EP4247991B1 - Verfahren zur herstellung von aluminiumlegierungsprodukten der reihe 2xxx - Google Patents

Verfahren zur herstellung von aluminiumlegierungsprodukten der reihe 2xxx

Info

Publication number
EP4247991B1
EP4247991B1 EP21816164.4A EP21816164A EP4247991B1 EP 4247991 B1 EP4247991 B1 EP 4247991B1 EP 21816164 A EP21816164 A EP 21816164A EP 4247991 B1 EP4247991 B1 EP 4247991B1
Authority
EP
European Patent Office
Prior art keywords
product
aluminum alloy
2xxx
aging
series aluminum
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
EP21816164.4A
Other languages
English (en)
French (fr)
Other versions
EP4247991A1 (de
Inventor
Sabine Maria Spangel
Andreas Harald BACH
Achim BÜRGER
Philippe Meyer
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.)
Novelis Koblenz GmbH
Original Assignee
Novelis Koblenz GmbH
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 Novelis Koblenz GmbH filed Critical Novelis Koblenz GmbH
Publication of EP4247991A1 publication Critical patent/EP4247991A1/de
Application granted granted Critical
Publication of EP4247991B1 publication Critical patent/EP4247991B1/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
    • 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
    • C22C21/16—Alloys based on aluminium with copper as the next major constituent with magnesium

Definitions

  • the invention relates to a method of manufacturing 2XXX-series aluminum alloy wrought products, and to an improved aging process. Products made from this alloy are very suitable for aerospace applications, but not limited to that.
  • the aluminum alloy can be processed to various product forms, e.g., sheet, thin plate, thick plate, extruded, or forged products.
  • Aerospace applications generally require a very specific set of properties.
  • High strength alloys are generally desired, but according to the desired intended use, other properties such as high fracture toughness or ductility, as well as good corrosion resistance are also required.
  • SCC stress corrosion cracking
  • ST short-transverse
  • Controls on alloy processing and heat treatment are key to ensuring high resistance to SCC without appreciable loss in mechanical properties.
  • Thick-section products of 2XXX-series aluminum alloys in the naturally aged T3 and T4 tempers have low ratings of resistance to SCC in the short-transverse direction. Ratings of such products in other directions are higher, as are ratings of thin-section products in all directions. These differences are related to the effects of quenching rate (largely determined by section thickness) on the amount of precipitation that occurs during quenching.
  • the response to the age-hardening is enhanced by the strain hardening due to the stretching, or cold working by other means, prior to artificial aging (T8 temper) and the yield strength may be increased very significantly as compared to the T6 temper.
  • the T6 tempers relate to wrought products that are solution heat treated, quenched and artificially aged with little or no cold work such that the cold work is not thought to affect mechanical property limits. What is needed is a high strength 2XXX-series aluminum alloy having very high resistance to stress corrosion cracking.
  • JPH02-247361 A is directed to a method of heat treating a material made of an aluminum alloy having a first temperature at which the solid solution elements cluster and nucleate for formation and growth of strengthening precipitates and a second temperature at which the strengthening precipitates form a solid solution.
  • WO 2018/144568 A1 describes a method of making an extruded aluminum alloy product comprising from, in weight percent, 2.6-3.0 Cu, 1.4-1.75 Li, 0.1-0.45 Mg, 0-0.25 Mn, 0.2 max Zn, 0.05 max Ag, 0.1 max Si, 0.12 max Fe, 0.05-0.15 Zr, 0-0.1 Ti, and the balance Al and incidental impurities, wherein the extruded aluminum alloy product has less than or equal to 25% recrystallized grains, the method comprising: homogenizing a cast billet or shape of the aluminum alloy; hot working the billet or shape into an extruded product; subjecting the extruded product to a solution heat treatment at a temperature of from 940°F (504°C) to 1020°F (549°C); quenching the solution heat treated extruded product; stretching the extruded product to a permeant set of 3 -9%; and artificially aging the extruded product by heating to at least one temperature of from 290°
  • US 2006/0011272 A1 is directed to a 2000 series aluminum alloy having enhanced damage tolerance, the alloy consisting essentially of about 3.0-4.0 wt % Cu; about 0.4-1.1 wt % Mg; up to about 0.8 wt % Ag; up to about 1.0 wt % Zn; up to about 0.25 wt % Zr; up to about 0.9 wt % Mn; up to about 0.5 wt % Fe; and up to about 0.5 wt % Si, the balance substantially aluminum, incidental impurities and elements, wherein Cu and Mg are present in a ratio of about 3.6-5 parts Cu to about 1 part Mg.
  • CN 103981410 A is directed to a damage-resistant aluminium alloy and a preparation method thereof.
  • the aluminium alloy disclosed therein comprises the following components in mass percentage: 3.0-4.0% of Cu, 0.7-1.5% of Mg, 0.15-0.6% of Mn, 0.3-0.8% of Ag, 0.08-0.2% of Zr, and the balance of Al and trace impurity elements, wherein the total content of the impurity elements is less than 0.1%.
  • a traditional damage-resistant Al-Cu-Mg alloy (2X24 alloy)
  • Ag and Zr are added, therefore, a high damage-resistant Al-Cu-Mg-Ag-Mn-Zr alloy is designed.
  • CN 106521270 A is directed to a thermal treatment process for improving corrosion resistance of an aluminum-lithium alloy.
  • the process is suitable for the alloy which comprises the main alloying elements of, by weight, 2.4-4.5% of Cu and 1.2-1.8% of Li, and one to four of micro-alloying elements of, by weight, 0.2-0.8% of Mg, 0.1-0.8% of Zn, 0.04-0.20% of Zr, 0.20-0.80% of Mn, 0.05-0.35% of Sc, and 0.1-0.9% of Ag, and the alloy also comprises no more than 0.10% of Si, no more than 0.10% of Fe, no more than 0.10% of Ti, no more than 0.15% of total impurity elements, and the balance Al, wherein the weight percentage of each impurity element is smaller than or equal to 0.05%.
  • the thermal treatment process is characterized in that an aluminum-lithium alloy thick plate is subjected to solid solution quenching and then large-deformation pre-stretching, and regulation and control over intragranular and grain-boundary precipitated phases can be achieved through the multi-stage aging process, and the corrosion resistance of the thick plate is improved while other mechanical properties of the alloy are not changed.
  • the thermal treatment process is suitable for aluminum-lithium alloy thick plates, thin plates and extruded materials in the field of aviation and aerospace.
  • Described herein is an aging process of a solution-heat-treated and quenched 2XXX-series aluminum alloy wrought product as defined in the claims, comprising the steps of: (1) aging the product in a first aging step at one or more temperatures within a range of 90 °C to 120 °C for a cumulative period time of at least 10 hours; and (2) subsequently aging the product in a second aging step at one or more temperatures within a range of 160 °C to 190 °C for a cumulative period of time of at least 4 hours.
  • Also described herein is a method of manufacturing a 2XXX-series aluminum alloy wrought product, the method comprising the following steps: (i) casting of an ingot of an 2XXX-series aluminum alloy as defined in the claims; (ii) preheating and/or homogenizing the ingot; (iii) hot working the ingot by one or more methods selected from the group consisting of rolling, extrusion, and forging, into a hot worked wrought product; (iv) optionally cold working the hot worked wrought product; (v) solution heat treating ("SHT") the wrought product; (vi) rapid cooling or quenching the SHT product; (vii) optionally cold working or cold forming the SHT and quenched product; and (viii) artificial aging in accordance with the methods described herein of the SHT, quenched product and optionally cold working or cold forming.
  • SHT solution heat treating
  • the wrought 2XXX-series aluminum alloy product optionally having a clad layer on one or two sides, has a cross-sectional thickness from 1.6 mm to 12 mm, and preferably from 1.6 mm to 8 mm, and is aged to achieve (1) a conventional tensile yield strength (in MPa) measured in L-direction of more than 400 MPa; or (2) an improved IGC resistance measured without cladding showing predominantly pitting attack and negligent IGC.
  • the wrought 2XXX-series aluminum alloy product having a cross-sectional thickness from 12 mm to 250 mm, and preferably from 12 mm to 130 mm is aged to achieve (1) a conventional tensile yield strength (in MPa) measured in L-direction at quarter thickness of more than 380 MPa + 0.57 (120-t) MPa, wherein t is the thickness of the product in mm; or (2) a minimum service life without failure due to stress corrosion cracking in accordance with ASTM G47 of at least 20 days, preferably of at least 25 days at a short transverse stress level of 250 MPa.
  • the wrought 2XXX-series aluminum alloy product having a cross-sectional thickness from 12 mm to 250 mm, and preferably from 12 mm to 130 mm is aged to achieve (1) a conventional tensile yield strength (in MPa) measured in L-direction at quarter thickness of more than 380 MPa + 0.57 (120-t) MPa, wherein t is the thickness of the product in mm; or (2) an improved IGC resistance measured without cladding showing predominantly pitting attack and negligent IGC.
  • aluminum alloy designations and temper designations refer to the Aluminum Association designations in Aluminum Standards and Data and the Registration Records, as published by the Aluminum Association in 2019 and are well known to the person skilled in the art for example as the "Teal Sheets.”
  • the temper designations are laid down in European standard EN515.
  • the term "about" when used to describe a compositional range or amount of an alloying addition means that the actual amount of the alloying addition may vary from the nominal intended amount due to factors such as standard processing variations as understood by those skilled in the art.
  • up to 0.25% Cr may include an aluminum alloy having no Cr.
  • a sheet product or a sheet material (also referred to herein as "sheet”) is to be understood as a rolled product having a thickness of not less than 1.3 mm (0.05 inches) and not more than 6.3 mm (0.25 inches).
  • a sheet may have a thickness of 1.3 mm, 1.4 mm, 1.5 mm, 1.6 mm, 1.7 mm, 1.8 mm, 1.9 mm, 2.0 mm, 2.1 mm, 2.2 mm, 2.3 mm, 2.4 mm, 2.5 mm, 2.6 mm, 2.7 mm, 2.8 mm, 2.9 mm, 3.0 mm, 3.1 mm, 3.2 mm, 3.3 mm, 3.4 mm, 3.5 mm, 3.6 mm, 3.7 mm, 3.8 mm, 3.9 mm, 4.0 mm, 4.1 mm, 4.2 mm, 4.3 mm, 4.4 mm, 4.5 mm, 4.6 mm, 4.7 mm, 4.8 mm, 4.9 mm, 5.0 mm, 5.1 mm, 5.2 mm, 5.3 mm, 5.4 mm, 5.5 mm, 5.6 mm, 5.7 mm, 5.8 mm, 5.9 mm, 6.0 mm, 6.1 mm,
  • a plate material or a plate product (also referred to herein as "plate”) is to be understood as a rolled product having a thickness of more than 6.3 mm (0.25 inches).
  • a plate material or a plate product may have a thickness of more than 6.3 mm, more than 6.4 mm, more than 6.5 mm, more than 6.6 mm, more than 6.7 mm, more than 6.8 mm, more than 6.9 mm, more than 7.0 mm, more than 7.1 mm, more than 7.2 mm, more than 7.3 mm, more than 7.4 mm, more than 7.5 mm, more than 7.8 mm, more than 7.9 mm, more than 8.0 mm, more than 10.0 mm, more than 15.0 mm, more than 20.0 mm, more than 25.0 mm, more than 30.0 mm, more than 35.0 mm, more than 40.0 mm, more than 45.0 mm, more than 50.0 mm, or more than 100.0 mm. See Aluminium Standard
  • ambient temperature can include a temperature of from about 15 °C to a temperature of a first aging step as described herein (e.g., about 15 °C to about 90 °C, about 15 °C to about 120 °C, about 20 °C to about 90 °C, about 20 °C to about 120 °C, about 22 °C to about 90 °C, about 22 °C to about 120 °C, about 20 °C to about 100 °C, about 20 °C to about 110 °C, about 15 °C to about 100 °C, or about 15 °C to about 110 °C).
  • a temperature of from about 15 °C to a temperature of a first aging step as described herein e.g., about 15 °C to about 90 °C, about 15 °C to about 120 °C, about 20 °C to about 90 °C, about 20 °C to about 120 °C, about 22 °C to about 90 °C, about 22 °C
  • ambient temperature can be about 15 °C, about 16 °C, about 17 °C, about 18 °C, about 19 °C, about 20 °C, about 21 °C, about 22 °C, about 23 °C, about 24 °C, about 25 °C, about 26 °C, about 27 °C, about 28 °C, about 29 °C, about 30 °C, about 31 °C, about 32 °C, about 33 °C, about 34 °C, about 35 °C, about 36 °C, about 37 °C, about 38 °C, about 39 °C, about 40 °C, about 41 °C, about 42 °C, about 43 °C, about 44 °C, about 45 °C, about 46 °C, about 47 °C, about 48 °C, about 49 °C, about 50 °C, about 51 °C, about 52 °C, about 53 °C, about 54 °C, about 55 °C,
  • a wrought product is a cast aluminum alloy that is solution-heat-treated, quenched, and subsequently cold worked or cold formed.
  • the aging process described herein can include any desired number of aging steps.
  • the aging process can include two steps, three steps, four steps, five steps, six steps, seven steps, eight steps, nine steps, ten steps, or greater.
  • An aging step can include heating the aluminum alloy wrought product to any desired temperature and holding the aluminum alloy wrought product at the desired temperature for any desired period of time.
  • all ranges describing processes, properties, compositions, characteristics, or the like encompass any and all endpoints and any and all subranges subsumed therein.
  • the cooling from solution heat treatment (i.e., quenching) for a 2XXX-series aluminum alloy plate in the thickness range of 1.6 mm to 12 mm is performed with a cooling rate between 100 °C/min and 1000 °C/min (e.g., 110 °C/min to 900 °C/min, 100 °C/min to 800 °C/min, 110 °C/min to 700 °C/min, or 120 °C/min to 600 °C/min), more preferably between 200 °C/min and 600 °C/min (e.g., 210 °C/min to 600 °C/min, 200 °C/min to 550 °C/min, or 250 °C/min to 500 °C/min) when measured during cooling when the temperature of the 2XXX-series aluminum alloy is in a range from 150 °C to 400 °C.
  • the cooling rate is similar to a cooling rate using a water quench on a
  • the aging process achieves improved metallurgical properties in the ST-direction.
  • the 2XXX-series aluminum alloy wrought product is more ST stress corrosion cracking resistant.
  • the improvement in SCC resistance in ST-direction is particularly noticeable in thicker gauge wrought products.
  • ST stress corrosion cracking resistant means that at least two-of-three specimens of a 2XXX-series aluminum alloy product do not fail after 20 days of alternate immersion testing at a net stress of 250 megaPascals (MPa) in the ST direction and in accordance with ASTM G47 and with at least 3 specimens being required for testing.
  • all three specimens do not fail after 20 days of alternate immersion testing at a net stress of 250 MPa in the ST direction and in accordance with ASTM G47.
  • all three specimens do not fail after 25 days of alternate immersion testing at a net stress of 250 MPa in the ST direction and in accordance with ASTM G47.
  • the aging process as described herein achieves an improved balance in engineering properties in the 2XXX-series aluminum alloy wrought product, as SCC corrosion resistance is improved and the mechanical strength levels are maintained at least to the level of a counterpart aged in a one-step aging process for 12 hours at 190 °C.
  • a counterpart is a wrought product of the same thickness and having a similar alloy composition and the same thermo-mechanical history except for the final aging treatment.
  • the wrought product in the first aging step is aged at one or more temperatures within a range of 90 °C to 120 °C for a cumulative period of time of at least 10 hours, and more preferably for at least 24 hours.
  • the wrought product is aged for a cumulative period of time not longer than 144 hours, and preferably for not longer than 96 hours, and more preferably for not more than 64 hours.
  • the wrought product in the second aging step is aged at one or more temperatures within a range of 160 °C to 190 °C for a cumulative period of time of at least 8 hours, and preferably for at least 12 hours. In a preferred embodiment of the second aging step, the wrought product is aged for a cumulative period of time of no longer than 144 hours and preferably not longer than 96 hours.
  • the aging of the wrought product may be effected in a single, programmable furnace for convenience purposes as is known in the art for other aging treatment for other heat-treatable aluminum alloys.
  • the wrought product is cooled at the end of the first aging step, e.g., to ambient temperature, and reheated to the second aging step for completing the aging cycle as described herein to realize the improved metallurgical properties.
  • This intermediate cooling to ambient temperature can be done for reasons of logistics; however, also an intermediate cold working operation can be done, in particular a stretching operation by stretching in the range of about 0.5% to 11% of its original length to enhance subsequent aging kinetics and to increase strength levels, if so desired.
  • the stretching is in the range of about 0.5% to 6%, more preferably of about 1% to 3%, of its original length.
  • the aging process in accordance with the invention can be used for 2XXX-series aluminum alloy wrought products as defined in the claims.
  • the 2XXX-series aluminum alloy wrought product has a composition, in wt.%: Cu 3.5% to 5.5%; Mn 0.15% to 1.0%; Mg 0.2% to 1.8%; Ag up to 0.7%; Zn up to 1.0%; Fe up to 0.3%; Si up to 0.2%; Ti 0.01% to 0.2%; and optionally one or more dispersoid forming elements selected from the group consisting of about 0.05% to 0.25% Cr, about 0.05% to 0.25% Zr, about 0.05% to 0.25% V, about 0.05% to 0.4% Hf, and about 0.05% to 0.4% Sc, preferably 0.05% to 0.2% Cr, 0.05% to 0.15% Zr, 0.05% to 0.15% V, 0.05% to 0.25% Hf, 0.05% to 0.25% Sc; impurities up to 0.15%, and balance aluminum; and with preferred narrower
  • the Cu is the main alloying element in 2XXX-series alloys and for the method or process described herein it is in a range of 3.5% to 5.5%.
  • a preferred upper limit for the Cu content is about 5.1%.
  • the Cu content is in a range of about 3.5% to 4.4% (e.g., 3.6% to 4.4%, 3.5% to 4.3%, 3.75% to 4.25%, or 3.6% to 4.3%).
  • the Cu content is in a range of about 4.4% to 5.5%, and preferably in a range of about 4.4% to 5.1% (e.g., 4.4% to 5.4%, 4.5% to 5.5%, 4.5% to 5.4%, 4.7% to 5.2%, or 4.75% to 5.25%).
  • Mn is another important alloying element in the 2XXX-series aluminum alloy and is present in a range of 0.15% to 1.0%.
  • the Mn content is in a range of about 0.15% to 0.8%, and preferably about 0.2% to about 0.8% (e.g., 0.25% to 0.75%, 0.3% to 0.8%, 0.2% to 0.5%, 0.2% to 0.6%, or 0.21% to 0.79%).
  • Mg is another important alloying element and is present in a range of 0.2% to 1.8% (e.g., 0.25% to 1.75%, 0.3% to 1.8%, 0.2% to 1.5%, 0.2% to 1.6%, or 0.21% to 1.79%).
  • a preferred lower limit for the Mg content is about 0.4%.
  • a preferred upper limit for the Mg content is about 1.4%.
  • Ag in a range of up to 0.7% can be added to further enhance the strength following artificial aging.
  • a preferred lower limit for the purposive Ag addition would be about 0.05%, and more preferably about 0.2%.
  • a preferred upper limit is about 0.7%.
  • Ag can be added in an amount of 0.05% to 0.7%, 0.1% to 0.7%, 0.2% to 0.7%, 0.15% to 0.69%, 0.05% to 0.65%, or from 0.2% to 0.66%.
  • the Ag is an impurity element and it can be present up to about 0.05%, and preferably up to about 0.03%.
  • Zn in a range of up to 1% can be purposively added to further enhance the strength during aging and may replace some of the purposive Ag, if added.
  • a preferred lower limit for the purposive Zn addition would be 0.2% and more preferably about 0.3%.
  • a preferred upper limit would be about 0.5%.
  • the Zn is an impurity element and it can be present up to about 0.25%, and preferably up to about 0.15%.
  • dispersoid forming elements can be added to the aluminum alloy to control the evolution of grain structure or grain size during hot working operations such as hot rolling, extrusion, or forging.
  • the one or more dispersoid forming elements can be selected from the group consisting of: 0.05% to 0.25% Cr (e.g., 0.05% to 0.2%, 0.05% to 0.15%, or 0.09% to 0.24%), 0.05% to 0.25% Zr (e.g., 0.05% to 0.2%, 0.05% to 0.15%, or 0.09% to 0.24%), 0.05% to 0.25% V (e.g., 0.05% to 0.2%, 0.05% to 0.15%, or 0.09% to 0.24%), 0.05% to 0.4% Hf (e.g., 0.05% to 0.35%, 0.05% to 0.25%, or 0.09% to 0.39%), and/or 0.05% to 0.4% Sc (e.g., 0.05% to 0.35%, 0.05% to 0.25%, or
  • Ti is added to the alloy product amongst others for grain refiner purposes during casting of the 2XXX-series aluminum alloy.
  • the addition of Ti does not exceed 0.2%, and preferably it does not exceed 0.15% (e.g., 0.05% to 0.2%, 0.05% to 0.15%, 0.1% to 0.15%, or 0.09% to 0.15%).
  • the lower limit for the Ti addition is 0.01%.
  • Ti can be added as a sole element or with either B (e.g., TiB 2 ) or C (TiC) serving as a casting aid, for grain size control.
  • B e.g., TiB 2
  • TiC C serving as a casting aid
  • Fe is a regular impurity in aluminum alloys and can be tolerated up to 0.3% (e.g., 0.05% to 0.3%, 0.05% to 0.2%, 0.05% to 0.1%, 0.1% to 0.3%, 0.1% to 0.2%, or 0.09% to 0.29%). Preferably it is kept to a level of up to about 0.2%, and more preferably up to about 0.1%.
  • Si is also a regular impurity in aluminum alloys and can be tolerated up to 0.2% (e.g., 0.05% to 0.2%, 0.1% to 0.2%, 0.05% to 0.15%, or 0.05% to 0.1%). Preferably it is kept to a level of up to 0.15%, and more preferably up to 0.1%.
  • impurities can be present each up to 0.05% and in total up to 0.15%. In an embodiment, the impurities can be present each up to 0.03% and in total up to 0.1%.
  • inevitable impurities include other elements that can be added during casting operations, e.g., Be or Ca. These elements are generally referred to as deoxidizers and are used to control or limit oxidation of the molten aluminum. These elements are regarded as trace elements or impurities with additions typically less than 0.01%, with preferred additions less than about 100 ppm, e.g., 10 to 80 ppm of Ca and/or up to about 20 ppm of Be.
  • the 2XXX-series aluminum alloy wrought products processed in accordance with the methods described herein are products being hot worked after casting, and includes rolled products (i.e. sheet or plate), extruded products, and forged products. Forged products are either die forged or hand forged.
  • the 2XXX-series aluminum alloy wrought product processed or manufactured in accordance with the method described herein is in the form of thin gauge plate product having a cross-sectional thickness in the range of 1.6 mm to 12 mm (e.g., 1.7 mm to 12 mm, 1.6 mm to 11.9 mm, 1.7 mm to 11 mm, 1.6 mm to 8 mm, 2 mm to 12 mm, 2 mm to 10 mm, or 2.5 mm to 9.5 mm).
  • the 2XXX-series aluminum alloy wrought product processed or manufactured in accordance with the invention is a thick product with a cross-sectional thickness of at least 12 mm.
  • the wrought product may be rolled product, forged product or extruded product.
  • the thick wrought product is a plate product having a cross-sectional thickness of at least 12 mm, and preferably of at least 25 mm.
  • the thick wrought product is a plate product having a cross-sectional thickness of at least 38 mm.
  • the improved properties described herein may be achieved with thick wrought products having a cross-sectional thickness of up to 250 mm.
  • the thick wrought product is a plate product having a cross-sectional thickness of up to 250 mm.
  • the thick wrought product is a plate product having a cross-sectional thickness of up to 180 mm. In yet another embodiment, the thick wrought product is a plate product having a cross-sectional thickness of up to 130 mm.
  • thickness refers to the minimum thickness of the product, realizing that some portions of the product may legalize slightly larger thicknesses than the minimum stated.
  • the 2XXX-series aluminum alloy product has a thickness in the range of 1.6 mm to 12 mm and realises a conventional yield strength (in MPa) measured in the longitudinal direction relative to the rolling direction (i.e., L-direction) of more than 400 MPa.
  • the 2XXX-series aluminum alloy product has a thickness in the range of 1.6 mm to 12 mm and achieves an improved intergranular corrosion (IGC) resistance measured without cladding showing predominantly pitting attack and negligent IGC (e.g., pitting attack accounts for greater than 50% of the total corrosion attack, preferably greater than 70%, and more preferably greater than 90%).
  • IGC intergranular corrosion
  • a wrought 2XXX-series aluminum alloy product optionally having a clad layer on at least one side, or on two sides, of the wrought aluminum alloy product.
  • the wrought aluminum alloy product can have a cross-sectional thickness from 1.6 mm to 12 mm (and preferably from 1.6 mm to 8 mm) and can be aged according to the methods described herein to achieve a conventional tensile yield strength (in MPa) measured in the L-direction of more than 400 MPa and/or an improved IGC resistance measured without cladding showing predominantly pitting attack and negligent IGC.
  • a conventional tensile yield strength in MPa
  • IGC resistance measured without cladding showing predominantly pitting attack and negligent IGC.
  • the 2XXX-series aluminum alloy product has a thickness of at least 12 mm and achieves a minimum life without failure due to stress corrosion cracking (SCC) measured in accordance with ASTM G47-98 of at least 20 days preferably at least 25 days) at a short transverse (ST) stress level of 250 MPa.
  • SCC stress corrosion cracking
  • ST short transverse
  • the wrought aluminum alloy product having a thickness of 12 mm to 250 mm can be aged according to the methods described herein to achieve a conventional tensile yield strength measured in the L-direction at quarter thickness of more than 380 MPa + 0.57 (120-t) MPa (where t is the quarter thickness of the wrought aluminum alloy product in mm). Additionally, the wrought aluminum alloy product can exhibit a minimum service life without failure due to stress corrosion cracking in accordance with ASTM G47 of at least 20 days (preferably of at least 25 days) at a short transverse stress level of 250 MPa.
  • the 2XXX-series aluminum alloy product has a thickness of at least 12 mm and achieves a conventional tensile yield strength (in MPa) measured in the L-direction at quarter thickness of more than 380 MPa + 0.57 (120-t) MPa (t being the thickness of the product in mm).
  • the wrought aluminum alloy product can be a wrought 2XXX-series aluminum alloy product having a cross-sectional thickness from 12 mm to 250 mm (preferably from 12 mm to 130 mm) and can be aged according to the methods described herein to achieve a conventional tensile yield strength measured in the L-direction at a quarter thickness of more than 380 MPa + 0.57 (120-t) MPa.
  • the wrought aluminum alloy product can further exhibit an improved IGC resistance measured without cladding showing a predominantly pitting-type corrosion attack and negligent IGC.
  • the disclosure also includes embodiments in which the 2XXX-series wrought product may be provided with a cladding, in particular for the thinner gauge rolled product.
  • clad products utilize a core of the 2XXX-series aluminum base alloy and a cladding of usually higher purity which in particular further corrosion protects the 2XXX-series aluminum alloy core.
  • the cladding includes, but is not limited to, essentially unalloyed aluminum or aluminum containing not more than 0.1% or 1% of all other elements.
  • Aluminum alloys herein designated as 1xxx-type series include all Aluminum Association (AA) alloys, including the sub-classes of the 1000-type, 1100-type, 1200-type, and 1300-type.
  • AA Aluminum Association
  • the cladding on the core may be selected from alloys such as 1060, 1045, 1100, 1200, 1230, 1135, 1235, 1435, 1145, 1345, 1250, 1350, 1170, 1175, 1180, 1185, 1285, 1188, or 1199.
  • alloys of the AA7000-series alloys such as 7072 containing zinc (0.8 to 1.3%) can serve as the cladding and alloys of the AA6000-series alloys, such as 6003 or 6253, which contain typically more than 1% of alloying additions, can serve as cladding.
  • Other alloys could also be useful as cladding as long as they provide in particular sufficient overall corrosion protection to the core alloy.
  • the clad layer or layers are usually much thinner than the core, each constituting 1% to 15% of the total composite thickness.
  • a cladding layer more typically constitutes around 1% to 10% of the total composite thickness.
  • a method of producing a 2XXX-series aluminum alloy wrought product comprising the steps, in the following order, of:
  • the artificial aging comprises the steps of, in the following order: (1) aging the product in a first aging step at one or more temperatures within a range of 90 °C to 120 °C for a cumulative period of time of at least 10 hours; and (2) subsequently aging the product in a second aging step at one or more temperatures within a range of 160 °C to 190 °C for a cumulative period of time of at least 4 hours.
  • the 2XXX-series aluminum alloy can be provided as an ingot or slab or billet for fabrication into a suitable wrought product by casting techniques regular in the art for cast products, e.g., direct-chill (DC)-casting, electro-magnetic-casting (EMC)-casting, or electro-magnetic-stirring (EMS)-casting.
  • DC direct-chill
  • EMC electro-magnetic-casting
  • EMS electro-magnetic-stirring
  • Slabs resulting from continuous casting e.g., belt casters or roll casters, also may be used, which in particular may be advantageous when producing thinner gauge (e.g., up to 12 mm thick) rolled end products.
  • Grain refiners such as those containing Ti and B, or Ti and C, may also be used as is well known in the art.
  • the Ti content in the aluminum alloy is preferably in a range of 0.01% to 0.12%.
  • Ti can be added as a sole element or with either boron or carbon serving as a casting aid, for grain size control. After casting the aluminum alloy ingot it is commonly scalped to remove segregation zones near the as-cast surface of the ingot.
  • a homogenization heat treatment has at least the following objectives: (i) to dissolve as many as possible coarse soluble phases formed during solidification, and (ii) to reduce concentration gradients to facilitate the dissolution step.
  • a preheat treatment achieves also some of these objectives.
  • a typical preheat treatment for 2xxx-series alloys would be a temperature of about 420 °C to 505 °C with a soaking time in the range of about 3 to 50 hours, more typically for about 3 to 20 hours.
  • a common homogenization and/or preheating process can also be done in one or more steps if desired, and which are typically carried out in a temperature range of about 400 °C to 505 °C.
  • a two-step process there is a first step between about 480 °C and 500 °C, and a second step between about 450 °C and 490 °C, to optimize the dissolving process of the various phases depending on the exact alloy composition.
  • the segregation of alloying elements in the as-cast ingot is reduced and soluble elements are dissolved.
  • the treatment is carried out below 400 °C, the resultant homogenization effect is inadequate.
  • the temperature is above 505 °C, eutectic melting might occur resulting in undesirable pore formation.
  • the soaking time at the homogenization temperature is in the range of about 1 to 50 hours, and more typically for about 2 to 20 hours.
  • the heat-up rates that can be applied are those which are regular in the art.
  • the stock is hot worked by one or more methods selected from the group consisting of rolling, extrusion, and forging.
  • the method of hot rolling is preferred for the present invention.
  • the plate material is hot rolled to final hot rolled thickness.
  • the hot working step can be performed to provide stock at intermediate thickness. Thereafter, this stock at intermediate thickness can be cold worked, e.g., by means of rolling, to a thinner thickness. Depending on the amount of cold work an intermediate anneal may be used before or during the cold working operation.
  • a next process step is solution heat treating ("SHT") of the hot worked product and optionally cold worked product.
  • the product should be heated to bring as much as possible all or substantially all portions of the soluble Cu, Mg, and the optional Ag into solution.
  • SHT is preferably carried out in the temperature range of about 450 °C to 505 °C for a time sufficient for solution effects to approach equilibrium, with typical soaking times in the range of about 5 minutes to 300 minutes, more preferably in a range of about 5 minutes to 120 minutes.
  • the solution heat treatment is typically carried out in a batch furnace.
  • the aluminum alloy product be cooled with a high cooling rate to a temperature of about 100 °C or lower, preferably to ambient temperature, to prevent or minimize the uncontrolled precipitation of secondary phases, e.g., Al 2 CuMg and Al 2 Cu.
  • Cooling rates should preferably not be too high to allow for a sufficient flatness and acceptable level of residual stresses in the product. Suitable cooling rates can be achieved with the use of water, e.g., water immersion or water jets.
  • the SHT and quenched product may be further cold worked.
  • Cold working means working or forming the aluminum alloy product at temperatures that are not considered hot working temperatures, generally below about 120 °C (e.g., at ambient temperature).
  • Stretched and/or stretching can be done to develop adequate strength, relieve internal stresses, and/or straighten the product.
  • stretching in the range of about 0.5% to 11% of its original length can be performed to relieve residual stresses therein and to improve the flatness of the product.
  • the stretching is in the range of about 0.5% to 6%, more preferably of about 1% to 3%.
  • the SHT and quenched product is naturally aged, for example to a T3X temper, e.g., T39 or T351, and is subsequently subjected to a cold deformation or cold forming process by for example an aircraft manufacturer or supplier to produce a structural component.
  • a cold working operation includes, but is not limited to, a bending operation, a roll forming operation, or an electrohydraulic forming operation.
  • the cold deformation step can be performed by stretching, cold compression, bending, rolling, roll forming, or whatever quasi-static or higher speed cold deformation (quasi static speed below 0.008 s-1 typically, higher speed for example typically up to 100 to 150 s-1 max or higher) with a total range of deformation typically up to 10% max but not limited to that.
  • the wrought product is artificially aged in accordance with the methods as herein described and/or claimed to increase strength and to achieve improved metallurgical properties, e.g., SCC resistance.
  • the SHT, quench, cold working, and the artificial aging in accordance with the methods described herein are also used in the manufacture of sections made by extrusion or forged processing steps.
  • Another aspect of the disclosure relates to an aircraft structural member made from the 2XXX-series aluminum alloy wrought product manufactured and aged in accordance with the methods described herein.
  • the 2XXX-series aluminum alloy product manufactured according to these methods can be used, amongst other uses, in the thickness range of up to about 12 mm to have properties that will be excellent for fuselage sheet.
  • the properties will be excellent for wing plate, e.g., lower wing plate.
  • the thin plate thickness range can be used also for stringers or to form an integral wing panel and stringer for use in an aircraft wing structure.
  • excellent properties have been obtained for integral part machined from plates, or to form an integral spar for use in an aircraft wing structure, or in the form of a rib for use in an aircraft wing structure.
  • the thicker gauge products can be used also as tooling plate, e.g., moulds for manufacturing formed plastic products, for example via die-casting or injection moulding.
  • the alloy products as described herein can also be provided in the form of a stepped extrusion or extruded spar for use in an aircraft structure, or in the form of a forged spar for use in an aircraft wing structure.
  • a 33 mm thick plate material was manufactured by DC-casting of an ingot having a chemical composition as set out in Table 1.
  • the ingot was homogenised for 21 hours at 495 °C and subsequently hot rolled from a thickness of about 400 mm to 33 mm.
  • the plate material was solution heat treated for 2 hours at 495 °C on laboratory scale; cooled down by a water quench; and subsequently artificially aged to a T8 temper using various aging practices, both according to standard industrial practice and according to the methods described herein see Table 2.
  • aging practice 1 is a standard aging practice for arriving at a T8 condition
  • aging practice 2 is a second industrial practice
  • aging practice 3 is according to the methods described herein.
  • a 120 mm thick plate material was manufactured by DC-casting of an ingot having a chemical composition as set out in Table 4.
  • the ingot was homogenized for 36 hours at 495 °C and subsequently hot rolled from a thickness of about 430 mm to 120 mm.
  • the plate material was solution heat treated for 6 hours at 495 °C on production scale; cooled down by a water quench; stretched by 1.4% cold deformation in the L-direction, and was subsequently artificially aged to a T8 temper using an aging practice as described herein and outlined in Table 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)
  • Forging (AREA)
  • Continuous Casting (AREA)
  • Extrusion Of Metal (AREA)
  • Heat Treatment Of Steel (AREA)

Claims (12)

  1. Alterungsprozess eines lösungsgeglühten und abgeschreckten Aluminiumlegierungs-Knetprodukts der 2XXX-Serie, umfassend die Schritte aus:
    (1) Altern des Produkts in einem ersten Alterungsschritt bei einer oder mehreren Temperaturen innerhalb eines Bereichs von 90 °C bis 120 °C für eine kumulative Zeitspanne von mindestens 10 Stunden; und
    (2) anschließendem Altern des Produkts in einem zweiten Alterungsschritt bei einer oder mehreren Temperaturen innerhalb eines Bereichs von 160 °C bis 190 °C für eine kumulative Zeitspanne von mindestens 4 Stunden, wobei das Aluminiumlegierungs-Knetprodukt der 2XXX-Serie in Gew.-% umfasst: Cu 3,5 % bis 5,5 %; Mn 0,15 % bis 1,0 %; Mg 0,2 % bis 1,8 %; Ag bis zu 0,7 %; Zn bis zu 1,0 %; Fe bis zu 0,3 %; Si bis zu 0,2 %; Ti 0,01 % bis 0,2 %;
    gegebenenfalls eines oder mehrere Dispersoid-bildende Elemente ausgewählt aus der Gruppe bestehend aus 0,05 % bis 0,25 % Cr, 0,05 % bis 0,25 % Zr, 0,05 % bis 0,25 % V, 0,05 % bis 0,4 % Hf, 0,05 % bis 0,4 % Sc, vorzugsweise 0,05 % bis 0,2 % Cr, 0,05 % bis 0,15 % Zr, 0,05 % bis 0,15 % V, 0,05 % bis 0,25 % Hf, 0,05 % bis 0,25 % Sc; Verunreinigungen bis zu 0,15 %; und Rest Aluminium.
  2. Alterungsprozess nach Anspruch 1, wobei der Alterungsprozess ein lösungsgeglühtes, abgeschrecktes, und anschließend kaltbearbeitetes oder kaltgeformtes Aluminiumlegierungsprodukt der 2XXX-Serie betrifft.
  3. Alterungsprozess nach Anspruch 1 oder 2, wobei Kaltbearbeitung in einem oder mehreren Kaltbearbeitungsschritten angewendet wird, welche nach Lösungsglühen und Abschrecken angewendet werden, gegebenenfalls nach weiterem natürlichem Altern, und entweder vor endgültigem künstlichem Altern oder zwischen den zwei künstlichen Alterungsschritten.
  4. Alterungsprozess nach einem der Ansprüche 1 bis 3, wobei das Abschrecken vom Lösungsglühen für eine Platte in einem Dickenbereich von 1,6 bis 12 mm bei einer Rate zwischen 100 °C/min und 1000 °C/min durchgeführt wird, insbesondere wobei das Abschrecken vom Lösungsglühen für eine Platte in einem Dickenbereich von 1,6 bis 12 mm bei einer Rate zwischen 200 °C/min und 600 °C/min durchgeführt wird.
  5. Alterungsprozess nach Anspruch 1 oder 2, wobei der Alterungsprozess ein bearbeitetes Produkt betrifft, um ein Knetprodukt, lösungsgeglühtes, abgeschrecktes, und anschließend kaltbearbeitetes oder kaltgeformtes Aluminiumlegierungsprodukt der 2XXX-Serie bereitzustellen.
  6. Alterungsprozess nach einem der Ansprüche 1 bis 5, wobei der zweite Alterungsschritt für eine kumulative Zeitspanne von mindestens 12 Stunden andauert; und insbesondere wobei der zweite Alterungsschritt für eine kumulative Zeitspann von 12 Stunden bis 144 Stunden andauert.
  7. Alterungsprozess nach einem der Ansprüche 1 bis 6, wobei die Aluminiumlegierung der 2XXX-Serie Ag in einem Bereich von 0,1 % bis 0,7 %, und vorzugsweise in einem Bereich von 0,2 % bis 0,7 %, umfasst.
  8. Alterungsprozess nach einem der Ansprüche 1 bis 7, wobei die Aluminiumlegierung der 2XXX-Serie einen Cu-Gehalt in einem Bereich von 3,5 % bis 4,4 % umfasst.
  9. Alterungsprozess nach einem der Ansprüche 1 bis 7, wobei die Aluminiumlegierung der 2XXX-Serie einen Cu-Gehalt in einem Bereich von 4,4 % bis 5,5 % umfasst; und insbesondere, wobei die Aluminiumlegierung der 2XXX-Serie einen Cu-Gehalt in einem Bereich von 4,4 % bis 5,1 % umfasst.
  10. Alterungsprozess nach einem der Ansprüche 1 bis 9, wobei die Aluminiumlegierung der 2XXX-Serie als ein gewalztes Produkt bereitgestellt wird; und/oder wobei das Aluminiumlegierungsprodukt der 2XXX-Serie ein Flugzeugstrukturelement ist.
  11. Verfahren zum Herstellen eines Aluminiumlegierungs-Knetprodukts der 2XXX-Serie, wobei das Verfahren die folgenden Schritte umfasst:
    (i) Gießen eines Barrens einer Aluminiumlegierung der 2XXX-Serie mit einer Zusammensetzung nach einem der Ansprüche 1 und 7 bis 9;
    (ii) Vorheizen und/oder Homogenisieren des Barrens;
    (iii) Heißbearbeiten des Barrens durch eine oder mehrere Verfahren ausgewählt aus der Gruppe bestehend aus Walzen, Extrusion, und Schmieden in ein heißbearbeitetes Knetprodukt
    (iv) gegebenenfalls Kaltbearbeiten des heißbearbeiteten Knetprodukts;
    (v) Lösungsglühen, SHT, des Knetprodukts;
    (vi) rasches Abkühlen oder Abschrecken des SHT-Produkts;
    (vii) gegebenenfalls Kaltbearbeiten oder Kaltformen des SHT und abgeschreckten Produkts; und
    (viii) künstliches Altern nach einem der Ansprüche 1 bis 5 des SHT, abgeschreckten Produkts und gegebenenfalls Kaltbearbeiten oder Kaltformen.
  12. Geknetetes Aluminiumlegierungsprodukt der 2XXX-Serie nach Anspruch 11, wobei das Produkt eine Querschnittsdicke von 12 mm bis 250 mm, und vorzugsweise von 12 mm bis 130 mm, aufweist und wobei das Produkt eine minimale Lebensdauer ohne Defekt aufgrund von Spannungsrisskorrosion gemäß ASTM G47 von mindestens 20 Tagen, bevorzugt von mindestens 25 Tagen, bei einem Kurztransversalspannungsniveau von 250 MPa vorzeigt.
EP21816164.4A 2020-11-20 2021-11-19 Verfahren zur herstellung von aluminiumlegierungsprodukten der reihe 2xxx Active EP4247991B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US202063198906P 2020-11-20 2020-11-20
PCT/IB2021/060749 WO2022107065A1 (en) 2020-11-20 2021-11-19 Method of manufacturing 2xxx-series aluminum alloy products

Publications (2)

Publication Number Publication Date
EP4247991A1 EP4247991A1 (de) 2023-09-27
EP4247991B1 true EP4247991B1 (de) 2025-10-22

Family

ID=78819578

Family Applications (1)

Application Number Title Priority Date Filing Date
EP21816164.4A Active EP4247991B1 (de) 2020-11-20 2021-11-19 Verfahren zur herstellung von aluminiumlegierungsprodukten der reihe 2xxx

Country Status (10)

Country Link
US (1) US20240102141A1 (de)
EP (1) EP4247991B1 (de)
JP (1) JP2023549190A (de)
KR (1) KR20230106180A (de)
CN (1) CN116529412A (de)
BR (1) BR112023006092A2 (de)
CA (1) CA3199970A1 (de)
ES (1) ES3053222T3 (de)
PT (1) PT4247991T (de)
WO (1) WO2022107065A1 (de)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115261752B (zh) * 2022-07-20 2023-07-18 重庆大学 一种高强2024铝合金加工工艺及高强2024铝合金
JP2025062287A (ja) * 2023-10-02 2025-04-14 株式会社レゾナック アルミニウム部材の特性予測方法
CN119736505B (zh) * 2024-12-24 2026-01-23 东北轻合金有限责任公司 一种2系航天用超高强度铝合金厚板的制备方法

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103981410A (zh) * 2014-05-27 2014-08-13 中南大学 一种高耐损伤铝合金及其制备方法
CN106521270A (zh) * 2016-12-07 2017-03-22 中国航空工业集团公司北京航空材料研究院 一种改善铝锂合金耐腐蚀性能的热处理工艺

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5137019A (ja) * 1974-09-24 1976-03-29 Sumitomo Light Metal Ind Korikiaruminiumugokin no kyojinkahoho
JPH0814018B2 (ja) * 1987-12-14 1996-02-14 アルミニウム カンパニー オブ アメリカ アルミニウム合金の熱処理方法
US4861391A (en) * 1987-12-14 1989-08-29 Aluminum Company Of America Aluminum alloy two-step aging method and article
US8043445B2 (en) * 2003-06-06 2011-10-25 Aleris Aluminum Koblenz Gmbh High-damage tolerant alloy product in particular for aerospace applications
US7449073B2 (en) * 2004-07-15 2008-11-11 Alcoa Inc. 2000 Series alloys with enhanced damage tolerance performance for aerospace applications
US7547366B2 (en) * 2004-07-15 2009-06-16 Alcoa Inc. 2000 Series alloys with enhanced damage tolerance performance for aerospace applications
WO2009073794A1 (en) * 2007-12-04 2009-06-11 Alcoa Inc. Improved aluminum-copper-lithium alloys
WO2018144568A1 (en) * 2017-01-31 2018-08-09 Universal Alloy Corporation Low density aluminum-copper-lithium alloy extrusions
CN112996941A (zh) * 2018-11-12 2021-06-18 诺维尔里斯公司 快速老化的高强度可热处理的铝合金产品以及其制造方法
CN110423966B (zh) * 2019-07-29 2020-09-22 中国航发北京航空材料研究院 一种提高铝锂合金产品综合性能的制备工艺
CN111424200B (zh) * 2020-04-23 2021-10-08 西安交通大学 一种高强高耐热低钪银添加的Al-Cu-Mg系合金及其热处理工艺

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103981410A (zh) * 2014-05-27 2014-08-13 中南大学 一种高耐损伤铝合金及其制备方法
CN106521270A (zh) * 2016-12-07 2017-03-22 中国航空工业集团公司北京航空材料研究院 一种改善铝锂合金耐腐蚀性能的热处理工艺

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
DAVIS J R: "Aluminum and Aluminum Alloys, FORGING", ASM SPECIALTY HANDBOOK. ALUMINUM AND ALUMINUM ALLOYS, XX, XX, 1 March 1996 (1996-03-01), pages 247 - 249, 254, XP002227160 *

Also Published As

Publication number Publication date
US20240102141A1 (en) 2024-03-28
BR112023006092A2 (pt) 2024-03-12
WO2022107065A1 (en) 2022-05-27
ES3053222T3 (en) 2026-01-20
KR20230106180A (ko) 2023-07-12
EP4247991A1 (de) 2023-09-27
PT4247991T (pt) 2025-11-19
JP2023549190A (ja) 2023-11-22
CA3199970A1 (en) 2022-05-27
CN116529412A (zh) 2023-08-01

Similar Documents

Publication Publication Date Title
EP2038446B1 (de) Verfahren zur Herstellung von Al-Legierungen der AA7000-Serie
EP3833794B1 (de) Produkt aus einer 7xxx serien aluminiumlegierung
EP2288738B1 (de) Al-zn-mg-legierungsprodukt mit verringerter quetschempfindlichkeit
US8608876B2 (en) AA7000-series aluminum alloy products and a method of manufacturing thereof
CA2700250C (en) Al-cu-li alloy product suitable for aerospace application
EP2121997B1 (de) Al-cu-legierungsprodukt, das für die luft- und raumfahrtanwendung geeignet ist
EP3911777B1 (de) 7xxx-serien-aluminiumlegierungsprodukt
EP3414352B1 (de) Aus al-cu-li-mg-mn-zn-legierung geschmiedetes produkt
EP4247991B1 (de) Verfahren zur herstellung von aluminiumlegierungsprodukten der reihe 2xxx
RU2826059C1 (ru) Способ изготовления изделий из алюминиевого сплава серии 2xxx

Legal Events

Date Code Title Description
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: UNKNOWN

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

Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE

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

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

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20230509

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

DAV Request for validation of the european patent (deleted)
DAX Request for extension of the european patent (deleted)
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20240403

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20250130

GRAJ Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted

Free format text: ORIGINAL CODE: EPIDOSDIGR1

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

Free format text: STATUS: EXAMINATION IS IN PROGRESS

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTC Intention to grant announced (deleted)
INTG Intention to grant announced

Effective date: 20250612

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

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

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

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

Free format text: CASE NUMBER: UPC_APP_4167_4247991/2025

Effective date: 20250825

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: CH

Ref legal event code: F10

Free format text: ST27 STATUS EVENT CODE: U-0-0-F10-F00 (AS PROVIDED BY THE NATIONAL OFFICE)

Effective date: 20251022

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602021040919

Country of ref document: DE

REG Reference to a national code

Ref country code: CH

Ref legal event code: R17

Free format text: ST27 STATUS EVENT CODE: U-0-0-R10-R17 (AS PROVIDED BY THE NATIONAL OFFICE)

Effective date: 20251118

REG Reference to a national code

Ref country code: PT

Ref legal event code: SC4A

Ref document number: 4247991

Country of ref document: PT

Date of ref document: 20251119

Kind code of ref document: T

Free format text: AVAILABILITY OF NATIONAL TRANSLATION

Effective date: 20251113

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: CH

Ref legal event code: U11

Free format text: ST27 STATUS EVENT CODE: U-0-0-U10-U11 (AS PROVIDED BY THE NATIONAL OFFICE)

Effective date: 20251201

REG Reference to a national code

Ref country code: NL

Ref legal event code: FP

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

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

Ref country code: NL

Payment date: 20251119

Year of fee payment: 5

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

Ref country code: DE

Payment date: 20251009

Year of fee payment: 5

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

Ref country code: GB

Payment date: 20251119

Year of fee payment: 5

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

Ref country code: PT

Payment date: 20251222

Year of fee payment: 5

Ref country code: AT

Payment date: 20260113

Year of fee payment: 5

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

Ref country code: FR

Payment date: 20251119

Year of fee payment: 5

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

Ref country code: BE

Payment date: 20251119

Year of fee payment: 5

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

Ref country code: SE

Payment date: 20251022

Year of fee payment: 5

Ref country code: CH

Payment date: 20251201

Year of fee payment: 5

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 3053222

Country of ref document: ES

Kind code of ref document: T3

Effective date: 20260120

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

Ref country code: ES

Payment date: 20251204

Year of fee payment: 5

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG9D

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

Ref country code: NO

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: 20260122

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

Ref country code: HR

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: 20251022

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: 20251022

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

Ref country code: RS

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: 20260122

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

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: 20260222

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: 20251022

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

Ref country code: LV

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: 20251022