WO2009073794A1 - Improved aluminum-copper-lithium alloys - Google Patents
Improved aluminum-copper-lithium alloys Download PDFInfo
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- WO2009073794A1 WO2009073794A1 PCT/US2008/085547 US2008085547W WO2009073794A1 WO 2009073794 A1 WO2009073794 A1 WO 2009073794A1 US 2008085547 W US2008085547 W US 2008085547W WO 2009073794 A1 WO2009073794 A1 WO 2009073794A1
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- alloy
- aluminum alloy
- extruded
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- aluminum
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- 229910000733 Li alloy Inorganic materials 0.000 title abstract description 5
- -1 aluminum-copper-lithium Chemical compound 0.000 title abstract description 5
- 239000001989 lithium alloy Substances 0.000 title abstract description 5
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 158
- 239000000956 alloy Substances 0.000 claims abstract description 158
- 229910052749 magnesium Inorganic materials 0.000 claims abstract description 12
- 229910052802 copper Inorganic materials 0.000 claims abstract description 11
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 10
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 10
- 239000012535 impurity Substances 0.000 claims abstract description 10
- 229910052744 lithium Inorganic materials 0.000 claims abstract description 10
- 229910052709 silver Inorganic materials 0.000 claims abstract description 10
- 229910052725 zinc Inorganic materials 0.000 claims abstract description 10
- 229910052748 manganese Inorganic materials 0.000 claims abstract description 8
- 229910000838 Al alloy Inorganic materials 0.000 claims description 69
- 238000005260 corrosion Methods 0.000 claims description 41
- 230000007797 corrosion Effects 0.000 claims description 41
- 238000001125 extrusion Methods 0.000 claims description 30
- 238000005336 cracking Methods 0.000 claims description 12
- 229910052710 silicon Inorganic materials 0.000 claims description 6
- 230000006835 compression Effects 0.000 claims description 5
- 238000007906 compression Methods 0.000 claims description 5
- 229910052742 iron Inorganic materials 0.000 claims description 5
- 229910052726 zirconium Inorganic materials 0.000 claims description 3
- 238000012360 testing method Methods 0.000 description 32
- 230000035882 stress Effects 0.000 description 28
- 230000032683 aging Effects 0.000 description 16
- 239000000463 material Substances 0.000 description 13
- 238000000034 method Methods 0.000 description 13
- 238000010438 heat treatment Methods 0.000 description 11
- 239000000203 mixture Substances 0.000 description 10
- 230000008569 process Effects 0.000 description 9
- FAPWRFPIFSIZLT-UHFFFAOYSA-M Sodium chloride Chemical compound [Na+].[Cl-] FAPWRFPIFSIZLT-UHFFFAOYSA-M 0.000 description 8
- XEEYBQQBJWHFJM-UHFFFAOYSA-N iron Substances [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 7
- 239000011777 magnesium Substances 0.000 description 7
- 239000010936 titanium Substances 0.000 description 7
- 239000011575 calcium Substances 0.000 description 6
- 238000005266 casting Methods 0.000 description 6
- 239000010949 copper Substances 0.000 description 6
- 230000006872 improvement Effects 0.000 description 6
- 238000004519 manufacturing process Methods 0.000 description 6
- 239000011572 manganese Substances 0.000 description 5
- 239000011701 zinc Substances 0.000 description 5
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 4
- 238000005275 alloying Methods 0.000 description 4
- 238000005242 forging Methods 0.000 description 4
- 238000000265 homogenisation Methods 0.000 description 4
- 238000010791 quenching Methods 0.000 description 4
- 239000011780 sodium chloride Substances 0.000 description 4
- 238000011282 treatment Methods 0.000 description 4
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 3
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 3
- 238000007792 addition Methods 0.000 description 3
- 238000013459 approach Methods 0.000 description 3
- 229910052796 boron Inorganic materials 0.000 description 3
- 239000011651 chromium Substances 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 238000004299 exfoliation Methods 0.000 description 3
- 235000012438 extruded product Nutrition 0.000 description 3
- 238000009661 fatigue test Methods 0.000 description 3
- 238000001953 recrystallisation Methods 0.000 description 3
- 229910052719 titanium Inorganic materials 0.000 description 3
- QYEXBYZXHDUPRC-UHFFFAOYSA-N B#[Ti]#B Chemical compound B#[Ti]#B QYEXBYZXHDUPRC-UHFFFAOYSA-N 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 2
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 2
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 description 2
- 229910033181 TiB2 Inorganic materials 0.000 description 2
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 2
- 229910052790 beryllium Inorganic materials 0.000 description 2
- 229910052791 calcium Inorganic materials 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 239000004918 carbon fiber reinforced polymer Substances 0.000 description 2
- 229910052804 chromium Inorganic materials 0.000 description 2
- 230000001186 cumulative effect Effects 0.000 description 2
- 230000001419 dependent effect Effects 0.000 description 2
- ZOMNIUBKTOKEHS-UHFFFAOYSA-L dimercury dichloride Chemical class Cl[Hg][Hg]Cl ZOMNIUBKTOKEHS-UHFFFAOYSA-L 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000011156 evaluation Methods 0.000 description 2
- 229910052735 hafnium Inorganic materials 0.000 description 2
- 238000007654 immersion Methods 0.000 description 2
- 230000008018 melting Effects 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
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- 239000002245 particle Substances 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
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- 230000000171 quenching effect Effects 0.000 description 2
- 238000007670 refining Methods 0.000 description 2
- 150000003839 salts Chemical class 0.000 description 2
- 229910052706 scandium Inorganic materials 0.000 description 2
- 239000004332 silver Substances 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 229910052712 strontium Inorganic materials 0.000 description 2
- 229910001148 Al-Li alloy Inorganic materials 0.000 description 1
- 229910018575 Al—Ti Inorganic materials 0.000 description 1
- OYPRJOBELJOOCE-UHFFFAOYSA-N Calcium Chemical compound [Ca] OYPRJOBELJOOCE-UHFFFAOYSA-N 0.000 description 1
- 239000002970 Calcium lactobionate Substances 0.000 description 1
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 1
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 1
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- ATBAMAFKBVZNFJ-UHFFFAOYSA-N beryllium atom Chemical compound [Be] ATBAMAFKBVZNFJ-UHFFFAOYSA-N 0.000 description 1
- 239000001768 carboxy methyl cellulose Substances 0.000 description 1
- 239000010406 cathode material Substances 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000000593 degrading effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 description 1
- 230000036541 health Effects 0.000 description 1
- 238000005098 hot rolling Methods 0.000 description 1
- 239000004615 ingredient Substances 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 239000002054 inoculum Substances 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000002386 leaching Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000001556 precipitation Methods 0.000 description 1
- 238000004881 precipitation hardening Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- SIXSYDAISGFNSX-UHFFFAOYSA-N scandium atom Chemical compound [Sc] SIXSYDAISGFNSX-UHFFFAOYSA-N 0.000 description 1
- VSZWPYCFIRKVQL-UHFFFAOYSA-N selanylidenegallium;selenium Chemical compound [Se].[Se]=[Ga].[Se]=[Ga] VSZWPYCFIRKVQL-UHFFFAOYSA-N 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
- 239000010703 silicon Substances 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000005482 strain hardening Methods 0.000 description 1
- CIOAGBVUUVVLOB-UHFFFAOYSA-N strontium atom Chemical compound [Sr] CIOAGBVUUVVLOB-UHFFFAOYSA-N 0.000 description 1
- 238000003878 thermal aging Methods 0.000 description 1
- 229910052720 vanadium Inorganic materials 0.000 description 1
- LEONUFNNVUYDNQ-UHFFFAOYSA-N vanadium atom Chemical compound [V] LEONUFNNVUYDNQ-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/12—Alloys based on aluminium with copper as the next major constituent
- C22C21/16—Alloys based on aluminium with copper as the next major constituent with magnesium
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/12—Alloys based on aluminium with copper as the next major constituent
- C22C21/18—Alloys based on aluminium with copper as the next major constituent with zinc
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/12—Alloys based on aluminium with copper as the next major constituent
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
- C22F1/057—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
Definitions
- Aluminum alloys are useful in a variety of applications. However, improving one property of an aluminum alloy without degrading another property often proves 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, density and fatigue, to name a few.
- the present disclosure relates to aluminum-copper-lithium alloys having an improved combination of properties.
- the aluminum alloy is a wrought aluminum alloy consisting essentially of 3.4 - 4.2 wt. % Cu, 0.9 - 1.4 wt. % Li, 0.3 - 0.7 wt. % Ag, 0.1 - 0.6 wt. % Mg, 0.2 - 0.8 wt. % Zn, 0.1 - 0.6 wt. % Mn, and 0.01 - 0.6 wt. % of at least one grain structure control element, the balance being aluminum and incidental elements and impurities.
- the wrought product may be an extrusion, plate, sheet or forging product. In one embodiment, the wrought product is an extruded product. In one embodiment, the wrought product is a plate product. In one embodiment, the wrought product is a sheet product. In one embodiment, the wrought product is a forging.
- the alloy is an extruded aluminum alloy.
- the alloy has an accumulated cold work of not greater than an equivalent of 4% stretch.
- the alloy has an accumulated cold work of not greater than an equivalent of 3.5% or not greater than an equivalent of 3% or even not greater than an equivalent of 2.5 % stretch.
- accumulated cold work means cold work accumulated in the product after solution heat treatment.
- the aluminum alloy includes at least about 3.6 or 3.7 wt. %, or even at least about 3.8 wt. % Cu. In some embodiments, the aluminum alloy includes not greater than about 4.1 or 4.0 wt. % Cu. In some embodiments, the aluminum alloy includes copper in the range of from about 3.6 or 3.7 wt. % to about 4.0 or 4.1 wt. %. In one embodiment, the aluminum alloy includes copper in the range of from about 3.8 wt. % to about 4.0 wt. %.
- the aluminum alloy includes at least about 1.0 or 1.1 wt. % Li. In some embodiments, the aluminum alloy includes not greater than about 1.3 or 1.2 wt. % Li. In some embodiments, the aluminum alloy includes lithium in the range of from about 1.0 or 1.1 wt. % to about 1.2 or 1.3 wt. %.
- the aluminum alloy includes at least about 0.3 or 0.35 or 0.4 or 0.45 wt. % Zn. In some embodiments, the aluminum alloy includes not greater than about 0.7 or 0.65 or 0.6 or 0.55 wt. % Zn. In some embodiments, the aluminum alloy includes zinc in the range of from about 0.3 or 0.4 wt. % to about 0.6 or 0.7 wt. %.
- the aluminum alloy includes at least about 0.35 or 0.4 or 0.45 wt. % Ag. In some embodiments, the aluminum alloy includes not greater than about 0.65 or 0.6 or 0.55 wt. % Ag. In some embodiments, the aluminum alloy includes silver in the range of from about 0.35 or 0.4 or 0.45 wt. % to about 0. 55 or 0.6 or 0.65 wt. %.
- the aluminum alloy includes at least about 0.2 or 0.25 wt. % Mg. In some embodiments, the aluminum alloy includes not greater than about 0.5 or 0.45 wt. % Mg. In some embodiments, the aluminum alloy includes magnesium in the range of from about 0.2 or 0.25 wt. % to about 0.45 or 0.5 wt. %.
- the aluminum alloy includes at least about 0.15 or 0.2 wt. % Mg. In some embodiments, the aluminum alloy includes not greater than about 0.5 or 0.4 wt. % Mg. In some embodiments, the aluminum alloy includes manganese in the range of from about 0.15 or 0.2 wt. % to about 0.4 or 0.5 wt. %.
- the grain structure control element is Zr.
- the aluminum alloy includes 0.05 - 0.15 wt. % Zr.
- the impurities include Fe and Si.
- the alloy includes not greater than about 0.06 wt. % Si (e.g., ⁇ 0.03 wt. % Si) and not greater than about 0.08 wt. % Fe (e.g., ⁇ 0.04 wt. % Fe).
- the aluminum alloy may realize an improved combination of mechanical properties and corrosion resistant properties.
- an aluminum alloy realizes a longitudinal tensile yield strength of at least about 86 ksi.
- the aluminum alloy realizes an L-T plane strain fracture toughness of at least about 20 ksWin.
- the aluminum alloy realizes a typical tension modulus of at least about 11.3 x 10 3 ksi and a typical compression modulus of at least about 11.6 x 10 3 ksi.
- the aluminum alloy has a density of not greater than about 0.097 lbs./in 3 .
- the aluminum alloy has a specific strength of at least about 8.66 x 10 5 in.
- the aluminum alloy realizes a compressive yield strength of at least about 90 ksi. In one embodiment, the aluminum alloy is resistant to stress corrosion cracking. In one embodiment, the aluminum alloy achieves a MASTMAASIS rating of at least EA. In one embodiment, the alloy is resistant to galvanic corrosion. In some aspects, a single aluminum alloy may realize numerous ones (or even all) of the above properties. In one embodiment, the aluminum alloy at least realizes a longitudinal strength of at least about 84 ksi, an L-T plane strain fracture toughness of at least about 20 ksWin, is resistant to stress corrosion cracking and is resistant to galvanic corrosion.
- FIG. Ia is a schematic view illustrating one embodiment of a test specimen for use in fracture toughness testing.
- FIG. Ib is a dimension and tolerance table relating to FIG. Ia.
- FIG. 2 is a graph illustrating typical tensile yield strength versus tensile modulus values for various alloys.
- FIG. 3 is a graph illustrating typical specific tensile yield strength values for various alloys.
- FIG. 4 is a schematic view illustrating one embodiment of a test coupon for use in notched S/N fatigue testing.
- FIG. 5 is a graph illustrating the galvanic corrosion resistance of various alloys.
- the instant disclosure relates to aluminum-copper-lithium alloys having an improved combination of properties.
- the aluminum alloys generally comprise (and in some instances consist essentially of) copper, lithium, zinc, silver, magnesium, and manganese, the balance being aluminum, optional grain structure control elements, optional incidental elements and impurities.
- Table 1, below The composition limits of several alloys useful in accordance with the present teachings are disclosed in Table 1, below.
- the composition limits of several prior art alloys are disclosed in Table 2, below. All values given are in weight percent.
- the alloys of the present disclosure generally include the stated alloying ingredients, the balance being aluminum, optional grain structure control elements, optional incidental elements and impurities.
- grain structure control element means elements or compounds that are deliberate alloying additions with the goal of forming second phase particles, usually in the solid state, to control solid state grain structure changes during thermal processes, such as recovery and recrystallization. Examples of grain structure control elements include Zr, Sc, V, Cr, and Hf, to name a few.
- the amount of grain structure control material utilized in an alloy is generally dependent on the type of material utilized for grain structure control and the alloy production process. When zirconium (Zr) is included in the alloy, it may be included in an amount up to about 0.4 wt.
- Zr is included in the alloy in an amount of 0.05 - 0.15 wt. %.
- Scandium (Sc), vanadium (V), chromium (Cr), and/or hafnium (Hf) may be included in the alloy as a substitute (in whole or in part) for Zr, and thus may be included in the alloy in the same or similar amounts as Zr.
- manganese (Mn) may be included in the alloy in addition to or as a substitute (in whole or in part) for Zr.
- Mn manganese
- it may be included in the amounts disclosed above.
- incidental elements means those elements or materials that may optionally be added to the alloy to assist in the production of the alloy.
- incidental elements include casting aids, such as grain refiners and deoxidizers.
- Grain refiners are inoculants or nuclei to seed new grains during solidification of the alloy.
- An example of a grain refiner is a 3/8 inch rod comprising 96% aluminum, 3% titanium (Ti) and 1% boron (B), where virtually all boron is present as finely dispersed TiB 2 particles.
- the grain refining rod is fed in-line into the molten alloy flowing into the casting pit at a controlled rate.
- the amount of grain refiner included in the alloy is generally dependent on the type of material utilized for grain refining and the alloy production process.
- grain refiners examples include Ti combined with B (e.g., TiB 2 ) or carbon (TiC), although other grain refiners, such as Al-Ti master alloys may be utilized.
- B e.g., TiB 2
- TiC carbon
- grain refiners are added in an amount of ranging from 0.0003 wt. % to 0.005 wt. % to the alloy, depending on the desired as-cast grain size.
- Ti may be separately added to the alloy in an amount up to 0.03 wt. % to increase the effectiveness of grain refiner. When Ti is included in the alloy, it is generally present in an amount of up to about 0.10 or 0.20 wt. %.
- Some alloying elements may be added to the alloy during casting to reduce or restrict (and is some instances eliminate) cracking of the ingot resulting from, for example, oxide fold, pit and oxide patches.
- deoxidizers include Ca, Sr, and Be.
- calcium (Ca) is included in the alloy, it is generally present in an amount of up to about 0.05 wt. %, or up to about 0.03 wt. %.
- Ca is included in the alloy in an amount of 0.001 - 0.03 wt% or 0.05 wt. %, such as 0.001-0.008 wt. % (or 10 to 80 ppm).
- Strontium (Sr) may be included in the alloy as a substitute for Ca (in whole or in part), and thus may be included in the alloy in the same or similar amounts as Ca.
- Be beryllium
- some embodiments of the alloy are substantially Be-free.
- Be is included in the alloy, it is generally present in an amount of up to about 20 ppm.
- Incidental elements may be present in minor amounts, or may be present in significant amounts, and may add desirable or other characteristics on their own without departing from the alloy described herein, so long as the alloy retains the desirable characteristics described herein. It is to be understood, however, that the scope of this disclosure should not/cannot be avoided through the mere addition of an element or elements in quantities that would not otherwise impact on the combinations of properties desired and attained herein.
- impurities are those materials that may be present in the alloy in minor amounts due to, for example, the inherent properties of aluminum or and/or leaching from contact with manufacturing equipment.
- Iron (Fe) and silicon (Si) are examples of impurities generally present in aluminum alloys.
- the Fe content of the alloy should generally not exceed about 0.25 wt. %. In some embodiments, the Fe content of the alloy is not greater than about 0.15 wt. %, or not greater than about 0.10 wt. %, or not greater than about 0.08 wt. %, or not greater than about 0.05 or 0.04 wt. %.
- the Si content of the alloy should generally not exceed about 0.25 wt.
- the Si content of the alloy is not greater than about 0.12 wt. %, or not greater than about 0.10 wt. %, or not greater than about 0.06 wt. %, or not greater than about 0.03 or 0.02 wt. %.
- the alloys can be prepared by more or less conventional practices including melting and direct chill (DC) casting into ingot form.
- Conventional grain refiners such as those containing titanium and boron, or titanium and carbon, may also be used as is well-known in the art.
- the product may be solution heat treated (SHT) and quenched, and then mechanically stress relieved, such as by stretching and/or compression up to about 4% permanent strain, for example, from about 1 to 3%, or 1 to 4 %.
- SHT solution heat treated
- Similar SHT, quench, stress relief and artificial aging operations may also be completed to manufacture rolled products (e.g., sheet/plate) and/or forged products.
- the new alloys disclosed herein achieve an improved combination of properties relative to 7xxx and other 2xxx series alloys.
- the new alloys may achieve an improved combination of two or more of the following properties: ultimate tensile strength (UTS), tensile yield strength (TYS), compressive yield strength (CYS), elongation (El) fracture toughness (FT), specific strength, modulus (tensile and/or compressive), specific modulus, corrosion resistance, and fatigue, to name a few.
- UTS ultimate tensile strength
- TYS tensile yield strength
- CYS compressive yield strength
- El elongation
- FT fracture toughness
- specific strength, modulus (tensile and/or compressive) specific modulus, corrosion resistance, and fatigue, to name a few.
- Realizing these properties with low amounts of accumulated cold work is
- the alloys may achieve a longitudinal (L) ultimate tensile strength of at least about 92 ksi, or even at least about 100 ksi.
- the alloys may achieve a longitudinal tensile yield strength of at least about 84 ksi, or at least about 86 ksi, or at least about 88 ksi, or at least about 90 ksi, or even at least about 97 ksi.
- the alloys may achieve a longitudinal compressive yield strength of at least about 88 ksi, or at least about 90 ksi, or at least about 94 ksi, or even at least about 98 ksi.
- the alloys may achieve an elongation of at least about 7%, or even at least about 10%.
- the ultimate tensile strength and/or tensile yield strength and/or elongation is measured in accordance with ASTM E8 and/or B557, and at the quarter-plane of the product.
- the product e.g., the extrusion
- the compressive yield strength is measured in accordance with ASTM E9 and/or El 11, and at the quarter-plane of the product. It may be appreciated that strength can vary somewhat with thickness. For example, thin (e.g., 0.500 inch) or thick products (e.g., >3.0 inches) may have somewhat lower strengths than those described above. Nonetheless, those thin or thick products still provide distinct advantages relative to previously available alloy products.
- the alloys may achieve a long-transverse (L-T) plane strain fracture toughness of at least about 20 ksiVin., or at least about 23 ksWin., or at least about 27 ksiVin., or even at least about 31 ksWin.
- the fracture toughness is measured in accordance with ASTM E399 at the quarter-plane, and with the specimen configuration illustrated in FIG. Ia. It may be appreciated that fracture toughness can vary somewhat with thickness and testing conditions. For example, thick products (e.g., >3.0 inches) may have somewhat lower fracture toughness than those described above. Nonetheless, those thick products still provide distinct advantages relative to previously available products.
- FIG. Ia a dimension and tolerances table is provided in FIG Ib.
- Note 1 of FIG. Ia states grains in this direction for L-T and L-S specimens.
- Note 2 of FIG. Ia states grain in this direction for T-L and T-S specimens.
- Note 3 of FIG. Ia states S notch dimension shown is maximum, if necessary may be narrower.
- the alloys may realize a density of not greater than about 0.097 lb/in 3 , such as in the range of 0.096 to 0.097 lb/in 3 .
- the alloys may achieve a typical tensile modulus of at least about 11.3 or 11.4 x 10 3 ksi.
- the alloys may realize a typical compressive modulus of at least about 11.6 or 11.7 x 10 3 ksi.
- the modulus (tensile or compressive) may be measured in accordance with ASTM El I l and/or B557, and at the quarter-plane of the specimen.
- the alloys may realize a specific tensile modulus of at least about 1.16 x 10 in.
- the alloys may realize a specific compression modulus of at least about 1.19 x 10 8 in.
- the alloys may be resistant to stress corrosion cracking.
- resistant to stress corrosion cracking means that the alloys pass an alternate immersion corrosion test (3.5 wt. % NaCl) while being stressed (i) at least about 55 ksi in the LT direction, and/or (ii) at least about 25 ksi in the ST direction.
- the stress corrosion cracking tests are conducted in accordance with ASTM G47.
- the alloys may achieve at least an "EA” rating, or at least an "N” rating, or even at least an "P” rating in a MASTMAASIS testing process for either or both of the T/2 or T/ 10 planes of the product, or other relevant test planes and locations.
- the MASTMAASIS tests are conducted in accordance with ASTM G85-Annex 2 and/or ASTM G34.
- the alloys may realize improved galvanic corrosion resistance, achieving low corrosion rates when connected to a cathode, which is known to accelerate corrosion of aluminum alloys.
- Galvanic corrosion refers to the process in which corrosion of a given material, usually a metal, is accelerated by connection to another electrically conductive material.
- the morphology of this type of accelerated corrosion can vary depending on the material and environment, but could include pitting, intergranular, exfoliation, and other known forms of corrosion. Often this acceleration is dramatic, causing materials that would otherwise be highly resistant to corrosion to deteriorate rapidly, thereby shortening structure lifetime.
- Galvanic corrosion resistance is a consideration for modern aircraft designs.
- Some modern aircraft may combine many different materials, such as aluminum with carbon fiber reinforced plastic composites (CFRP) and/or titanium parts.
- CFRP carbon fiber reinforced plastic composites
- Some of these parts are very cathodic to aluminum, meaning that the part or structure produced from an aluminum alloy may experience accelerated corrosion rates when in electrical communication (e.g., direct contact) with these materials.
- the new alloy disclosed herein is resistant to galvanic corrosion.
- resistant to galvanic corrosion means that the new alloy achieves at least 50% lower current density (uA/cm 2 ) in a quiescent 3.5% NaCl solution at a potential of from about -0.7 to about -0.6 (volts versus a saturated calomel electrode (SCE)) than a 7xxx alloy of similar size and shape, and which 7xxx alloy has a similar strength and toughness to that of the new alloy.
- Some 7xxx alloys suitable for this comparative purpose include 7055 and 7150.
- the galvanic corrosion resistance tests are performed by immersing the alloy sample in the quiescent solution and then measuring corrosion rates by monitoring electrical current density at the noted electrochemical potentials (measured in volts vs. a saturated calomel electrode). This test simulates connection with a cathodic material, such as those described above.
- the new alloy achieves at least 75%, or at least 90%, or at least 95%, or even at least 98% or 99% lower current density (uA/cm ) in a quiescent 3.5% NaCl solution at a potential of from about -0.7 to about -0.6 (volts versus SCE) than a 7xxx alloy of similar size and shape, and which 7xxx alloy has a similar strength and toughness to that of the new alloy.
- the new alloy achieves better galvanic corrosion resistance and a lower density than these 7xxx alloys, while achieving similar strength and toughness, the new alloy is well suited as a replacement for these 7xxx alloys. The new alloy may even be used in applications for which the 7xxx alloys would be rejected because of corrosion concerns.
- the alloys may realize a notched S/N fatigue life of at least about 90,000 cycles, on average, for a 0.95 inch thick extrusion, at a max stress of 35 ksi.
- the alloys may achieve a notched S/N fatigue life of at least about 75,000 cycles, on average for a 3.625 inches thick extrusion at a max stress of 35 ksi. Similar values may be achieved for other wrought products.
- the new alloy realizes an improved combination of mechanical properties relative to the prior art alloys.
- the new alloy realizes an improved combination of strength and modulus relative to the prior art alloys.
- the new alloy realizes improved specific tensile yield strength relative to the prior art alloys.
- the new aluminum alloy due to its improved combination of properties, may be employed in many structures including vehicles such as airplanes, bicycles, automobiles, trains, recreational equipment, and piping, to name a few.
- vehicles such as airplanes, bicycles, automobiles, trains, recreational equipment, and piping, to name a few.
- Examples of some typical uses of the new alloy in extruded form relative to airplane construction include stringers (e.g., wing or fuselage), spars (integral or non-integral), ribs, integral panels, frames, keel beams, floor beams, seat tracks, false rails, general floor structure, pylons and engine surrounds, to name a few.
- the alloys may be produced by a series of conventional aluminum alloy processing steps, including casting, homogenization, solution heat treatment, quench, stretch and/or aging.
- the alloy is made into a product, such as an ingot derived product, suitable for extruding.
- a product such as an ingot derived product
- large ingots can be semi-continuously cast having the compositions described above.
- the ingot may then be preheated to homogenize and solutionize its interior structure.
- a suitable preheat treatment step heats the ingot to a relatively high temperature, such as about 955 0 F.
- a first lesser temperature level such as heating above 900 0 F, for instance about 925 - 94O 0 F, and then hold the ingot at that temperature for several hours (e.g., 7 or 8 hours).
- the ingot is heated to the final holding temperature (e.g., 940-955 0 F and held at that temperature for several hours (e.g., 2-4 hours).
- the homogenization step is generally conducted at cumulative hold times in the neighborhood of 4 to 20 hours, or more.
- the homogenizing temperatures are generally the same as the final preheat temperature (e.g., 940 - 955 0 F).
- the cumulative hold time at temperatures above 94O 0 F should be at least 4 hours, such as 8 to 20 or 24 hours, or more, depending on, for example, ingot size.
- Preheat and homogenization aid in keeping the combined total volume percent of insoluble and soluble constituents low, although high temperatures warrant caution to avoid partial melting. Such cautions can include careful heat- ups, including slow or step-type heating, or both.
- the ingot may be scalped and/or machined to remove surface imperfections, as needed, or to provide a good extrusion surface, depending on the extrusion method.
- the ingot may then be cut into individual billets and reheated.
- the reheat temperatures are generally in the range of 700-800 0 F and the reheat period varies from a few minutes to several hours, depending on the size of the billet and the capability of the furnace used for processing.
- the ingot may be extruded via a heated setup, such as a die or other tooling set at elevated temperatures (e.g., 650 - 900 0 F) and may include a reduction in cross-sectional area (extrusion ratio) of about 7:1 or more.
- the extrusion speed is generally in the range of 3 - 12 feet per minute, depending on the reheat and tooling and/or die temperatures.
- the extruded aluminum alloy product may exit the tooling at a temperature in the range of, for example, 830 - 88O 0 F.
- the extrusion may be solution heat treated (SHT) by heating at elevated temperature, generally 940 - 955°F to take into solution all or nearly all of the alloying elements at the SHT temperature.
- SHT solution heat treated
- the product may be quenched by immersion or spraying, as is known in the art. After quenching, certain products may need to be cold worked, such as by stretching or compression, so as to relieve internal stresses or straighten the product, and, in some cases, to further strengthen the product.
- an extrusion may have an accumulated stretch of as little as 1% or 2%, and, in some instance, up to 2.5%, or 3%, or 3.5%, or, in some cases, up to 4%, or a similar amount of accumulated cold work.
- accumulated cold work means cold work accumulated in the product after solution heat treatment, whether by stretching or otherwise.
- a solution heat treated and quenched product, with or without cold working, is then in a precipitation-hardenable condition, or ready for artificial aging, described below.
- solution heat treat includes quenching, unless indicated otherwise.
- Other wrought product forms may be subject to other types of cold deformation prior to aging.
- the product may be artificially aged by heating to an appropriate temperature to improve strength and/or other properties.
- the thermal aging treatment includes two main aging steps. It is generally known that ramping up to and/or down from a given or target treatment temperature, in itself, can produce precipitation (aging) effects which can, and often need to be, taken into account by integrating such ramping conditions and their precipitation hardening effects into the total aging treatments.
- the first stage aging occurs in the temperature range of 200-275 0 F and for a period of about 12-17 hours.
- the second stage aging occurs in the temperature range of 290 - 325 0 F, and for a period of about 16 - 22 hours.
- the two ingots are stress relieved, cropped to 105" lengths each and ultrasonically inspected.
- the billets are homogenized as follows:
- each parent shape is individually heat treated, quenched, and stretched. Heat treatment is accomplished at about 945-955 0 F, with a one hour soak. A stretch of 2.5% is targeted.
- etch slices for each shape are examined and reveal recrystallization layers ranging from 0.001 to 0.010 inches. Some of the thinner small press shapes do, however, exhibit a mixed grain (recrystallized and unrecrystallized) microstructure.
- a multi-step age practice is developed. Multi-step age combinations are evaluated to improve the strength - toughness relationship, while also endeavoring to achieve the static property targets of known high strength 7xxx alloys.
- the finally developed multi-step aging practice is a first aging step at 270 0 F for about 15 hours, and a second aging step at about 32O 0 F for about 18 hours.
- Corrosion testing is performed during temper development. Stress corrosion cracking (SCC) tests are performed in accordance with ASTM G47 and G49 on the sample alloy, and in the direction and stress combinations of LT/55 ksi and ST/25 ksi. The alloys passes the SCC tests even after 155 days.
- SCC Stress corrosion cracking
- MASTMAASIS testing is also performed, and reveals only a slight degree of exfoliation at the T/10 and T2 planes for single and multi-step age practices.
- the MASTMAASIS results yield a "P" rating for the alloys at both T/2 and T/10 planes.
- the alloys realize an improved combination of strength and toughness over conventionally extruded alloys 2099 and 2196.
- the alloys also realize similar strength and toughness relative to conventional 7xxx alloys 7055 and 7150, but are much lighter, providing a higher specific strength than the 7xxx alloys.
- the new alloys also achieve a much better tensile and compressive modulus relative to the 7xxx alloys. This combination of properties is unique and unexpected.
- the ingots are stress relieved and three ingots of cast 1-A and three ingots of cast 1- B are homogenized as follows:
- Furnace set at 94O 0 F and charge all 6 ingots into said furnace;
- the billets are cut to length and pealed to the desired diameter.
- the billets are extruded into 7 large press shapes.
- the shape thicknesses range from 0.75 inch to 7 inches thick.
- Extrusion speeds and press thermal settings are in the range of 3 - 12 feet per minute, and at from about 690-710 0 F to about 750-810 0 F.
- each parent shape is individually solution heat treated, quenched and stretched. Solution heat treatments targeted 945 - 955°F, with soak times set, depending on extrusion thickness, in the range of 30 minutes to 75 minutes. A stretch of 3% is targeted.
- etch slices for each shape are examined and reveal recrystallization layers ranging from 0.001 to 0.010 inches.
- Multi-step aging cycles are completed to increase the strength and toughness combination.
- a first step aging is at about 27O 0 F for about 15 hours
- a second step aging is at about 32O 0 F for about 18 hours.
- MASTMAASIS testing is also performed in accordance with ASTM G85-Annex 2 and/or ASTM G34.
- the alloys achieve a MASTMAASIS rating of
- Notched S/N fatigue testing is also performed in accordance with ASTM E466 at the T/2 plane to obtain stress-life (S-N or S/N) fatigue curves.
- Stress-life fatigue tests characterize a material's resistance to fatigue initiation and small crack growth which comprises a major portion of the total fatigue life.
- improvements in S-N fatigue properties may enable a component to operate at a higher stress over its design life or operate at the same stress with increased lifetime.
- the former can translate into significant weight savings by downsizing, while the latter can translate into fewer inspections and lower support costs.
- the S-N fatigue results are provided in Table 7, below.
- the results are obtained for a net max stress concentration factor, Kt, of 3.0 using notched test coupons.
- the test coupons are fabricated as illustrated in FIG. 4.
- the test frequency is 25 Hz, and the tests are performed in ambient laboratory air.
- the notch should be machined as follows: (i) feed tool at 0.0005" per rev. until specimen is 0.280"; (ii) pull tool out to break chip; (iii) feed tool at 0.0005" per rev. to final notch diameter. Also, all specimens should be degreased and ultrasonically cleaned, and hydraulic grips should be utilized.
- the new alloy showed significant improvements in fatigue life with respect to the industry standard 7150-T77511 product.
- the new alloy realizes a lifetime (based on the log average of all specimens tested at that stress) of 93,771 cycles compared to a typical 11,250 cycles for the standard 7150-T77511 alloy.
- the alloy realizes an average lifetime of 3,844,742 cycles compared to a typical 45,500 cycles at net stress of 25 ksi for the 7150-T77511 alloy.
- fatigue lifetime will depend not only on stress concentration factor (Kt), but also on other factors including but not limited to specimen type and dimensions, thickness, method of surface preparation, test frequency and test environment.
- Kt stress concentration factor
- FIG. 5 is a graph illustrating the galvanic corrosion resistance of the new alloy.
- the new alloy realizes at least a 50% lower current density than alloy 7150, the degree of improvement varying somewhat with potential.
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CA2707311A CA2707311C (en) | 2007-12-04 | 2008-12-04 | Improved aluminum-copper-lithium alloys |
BRPI0820679A BRPI0820679A2 (en) | 2007-12-04 | 2008-12-04 | improved aluminum-copper-lithium alloys |
EP08857160.9A EP2231888B1 (en) | 2007-12-04 | 2008-12-04 | Improved aluminum-copper-lithium alloys |
RU2010127284/02A RU2497967C2 (en) | 2007-12-04 | 2008-12-04 | Improved aluminium-copper-lithium alloys |
JP2010537054A JP2011505500A (en) | 2007-12-04 | 2008-12-04 | Improved aluminum-copper-lithium alloy |
CN2008801194806A CN101889099A (en) | 2007-12-04 | 2008-12-04 | Improved Solder for Al-Cu Joint Welding-lithium alloy |
AU2008333796A AU2008333796B2 (en) | 2007-12-04 | 2008-12-04 | Improved aluminum-copper-lithium alloys |
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- 2008-12-04 KR KR1020107014731A patent/KR101538529B1/en active IP Right Grant
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EP2847361B1 (en) | 2012-05-09 | 2017-01-11 | Alcoa Inc. | 2xxx series aluminum lithium alloys |
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Also Published As
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US20090142222A1 (en) | 2009-06-04 |
BRPI0820679A2 (en) | 2019-09-10 |
AU2008333796A1 (en) | 2009-06-11 |
CN104674090A (en) | 2015-06-03 |
EP2231888A1 (en) | 2010-09-29 |
AU2008333796B2 (en) | 2013-08-22 |
US8118950B2 (en) | 2012-02-21 |
CA2707311A1 (en) | 2009-06-11 |
CA2707311C (en) | 2017-09-05 |
EP2231888B1 (en) | 2014-08-06 |
EP2829623A1 (en) | 2015-01-28 |
US20120132324A1 (en) | 2012-05-31 |
RU2639177C2 (en) | 2017-12-20 |
RU2010127284A (en) | 2012-01-10 |
US9587294B2 (en) | 2017-03-07 |
AU2013257457B2 (en) | 2016-03-31 |
RU2013135284A (en) | 2015-02-10 |
KR20100099248A (en) | 2010-09-10 |
JP2011505500A (en) | 2011-02-24 |
KR101538529B1 (en) | 2015-07-21 |
CN101889099A (en) | 2010-11-17 |
RU2497967C2 (en) | 2013-11-10 |
EP2829623B1 (en) | 2018-02-07 |
US20140212326A1 (en) | 2014-07-31 |
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