EP2971213B1 - Improved aluminum-magnesium-lithium alloys, and methods for producing the same - Google Patents
Improved aluminum-magnesium-lithium alloys, and methods for producing the same Download PDFInfo
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- EP2971213B1 EP2971213B1 EP14775660.5A EP14775660A EP2971213B1 EP 2971213 B1 EP2971213 B1 EP 2971213B1 EP 14775660 A EP14775660 A EP 14775660A EP 2971213 B1 EP2971213 B1 EP 2971213B1
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- 238000000034 method Methods 0.000 title claims description 13
- VCHVXUQQZMQWIY-UHFFFAOYSA-N [AlH3].[Mg].[Li] Chemical compound [AlH3].[Mg].[Li] VCHVXUQQZMQWIY-UHFFFAOYSA-N 0.000 title description 4
- 229910000733 Li alloy Inorganic materials 0.000 title description 2
- 239000001989 lithium alloy Substances 0.000 title description 2
- 229910000838 Al alloy Inorganic materials 0.000 claims description 147
- 238000005097 cold rolling Methods 0.000 claims description 34
- 229910052744 lithium Inorganic materials 0.000 claims description 32
- 229910052725 zinc Inorganic materials 0.000 claims description 29
- 229910052749 magnesium Inorganic materials 0.000 claims description 25
- 229910052802 copper Inorganic materials 0.000 claims description 24
- 229910052748 manganese Inorganic materials 0.000 claims description 21
- 229910052710 silicon Inorganic materials 0.000 claims description 20
- 229910052709 silver Inorganic materials 0.000 claims description 17
- 229910052726 zirconium Inorganic materials 0.000 claims description 16
- 229910052742 iron Inorganic materials 0.000 claims description 14
- 238000005098 hot rolling Methods 0.000 claims description 13
- 229910052706 scandium Inorganic materials 0.000 claims description 12
- 229910052719 titanium Inorganic materials 0.000 claims description 12
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 11
- 229910052782 aluminium Inorganic materials 0.000 claims description 11
- 229910052761 rare earth metal Inorganic materials 0.000 claims description 11
- 229910052804 chromium Inorganic materials 0.000 claims description 10
- 229910052735 hafnium Inorganic materials 0.000 claims description 9
- 229910052720 vanadium Inorganic materials 0.000 claims description 9
- 238000005266 casting Methods 0.000 claims description 5
- 239000012535 impurity Substances 0.000 claims description 5
- 238000010791 quenching Methods 0.000 claims description 3
- 238000007669 thermal treatment Methods 0.000 claims description 3
- 238000001816 cooling Methods 0.000 claims 9
- 239000013067 intermediate product Substances 0.000 claims 5
- 230000000171 quenching effect Effects 0.000 claims 2
- 230000032683 aging Effects 0.000 claims 1
- 229910045601 alloy Inorganic materials 0.000 description 119
- 239000000956 alloy Substances 0.000 description 119
- 238000005260 corrosion Methods 0.000 description 27
- 230000007797 corrosion Effects 0.000 description 27
- 239000011701 zinc Substances 0.000 description 20
- 239000010949 copper Substances 0.000 description 18
- 239000011777 magnesium Substances 0.000 description 17
- 239000011572 manganese Substances 0.000 description 17
- XEEYBQQBJWHFJM-UHFFFAOYSA-N iron Substances [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 14
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 description 9
- 239000011651 chromium Substances 0.000 description 9
- 239000010936 titanium Substances 0.000 description 9
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 8
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 7
- 239000000203 mixture Substances 0.000 description 7
- 239000010703 silicon Substances 0.000 description 7
- 102100027446 Acetylserotonin O-methyltransferase Human genes 0.000 description 6
- 101000936718 Homo sapiens Acetylserotonin O-methyltransferase Proteins 0.000 description 6
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 6
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 5
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 description 5
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 description 5
- 239000004332 silver Substances 0.000 description 5
- 229910000599 Cr alloy Inorganic materials 0.000 description 4
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 4
- 239000000470 constituent Substances 0.000 description 4
- 230000003247 decreasing effect Effects 0.000 description 4
- 239000002245 particle Substances 0.000 description 4
- SIXSYDAISGFNSX-UHFFFAOYSA-N scandium atom Chemical compound [Sc] SIXSYDAISGFNSX-UHFFFAOYSA-N 0.000 description 4
- 229910001316 Ag alloy Inorganic materials 0.000 description 3
- 229910000861 Mg alloy Inorganic materials 0.000 description 3
- 238000004299 exfoliation Methods 0.000 description 3
- 238000005242 forging Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 2
- 229910017518 Cu Zn Inorganic materials 0.000 description 2
- 238000005275 alloying Methods 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 230000001627 detrimental effect Effects 0.000 description 2
- 238000001125 extrusion Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 238000000265 homogenisation Methods 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 230000000593 degrading effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 238000001953 recrystallisation Methods 0.000 description 1
- 238000007670 refining Methods 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- VSZWPYCFIRKVQL-UHFFFAOYSA-N selanylidenegallium;selenium Chemical compound [Se].[Se]=[Ga].[Se]=[Ga] VSZWPYCFIRKVQL-UHFFFAOYSA-N 0.000 description 1
- 239000003381 stabilizer Substances 0.000 description 1
- 239000003351 stiffener Substances 0.000 description 1
Images
Classifications
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
- C22F1/047—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 magnesium 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
- C22C21/06—Alloys based on aluminium with magnesium 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
-
- 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
- Aluminum alloys are useful in a variety of applications. However, improving one property of an aluminum alloy without degrading another property is elusive. For example, it is difficult to increase the strength of an alloy without decreasing the toughness of an alloy. Other properties of interest for aluminum alloys include corrosion resistance and fatigue resistance, to name two.
- GB 2 146 353 discloses alloys consisting essentially of, by weight, 1.0 to 8.0 of Mg, 0.05 to 1.0 % of Li, at least one element selected from the group consisting of 0.05 to 0.20% of Ti, 0.05 to 0,40% of Cr, 0.05 to 0.30% of Zr, 0.05 to 0.35% of V, 0.05 to 0.30% of W and 0.05 to 2.0% of Mn, and the balance being aluminum and incidental impurities. Further, Bi in the range of 0.05 to 0.50 wt.% may be contained in said alloy.
- the present patent application relates to new aluminum-magnesium-lithium alloys, and methods for producing the same, as defined in claims 1 and 6.
- the new aluminum-magnesium-lithium generally alloys contain 2.0 to 3.9 wt. % Mg. Magnesium may help improve strength, but too much magnesium may degrade corrosion resistance.
- the new alloys include at least 2.25 wt. % Mg.
- the new alloys contain at least 2.5 wt. % Mg.
- the new alloys include at least 2.75 wt. % Mg.
- the new alloys include not greater than 3.75 wt. % Mg.
- the new alloys include not greater than 3.5 wt. % Mg.
- the new alloys include not greater than 3.25 wt. % Mg.
- the new aluminum-magnesium-lithium generally contain 0.1 to 1.8 wt. % Li. Lithium helps reduce density and may help improve strength, but too much lithium may reduce ductility.
- the new alloys include at least 0.4 wt. % Li. In another embodiment, the new alloys include at least 0.6 wt. % Li. In yet another embodiment, the new alloys include at least 0.8 wt. % Li. In another embodiment, the new alloys include at least 1.0 wt. % Li. In yet another embodiment, the new alloys include at least 1.05 wt. % Li. In another embodiment, the new alloys include at least 1.10 wt. % Li.
- the new alloys include at least 1.20 wt. % Li. In one embodiment, the new alloys include not greater than 1.5 wt. % Li. In another embodiment, the new alloys include not greater than 1.45 wt. % Li. In yet another embodiment, the new alloys include not greater than 1.4 wt. % Li.
- the new alloys may contain up to 1.5 wt. % Cu. Copper may improve strength but increases density. In one embodiment, the new alloys contain not greater than 1.0 wt. % Cu. In another embodiment, the new alloys contain not greater than 0.9 wt. % Cu. In yet another embodiment, the new alloys contain not greater than 0.6 wt. % Cu. In another embodiment, the new alloys contain not greater than 0.5 wt. % Cu. In embodiments where copper is used, the new alloys generally contain at least 0.05 wt. % Cu. In one embodiment, the new alloys include at least 0.10 wt. % Cu. In embodiments where copper is not used, the new alloys include less than 0.05 wt. % Cu.
- the new alloys may contain up to 2.0 wt. % Zn when Mg is within 2.5 - 3.9 wt.-% and Li is within 1.05 and 1.8 wt.-%. Alternatively, the new alloys generally contain 0.4 to 2.0 wt.-% Zn. Zinc may improve strength, but increases density. In one embodiment, the new alloys contain not greater than 1.5 wt. % Zn. In another embodiment, the new alloys contain not greater than 1.0 wt. % Zn. In embodiments where zinc is used, the new alloys generally contain at least 0.20 wt. % Zn. In one embodiment, the new alloys contain at least 0.4 wt. % Zn. In another embodiment, the new alloys contain at least 0.5 wt. % Zn. In embodiments where zinc is not used, the new alloys include less than 0.20 wt. % Zn.
- the new alloys may contain up to 1.5 wt. % Mn. Manganese may improve strength, but increases density. In one embodiment, the new alloys contain not greater than 1.0 wt. % Mn. In another embodiment, the new alloys contain not greater than 0.9 wt. % Mn. In yet another embodiment, the new alloys contain not greater than 0.7 wt. % Mn. In embodiments where manganese is used, the new alloys generally contain at least 0.05 wt. % Mn. In one embodiment, the new alloys include at least 0.20 wt. % Mn. In embodiments where manganese is not used, the new alloys include not greater than 0.04 wt. % Mn.
- the new alloys may contain up to 1.0 wt. % Ag. Silver may improve strength, but silver decreases density and is expensive. In one embodiment, the new alloys contain not greater than 0.9 wt. % Ag. In another embodiment, the new alloys contain not greater than 0.6 wt. % Ag. In embodiments where silver is used, the new alloys generally contain at least 0.05 wt. % Ag. In one embodiment, the new alloys include at least 0.20 wt. % Ag. In embodiments where silver is not used, the new alloys include not greater than 0.04 wt. % Ag.
- the new alloys may contain up to 0.5 wt. % Si. Silicon may improve corrosion resistance, but may decrease fracture toughness. In one embodiment, the new alloys contain not greater than 0.35 wt. % Si. In another embodiment, the new alloys contain not greater than 0.25 wt. % Si. In embodiments where silicon is used, the new alloys generally contain at least 0.10 wt. % Si. In embodiments where silicon is not used, the new alloys include not greater than 0.09 wt. % Si.
- the new alloys may optionally include at least one secondary element selected from the group consisting of Zr, Sc, Cr, Hf, V, Ti, and rare earth elements. Such elements may be used, for instance, to facilitate the appropriate grain structure in the resultant aluminum alloy product.
- the secondary elements may optionally be present as follows: up to 0.20 wt. % Zr, up to 0.30 wt. % Sc, up to 0.50 wt. % of Cr, up to 0.25 wt. % each of any of Hf, V, and rare earth elements, and up to 0.10 wt. % Ti.
- Zirconium (Zr) and/or scandium are preferred for grain structure control.
- the new aluminum alloys When zirconium is used, it is generally included in the new aluminum alloys at 0.05 to 0.20 wt. % Zr. In one embodiment, the new aluminum alloys include 0.07 to 0.16 wt. % Zr. Scandium (Sc) may be used in addition to, or as a substitute for zirconium, and, when present, is generally included in the new aluminum alloys at 0.05 to 0.30 wt. % Sc. In one embodiment, the new aluminum alloys include 0.07 to 0.25 wt. % Sc. Chromium (Cr) may also be used in addition to, or as a substitute for zirconium, and/or scandium, and when present is generally included in the new alloys at 0.05 to 0.50 wt. % Cr.
- the new aluminum alloys include 0.05 to 0.35 wt. % Cr. In another embodiment, the new aluminum alloys include 0.05 to 0.25 wt. % Cr. In other embodiments, any of zirconium, scandium, and/or chromium may be included in the alloy as an impurity, and in these embodiments such elements would be included in the alloy at less than 0.05 wt. %.
- Hf, V and rare earth elements may be included an in an amount of up to 0.25 wt. % each of any of Hf, V, and rare earth elements (0.25 wt. % each of any rare earth element may be included).
- the new aluminum alloys include not greater than 0.05 wt. % each of Hf, V, and rare earth elements ( ⁇ 0.05 wt. % each of any rare earth element).
- Titanium is preferred for grain refining during casting, and, when present is generally included in the new aluminum alloys at 0.005 to 0.10 wt. % Ti.
- the new aluminum alloys include 0.01 to 0.05 wt. % Ti.
- the aluminum alloys include 0.01 to 0.03 wt. % Ti.
- the new alloys may include up to 0.35 wt. % Fe.
- the iron content of the new aluminum alloys is not greater than 0.25 wt. % Fe, or not greater than 0.15 wt. % Fe, or not greater than 0.10 wt. % Fe, or not greater than 0.08 wt. % Fe, or not greater than 0.05 wt. % Fe, or less.
- the balance (remainder) of the new aluminum alloys is generally aluminum and impurities.
- the total amount of magnesium, lithium, copper, zinc, silicon, iron, the secondary elements and the other elements should be chosen so that the aluminum alloy can be appropriately solutionized (e.g., to promote hardening while restricting the amount of constituent particles).
- the aluminum alloy includes an amount of alloying elements that leaves the aluminum alloy free of, or substantially free of, soluble constituent particles after solutionizing.
- the aluminum alloy includes an amount of alloying elements that leaves the aluminum alloy with low amounts of (e.g., restricted / minimized) insoluble constituent particles after solutionizing. In other embodiments, the aluminum alloy may benefit from controlled amounts of insoluble constituent particles.
- the new aluminum alloys may be processed into a variety of wrought forms, such as in rolled form (sheet, plate), as an extrusion, or as a forging, and in a variety of tempers.
- new aluminum alloys may be cast (e.g., direct chill cast or continuously cast), and then worked (hot and/or cold worked) into the appropriate product form (sheet, plate, extrusion, or forging).
- the new aluminum alloys may be processed into one of an H temper, T temper or a W temper, as defined by the Aluminum Association.
- the aluminum alloy may be hot worked, such as by rolling, extruding and/or forging.
- the hot working temperature is maintained below the recrystallization temperature of the alloy.
- the hot working exit temperature is not greater than 316°C (600°F).
- the hot working exit temperature is not greater than 288°C (550°F).
- the hot working exit temperature is not greater than 260°C (500°F).
- the hot working exit temperature is not greater than 232°C (450°F).
- the hot working exit temperature is not greater than 204°C (400°F).
- the new alloy is processed to an H temper.
- the processing may include casting the new aluminum alloy, including any version of the aluminum alloy described above, after which the aluminum alloy is hot rolled to an intermediate gauge or final gauge.
- the alloy will then be cold rolled to final gauge (e.g., cold rolled 2-25%), and then optionally stretched (e.g., 1-10%), for instance, for flatness and/or for stress relief.
- the alloy may be stretched (e.g., 1-10%), for instance, for flatness and/or for stress relief.
- the aluminum alloy may be cooled to a temperature of not greater than 204°C (400°F) prior to the cold rolling and/or the stretching.
- the aluminum alloy is cooled to a temperature of not greater than 121°C (250°F) prior to the cold rolling and/or the stretching.
- the aluminum alloy is cooled to a temperature of not greater than 93°C (200°F) prior to the cold rolling and/or the stretching.
- the aluminum alloy is cooled to a temperature of not greater than 66°C (150°F) prior to the cold rolling and/or the stretching.
- the aluminum alloy is cooled to ambient temperature prior to the cold rolling and/or the stretching.
- the process includes maintaining the aluminum alloy at a temperature below 204°C(400°F) between the hot rolling step and any cold rolling and/or stretching step.
- the process includes maintaining the aluminum alloy at a temperature of net 121°C (250°F) between the hot rolling step and/or any cold rolling and/or stretching step.
- the process includes maintaining the aluminum alloy at a temperature of net 93°C (200°F) between the hot rolling step and/or any cold rolling and/or stretching step.
- the process includes maintaining the aluminum alloy at a temperature of net 66°C (150°F) between the hot rolling step and/or any cold rolling and/or stretching step. In another H-temper embodiment, the process includes maintaining the aluminum alloy at ambient temperature between the hot rolling step and/or any cold rolling and/or stretching step.
- an H-temper processing method is absent of any thermal treatments after any cold rolling step and/or any stretching step.
- one or more anneal steps could be used, such as before or after hot and/or cold rolling.
- the cold rolling when cold rolling is used as a part of H-temper processing, the cold rolling may be restricted to so as to facilitate good strength, ductility and/or corrosion resistance.
- the cold rolling comprises cold rolling the intermediate gauge product by 1-25%, i.e., the thickness of the intermediate gauge product is reduced by 1-25% by cold rolling.
- the cold rolling is 2-22%, i.e., the thickness of the intermediate gauge product is reduced by 2-22% by cold rolling.
- the cold rolling is 3-20%, i.e., the thickness of the intermediate gauge product is reduced by 3-20% by cold rolling.
- the new aluminum alloy is processed to a "T temper" (thermally treated).
- the new aluminum alloys may be processed to any of a T1, T2, T3, T4, T5, T6, T7, T8 or T9 temper, as defined by the Aluminum Association.
- the new aluminum alloys are processed to one of a T4, T6 or T7 temper, where the new aluminum alloys are solution heat treated, and then quenched, and then either naturally aged (T4) or artificially aged (T6 or T7).
- the new aluminum alloys are processed to one of a T3 or T8 temper, where the new aluminum alloys are solution heat treated, and then quenched, and then cold worked, and then either naturally aged (T3) or artificially aged (T8).
- the new aluminum alloy is processed to an "W temper” (solution heat treated), as defined by the Aluminum Association.
- no solution heat treatment is applied after the hot working, and thus the new aluminum alloy may be processed to an "F temper" (as fabricated), as defined by the Aluminum Association.
- the alloys may also be processed with high cold work after the solution heat treatment and quench, e.g., 25% or more cold work, as described in commonly-owned U.S. Patent Publication No. 2012/0055590 .
- the new aluminum alloys may achieve an improved combination of properties.
- the new aluminum alloys may achieve an improved combination of strength, corrosion resistance and/or ductility, among others.
- the new aluminum alloys are in an H-temper, are hot rolled, and then stretched 1-10%, (no cold rolling step) and realize a tensile yield strength (L) of at least 241 MPa (35 ksi) (tested via ASTM E8 and B557).
- the new aluminum alloys realize a tensile yield strength (L) of at least 248 MPa (36 ksi).
- the new aluminum alloys realize a tensile yield strength (L) of at least 262 MPa (38 ksi).
- the new aluminum alloys realize a tensile yield strength (L) of at least 276 MPa (40 ksi).
- the new aluminum alloys realize a tensile yield strength (L) of at least 290 MPa (42 ksi). In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 303 MPa (44 ksi). In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 317 MPa (46 ksi). In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 331 MPa (48 ksi). In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 345 MPa (50 ksi).
- the new aluminum alloys realize a tensile yield strength (L) of at least 352 MPa (51 ksi), or more.
- the new aluminum alloys may realize an elongation (L) of at least 10% (tested via ASTM E8 and B557).
- the new aluminum alloys realize an elongation (L) of at least 12%.
- the new aluminum alloys realize an elongation (L) of at least 14%.
- the new aluminum alloys realize an elongation (L) of at least 16%.
- the new aluminum alloys realize an elongation (L) of at least 18%, or more.
- the new aluminum alloys may realize a mass loss of not greater than 25 mg/cm 2 (tested in accordance with ASMT G67, and with 1 week of exposure to 100°C). In one embodiment, the new aluminum alloys realize a mass loss of not greater than 15 mg/cm 2 . In these H-temper and stretching embodiments, the new aluminum alloys may realize an EXCO rating of at least EB (at T/10 and/or at surface, and as tested in accordance with ASMT G66, and with 1 week of exposure to 100°C). In one embodiment, the new aluminum alloys realize an EXCO rating of at least EA. In another embodiment, the new aluminum alloys realize an EXCO rating of at least PC. In yet another embodiment, the new aluminum alloys realize an EXCO rating of at least PB. In another embodiment, the new aluminum alloys realize an EXCO rating of at least PA.
- the new aluminum alloys are in an H-temper, are hot rolled, and then cold rolled 1-25% and realize a tensile yield strength (L) of at least 276 MPa (40 ksi) (tested via ASTM E8 and B557).
- the new aluminum alloys realize a tensile yield strength (L) of at least 290 MPa (42 ksi).
- the new aluminum alloys realize a tensile yield strength (L) of at least 303 MPa (44 ksi).
- the new aluminum alloys realize a tensile yield strength (L) of at least 317 MPa (46 ksi).
- the new aluminum alloys realize a tensile yield strength (L) of at least 331 MPa (48 ksi). In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 345 MPa (50 ksi). In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 358 MPa (52 ksi). In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 372 MPa (54 ksi). In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 386 MPa (56 ksi).
- the new aluminum alloys realize a tensile yield strength (L) of at least 400 MPa (58 ksi), or more.
- the new aluminum alloys may realize an elongation (L) of at least 6% (tested via ASTM E8 and B557).
- the new aluminum alloys realize an elongation (L) of at least 8%.
- the new aluminum alloys realize an elongation (L) of at least 10%.
- the new aluminum alloys realize an elongation (L) of at least 12%.
- the new aluminum alloys realize an elongation (L) of at least 14%, or more.
- the new aluminum alloys may realize a mass loss of not greater than 25 mg/cm 2 (tested in accordance with ASMT G67, and with 1 week of exposure to 100°C). In these H-temper and cold rolling embodiments, the new aluminum alloys may realize a mass loss of not greater than 15 mg/cm 2 . In these H-temper and cold rolling embodiments, the new aluminum alloys may realize an EXCO rating of at least EB (at T/10 and/or at surface, and as tested in accordance with ASMT G66, and with 1 week of exposure to 100°C). In one embodiment, the new aluminum alloys realize an EXCO rating of at least EA. In another embodiment, the new aluminum alloys realize an EXCO rating of at least PC. In yet another embodiment, the new aluminum alloys realize an EXCO rating of at least PB. In another embodiment, the new aluminum alloys realize an EXCO rating of at least PA.
- the new aluminum alloys are in an T-temper, and realize a tensile yield strength (L) of at least 310 MPa (45 ksi) (tested via ASTM E8 and B557). In one embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 317 MPa (46 ksi). In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 331 MPa (48 ksi). In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 345 MPa (50 ksi).
- the new aluminum alloys realize a tensile yield strength (L) of at least 359 MPa (52 ksi). In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 372 MPa (54 ksi). In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 386 MPa (56 ksi). In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 400 MPa (58 ksi). In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 414 MPa (60 ksi).
- the new aluminum alloys realize a tensile yield strength (L) of at least 428 MPa (62 ksi), or more.
- new aluminum alloys may realize an elongation (L) of at least 6% (tested via ASTM E8 and B557).
- the new aluminum alloys realize an elongation (L) of at least 8%.
- the new aluminum alloys realize an elongation (L) of at least 10%.
- the new aluminum alloys realize an elongation (L) of at least 12%.
- the new aluminum alloys realize an elongation (L) of at least 14%, or more.
- the new aluminum alloys may realize a mass loss of not greater than 25 mg/cm 2 (tested in accordance with ASMT G67, and with 1 week of exposure to 100°C). In one embodiment, the new aluminum alloys realize mass loss of not greater than 15 mg/cm 2 . In these T-temper embodiments, the new aluminum alloys may realize an EXCO rating of at least EB (at T/10 and/or at surface, and as tested in accordance with ASMT G66, and with 1 week of exposure to 100°C). In one embodiment, the new aluminum alloys realize an EXCO rating of at least EA. In another embodiment, the new aluminum alloys realize an EXCO rating of at least PC. In yet another embodiment, the new aluminum alloys realize an EXCO rating of at least PB. In another embodiment, the new aluminum alloys realize an EXCO rating of at least PA.
- the new aluminum alloys described herein may be used in a variety of applications, such as in automotive and/or aerospace applications, among others.
- the new aluminum alloys are used in an aerospace application, such as wing skins (upper and lower) or stringers / stiffeners, fuselage skin or stringers, ribs, frames, spars, bulkheads, circumferential frames, empennage (such as horizontal and vertical stabilizers), floor beams, seat tracks, doors, and control surface components (e.g., rudders, ailerons) among others.
- the new aluminum alloys are used in an automotive application, such as closure panels (e.g., hoods, fenders, doors, roofs, and trunk lids, among others), wheels, and critical strength applications, such as in body-in-white (e.g., pillars, reinforcements) applications, among others.
- the new aluminum alloys are used in a marine application, such as for ships and boats (e.g., hulls, decks, masts, and superstructures, among others).
- the new aluminum alloys are used in a munitions / ballistics / military application, such as in ammunition cartridges and armor, among others.
- Ammunition cartridges may include those used in small arms and cannons or for artillery or tank rounds.
- Other possible ammunition components would include sabots and fins.
- Artillery, fuse components are another possible application as are fins and control surfaces for precision guided bombs and missiles. Armor components could include armor plates or structural components for military vehicles.
- all alloys contained the listed elements, from 0.10 to 0.13 wt. % Zr, 0.60 wt. % Mn, not more than 0.04 wt. % Fe, not more than 0.03 wt. % Si, 0.02 wt. % Ti, the balance being aluminum and other elements, where the other elements did not exceed more than 0.05 wt. % each, and not more than 0.15 wt. % total of the other elements.
- the alloys were cast as approximately 73.025 mm (2.875 inch) (ST) x 120.65 mm (4.75 inch) (LT) x 431.8 mm (17 inch) (L) ingots that were scalped (machined) to about 50.8 mm (2 inches) thick. Alloys 10-12 were then homogenized. Each ingot was then hot rolled to a gauge of about 6.35 mm (0.25 inch). The finish hot rolling temperature varied as shown below (the starting hot rolling temperature was about 454 °C (850°F)). Part of these hot rolled pieces were then cold rolled to a gauge of about 4.763 mm (0.1875 inch) (about a 25% reduction in thickness).
- the HR only alloys and the HR + 25% CR alloys were also tested for corrosion resistance in accordance with ASTM G66 (exfoliation resistance) and G67 (mass loss). Specifically, the alloys were tested for corrosion resistance before and after exposure to a temperature of about 100°C for about 1 week. Alloys 1-5 that were hot rolled and then stretched 2% were also tested for corrosion resistance in accordance with ASTM G67 (mass loss). The corrosion resistance results are shown in Tables 5-7, below. Table 5 - Corrosion Resistance Results - Hot Rolled (HR) Alloys Alloy Hot Rolling Finish Temp.
- FIG. 10 illustrates mass loss as a function of lithium for high magnesium alloys. As shown above, the higher magnesium alloys also realize worse exfoliation resistance.
- alloys contained the listed elements, from about 0.10 to 0.012 wt. % Zr, not more than about 0.03 wt. % Fe, not more than 0.04 wt. % Si, about 0.02 wt. % Mn, about 0.02 wt. % Ti, the balance being aluminum and other elements, where the other elements did not exceed more than 0.05 wt. % each, and not more than 0.15 wt. % total of the other elements. Alloy 25 contained about 0.24 wt. % Si. Alloy 26 contained about 0.87 wt. % Si.
- the alloys were cast as approximately 73.025 mm (2.875 inch) (ST) x 120.65 mm (4.75 inch) (LT) x 431.8 mm (17 inch) (L) ingots that were scalped to about 50.8 mm (2 inches) thick, and then homogenized. After homogenization, each ingot was hot rolled to a gauge of about 6.35 mm (0.25 inch), and then cold rolled about 25% (reduced in thickness by 25%) to a final gauge of about 4.763 mm (0.1875 inch). Tensile yield strength and corrosion resistance properties were then tested, the results of which are provided in Tables 9a-9b, below.
- the strongest alloy contained about 1.0 wt. % Zn, 0.35 wt. % Cu and 0.65 wt. % Ag.
- low silver alloys ⁇ 0.25 wt. % Ag
- increasing copper from about 0.35 to 0.95 wt. % and/or increasing zinc did appear to benefit strength.
- medium silver alloys ⁇ 0.45 wt. % Ag
- increasing copper from about 0.65 to 1.85 wt. % decreased strength
- increasing zinc from about 1.45 to 2.82 wt. % had little effect on strength.
- moderately-high silver alloys ⁇ 0.65 wt. % Ag
- increasing copper from about 0.35 to about 0.90 wt. % decreased strength, and increasing zinc also decreased strength.
- Alloy 46 contained about 0.09 wt. % Zr, about 0.10 wt. % Fe and about 0.14 wt. % Si.
- the alloys were cast as 73.025 mm (2.875 inch) (ST) x 120.65 mm (4.75 inch) (LT) x 431.8 mm (17 inch) (L) ingots that were scalped to 50.8 mm (2 inches) thick and then homogenized. After homogenization, each ingot was hot rolled to a gauge of about 6.35 mm (0.25 inch) (Alloy 36 could not be rolled due to too much manganese). Part of these hot rolled pieces were then cold rolled to a gauge of about 4.763 mm (0.1875 inch) (about 25% reduction in thickness). Other parts of the hot rolled pieces were stretched about 2% for flatness.
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Description
- Aluminum alloys are useful in a variety of applications. However, improving one property of an aluminum alloy without degrading another property is elusive. For example, it is difficult to increase the strength of an alloy without decreasing the toughness of an alloy. Other properties of interest for aluminum alloys include corrosion resistance and fatigue resistance, to name two.
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GB 2 146 353 - Broadly, the present patent application relates to new aluminum-magnesium-lithium alloys, and methods for producing the same, as defined in
claims - The new aluminum-magnesium-lithium generally alloys contain 2.0 to 3.9 wt. % Mg. Magnesium may help improve strength, but too much magnesium may degrade corrosion resistance. In one embodiment, the new alloys include at least 2.25 wt. % Mg. In another embodiment, the new alloys contain at least 2.5 wt. % Mg. In yet another embodiment, the new alloys include at least 2.75 wt. % Mg. In one embodiment, the new alloys include not greater than 3.75 wt. % Mg. In another embodiment, the new alloys include not greater than 3.5 wt. % Mg. In yet another embodiment, the new alloys include not greater than 3.25 wt. % Mg.
- The new aluminum-magnesium-lithium generally contain 0.1 to 1.8 wt. % Li. Lithium helps reduce density and may help improve strength, but too much lithium may reduce ductility. In one embodiment, the new alloys include at least 0.4 wt. % Li. In another embodiment, the new alloys include at least 0.6 wt. % Li. In yet another embodiment, the new alloys include at least 0.8 wt. % Li. In another embodiment, the new alloys include at least 1.0 wt. % Li. In yet another embodiment, the new alloys include at least 1.05 wt. % Li. In another embodiment, the new alloys include at least 1.10 wt. % Li. In yet another embodiment, the new alloys include at least 1.20 wt. % Li. In one embodiment, the new alloys include not greater than 1.5 wt. % Li. In another embodiment, the new alloys include not greater than 1.45 wt. % Li. In yet another embodiment, the new alloys include not greater than 1.4 wt. % Li.
- The new alloys may contain up to 1.5 wt. % Cu. Copper may improve strength but increases density. In one embodiment, the new alloys contain not greater than 1.0 wt. % Cu. In another embodiment, the new alloys contain not greater than 0.9 wt. % Cu. In yet another embodiment, the new alloys contain not greater than 0.6 wt. % Cu. In another embodiment, the new alloys contain not greater than 0.5 wt. % Cu. In embodiments where copper is used, the new alloys generally contain at least 0.05 wt. % Cu. In one embodiment, the new alloys include at least 0.10 wt. % Cu. In embodiments where copper is not used, the new alloys include less than 0.05 wt. % Cu.
- The new alloys may contain up to 2.0 wt. % Zn when Mg is within 2.5 - 3.9 wt.-% and Li is within 1.05 and 1.8 wt.-%. Alternatively, the new alloys generally contain 0.4 to 2.0 wt.-% Zn. Zinc may improve strength, but increases density. In one embodiment, the new alloys contain not greater than 1.5 wt. % Zn. In another embodiment, the new alloys contain not greater than 1.0 wt. % Zn. In embodiments where zinc is used, the new alloys generally contain at least 0.20 wt. % Zn. In one embodiment, the new alloys contain at least 0.4 wt. % Zn. In another embodiment, the new alloys contain at least 0.5 wt. % Zn. In embodiments where zinc is not used, the new alloys include less than 0.20 wt. % Zn.
- The new alloys may contain up to 1.5 wt. % Mn. Manganese may improve strength, but increases density. In one embodiment, the new alloys contain not greater than 1.0 wt. % Mn. In another embodiment, the new alloys contain not greater than 0.9 wt. % Mn. In yet another embodiment, the new alloys contain not greater than 0.7 wt. % Mn. In embodiments where manganese is used, the new alloys generally contain at least 0.05 wt. % Mn. In one embodiment, the new alloys include at least 0.20 wt. % Mn. In embodiments where manganese is not used, the new alloys include not greater than 0.04 wt. % Mn.
- The new alloys may contain up to 1.0 wt. % Ag. Silver may improve strength, but silver decreases density and is expensive. In one embodiment, the new alloys contain not greater than 0.9 wt. % Ag. In another embodiment, the new alloys contain not greater than 0.6 wt. % Ag. In embodiments where silver is used, the new alloys generally contain at least 0.05 wt. % Ag. In one embodiment, the new alloys include at least 0.20 wt. % Ag. In embodiments where silver is not used, the new alloys include not greater than 0.04 wt. % Ag.
- The new alloys may contain up to 0.5 wt. % Si. Silicon may improve corrosion resistance, but may decrease fracture toughness. In one embodiment, the new alloys contain not greater than 0.35 wt. % Si. In another embodiment, the new alloys contain not greater than 0.25 wt. % Si. In embodiments where silicon is used, the new alloys generally contain at least 0.10 wt. % Si. In embodiments where silicon is not used, the new alloys include not greater than 0.09 wt. % Si.
- The new alloys may optionally include at least one secondary element selected from the group consisting of Zr, Sc, Cr, Hf, V, Ti, and rare earth elements. Such elements may be used, for instance, to facilitate the appropriate grain structure in the resultant aluminum alloy product. The secondary elements may optionally be present as follows: up to 0.20 wt. % Zr, up to 0.30 wt. % Sc, up to 0.50 wt. % of Cr, up to 0.25 wt. % each of any of Hf, V, and rare earth elements, and up to 0.10 wt. % Ti. Zirconium (Zr) and/or scandium are preferred for grain structure control. When zirconium is used, it is generally included in the new aluminum alloys at 0.05 to 0.20 wt. % Zr. In one embodiment, the new aluminum alloys include 0.07 to 0.16 wt. % Zr. Scandium (Sc) may be used in addition to, or as a substitute for zirconium, and, when present, is generally included in the new aluminum alloys at 0.05 to 0.30 wt. % Sc. In one embodiment, the new aluminum alloys include 0.07 to 0.25 wt. % Sc. Chromium (Cr) may also be used in addition to, or as a substitute for zirconium, and/or scandium, and when present is generally included in the new alloys at 0.05 to 0.50 wt. % Cr. In one embodiment, the new aluminum alloys include 0.05 to 0.35 wt. % Cr. In another embodiment, the new aluminum alloys include 0.05 to 0.25 wt. % Cr. In other embodiments, any of zirconium, scandium, and/or chromium may be included in the alloy as an impurity, and in these embodiments such elements would be included in the alloy at less than 0.05 wt. %.
- Hf, V and rare earth elements may be included an in an amount of up to 0.25 wt. % each of any of Hf, V, and rare earth elements (0.25 wt. % each of any rare earth element may be included). In one embodiment, the new aluminum alloys include not greater than 0.05 wt. % each of Hf, V, and rare earth elements (≤ 0.05 wt. % each of any rare earth element).
- Titanium is preferred for grain refining during casting, and, when present is generally included in the new aluminum alloys at 0.005 to 0.10 wt. % Ti. In one embodiment, the new aluminum alloys include 0.01 to 0.05 wt. % Ti. In another embodiment, the aluminum alloys include 0.01 to 0.03 wt. % Ti.
- The new alloys may include up to 0.35 wt. % Fe. In some embodiments, the iron content of the new aluminum alloys is not greater than 0.25 wt. % Fe, or not greater than 0.15 wt. % Fe, or not greater than 0.10 wt. % Fe, or not greater than 0.08 wt. % Fe, or not greater than 0.05 wt. % Fe, or less.
- Aside from the above-listed elements, the balance (remainder) of the new aluminum alloys is generally aluminum and impurities.
- Except where stated otherwise, the expression "up to" when referring to the amount of an element means that that elemental composition is optional and includes a zero amount of that particular compositional component. Unless stated otherwise, all compositional percentages are in weight percent (wt. %).
- In embodiments where the aluminum alloy is solution heat treated (described below), the total amount of magnesium, lithium, copper, zinc, silicon, iron, the secondary elements and the other elements should be chosen so that the aluminum alloy can be appropriately solutionized (e.g., to promote hardening while restricting the amount of constituent particles). In one embodiment, the aluminum alloy includes an amount of alloying elements that leaves the aluminum alloy free of, or substantially free of, soluble constituent particles after solutionizing. In one embodiment, the aluminum alloy includes an amount of alloying elements that leaves the aluminum alloy with low amounts of (e.g., restricted / minimized) insoluble constituent particles after solutionizing. In other embodiments, the aluminum alloy may benefit from controlled amounts of insoluble constituent particles.
- The new aluminum alloys may be processed into a variety of wrought forms, such as in rolled form (sheet, plate), as an extrusion, or as a forging, and in a variety of tempers. In this regard, new aluminum alloys may be cast (e.g., direct chill cast or continuously cast), and then worked (hot and/or cold worked) into the appropriate product form (sheet, plate, extrusion, or forging). After working, the new aluminum alloys may be processed into one of an H temper, T temper or a W temper, as defined by the Aluminum Association.
- For any of the H temper, T temper or W temper products, the aluminum alloy may be hot worked, such as by rolling, extruding and/or forging. In one embodiment, the hot working temperature is maintained below the recrystallization temperature of the alloy. In one embodiment, the hot working exit temperature is not greater than 316°C (600°F). In another embodiment, the hot working exit temperature is not greater than 288°C (550°F). In yet another embodiment, the hot working exit temperature is not greater than 260°C (500°F). In another embodiment, the hot working exit temperature is not greater than 232°C (450°F). In yet another embodiment, the hot working exit temperature is not greater than 204°C (400°F).
- In one embodiment, the new alloy is processed to an H temper. In these embodiments, the processing may include casting the new aluminum alloy, including any version of the aluminum alloy described above, after which the aluminum alloy is hot rolled to an intermediate gauge or final gauge. In instances where the alloy is hot rolled to an intermediate gauge, it will then be cold rolled to final gauge (e.g., cold rolled 2-25%), and then optionally stretched (e.g., 1-10%), for instance, for flatness and/or for stress relief. In instances where the alloy is hot rolled to final gauge, it may be stretched (e.g., 1-10%), for instance, for flatness and/or for stress relief.
- In embodiments where the aluminum alloy is cold rolled and/or stretched, the aluminum alloy may be cooled to a temperature of not greater than 204°C (400°F) prior to the cold rolling and/or the stretching. In one embodiment, the aluminum alloy is cooled to a temperature of not greater than 121°C (250°F) prior to the cold rolling and/or the stretching. In another embodiment, the aluminum alloy is cooled to a temperature of not greater than 93°C (200°F) prior to the cold rolling and/or the stretching. In yet another embodiment, the aluminum alloy is cooled to a temperature of not greater than 66°C (150°F) prior to the cold rolling and/or the stretching. In yet another embodiment, the aluminum alloy is cooled to ambient temperature prior to the cold rolling and/or the stretching.
- When producing the aluminum alloy in an H temper, it may be detrimental to anneal the product. Thus, in some H-temper embodiments, the process includes maintaining the aluminum alloy at a temperature below 204°C(400°F) between the hot rolling step and any cold rolling and/or stretching step. In one H-temper embodiment, the process includes maintaining the aluminum alloy at a temperature of net 121°C (250°F) between the hot rolling step and/or any cold rolling and/or stretching step. In another H-temper embodiment, the process includes maintaining the aluminum alloy at a temperature of net 93°C (200°F) between the hot rolling step and/or any cold rolling and/or stretching step. In yet another H-temper embodiment, the process includes maintaining the aluminum alloy at a temperature of net 66°C (150°F) between the hot rolling step and/or any cold rolling and/or stretching step. In another H-temper embodiment, the process includes maintaining the aluminum alloy at ambient temperature between the hot rolling step and/or any cold rolling and/or stretching step.
- In some embodiments, when producing the aluminum alloy in an H temper, it may be detrimental to apply any thermal treatment to the product after any cold rolling and/or stretching step. Thus, in some embodiments, an H-temper processing method is absent of any thermal treatments after any cold rolling step and/or any stretching step. However, in other embodiments, one or more anneal steps could be used, such as before or after hot and/or cold rolling.
- In some embodiments when cold rolling is used as a part of H-temper processing, the cold rolling may be restricted to so as to facilitate good strength, ductility and/or corrosion resistance. In one embodiment, the cold rolling comprises cold rolling the intermediate gauge product by 1-25%, i.e., the thickness of the intermediate gauge product is reduced by 1-25% by cold rolling. In one embodiment, the cold rolling is 2-22%, i.e., the thickness of the intermediate gauge product is reduced by 2-22% by cold rolling. In another embodiment, the cold rolling is 3-20%, i.e., the thickness of the intermediate gauge product is reduced by 3-20% by cold rolling.
- In another embodiment, the new aluminum alloy is processed to a "T temper" (thermally treated). In this regard, during or after the hot working (as appropriate), the new aluminum alloys may be processed to any of a T1, T2, T3, T4, T5, T6, T7, T8 or T9 temper, as defined by the Aluminum Association. In one embodiment, the new aluminum alloys are processed to one of a T4, T6 or T7 temper, where the new aluminum alloys are solution heat treated, and then quenched, and then either naturally aged (T4) or artificially aged (T6 or T7). In one embodiment, the new aluminum alloys are processed to one of a T3 or T8 temper, where the new aluminum alloys are solution heat treated, and then quenched, and then cold worked, and then either naturally aged (T3) or artificially aged (T8). In another embodiment, the new aluminum alloy is processed to an "W temper" (solution heat treated), as defined by the Aluminum Association. In yet another embodiment, no solution heat treatment is applied after the hot working, and thus the new aluminum alloy may be processed to an "F temper" (as fabricated), as defined by the Aluminum Association. The alloys may also be processed with high cold work after the solution heat treatment and quench, e.g., 25% or more cold work, as described in commonly-owned
U.S. Patent Publication No. 2012/0055590 . - The new aluminum alloys may achieve an improved combination of properties. For example, the new aluminum alloys may achieve an improved combination of strength, corrosion resistance and/or ductility, among others.
- In one approach, the new aluminum alloys are in an H-temper, are hot rolled, and then stretched 1-10%, (no cold rolling step) and realize a tensile yield strength (L) of at least 241 MPa (35 ksi) (tested via ASTM E8 and B557). In one embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 248 MPa (36 ksi). In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 262 MPa (38 ksi). In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 276 MPa (40 ksi). In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 290 MPa (42 ksi). In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 303 MPa (44 ksi). In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 317 MPa (46 ksi). In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 331 MPa (48 ksi). In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 345 MPa (50 ksi). In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 352 MPa (51 ksi), or more. In these H-temper and stretching embodiments, the new aluminum alloys may realize an elongation (L) of at least 10% (tested via ASTM E8 and B557). In one embodiment, the new aluminum alloys realize an elongation (L) of at least 12%. In another embodiment, the new aluminum alloys realize an elongation (L) of at least 14%. In yet another embodiment, the new aluminum alloys realize an elongation (L) of at least 16%. In another embodiment, the new aluminum alloys realize an elongation (L) of at least 18%, or more. In these H-temper and stretching embodiments, the new aluminum alloys may realize a mass loss of not greater than 25 mg/cm2 (tested in accordance with ASMT G67, and with 1 week of exposure to 100°C). In one embodiment, the new aluminum alloys realize a mass loss of not greater than 15 mg/cm2. In these H-temper and stretching embodiments, the new aluminum alloys may realize an EXCO rating of at least EB (at T/10 and/or at surface, and as tested in accordance with ASMT G66, and with 1 week of exposure to 100°C). In one embodiment, the new aluminum alloys realize an EXCO rating of at least EA. In another embodiment, the new aluminum alloys realize an EXCO rating of at least PC. In yet another embodiment, the new aluminum alloys realize an EXCO rating of at least PB. In another embodiment, the new aluminum alloys realize an EXCO rating of at least PA.
- In another approach, the new aluminum alloys are in an H-temper, are hot rolled, and then cold rolled 1-25% and realize a tensile yield strength (L) of at least 276 MPa (40 ksi) (tested via ASTM E8 and B557). In one embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 290 MPa (42 ksi). In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 303 MPa (44 ksi). In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 317 MPa (46 ksi). In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 331 MPa (48 ksi). In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 345 MPa (50 ksi). In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 358 MPa (52 ksi). In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 372 MPa (54 ksi). In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 386 MPa (56 ksi). In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 400 MPa (58 ksi), or more. In these H-temper and cold rolling embodiments, the new aluminum alloys may realize an elongation (L) of at least 6% (tested via ASTM E8 and B557). In one embodiment, the new aluminum alloys realize an elongation (L) of at least 8%. In another embodiment, the new aluminum alloys realize an elongation (L) of at least 10%. In yet another embodiment, the new aluminum alloys realize an elongation (L) of at least 12%. In another embodiment, the new aluminum alloys realize an elongation (L) of at least 14%, or more. In these H-temper and cold rolling embodiments, the new aluminum alloys may realize a mass loss of not greater than 25 mg/cm2 (tested in accordance with ASMT G67, and with 1 week of exposure to 100°C). In these H-temper and cold rolling embodiments, the new aluminum alloys may realize a mass loss of not greater than 15 mg/cm2. In these H-temper and cold rolling embodiments, the new aluminum alloys may realize an EXCO rating of at least EB (at T/10 and/or at surface, and as tested in accordance with ASMT G66, and with 1 week of exposure to 100°C). In one embodiment, the new aluminum alloys realize an EXCO rating of at least EA. In another embodiment, the new aluminum alloys realize an EXCO rating of at least PC. In yet another embodiment, the new aluminum alloys realize an EXCO rating of at least PB. In another embodiment, the new aluminum alloys realize an EXCO rating of at least PA.
- In yet another approach, the new aluminum alloys are in an T-temper, and realize a tensile yield strength (L) of at least 310 MPa (45 ksi) (tested via ASTM E8 and B557). In one embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 317 MPa (46 ksi). In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 331 MPa (48 ksi). In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 345 MPa (50 ksi). In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 359 MPa (52 ksi). In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 372 MPa (54 ksi). In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 386 MPa (56 ksi). In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 400 MPa (58 ksi). In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 414 MPa (60 ksi). In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 428 MPa (62 ksi), or more. In these T-temper embodiments, new aluminum alloys may realize an elongation (L) of at least 6% (tested via ASTM E8 and B557). In one embodiment, the new aluminum alloys realize an elongation (L) of at least 8%. In another embodiment, the new aluminum alloys realize an elongation (L) of at least 10%. In yet another embodiment, the new aluminum alloys realize an elongation (L) of at least 12%. In another embodiment, the new aluminum alloys realize an elongation (L) of at least 14%, or more. In these T-temper embodiments, the new aluminum alloys may realize a mass loss of not greater than 25 mg/cm2 (tested in accordance with ASMT G67, and with 1 week of exposure to 100°C). In one embodiment, the new aluminum alloys realize mass loss of not greater than 15 mg/cm2. In these T-temper embodiments, the new aluminum alloys may realize an EXCO rating of at least EB (at T/10 and/or at surface, and as tested in accordance with ASMT G66, and with 1 week of exposure to 100°C). In one embodiment, the new aluminum alloys realize an EXCO rating of at least EA. In another embodiment, the new aluminum alloys realize an EXCO rating of at least PC. In yet another embodiment, the new aluminum alloys realize an EXCO rating of at least PB. In another embodiment, the new aluminum alloys realize an EXCO rating of at least PA.
- The new aluminum alloys described herein may be used in a variety of applications, such as in automotive and/or aerospace applications, among others. In one embodiment, the new aluminum alloys are used in an aerospace application, such as wing skins (upper and lower) or stringers / stiffeners, fuselage skin or stringers, ribs, frames, spars, bulkheads, circumferential frames, empennage (such as horizontal and vertical stabilizers), floor beams, seat tracks, doors, and control surface components (e.g., rudders, ailerons) among others. In another embodiment, the new aluminum alloys are used in an automotive application, such as closure panels (e.g., hoods, fenders, doors, roofs, and trunk lids, among others), wheels, and critical strength applications, such as in body-in-white (e.g., pillars, reinforcements) applications, among others. In yet another embodiment, the new aluminum alloys are used in a marine application, such as for ships and boats (e.g., hulls, decks, masts, and superstructures, among others). In another embodiment, the new aluminum alloys are used in a munitions / ballistics / military application, such as in ammunition cartridges and armor, among others. Ammunition cartridges may include those used in small arms and cannons or for artillery or tank rounds. Other possible ammunition components would include sabots and fins. Artillery, fuse components are another possible application as are fins and control surfaces for precision guided bombs and missiles. Armor components could include armor plates or structural components for military vehicles.
-
-
FIGS. 1-12 are graphs illustrating results of Example 1. -
FIGS. 13 is a graph illustrating results of Example 2. -
FIGS. 14-21 are graphs illustrating results of Example 3. - Twelve book mold ingots were produced, the compositions of which are provided in Table 1, below (all values in weight percent).
Table 1 - Example 1 Alloy Compositions (alloys marked with * are outside of the claims) Alloy Mg Li Cu Zn 1* 2.89 0.00 0 0 2* 2.80 0.21 0 0 3* 2.90 0.87 0 0 4 2.80 1.20 0 0 5 2.70 1.60 0 0 6* 5.03 0.00 0 0 7* 4.75 0.23 0 0 8* 4.75 0.87 0 0 9* 4.55 1.20 0 0 10* 5.55 0.85 0 0 11* 5.04 0.00 0.19 0.54 12* 4.50 0.86 0.18 0.46 - Unless otherwise indicated, all alloys contained the listed elements, from 0.10 to 0.13 wt. % Zr, 0.60 wt. % Mn, not more than 0.04 wt. % Fe, not more than 0.03 wt. % Si, 0.02 wt. % Ti, the balance being aluminum and other elements, where the other elements did not exceed more than 0.05 wt. % each, and not more than 0.15 wt. % total of the other elements.
- The alloys were cast as approximately 73.025 mm (2.875 inch) (ST) x 120.65 mm (4.75 inch) (LT) x 431.8 mm (17 inch) (L) ingots that were scalped (machined) to about 50.8 mm (2 inches) thick. Alloys 10-12 were then homogenized. Each ingot was then hot rolled to a gauge of about 6.35 mm (0.25 inch). The finish hot rolling temperature varied as shown below (the starting hot rolling temperature was about 454 °C (850°F)). Part of these hot rolled pieces were then cold rolled to a gauge of about 4.763 mm (0.1875 inch) (about a 25% reduction in thickness). For Alloys 1-5, other parts of the hot rolled pieces were stretched about 2% for flatness. The mechanical properties of the as hot rolled (HR), the as cold rolled materials (CR) and hot rolled and 2% stretched material (HR-2%S) were then tested, the results of which are provided in Tables 2-4, below. Strength and elongation properties were measured in accordance with ASTM E8 and B557 -- all test values relative to the longitudinal (L) direction, unless otherwise indicated.
Table 2 - Mechanical Properties of Hot Rolled (HR) Alloys Alloy Hot Rolling Finish Temp. *(°C) ((°F)) TYS **(MPa) ((ksi)) UTS **(MPa) ((ksi)) Elong. (%) 1 500-550 25.2 35.8 28.4 1 400-450 28.7 38.3 26.1 2 500-550 24.3 37.9 24.9 3 400-450 32.5 46.2 15.2 4 400-450 35.0 48.5 12.9 5 400-450 35.7 53.0 11.8 6 400-450 35.0 50.0 24.1 6 500-550 32.4 49.7 23.2 7 400-450 36.8 53.2 17.0 8 500-550 31.5 51.8 23.5 9 400-450 38.3 55.8 19.1 10 400-450 39.0 57.5 18.9 11 400-450 40.4 56.5 17.5 12 400-450 39.1 56.8 16.4 * 0 °C = 32°F ** 1 ksi = 6.8948 MPa Table 3 - Mechanical Properties of HR + 25% CR Alloys Alloy Hot Rolling Finish Temp. *(°C) ((°F)) TYS **(MPa) ((ksi)) UTS **(MPa) ((ksi)) Elong. (%) 1 500-550 37.6 41.9 14.1 1 400-450 41.4 43.7 10.7 2 500-550 39.0 42.6 13.5 3 400-450 48.8 50.4 7.2 4 400-450 51.5 53.2 5.7 5 400-450 55.1 57.7 5.0 6 400-450 51.2 57.9 11.6 6 500-550 48.9 57.4 12.2 7 400-450 53.3 60.5 8.0 8 500-550 51.0 59.0 11.0 9 400-450 56.2 64.4 7.7 10 400-450 60.4 67.1 8.8 11 400-450 56.5 63.7 8.5 12 400-450 59.3 66.4 6.8 * 0 °C = 32°F ** 1 ksi = 6.8948 MPa Table 4 - Mechanical Properties of HR + 2% Stretch Alloys Alloy Hot Rolling Finish Temp. *(°C) ((°F)) TYS **(MPa) ((ksi)) UTS **(MPa) ((ksi)) Elong. (%) 1 500-550 27.4 35.5 24.3 1 400-450 30.7 37.8 23.9 2 500-550 31.8 38.4 22.5 3 400-450 39.8 44.9 15.4 4 400-450 43.4 47.9 12.6 5 400-450 48.8 53.2 10.3 * 0 °C = 32°F ** 1 ksi = 6.8948 MPa - As shown in
FIGS. 1-3 , lower hot rolling exit temperatures resulted in better properties. As shown inFIGS. 4-5 , the cold rolled alloys generally realize better strength than the hot-rolled only alloys. As shown inFIGS. 6-7 , the hot rolled alloys without cold rolling generally realized good ductility at all lithium levels. As shown inFIGS. 8-9 , higher levels of magnesium and lithium generally result in higher strengths. - The HR only alloys and the HR + 25% CR alloys were also tested for corrosion resistance in accordance with ASTM G66 (exfoliation resistance) and G67 (mass loss). Specifically, the alloys were tested for corrosion resistance before and after exposure to a temperature of about 100°C for about 1 week. Alloys 1-5 that were hot rolled and then stretched 2% were also tested for corrosion resistance in accordance with ASTM G67 (mass loss). The corrosion resistance results are shown in Tables 5-7, below.
Table 5 - Corrosion Resistance Results - Hot Rolled (HR) Alloys Alloy Hot Rolling Finish Temp. *(°C) ((°F)) Before Thermal Exposure After Thermal Exposure G67 Mass Loss (mg/cm2 ) G66 Ratin g @ T/10 G66 Rating @ Surfac e G67 Mass Loss (mg/cm2) G66 Rating @ T/10 G66 Rating @ Surface 1 500-550 1.11 PB PB 1.75 PB PB 1 400-450 1.47 PB PB 1.90 PB PB 2 500-550 1.26 PB PB 1.79 PB PB 3 400-450 1.38 PA PA 3.06 PB PB 4 400-450 1.21 PB PB 2.99 PB PB 5 400-450 1.64 PB PB 2.48 EA PB 6 400-450 1.74 PB PB 40.05 EA EC 6 500-550 1.90 PB PB 49.23 EA EC 6 400-450 1.30 PB PB 49.17 PB PB 7 400-450 1.65 PB PB 31.11 EB ED 7 400-450 1.66 PB PB 33.68 EB EB 8 500-550 2.36 PB PB 55.61 EB EB 9 400-450 3.55 EA EA 33.18 EC ED 9 400-450 2.31 PB PB 29.68 PB PB 10 400-450 7.70 PB PB 46.20 EB EC 10 400-450 6.84 PB PB 73.16 EA EA 11 400-450 2.00 EC EC 13.73 EC EC 11 400-450 1.72 EC EC 15.72 EC EC 12 400-450 2.20 EC EC 14.98 EC EC 12 400-450 2.31 EC EC 17.77 ED ED * 0 °C = 32°F Table 6 - Corrosion Resistance Results - HR + 25% CR Alloys Alloy Hot Rolling Finish Temp. *(°C) ((°F)) Before Thermal Exposure After Thermal Exposure G67 Mass Loss (mg/cm2) G66 Rating @ T/10 G66 Rating @ Surface G67 Mass Loss (mg/cm2) G66 Rating @ T/10 G66 Rating @ Surface 1 500-550 1.16 PA PA 1.49 PA PA 1 400-450 1.55 PA PA 1.68 PA PA 2 500-550 1.33 PB PB 2.03 PA PA 3 400-450 1.26 PA PA 4.58 EA EA 4 400-450 1.25 PB PB 4.20 EA EA 5 400-450 1.37 PA PA 2.29 PA PA 6 400-450 1.48 PB PB 38.29 ED ED 6 500-550 1.34 PA PA 53.10 ED ED 6 400-450 1.37 PA PA 56.63 EA EA 7 400-450 1.49 PB PB 36.46 ED ED 7 400-450 1.76 PA PA 35.72 ED ED 8 500-550 2.08 PB PB 54.86 ED ED 9 400-450 2.70 EA EA 33.47 ED ED 9 400-450 2.08 PA PA 44.44 ED ED 10 400-450 5.01 PB EA 43.08 ED ED 10 400-450 4.11 PA PA 68.24 ED ED 11 400-450 1.77 EC EC 29.55 ED ED 11 400-450 1.63 EC EC 30.67 ED ED 12 400-450 2.31 EC EC 26.13 ED ED 12 400-450 2.25 EC EC 28.01 ED ED * 0 °C = 32°F Table 7 - Corrosion Resistance Results - Hot Rolled (HR) + 2% Stretch Alloys Alloy Hot Rolling Finish Temp. *(°C) ((°F)) Before Thermal Exposure After Thermal Exposure G67 Mass Loss (mg/cm2) 1 500-550 1.59 2.09 1 400-450 1.33 1.92 2 500-550 1.31 2.04 3 400-450 1.29 3.62 4 400-450 1.28 4.50 5 400-450 1.41 2.36 * 0 °C = 32°F - As shown in
FIG. 10 , all alloys realize low (good) mass loss prior to thermal exposure realizing less than 15 mg/cm2 mass loss during the ASTM G67 test. However, after thermal exposure, the about 3 wt. % Mg alloys realize low mass loss, but many of Alloys 6-12 with magnesium realize high mass loss (See,FIG. 11 ).FIG. 12 illustrates mass loss as a function of lithium for high magnesium alloys. As shown above, the higher magnesium alloys also realize worse exfoliation resistance. - Fourteen book mold ingots were produced, the compositions of which are provided in Table 8, below (all values in weight percent).
Table 8 - Example 2 Alloy Compositions Alloy Mg Li Zn Cu Ag 13 4.42 2.01 0.96 0.35 0.24 14 4.33 2.09 1.87 0.35 0.23 15 4.53 2.13 0.97 0.95 0.24 16 4.48 2.18 1.92 0.95 0.24 17 4.41 2.03 0.97 0.35 0.65 18 4.38 2.04 1.90 0.36 0.65 19 4.41 2.06 0.98 0.95 0.66 20 4.36 2.12 1.89 0.89 0.62 21 4.37 2.08 1.44 0.65 0.44 22 4.31 2.22 2.82 0.64 0.43 23 4.43 2.16 1.44 1.85 0.45 24 4.45 2.18 1.48 0.68 0.91 25 4.45 2.06 1.45 0.67 0.45 26 4.40 2.13 1.45 0.67 0.44 - Unless otherwise indicated, all alloys contained the listed elements, from about 0.10 to 0.012 wt. % Zr, not more than about 0.03 wt. % Fe, not more than 0.04 wt. % Si, about 0.02 wt. % Mn, about 0.02 wt. % Ti, the balance being aluminum and other elements, where the other elements did not exceed more than 0.05 wt. % each, and not more than 0.15 wt. % total of the other elements.
Alloy 25 contained about 0.24 wt. % Si. Alloy 26 contained about 0.87 wt. % Si. - The alloys were cast as approximately 73.025 mm (2.875 inch) (ST) x 120.65 mm (4.75 inch) (LT) x 431.8 mm (17 inch) (L) ingots that were scalped to about 50.8 mm (2 inches) thick, and then homogenized. After homogenization, each ingot was hot rolled to a gauge of about 6.35 mm (0.25 inch), and then cold rolled about 25% (reduced in thickness by 25%) to a final gauge of about 4.763 mm (0.1875 inch). Tensile yield strength and corrosion resistance properties were then tested, the results of which are provided in Tables 9a-9b, below. Tensile yield strength properties were measured in accordance with ASTM E8 and B557 -- all test values relative to the longitudinal (L) direction, unless otherwise indicated. Corrosion resistance was tested in accordance with ASTM G66 (exfoliation resistance) and G67 (mass loss) -- the alloys were tested for corrosion resistance before and after exposure to a temperature of about 100°C for about 1 week.
Table 9a - Mechanical Properties of Example 2 Alloys Alloy TYS *(MPa) ((ksi)) UTS *(MPa) ((ksi)) Elong. (%) 13 59.2 66.0 6.4 14 60.1 65.7 3.9 15 55.6 62.1 5.2 16 57.3 62.0 5.2 17 64.3 68.9 3.7 18 59.4 64.2 4.5 19 54.2 59.5 5.9 20 52.9 59.4 4.6 21 55.7 61.8 7.1 22 55.3 60.2 4.8 23 53.2 59.3 6.1 24 55.9 60.6 3.5 25 56.0 60.2 5.5 26 53.6 58.1 4.6 * 1 ksi = 6.8948 MPa Table 9b - Corrosion Resistance Properties of Example 2 Alloys Alloy Before Thermal Exposure After Thermal Exposure G67 Mass Loss (mg/cm2) G66 Rating @ T/10 G66 Rating @ Surface G67 Mass Loss (mg/cm2) G66 Rating @ T/10 G66 Rating @ Surface 13 1.64 PC PB 21.66 ED ED 14 2.26 PC PB 25.62 ED ED 15 2.43 PC PA 23.36 ED ED 16 2.48 PC PC 28.80 ED ED 17 2.14 PC PC 31.19 ED ED 18 2.72 PC PB 32.85 ED ED 19 3.71 PC PA 23.99 ED EC 20 2.99 PC EC 34.99 ED ED 21 2.48 PC PC 29.38 ED ED 22 3.31 PC PC 43.34 ED ED 23 4.09 PC PC 32.86 ED ED 24 3.41 PC PA 28.25 ED EC 25 2.40 PC PA 25.59 ED ED 26 3.41 PC PA 17.45 PC EC - As shown in
FIG. 13 , the strongest alloy contained about 1.0 wt. % Zn, 0.35 wt. % Cu and 0.65 wt. % Ag. In low silver alloys (∼ 0.25 wt. % Ag), increasing copper from about 0.35 to 0.95 wt. % and/or increasing zinc did appear to benefit strength. In medium silver alloys (∼ 0.45 wt. % Ag), increasing copper from about 0.65 to 1.85 wt. % decreased strength, and increasing zinc from about 1.45 to 2.82 wt. % had little effect on strength. In moderately-high silver alloys (∼ 0.65 wt. % Ag), increasing copper from about 0.35 to about 0.90 wt. % decreased strength, and increasing zinc also decreased strength. Increasing silver from about 0.45 to 0.91 wt. % did not appear to materially affect strength. Increasing silicon from about 0.04 wt. % to 0.24 wt. % also did not appear to materially affect strength. Increasing silicon to about 0.89 wt. %, however, did affect strength. - Regarding ductility, all of the alloys have somewhat low elongation, indicating that less than 25% cold work may be required to achieve better ductility.
- Regarding corrosion resistance, most of the alloys did not pass the mass loss test, all achieving a mass loss of more than 15 mg/cm2, and often a mass loss of more than 25 mg/cm2. Increasing the silicon level did appear to help with mass loss.
- Twenty-three book mold ingots were produced, the compositions of which are provided in Table 9, below (all values in weight percent).
Table 10 - Example 1 Alloy Compositions (alloys marked with* are outside of the claims) Alloy Mg Li Mn Cu Zn 27* 2.2 1.1 0.55 0.05 -- 28 2.5 1.0 0.58 -- -- 29 3.3 1.0 0.54 -- -- 30 3.5 1.1 0.56 -- -- 31* 4.1 1.1 0.57 -- -- 32 2.9 1.1 0.54 -- -- 33 3.1 1.0 0.29 -- -- 34 3.2 1.1 -- 0.01 -- 35 3.0 1.0 1.10 -- -- 36 3.0 1.0 1.60 -- -- 37 3.0 1.0 0.56 -- 0.10 38 3.0 1.1 0.56 -- 0.24 39 2.9 1.1 0.57 -- 0.51 40 3.0 1.1 0.56 -- 0.97 41 3.0 1.1 0.56 -- 1.90 42 2.9 1.0 0.57 0.14 0.02 43 3.1 1.1 0.56 0.29 - 44 2.9 1.1 0.56 0.48 -- 45 3.1 1.0 0.56 0.25 0.50 46 2.8 1.1 0.56 -- -- 47 2.94 -- 0.54 -- -- 48 * 2.9 0.50 0.57 -- -- 49 * 2.8 1.00 0.57 -- -- 50 2.9 1.60 0.57 -- -- - The alloys were cast as 73.025 mm (2.875 inch) (ST) x 120.65 mm (4.75 inch) (LT) x 431.8 mm (17 inch) (L) ingots that were scalped to 50.8 mm (2 inches) thick and then homogenized. After homogenization, each ingot was hot rolled to a gauge of about 6.35 mm (0.25 inch) (Alloy 36 could not be rolled due to too much manganese). Part of these hot rolled pieces were then cold rolled to a gauge of about 4.763 mm (0.1875 inch) (about 25% reduction in thickness). Other parts of the hot rolled pieces were stretched about 2% for flatness. The mechanical properties and corrosion resistance properties of the hot rolled and cold rolled materials were then tested, the results of which are provided in Tables 11-14, below. Strength and elongation properties were measured in accordance with ASTM E8 and B557 -- all test values relative to the longitudinal (L) direction, unless otherwise indicated. Corrosion resistance was tested in accordance with ASTM G67 (mass loss) -- the alloys were tested for corrosion resistance before and after exposure to a temperature of about 100°C for about 1 week.
Table 11 - Mechanical Properties of Hot Rolled + 2% Stretch Alloys Alloy TYS *(MPa ((ksi)) UTS *(MPa) ((ksi)) Elong. (%) 27 38.3 41.3 13.5 28 38.1 42.6 15.0 29 45.5 15.0 15.0 30 40.3 46.7 15.5 31 40.7 47.4 14.5 32 39.1 43.6 14.0 33 37.3 41.3 16.0 34 35.7 40.5 16.0 35 42.6 47.9 13.0 37 39.4 44.7 15.5 38 39.4 44.9 15.5 39 39.7 45.0 15.0 40 39.9 45.5 15.5 41 42.6 49.3 15.0 42 41.7 46.3 15.0 43 44.9 50.4 13.0 44 49.4 53.3 10.0 45 42.5 48.4 15.0 46 40.1 44.8 15.5 47 37.0 41.0 18.5 48 38.0 42.7 15.0 49 40.3 44.7 15.5 50 44.5 49.9 14.0 * 1 ksi = 6.8948 MPa Table 12 - Mechanical Properties of Hot Rolled + Cold Rolled Alloys Alloy TYS *(MPa) ((ksi)) UTS *(MPa) ((ksi)) Elong. (%) 27 45.5 46.7 7.0 28 47.4 49.1 8.5 29 45.3 53.6 8.0 30 51.4 55.7 8.0 31 52.2 57.2 9.0 32 51.3 52.2 8.0 33 46.9 49.4 10.0 34 43.0 45.4 9.5 35 51.9 56.7 6.0 37 48.5 52.0 9.0 38 49.2 52.8 8.0 39 49.0 52.4 8.0 40 49.6 53.4 8.0 41 48.5 56.0 7.5 42 44.5 53.3 8.0 43 55.9 56.9 8.0 44 57.5 59.7 7.5 45 52.7 55.0 8.5 46 50.5 51.7 7.0 47 43.7 47.1 10.5 48 45.2 48.4 8.5 49 48.9 51.2 8.5 50 57.9 59.6 7.5 * 1 ksi = 6.8948 MPa Table 13 - Corrosion Resistance Results - Hot Rolled (HR) Alloys Alloy Before Thermal Exposure After Thermal Exposure G67 Mass Loss (mg/cm2) 27 1.29 1.57 28 1.25 2.48 29 1.32 8.96 30 1.66 17.2 31 1.59 30.23 32 1.28 5.34 33 1.37 6.29 34 1.51 9.68 35 1.49 8.12 37 1.62 11.8 38 1.73 10.39 39 1.53 2.9 40 1.72 2.52 41 1.87 2.61 42 1.18 3.5 43 1.17 3.41 44 1.5 3.51 45 1.29 3.3 46 1.77 6.68 47 1.46 2.24 48 1.72 3.28 49 1.47 6.71 50 1.73 3.97 Table 14 - Corrosion Resistance Results - Hot Rolled (HR) + 25% CR Alloys Alloy Before Thermal Exposure After Thermal Exposure G67 Mass Loss (mg/cm2) 27 1.28 1.81 28 1.2 2.79 29 1.35 11.26 30 1.63 18.2 31 1.72 32.45 32 1.31 8.77 33 1.3 9.97 34 1.25 10.23 35 1.76 14.96 37 1.64 12.88 38 1.72 12.22 39 1.55 4.11 40 1.63 3.14 41 1.92 2.67 42 1.22 5.17 43 1.31 5.96 44 1.46 4.91 45 1.28 5.13 46 1.82 9.32 47 1.46 2.57 48 1.57 4.58 49 1.59 11.51 50 1.63 3.97 - As shown in
FIGS. 14-18 , increasing levels of Mg, Li, Mn and Cu resulted in increased strength. Increasing zinc may increase strength in hot rolled only alloys. However, as shown inFIG. 19 , poor corrosion resistance is realized in alloys having more than about 4.0 wt. % Mg, indicating that the alloys should include not greater than 3.9 wt. % Mg for good corrosion resistance. As shown inFIG. 20 , higher levels of copper tend to improve corrosion. As shown inFIG. 21 , higher levels of zinc (e.g., at or above 0.4 wt. % Zn) also tend to improve corrosion resistance. Manganese above about 1.0 wt. % tends to degrade corrosion resistance.
Claims (12)
- A method comprising:(a) casting an aluminum alloy consisting of:and either2.0 - 3.9 wt. % Mg;0.1 - 1.8 wt. % Li;up to 1.5 wt. % Cu;(A) 0.4 to 2.0 wt. % Zn, or alternatively(B) up to 2.0 wt. % Zn, when Mg is within 2.5 - 3.9 wt. % and Li is within 1.05 and 1.8 wt. %;up to 1.0 wt. % Ag;up to 1.5 wt. % Mn;up to 0.5 wt. % Si;up to 0.35 wt. % Fe;optionally at least one secondary element selected from the group consisting of Zr, Sc, Cr, Mn, Hf, V, Ti, and rare earth elements, and in the following amounts:up to 0.20 wt. % Zr;up to 0.30 wt. % Sc;up to 0.50 wt. % Cr;up to 1.0 wt. % Mn;up to 0.25 wt. % each of any of Hf, V, and rare earth elements;up to 0.10 wt. % Ti; andthe balance being aluminum and impurities;(b1) after the casting step (a), hot rolling the aluminum alloy into an intermediate product;(c1) after the hot rolling step (b1), cooling the intermediate product to a temperature of not greater than 204°C (400°F);(d1) after the cooling step (c1), cold rolling the intermediate product to final gauge, wherein the cold rolling reduces the thickness of the intermediate product by from 1% to 25%;(e1) maintaining the aluminum alloy at a temperature of not greater than 204°C (400°F) between the cooling step (c1) and the cold rolling step (d1);or(b2) after the casting, hot rolling the aluminum alloy to final gauge;(c2) after the hot rolling step (b2), cooling the aluminum alloy to a temperature of not greater than 204°C (400°F);(d2) after the cooling step (c2), stretching the aluminum alloy 1% to 10%;(e2) maintaining the aluminum alloy at a temperature of not greater than 400°F between the cooling step (c2) and the stretching step (d2).
- The method of claim 1, wherein the cooling step (c1) comprises cooling the intermediate product to a temperature of not greater than 121°C (250°F), preferably not greater than 93°C (200°F), preferably not greater than 66°C (150°F), preferably to ambient temperature, and wherein the maintaining step (e) comprises maintaining the aluminum alloy at a temperature of not greater than 121°C (250°F), preferably not greater than 93°C (200°F), preferably not greater than 66°C (150°F), preferably at ambient temperature, between the cooling step (c1) and the cold rolling step (d1).
- The method of any of claims 1 - 2, comprising:after the cold rolling step (d1), solution heat treating and then quenching the aluminum alloy.
- The method of claim 3, comprising:after the solution heat treating and then quenching step, artificially aging the aluminum alloy.
- The method of any of claims 1 - 2, wherein the method is absent of any thermal treatments after the cold rolling step (d1).
- An aluminum alloy consisting of:2.0 - 3.9 wt. % Mg;0.1 - 1.8 wt. % Li;(A) 0.4 to 2.0 wt.% Zn , or alternatively(B) up to 2.0 wt. % Zn, when Mg is within 2.5 - 3.9 wt.% and Li is within 1.05 and 1.8 wt.%, up to 1.5 wt. % Cu;up to 1.0 wt. % Ag;up to 1.5 wt. % Mn;up to 0.5 wt. % Si;up to 0.35 wt. % Fe;optionally at least one secondary element selected from the group consisting of Zr, Sc, Cr, Mn, Hf, V, Ti, and rare earth elements, and in the following amounts:up to 0.20 wt. % Zr;up to 0.30 wt. % Sc;up to 0.50 wt. % Cr;up to 1.0 wt. % Mn;up to 0.25 wt. % each of any of Hf, V, and rare earth elements; andup to 0.10 wt. % Ti; andthe balance being aluminum and impurities.
- The aluminum alloy of claim 6, wherein the aluminum alloy includes 0.4 to 2.0 wt. % Zn and from 2.25 wt. % Mg to 3.9 wt. % Mg, preferably from 2.5 wt. % Mg to 3.9 wt. % Mg, preferably from 2.5 wt. % Mg to 3.5 wt. % Mg.
- The aluminum alloy of any of claims 6-7, wherein the aluminum alloy includes 0.4 to 2.0 wt. % Zn and from 0.4 wt. % Li to 1.5 wt. % Li, preferably from 0.8 wt. % Li to 1.45 wt. % Li, preferably from 1.2 wt. % Li to 1.4 wt. % Li.
- The aluminum alloy of any of claims 6-8, wherein the aluminum alloy includes from 0.4 wt. % Zn to 1.5 wt. % Zn.
- The aluminum alloy of claim 6, wherein the aluminum alloy includes from 0.5 wt. % Zn to 1.0 wt. % Zn.
- The aluminum alloy of any of claims 6 or 10, wherein the aluminum alloy includes 2.5 - 3.9 wt. % Mg, 1.05 - 1.8 wt. % Li and not greater than 1.0 wt. % Cu, preferably not greater than 0.9 wt. % Cu, preferably not greater than 0.5 wt. % Cu.
- The aluminum alloy of any of claims 6, 10 or 11, wherein the aluminum alloy includes 2.5 - 3.9 wt. % Mg, 1.05 - 1.8 wt. % Li and at least 0.10 wt. % Cu.
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DE3775522D1 (en) * | 1986-11-04 | 1992-02-06 | Aluminum Co Of America | ALUMINUM LITHIUM ALLOYS AND METHOD FOR PRODUCING THE SAME. |
JPS63206445A (en) * | 1986-12-01 | 1988-08-25 | コマルコ・アルミニウム・エルティーディー | Aluminum-lithium ternary alloy |
US5108519A (en) * | 1988-01-28 | 1992-04-28 | Aluminum Company Of America | Aluminum-lithium alloys suitable for forgings |
JPH03183750A (en) * | 1989-12-12 | 1991-08-09 | Kobe Steel Ltd | Production of superplastic aluminum alloy having high strength |
JPH0514597A (en) * | 1991-06-28 | 1993-01-22 | Nec Corp | Linear color image sensor |
JPH05148597A (en) * | 1991-07-17 | 1993-06-15 | Aluminum Co Of America <Alcoa> | Alloy of aluminum and lithium and its production |
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EP1153152B1 (en) * | 1998-12-18 | 2003-11-12 | Corus Aluminium Walzprodukte GmbH | Method for the manufacturing of an aluminium-magnesium-lithium alloy product |
RU2232828C2 (en) * | 1998-12-18 | 2004-07-20 | Корус Алюминиум Вальцпродукте Гмбх | Method of manufacturing products from aluminum/magnesium/lithium alloy |
EP2288738B1 (en) * | 2008-06-24 | 2014-02-12 | Aleris Rolled Products Germany GmbH | Al-zn-mg alloy product with reduced quench sensitivity |
-
2013
- 2013-03-14 US US13/828,571 patent/US20150376740A1/en not_active Abandoned
-
2014
- 2014-03-11 CA CA2901879A patent/CA2901879C/en not_active Expired - Fee Related
- 2014-03-11 EP EP14775660.5A patent/EP2971213B1/en not_active Not-in-force
- 2014-03-11 RU RU2015143481A patent/RU2665655C2/en not_active IP Right Cessation
- 2014-03-11 CN CN201480014854.3A patent/CN105143492B/en not_active Expired - Fee Related
- 2014-03-11 WO PCT/US2014/023032 patent/WO2014159324A1/en active Application Filing
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2015
- 2015-08-18 IL IL240665A patent/IL240665A0/en unknown
Non-Patent Citations (1)
Title |
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None * |
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CN105143492B (en) | 2019-04-09 |
CA2901879C (en) | 2021-06-08 |
RU2015143481A (en) | 2017-04-26 |
WO2014159324A1 (en) | 2014-10-02 |
CA2901879A1 (en) | 2014-10-02 |
EP2971213A4 (en) | 2016-12-14 |
EP2971213A1 (en) | 2016-01-20 |
RU2665655C2 (en) | 2018-09-03 |
RU2015143481A3 (en) | 2018-03-06 |
CN105143492A (en) | 2015-12-09 |
IL240665A0 (en) | 2015-10-29 |
US20150376740A1 (en) | 2015-12-31 |
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