthält, zugesetzt wurde, so dass die zugesetzte Menge an Kohlenstoff im Bereich zwischen 0,4 und 3 g/t Kohlenstoff, vorzugsweise im Bereich zwischen 0,6 und 2 g/t liegt, und der Gesamtgehalt an Ti im Enderzeugnis im Bereich zwischen 50 und 500 (Gew.) ppm, vorzugsweise im Bereich zwischen 150 und 300 ppm liegt.
  7. Strukturelement für den Flugzeugbau, das aus mindestens einem Erzeugnis nach irgendeinem der Ansprüche 1 bis 6 hergestellt ist.
  8. Integralstruktur für den Flugzeugbau, die ein oder mehrere Erzeugnisse nach irgendeinem der Ansprüche 1 bis 6 beinhaltet.
  9. Verwendung eines gewalzten Erzeugnisses nach irgendeinem der Ansprüche 1 bis 6 mit einer Dicke größer als 40 mm für die Herstellung/Verarbeitung von Strukturelementen für Flugzeuge.
  10. Verwendung eines gewalzten Erzeugnisses nach irgendeinem der Ansprüche 1 bis 6 mit einer Dicke größer als 60 mm für die Herstellung von Versteifungen oder Rahmen für Flugzeuge.
EP04356196A 2003-12-16 2004-12-15 Knetprodukt in Form eines gewalzten Bleches und Strukturbauteil für Flugzeug aus Al-Zn-Cu-Mg-Legierung Active EP1544315B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US52959403P 2003-12-16 2003-12-16
US529594P 2003-12-16

Publications (2)

Publication Number Publication Date
EP1544315A1 EP1544315A1 (de) 2005-06-22
EP1544315B1 true EP1544315B1 (de) 2012-08-22

Family

ID=34520278

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04356196A Active EP1544315B1 (de) 2003-12-16 2004-12-15 Knetprodukt in Form eines gewalzten Bleches und Strukturbauteil für Flugzeug aus Al-Zn-Cu-Mg-Legierung

Country Status (3)

Country Link
US (1) US20050150578A1 (de)
EP (1) EP1544315B1 (de)
ES (1) ES2393706T3 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8721811B2 (en) 2005-10-28 2014-05-13 Automotive Casting Technology, Inc. Method of creating a cast automotive product having an improved critical fracture strain
US10835942B2 (en) 2016-08-26 2020-11-17 Shape Corp. Warm forming process and apparatus for transverse bending of an extruded aluminum beam to warm form a vehicle structural component
US11072844B2 (en) 2016-10-24 2021-07-27 Shape Corp. Multi-stage aluminum alloy forming and thermal processing method for the production of vehicle components

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6854276B1 (en) * 2003-06-19 2005-02-15 Superpower, Inc Method and apparatus of cryogenic cooling for high temperature superconductor devices
ES2292075T5 (es) * 2005-01-19 2010-12-17 Otto Fuchs Kg Aleacion de aluminio no sensible al enfriamiento brusco, asi como procedimiento para fabricar un producto semiacabado a partir de esta aleacion.
WO2006086534A2 (en) * 2005-02-10 2006-08-17 Alcan Rolled Products - Ravenswood Llc Al-zn-cu-mg aluminum base alloys and methods of manufacture and use
US8840737B2 (en) 2007-05-14 2014-09-23 Alcoa Inc. Aluminum alloy products having improved property combinations and method for artificially aging same
US8673209B2 (en) * 2007-05-14 2014-03-18 Alcoa Inc. Aluminum alloy products having improved property combinations and method for artificially aging same
EP2379765B2 (de) * 2009-01-16 2016-10-12 Aleris Rolled Products Germany GmbH Herstellungsverfahren eines aluminiumlegierungsplattenprodukts mit geringer eigenspannung
US9314826B2 (en) 2009-01-16 2016-04-19 Aleris Rolled Products Germany Gmbh Method for the manufacture of an aluminium alloy plate product having low levels of residual stress
US8206517B1 (en) 2009-01-20 2012-06-26 Alcoa Inc. Aluminum alloys having improved ballistics and armor protection performance
US9163304B2 (en) 2010-04-20 2015-10-20 Alcoa Inc. High strength forged aluminum alloy products
KR101974913B1 (ko) * 2017-04-13 2019-05-07 한국기계연구원 알루미늄-아연-구리(Al-Zn-Cu) 합금 및 이의 제조방법
FR3068370B1 (fr) 2017-07-03 2019-08-02 Constellium Issoire Alliages al- zn-cu-mg et procede de fabrication
FR3071513B1 (fr) * 2017-09-26 2022-02-11 Constellium Issoire Alliages al-zn-cu-mg a haute resistance et procede de fabrication
EP3670690A1 (de) 2018-12-20 2020-06-24 Constellium Issoire Al-zn-cu-mg-legierungen und deren herstellungsverfahren
CN114107759B (zh) * 2020-08-26 2022-08-16 宝山钢铁股份有限公司 一种7xxx铝合金薄带及其制造方法
CN115233008A (zh) * 2022-08-30 2022-10-25 西南铝业（集团）有限责任公司 一种铸锭成分控制方法和应用
WO2024126341A1 (en) 2022-12-12 2024-06-20 Constellium Rolled Products Ravenswood, Llc 7xxx wrought products with improved compromise of tensile and toughness properties and method for producing
EP4386097A1 (de) 2022-12-12 2024-06-19 Constellium Rolled Products Ravenswood, LLC 7xxx-legierung mit verbesserten zug- und zähigkeitseigenschaften und verfahren zu ihrer herstellung

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4863528A (en) * 1973-10-26 1989-09-05 Aluminum Company Of America Aluminum alloy product having improved combinations of strength and corrosion resistance properties and method for producing the same
CA1173277A (en) * 1979-09-29 1984-08-28 Yoshio Baba Aircraft stringer material and method for producing the same
US5312498A (en) * 1992-08-13 1994-05-17 Reynolds Metals Company Method of producing an aluminum-zinc-magnesium-copper alloy having improved exfoliation resistance and fracture toughness
FR2695942B1 (fr) * 1992-09-22 1994-11-18 Gerzat Metallurg Alliage d'aluminium pour corps creux sous pression.
US5865911A (en) * 1995-05-26 1999-02-02 Aluminum Company Of America Aluminum alloy products suited for commercial jet aircraft wing members
IL156386A0 (en) * 2000-12-21 2004-01-04 Alcoa Inc Aluminum alloy products and artificial aging method
JP4285916B2 (ja) * 2001-02-16 2009-06-24 株式会社神戸製鋼所 高強度、高耐食性構造用アルミニウム合金板の製造方法
US20050006010A1 (en) * 2002-06-24 2005-01-13 Rinze Benedictus Method for producing a high strength Al-Zn-Mg-Cu alloy
US7452429B2 (en) * 2003-06-24 2008-11-18 Pechiney Rhenalu Products made of Al-Zn-Mg-Cu alloys with an improved compromise between static mechanical characteristics and damage tolerance

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8721811B2 (en) 2005-10-28 2014-05-13 Automotive Casting Technology, Inc. Method of creating a cast automotive product having an improved critical fracture strain
US9353430B2 (en) 2005-10-28 2016-05-31 Shipston Aluminum Technologies (Michigan), Inc. Lightweight, crash-sensitive automotive component
US10835942B2 (en) 2016-08-26 2020-11-17 Shape Corp. Warm forming process and apparatus for transverse bending of an extruded aluminum beam to warm form a vehicle structural component
US11072844B2 (en) 2016-10-24 2021-07-27 Shape Corp. Multi-stage aluminum alloy forming and thermal processing method for the production of vehicle components

Also Published As

Publication number Publication date
US20050150578A1 (en) 2005-07-14
EP1544315A1 (de) 2005-06-22
ES2393706T3 (es) 2012-12-27

Similar Documents

Publication Publication Date Title
EP1544315B1 (de) Knetprodukt in Form eines gewalzten Bleches und Strukturbauteil für Flugzeug aus Al-Zn-Cu-Mg-Legierung
EP2235224B1 (de) HERSTELLUNGSVERFAHREN EINES Al-Li-GEWALZTEN PRODUKTS FÜR ANWENDUNGEN IN DER LUFTFAHRT
EP1966402B1 (de) Blech aus einer hochfesten aluminiumlegierung mit kupfer und lithium für einen flugzeugrumpf
EP1766102B1 (de) Verfahren zur herstellung hochfester und ermüdungsfester aluminiumlegierungsprodukte
EP2449142B1 (de) Aluminium-kupfer-lithium-legierung mit verbesserten mechanische beständigkeit und zähigkeit
EP2364378B1 (de) Produkte aus aluminium-kupfer-lithium-legierung
FR2907466A1 (fr) Produits en alliage d&#39;aluminium de la serie aa7000 et leur procede de fabrication
FR3068370B1 (fr) Alliages al- zn-cu-mg et procede de fabrication
FR2907796A1 (fr) Produits en alliage d&#39;aluminium de la serie aa7000 et leur procede de fabrication
FR2853666A1 (fr) ALLIAGE Al-Zn A HAUTE RESISTANCE,PROCEDE DE PRODUCTION DE PRODUITS EN UN TEL ALLIAGE, ET PRODUITS OBTENUS SELON CE PROCEDE
EP1382698B1 (de) Knetprodukt aus Al-Cu-Mg-Legierung für das Strukturbauteil eines Flugzeugs
CA2798480C (fr) Alliage aluminium-cuivre-lithium pour element d&#39;intrados
CA2528614C (fr) Produits en alliages al-zn-mg-cu a compromis caracteristiques mecaniques statiques/tolerance aux dommages ameliore
CA2923109C (fr) Tole d&#39;intrados a proprietes de tolerance aux dommages ameliorees
EP3411508B1 (de) Dicke bleche aus al- cu - li legierung mit verbesserten ermüdungseigenschaften
EP1544316B1 (de) Dickes Bech aus Al-Zn-Cu-Mg Zirkonarmen rekristallisierten Legierung
EP3610048B1 (de) Aluminium-kupfer-lithium-legierungsprodukte mit niedriger dichte
EP3610047B1 (de) Aluminium-kupfer-lithium-legierungsprodukte
WO2019211546A1 (fr) Procede de fabrication d&#39;un alliage aluminium cuivre lithium a resistance en compression et tenacite ameliorees
WO2017064407A1 (fr) Toles minces en alliage aluminium-magnesium-zirconium pour applications aerospatiales

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR LV MK YU

17P Request for examination filed

Effective date: 20051013

AKX Designation fees paid

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU MC NL PL PT RO SE SI SK TR

17Q First examination report despatched

Effective date: 20080115

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ALCAN RHENALU

Owner name: PECHINEY ROLLED PRODUCTS

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ALCAN RHENALU

Owner name: ALCAN ROLLED PRODUCTS - RAVENSWOOD, LLC

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: CONSTELLIUM ROLLED PRODUCTS RAVENSWOOD, LLC

Owner name: ALCAN RHENALU

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: CONSTELLIUM FRANCE

Owner name: CONSTELLIUM ROLLED PRODUCTS RAVENSWOOD, LLC

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RTI1 Title (correction)

Free format text: WROUGHT PRODUCT IN THE FORM OF A ROLLED PLATE AND STRUCTURAL PART FOR AIRCRAFT IN AL-ZN-CU-MG ALLOY

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU MC NL PL PT RO SE SI SK TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

Ref country code: DE

Ref legal event code: R081

Ref document number: 602004039009

Country of ref document: DE

Owner name: CONSTELLIUM ROLLED PRODUCTS RAVENSWOOD, LLC, R, US

Free format text: FORMER OWNERS: PECHINEY RHENALU, PARIS, FR; PECHINEY ROLLED PRODUCTS, RAVENSWOOD, W.VA., US

Ref country code: DE

Ref legal event code: R081

Ref document number: 602004039009

Country of ref document: DE

Owner name: CONSTELLIUM ISSOIRE, FR

Free format text: FORMER OWNERS: PECHINEY RHENALU, PARIS, FR; PECHINEY ROLLED PRODUCTS, RAVENSWOOD, W.VA., US

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 572071

Country of ref document: AT

Kind code of ref document: T

Effective date: 20120915

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602004039009

Country of ref document: DE

Effective date: 20121018

REG Reference to a national code

Ref country code: NL

Ref legal event code: VDEP

Effective date: 20120822

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2393706

Country of ref document: ES

Kind code of ref document: T3

Effective date: 20121227

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 572071

Country of ref document: AT

Kind code of ref document: T

Effective date: 20120822

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

Effective date: 20120822

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120822

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120822

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120822

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120822

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121222

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120822

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121224

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120822

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121123

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120822

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120822

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120822

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120822

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120822

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120822

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120822

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

BERE Be: lapsed

Owner name: CONSTELLIUM ROLLED PRODUCTS RAVENSWOOD, LLC

Effective date: 20121231

Owner name: CONSTELLIUM FRANCE

Effective date: 20121231

26N No opposition filed

Effective date: 20130523

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121122

Ref country code: MC

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121231

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602004039009

Country of ref document: DE

Effective date: 20130523

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121231

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121215

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120822

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121215

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20041215

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: CONSTELLIUM ROLLED PRODUCTS RAVENSWOOD, LLC, US

Effective date: 20150910

Ref country code: FR

Ref legal event code: CD

Owner name: CONSTELLIUM ISSOIRE, FR

Effective date: 20150910

Ref country code: FR

Ref legal event code: CA

Effective date: 20150910

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 12

REG Reference to a national code

Ref country code: CH

Ref legal event code: PFA

Owner name: CONSTELLIUM ROLLED PRODUCTS RAVENSWOOD, LLC, FR

Free format text: FORMER OWNER: CONSTELLIUM ROLLED PRODUCTS RAVENSWOOD, LLC, FR

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 602004039009

Country of ref document: DE

Owner name: CONSTELLIUM ROLLED PRODUCTS RAVENSWOOD, LLC, R, US

Free format text: FORMER OWNERS: CONSTELLIUM FRANCE, PARIS, FR; CONSTELLIUM ROLLED PRODUCTS RAVENSWOOD, LLC, RAVENSWOOD, W.VA., US

Ref country code: DE

Ref legal event code: R081

Ref document number: 602004039009

Country of ref document: DE

Owner name: CONSTELLIUM ISSOIRE, FR

Free format text: FORMER OWNERS: CONSTELLIUM FRANCE, PARIS, FR; CONSTELLIUM ROLLED PRODUCTS RAVENSWOOD, LLC, RAVENSWOOD, W.VA., US

REG Reference to a national code

Ref country code: ES

Ref legal event code: PC2A

Owner name: CONSTELLIUM ISSOIRE

Effective date: 20161010

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 13

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20151215

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20151215

PGRI Patent reinstated in contracting state [announced from national office to epo]

Ref country code: IT

Effective date: 20170710

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20191219

Year of fee payment: 16

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: ES

Payment date: 20200102

Year of fee payment: 16

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20220221

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201216

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201215

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230411

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20231227

Year of fee payment: 20

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20231227

Year of fee payment: 20

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20231229

Year of fee payment: 20

Ref country code: CH

Payment date: 20240102

Year of fee payment: 20