US20090263273A1 - High strength L12 aluminum alloys - Google Patents
High strength L12 aluminum alloys Download PDFInfo
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- US20090263273A1 US20090263273A1 US12/148,387 US14838708A US2009263273A1 US 20090263273 A1 US20090263273 A1 US 20090263273A1 US 14838708 A US14838708 A US 14838708A US 2009263273 A1 US2009263273 A1 US 2009263273A1
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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- C22C21/00—Alloys based on aluminium
- C22C21/10—Alloys based on aluminium with zinc as the next major constituent
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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
- C22F1/053—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
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- PA0006924U-U73.12-334KL HIGH STRENGTH L1 2 ALUMINUM ALLOYS, Ser. No. ______, Attorney Docket No. PA0006923U-U73.12-335KL; and L1 2 STRENGTHENED AMORPHOUS ALUMINUM ALLOYS, Ser. No. ______, Attorney Docket No. PA0001359U-U73.12-336KL.
- the present invention relates generally to aluminum alloys and more specifically to heat treatable aluminum alloys produced by melt processing and strengthened by L1 2 phase dispersions.
- aluminum alloys with improved elevated temperature mechanical properties is a continuing process.
- Some attempts have included aluminum-iron and aluminum-chromium based alloys such as Al—Fe—Ce, Al—Fe—V—Si, Al—Fe—Ce—W, and Al—Cr—Zr—Mn that contain incoherent dispersoids. These alloys, however, also lose strength at elevated temperatures due to particle coarsening. In addition, these alloys exhibit ductility and fracture toughness values lower than other commercially available aluminum alloys.
- U.S. Pat. No. 6,248,453 discloses aluminum alloys strengthened by dispersed Al 3 X L1 2 intermetallic phases where X is selected from the group consisting of Sc, Er, Lu, Yb, Tm, and U.
- the Al 3 X particles are coherent with the aluminum alloy matrix and are resistant to coarsening at elevated temperatures.
- the improved mechanical properties of the disclosed dispersion strengthened L1 2 aluminum alloys are stable up to 572° F. (300° C.).
- the alloys need to be manufactured by expensive rapid solidification processes with cooling rates in excess of 1.8 ⁇ 10 3 F/sec (10 3 C/sec).
- U.S. Patent Application Publication No. 2006/0269437 A1 discloses an aluminum alloy that contains scandium and other elements. While the alloy is effective at high temperatures, it is not capable of being heat treated using a conventional age hardening mechanism.
- the present invention is heat treatable aluminum alloys that can be cast, wrought, or formed by rapid solidification, and thereafter heat treated.
- the alloys can achieve high temperature performance and can be used at temperatures up to about 650° F. (343° C.).
- alloys comprise zinc, magnesium, and an Al 3 X L1 2 dispersoid where X is at least one first element selected from scandium, erbium, thulium, ytterbium, and lutetium, and at least one second element selected from gadolinium, yttrium, zirconium, titanium, hafnium, and niobium.
- the balance is substantially aluminum.
- the alloys may also include copper.
- the alloys have less than 1.0 weight percent total impurities.
- the alloys are formed by a process selected from casting, deformation processing and rapid solidification.
- the alloys are then heat treated at a temperature of from about 800° F. (426° C.) to about 1100° F. (593° C.) for between about 30 minutes and four hours, followed by quenching in water, and thereafter aged at a temperature from about 200° F. (93° C.) to about 600° F. (260° C.) for about two to about forty-eight hours.
- FIG. 1 is an aluminum zinc phase diagram.
- FIG. 2 is an aluminum copper phase diagram.
- FIG. 3 is an aluminum magnesium phase diagram.
- FIG. 4 is an aluminum scandium phase diagram.
- FIG. 5 is an aluminum erbium phase diagram.
- FIG. 6 is an aluminum thulium phase diagram.
- FIG. 7 is an aluminum ytterbium phase diagram.
- FIG. 8 is an aluminum lutetium phase diagram.
- the alloys of this invention are based on the aluminum, zinc, magnesium system.
- the amount of zinc in these alloys ranges from about 3.0 to about 12.0 weight percent, more preferably about 4.0 to about 10.0 weight percent, and even more preferably about 5.0 to about 9.0 weight percent.
- the amount of magnesium in these alloys ranges from about 0.5 to about 3.5 weight percent, more preferably about 1.0 to about 3.0 weight percent, and even more preferably about 1.5 to about 3.0 weight percent.
- the amount of copper in these alloys ranges from about 0.2 to about 3.0 weight percent, more preferably about 0.5 to about 2.5 weight percent, and even more preferably about 1.0 to about 2.5 weight percent.
- the aluminum zinc phase diagram is shown in FIG. 1 .
- the aluminum zinc binary system is a eutectic alloy system involving a monotectoid reaction and a miscibility gap in the solid state. There is a eutectic reaction at 94 weight percent zinc at 717.8° F. (381° C.).
- Zinc has maximum solid solubility of 83.1 weight percent in aluminum at 717.8° F. (381° C.) which can be extended by rapid solidification processing.
- the solubility of zinc in aluminum decreases with a decrease in temperature.
- Zinc provides significant amount of precipitation strengthening in aluminum by precipitation of fine second phases.
- the present invention is focused on hypoeutectic alloy composition ranges. Decomposition of the supersaturated solid solution of zinc in aluminum gives rise to spherical and ellipsoidal GP zones; precipitates with rhombohedral structure which are coherent with aluminum matrix and an incoherent ( ⁇ ′Al).
- the aluminum copper phase diagram is shown in FIG. 2 .
- the aluminum copper binary system is a eutectic alloy system with a eutectic reaction at 31.2 weight percent magnesium and 1018° F. (548.2° C.). Copper has maximum solid solubility of 6 weight percent in aluminum at 1018° F. (548.2° C.) which can be extended further by rapid solidification processing. Copper provides considerable amounts of precipitation strengthening in aluminum by precipitation of fine second phases.
- the present invention is focused on hypoeutectic alloy composition ranges.
- the aluminum magnesium phase diagram is shown in FIG. 3 .
- the binary system is a eutectic alloy system with a eutectic reaction at 36 weight percent magnesium and 842° F. (450° C.).
- Magnesium has maximum solid solubility of 16 weight percent in aluminum at 842° F. (450° C.) which can extended further by rapid solidification processing.
- Magnesium provides substantial solid solution strengthening in aluminum.
- magnesium provides precipitation strengthening through precipitation of Zn 2 Mg ( ⁇ ′) and Al 2 CuMg (S′) phases.
- the alloys of this invention contain aluminum solid solutions containing at least one element selected from zinc, copper and magnesium. These alloys also contain precipitates consisting of fine dispersions of Zn 2 Mg ( ⁇ ′) and Al 2 CuMg (S′) phases by decomposition of supersaturated solid solutions.
- solid solutions are dispersions of Al 3 X having an L1 2 structure where X is at least one element selected from scandium, erbium, thulium, ytterbium, and lutetium and at least one element selected from gadolinium, yttrium, zirconium, titanium, hafnium, and niobium.
- Exemplary aluminum alloys of this invention include, but are not limited to (in weight percent):
- scandium, erbium, thulium, ytterbium, and lutetium are potent strengtheners that have low diffusivity and low solubility in aluminum. All these elements form equilibrium Al 3 X intermetallic dispersoids where X is at least one of scandium, erbium, ytterbium, lutetium, that have an L1 2 structure that is an ordered face centered cubic structure with the X atoms located at the corners and aluminum atoms located on the cube faces of the unit cell.
- Al 3 Sc dispersoids forms Al 3 Sc dispersoids that are fine and coherent with the aluminum matrix.
- Lattice parameters of aluminum and Al 3 Sc are very close (0.405 nm and 0.410 nm respectively), indicating that there is minimal or no driving force for causing growth of the Al 3 Sc dispersoids.
- This low interfacial energy makes the Al 3 Sc dispersoids thermally stable and resistant to coarsening up to temperatures as high as about 840° F. (450° C.).
- these Al 3 Sc dispersoids are made stronger and more resistant to coarsening at elevated temperatures by adding suitable alloying elements such as gadolinium, yttrium, zirconium, titanium, hafnium, niobium, or combinations thereof, that enter Al 3 Sc in solution.
- Erbium forms Al 3 Er dispersoids in the aluminum matrix that are fine and coherent with the aluminum matrix.
- the lattice parameters of aluminum and Al 3 Er are close (0.405 nm and 0.417 nm respectively), indicating there is minimal driving force for causing growth of the Al 3 Er dispersoids.
- This low interfacial energy makes the Al 3 Er dispersoids thermally stable and resistant to coarsening up to temperatures as high as about 842° F. (450° C.).
- Addition of magnesium in solid solution in aluminum increases the lattice parameter of the aluminum matrix, and decreases the lattice parameter mismatch further increasing the resistance of the Al 3 Er to coarsening.
- additives of zinc and copper in aluminum provide significant precipitation strengthening through precipitation of fine second phases Zn 2 Mg ( ⁇ ′) and Al 2 CuMg (S′).
- these Al 3 Er dispersoids are made stronger and more resistant to coarsening at elevated temperatures by adding suitable alloying elements such as gadolinium, yttrium, zirconium, titanium, hafnium, niobium, or combinations thereof that enter Al 3 Er in solution.
- Thulium forms metastable Al 3 Tm dispersoids in the aluminum matrix that are fine and coherent with the aluminum matrix.
- the lattice parameters of aluminum and Al 3 Tm are close (0.405 nm and 420 nm respectively), indicating there is minimal driving force for causing growth of the Al 3 Tm dispersoids.
- This low interfacial energy makes the Al 3 Tm dispersoids thermally stable and resistant to coarsening up to temperatures as high as about 842° F. (450° C.).
- Addition of magnesium in solid solution in aluminum increases the lattice parameter of the aluminum matrix and decreases the lattice parameter mismatch further increasing the resistance to coarsening of the dispersoid.
- additives of zinc and copper in aluminum provide significant precipitation strengthening through precipitation of fine second phases Zn 2 Mg ( ⁇ ′) and Al 2 CuMg (S′).
- these Al 3 Tm dispersoids are made stronger and more resistant to coarsening at elevated temperatures by adding suitable alloying elements such as gadolinium, yttrium, zirconium, titanium, hafnium, niobium, or combinations thereof that enter Al 3 Tm in solution.
- Ytterbium forms Al 3 Yb dispersoids in the aluminum matrix that are fine and coherent with the aluminum matrix.
- the lattice parameters of Al and Al 3 Yb are close (0.405 nm and 0.420 nm respectively), indicating there is minimal driving force for causing growth of the Al 3 Yb dispersoids.
- This low interfacial energy makes the Al 3 Yb dispersoids thermally stable and resistant to coarsening up to temperatures as high as about 842° F. (450° C.).
- Addition of magnesium in solid solution in aluminum increases the lattice parameter of the aluminum matrix and decreases the lattice parameter mismatch further increasing the resistance to coarsening of the Al 3 Yb.
- additives of zinc and copper in aluminum provide significant precipitation strengthening through precipitation of fine second phases Zn 2 Mg ( ⁇ ′) and Al 2 CuMg (S′).
- these Al 3 Yb dispersoids are made stronger and more resistant to coarsening at elevated temperatures by adding suitable alloying elements such as gadolinium, yttrium, zirconium, titanium, hafnium, niobium, or combinations thereof that enter Al 3 Yb in solution.
- Al 3 Lu dispersoids forms Al 3 Lu dispersoids in the aluminum matrix that are fine and coherent with the aluminum matrix.
- the lattice parameters of Al and Al 3 Lu are close (0.405 nm and 0.419 nm respectively), indicating there is minimal driving force for causing growth of the Al 3 Lu dispersoids.
- This low interfacial energy makes the Al 3 Lu dispersoids thermally stable and resistant to coarsening up to temperatures as high as about 842° F. (450° C.).
- Addition of magnesium in solid solution in aluminum increases the lattice parameter of the aluminum matrix and decreases the lattice parameter mismatch further increasing the resistance to coarsening of Al 3 Lu.
- additives of zinc and copper in aluminum provide significant precipitation strengthening through precipitation of fine second phases Zn 2 Mg ( ⁇ ′) and Al 2 CuMg (S′).
- these Al 3 Lu dispersoids are made stronger and more resistant to coarsening at elevated temperatures by adding suitable alloying elements such as gadolinium, yttrium, zirconium, titanium, hafnium, niobium, or mixtures thereof that enter Al 3 Lu in solution.
- Gadolinium forms metastable Al 3 Gd dispersoids in the aluminum matrix that are stable up to temperatures as high as about 842° F. (450° C.) due to their low diffusivity in aluminum.
- the Al 3 Gd dispersoids have a D0 19 structure in the equilibrium condition.
- gadolinium has fairly high solubility in the Al 3 X intermetallic dispersoids (where X is scandium, erbium, thulium, ytterbium or lutetium).
- Gadolinium can substitute for the X atoms in Al 3 X intermetallic, thereby forming an ordered L1 2 phase which results in improved thermal and structural stability.
- Yttrium forms metastable Al 3 Y dispersoids in the aluminum matrix that have an L1 2 structure in the metastable condition and a D0 9 structure in the equilibrium condition.
- the metastable Al 3 Y dispersoids have a low diffusion coefficient which makes them thermally stable and highly resistant to coarsening.
- Yttrium has a high solubility in the Al 3 X intermetallic dispersoids allowing large amounts of yttrium to substitute for X in the Al 3 X L1 2 dispersoids which results in improved thermal and structural stability.
- Zirconium forms Al 3 Zr dispersoids in the aluminum matrix that have an L1 2 structure in the metastable condition and D0 23 structure in the equilibrium condition.
- the metastable Al 3 Zr dispersoids have a low diffusion coefficient which makes them thermally stable and highly resistant to coarsening.
- Zirconium has a high solubility in the Al 3 X dispersoids allowing large amounts of zirconium to substitute for X in the Al 3 X dispersoids, which results in improved thermal and structural stability.
- Titanium forms Al 3 Ti dispersoids in the aluminum matrix that have an L1 2 structure in the metastable condition and D0 22 structure in the equilibrium condition.
- the metastable Al 3 Ti dispersoids have a low diffusion coefficient which makes them thermally stable and highly resistant to coarsening.
- Titanium has a high solubility in the Al 3 X dispersoids allowing large amounts of titanium to substitute for X in the Al 3 X dispersoids, which results in improved thermal and structural stability.
- Hafnium forms metastable Al 3 Hf dispersoids in the aluminum matrix that have an L1 2 structure in the metastable condition and a D0 23 structure in the equilibrium condition.
- the Al 3 Hf dispersoids have a low diffusion coefficient, which makes them thermally stable and highly resistant to coarsening.
- Hafnium has a high solubility in the Al 3 X dispersoids allowing large amounts of hafnium to substitute for scandium, erbium, thulium, ytterbium, and lutetium in the above mentioned Al 3 X dispersoids, which results in stronger and more thermally stable dispersoids.
- Niobium forms metastable Al 3 Nb dispersoids in the aluminum matrix that have an L1 2 structure in the metastable condition and a D0 22 structure in the equilibrium condition.
- Niobium has a lower solubility in the Al 3 X dispersoids than hafnium or yttrium, allowing relatively lower amounts of niobium than hafnium or yttrium to substitute for X in the Al 3 X dispersoids. Nonetheless, niobium can be very effective in slowing down the coarsening kinetics of the Al 3 X dispersoids because the Al 3 Nb dispersoids are thermally stable. The substitution of niobium for X in the above mentioned Al 3 X dispersoids results in stronger and more thermally stable dispersoids.
- Al 3 X L1 2 precipitates improve elevated temperature mechanical properties in aluminum alloys for two reasons.
- the precipitates are ordered intermetallic compounds. As a result, when the particles are sheared by glide dislocations during deformation, the dislocations separate into two partial dislocations separated by an anti-phase boundary on the glide plane. The energy to create the anti-phase boundary is the origin of the strengthening.
- the cubic L1 2 crystal structure and lattice parameter of the precipitates are closely matched to the aluminum solid solution matrix. This results in a lattice coherency at the precipitate/matrix boundary that resists coarsening. The lack of an interphase boundary results in a low driving force for particle growth and resulting elevated temperature stability. Alloying elements in solid solution in the dispersed strengthening particles and in the aluminum matrix that tend to decrease the lattice mismatch between the matrix and particles will tend to increase the strengthening and elevated temperature stability of the alloy.
- the alloys are based on aluminum zinc copper magnesium systems. Addition of magnesium in solid solution in aluminum increases the lattice parameter of the aluminum matrix and decreases the lattice parameter mismatch further increasing the resistance to coarsening of the L1 2 Al 3 X phases where X is at least one element selected from scandium, erbium, thulium, ytterbium, and lutetium and at least on element selected from gadolinium, yttrium, zirconium, titanium, hafnium, and niobium. Additions of zinc and copper in aluminum provide significant precipitation strengthening through precipitation of fine second phases Zn 2 Mg ( ⁇ ′) and Al 2 CuMg (S′).
- the amount of zinc in these alloys ranges from about 3.0 to about 12.0 weight percent, more preferably about 4.0 to about 10.0 weight percent, and even more preferably about 5.0 to about 9.0 weight percent.
- the amount of magnesium in these alloys ranges from about 0.5 to about 3.5 weight percent, more preferably about 1.0 to about 3.0 weight percent, and even more preferably about 1.5 to about 3.0 weight percent.
- the amount of copper in these alloys ranges from about 0.2 to about 3.0 weight percent, more preferably about 0.5 to about 2.5 weight percent, and even more preferably about 1.0 to about 2.5 weight percent.
- the amount of scandium present in the alloys of this invention if any may vary from about 0.1 to about 0.5 weight percent, more preferably from about 0.1 to about 0.35 weight percent, and even more preferably from about 0.1 to about 0.25 weight percent.
- the Al—Sc phase diagram shown in FIG. 4 indicates a eutectic reaction at about 0.5 weight percent scandium at about 1219° F. (659° C.) resulting in a solid solution of scandium and aluminum and Al 3 Sc dispersoids.
- Aluminum alloys with less than 0.5 weight percent scandium can be quenched from the melt to retain scandium in solid solution that may precipitate as dispersed L1 2 intermetallic Al 3 Sc following an aging treatment.
- Alloys with scandium in excess of the eutectic composition can only retain scandium in solid solution by rapid solidification processing (RSP) where cooling rates are in excess of about 10 3 ° C./second. Alloys with scandium in excess of the eutectic composition cooled normally will have a microstructure consisting of relatively large Al 3 Sc grains in a finally divided aluminum-Al 3 Sc eutectic phase matrix.
- RSP rapid solidification processing
- the amount of erbium present in the alloys of this invention may vary from about 0.1 to about 6.0 weight percent, more preferably from about 0.1 to about 4.0 weight percent, and even more preferably from about 0.2 to about 2.0 weight percent.
- the Al—Er phase diagram shown in FIG. 5 indicates a eutectic reaction at about 6 weight percent erbium at about 1211° F. (655° C.).
- Aluminum alloys with less than about 6 weight percent erbium can be quenched from the melt to retain erbium in solid solutions that may precipitate as dispersed L1 2 intermetallic Al 3 Er following an aging treatment.
- Alloys with erbium in excess of the eutectic composition can only retain erbium in solid solution by rapid solidification processing (RSP) where cooling rates are in excess of about 10 3 ° C./second. Alloys with erbium in excess of the eutectic composition (hypereutectic alloys) cooled normally will have a microstructure consisting of relatively large Al 3 Er dispersoids in a finely divided aluminum-Al 3 Er eutectic phase matrix.
- the amount of thulium present in the alloys of this invention may vary from about 0.1 to about 10.0 weight percent, more preferably from about 0.2 to about 6.0 weight percent, and even more preferably from about 0.2 to about 4.0 weight percent.
- the Al—Tm phase diagram shown in FIG. 6 indicates a eutectic reaction at about 10 weight percent thulium at about 1193° F. (645° C.).
- Thulium forms metastable Al 3 TM dispersoids in the aluminum matrix that have an L1 2 structure in the equilibrium condition.
- the Al 3 TM dispersoids have a low diffusion coefficient which makes them thermally stable and highly resistant to coarsening.
- Aluminum alloys with less than 10 weight percent thulium can be quenched from the melt to retain thulium in solid solution that may precipitate as dispersed metastable L1 2 intermetallic Al 3 TM following an aging treatment. Alloys with thulium in excess of the eutectic composition can only retain Tm in solid solution by rapid solidification processing (RSP) where cooling rates are in excess of about 10 3 ° C./second.
- RSP rapid solidification processing
- the amount of ytterbium present in the alloys of this invention may vary from about 0.1 to about 15.0 weight percent, more preferably from about 0.2 to about 8.0 weight percent, and even more preferably from about 0.2 to about 4.0 weight percent.
- the Al—Yb phase diagram shown in FIG. 7 indicates a eutectic reaction at about 21 weight percent ytterbium at about 1157° F. (625° C.).
- Aluminum alloys with less than about 21 weight percent ytterbium can be quenched from the melt to retain ytterbium in solid solution that may precipitate as dispersed L1 2 intermetallic Al 3 Yb following an aging treatment.
- Alloys with ytterbium in excess of the eutectic composition can only retain ytterbium in solid solution by rapid solidification processing (RSP) where cooling rates are in excess of about 10 3 ° C./second. Alloys with ytterbium in excess of the eutectic composition cooled normally will have a microstructure consisting of relatively large Al 3 Yb grains in a finally divided aluminum-Al 3 Yb eutectic phase matrix.
- the amount of lutetium present in the alloys of this invention may vary from about 0.1 to about 12.0 weight percent, more preferably from about 0.2 to about 8.0 weight percent, and even more preferably from about 0.2 to about 4.0 weight percent.
- the Al—Lu phase diagram shown in FIG. 8 indicates a eutectic reaction at about 11.7 weight percent Lu at about 1202° F. (650° C.).
- Aluminum alloys with less than about 11.7 weight percent lutetium can be quenched from the melt to retain Lu in solid solution that may precipitate as dispersed L1 2 intermetallic Al 3 Lu following an aging treatment.
- Alloys with Lu in excess of the eutectic composition can only retain Lu in solid solution by rapid solidification processing (RSP) where cooling rates are in excess of about 10 3 ° C./second. Alloys with lutetium in excess of the eutectic composition cooled normally will have a microstructure consisting of relatively large Al 3 Lu grains in a finely divided aluminum-Al 3 Lu eutectic phase matrix.
- RSP rapid solidification processing
- the amount of gadolinium present in the alloys of this invention may vary from about 0.1 to about 4 weight percent, more preferably from 0.2 to about 2 weight percent, and even more preferably from about 0.5 to about 2 weight percent.
- the amount of yttrium present in the alloys of this invention may vary from about 0.1 to about 4 weight percent, more preferably from 0.2 to about 2 weight percent, and even more preferably from about 0.5 to about 2 weight percent.
- the amount of zirconium present in the alloys of this invention may vary from about 0.05 to about 1 weight percent, more preferably from 0.1 to about 0.75 weight percent, and even more preferably from about 0.1 to about 0.5 weight percent.
- the amount of titanium present in the alloys of this invention may vary from about 0.05 to about 2 weight percent, more preferably from 0.1 to about 1 weight percent, and even more preferably from about 0.1 to about 0.5 weight percent.
- the amount of hafnium present in the alloys of this invention may vary from about 0.05 to about 2 weight percent, more preferably from 0.1 to about 1 weight percent, and even more preferably from about 0.1 to about 0.5 weight percent.
- the amount of niobium present in the alloys of this invention may vary from about 0.05 to about 1 weight percent, more preferably from 0.1 to about 0.75 weight percent, and even more preferably from about 0.1 to about 0.5 weight percent.
- alloys of this invention include at least one of about 0.001 weight percent to about 0.10 weight percent sodium, about 0.001 weight percent to about 0.10 weight calcium, about 0.001 weight percent to about 0.10 weight percent strontium, about 0.001 weight percent to about 0.10 weight percent antimony, about 0.001 weight percent to about 0.10 weight percent barium and about 0.001 weight percent to about 0.10 weight percent phosphorus. These are added to refine the microstructure of the eutectic phase and the primary magnesium or lithium morphology and size.
- These aluminum alloys may be made by any and all consolidation and fabrication processes known to those in the art such as casting (without further deformation), deformation processing (wrought processing), rapid solidification processing, forging, extrusion, rolling, die forging, powder metallurgy and others.
- the rapid solidification process should have a cooling rate greater that about 1. ° C./second including but not limited to powder processing, atomization, melt spinning, splat quenching, spray deposition, cold spray, plasma spray, laser melting and deposition, ball milling and cryomilling.
- alloys with about 1.0 to about 3.0 weight percent magnesium, alloys with about 4.0 to about 10.0 weight percent zinc, and alloys with about 0.5 to about 2.5 weight percent copper are alloys with about 1.0 to about 3.0 weight percent magnesium, alloys with about 4.0 to about 10.0 weight percent zinc, and alloys with about 0.5 to about 2.5 weight percent copper, and include, but are not limited to (in weight percent):
- alloys with about 1.5 to about 3.0 weight percent magnesium alloys with about 5.0 to about 9.0 weight percent zinc, and alloys with about 1.0 to about 2.5 weight percent copper, and include, but are not limited to (in weight percent):
Abstract
High temperature heat treatable aluminum alloys that can be used at temperatures from about −420° F. (−251° C.) up to about 650° F. (343° C.) are described. The alloys are strengthened by dispersion of particles based on the L12 intermetallic compound Al3X. These alloys comprise aluminum, zinc, magnesium, at least one of scandium, erbium, thulium, ytterbium, and lutetium; and at least one of gadolinium, yttrium, zirconium, titanium, hafnium, and niobium. Copper is an optional alloying element.
Description
- This application is related to the following co-pending applications that are filed on even date herewith and are assigned to the same assignee: L12 ALUMINUM ALLOYS WITH BIMODAL AND TRIMODAL DISTRIBUTION, Ser. No. ______, Attorney Docket No. PA0006933U-U73.12-325KL; DISPERSION STRENGTHENED L12 ALUMINUM ALLOYS, Ser. No. ______, Attorney Docket No. PA0006932U-U73.12-326KL; HEAT TREATABLE L12 ALUMINUM ALLOYS, Ser. No. ______, Attorney Docket No. PA0006931U-U73.12-327KL; HIGH STRENGTH L12 ALUMINUM ALLOYS, Ser. No. ______, Attorney Docket No. PA0006929U-U73.12-329KL; HIGH STRENGTH L12 ALUMINUM ALLOYS, Ser. No. ______, Attorney Docket No. PA0006928U-U73.12-330KL; HEAT TREATABLE L12 ALUMINUM ALLOYS, Ser. No. ______, Attorney Docket No. PA0006927U-U73.12-331KL; HIGH STRENGTH ALUMINUM ALLOYS WITH L12 PRECIPITATES, Ser. No. ______, Attorney Docket No. PA0006924U-U73.12-334KL; HIGH STRENGTH L12 ALUMINUM ALLOYS, Ser. No. ______, Attorney Docket No. PA0006923U-U73.12-335KL; and L12 STRENGTHENED AMORPHOUS ALUMINUM ALLOYS, Ser. No. ______, Attorney Docket No. PA0001359U-U73.12-336KL.
- The present invention relates generally to aluminum alloys and more specifically to heat treatable aluminum alloys produced by melt processing and strengthened by L12 phase dispersions.
- The combination of high strength, ductility, and fracture toughness, as well as low density, make aluminum alloys natural candidates for aerospace and space applications. However, their use is typically limited to temperatures below about 300° F. (149° C.) since most aluminum alloys start to lose strength in that temperature range as a result of coarsening of strengthening precipitates.
- The development of aluminum alloys with improved elevated temperature mechanical properties is a continuing process. Some attempts have included aluminum-iron and aluminum-chromium based alloys such as Al—Fe—Ce, Al—Fe—V—Si, Al—Fe—Ce—W, and Al—Cr—Zr—Mn that contain incoherent dispersoids. These alloys, however, also lose strength at elevated temperatures due to particle coarsening. In addition, these alloys exhibit ductility and fracture toughness values lower than other commercially available aluminum alloys.
- Other attempts have included the development of mechanically alloyed Al—Mg and Al—Ti alloys containing ceramic dispersoids. These alloys exhibit improved high temperature strength due to the particle dispersion, but the ductility and fracture toughness are not improved.
- U.S. Pat. No. 6,248,453 discloses aluminum alloys strengthened by dispersed Al3X L12 intermetallic phases where X is selected from the group consisting of Sc, Er, Lu, Yb, Tm, and U. The Al3X particles are coherent with the aluminum alloy matrix and are resistant to coarsening at elevated temperatures. The improved mechanical properties of the disclosed dispersion strengthened L12 aluminum alloys are stable up to 572° F. (300° C.). In order to create aluminum alloys containing fine dispersions of Al3X L12 particles, the alloys need to be manufactured by expensive rapid solidification processes with cooling rates in excess of 1.8×103 F/sec (103 C/sec). U.S. Patent Application Publication No. 2006/0269437 A1 discloses an aluminum alloy that contains scandium and other elements. While the alloy is effective at high temperatures, it is not capable of being heat treated using a conventional age hardening mechanism.
- Heat treatable aluminum alloys strengthened by coherent L12 intermetallic phases produced by standard, inexpensive melt processing techniques would be useful.
- The present invention is heat treatable aluminum alloys that can be cast, wrought, or formed by rapid solidification, and thereafter heat treated. The alloys can achieve high temperature performance and can be used at temperatures up to about 650° F. (343° C.).
- These alloys comprise zinc, magnesium, and an Al3X L12 dispersoid where X is at least one first element selected from scandium, erbium, thulium, ytterbium, and lutetium, and at least one second element selected from gadolinium, yttrium, zirconium, titanium, hafnium, and niobium. The balance is substantially aluminum. The alloys may also include copper.
- The alloys have less than 1.0 weight percent total impurities.
- The alloys are formed by a process selected from casting, deformation processing and rapid solidification. The alloys are then heat treated at a temperature of from about 800° F. (426° C.) to about 1100° F. (593° C.) for between about 30 minutes and four hours, followed by quenching in water, and thereafter aged at a temperature from about 200° F. (93° C.) to about 600° F. (260° C.) for about two to about forty-eight hours.
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FIG. 1 is an aluminum zinc phase diagram. -
FIG. 2 is an aluminum copper phase diagram. -
FIG. 3 is an aluminum magnesium phase diagram. -
FIG. 4 is an aluminum scandium phase diagram. -
FIG. 5 is an aluminum erbium phase diagram. -
FIG. 6 is an aluminum thulium phase diagram. -
FIG. 7 is an aluminum ytterbium phase diagram. -
FIG. 8 is an aluminum lutetium phase diagram. - The alloys of this invention are based on the aluminum, zinc, magnesium system. The amount of zinc in these alloys ranges from about 3.0 to about 12.0 weight percent, more preferably about 4.0 to about 10.0 weight percent, and even more preferably about 5.0 to about 9.0 weight percent. The amount of magnesium in these alloys ranges from about 0.5 to about 3.5 weight percent, more preferably about 1.0 to about 3.0 weight percent, and even more preferably about 1.5 to about 3.0 weight percent. The amount of copper in these alloys ranges from about 0.2 to about 3.0 weight percent, more preferably about 0.5 to about 2.5 weight percent, and even more preferably about 1.0 to about 2.5 weight percent.
- The aluminum zinc phase diagram is shown in
FIG. 1 . The aluminum zinc binary system is a eutectic alloy system involving a monotectoid reaction and a miscibility gap in the solid state. There is a eutectic reaction at 94 weight percent zinc at 717.8° F. (381° C.). Zinc has maximum solid solubility of 83.1 weight percent in aluminum at 717.8° F. (381° C.) which can be extended by rapid solidification processing. The solubility of zinc in aluminum decreases with a decrease in temperature. Zinc provides significant amount of precipitation strengthening in aluminum by precipitation of fine second phases. The present invention is focused on hypoeutectic alloy composition ranges. Decomposition of the supersaturated solid solution of zinc in aluminum gives rise to spherical and ellipsoidal GP zones; precipitates with rhombohedral structure which are coherent with aluminum matrix and an incoherent (α′Al). - The aluminum copper phase diagram is shown in
FIG. 2 . The aluminum copper binary system is a eutectic alloy system with a eutectic reaction at 31.2 weight percent magnesium and 1018° F. (548.2° C.). Copper has maximum solid solubility of 6 weight percent in aluminum at 1018° F. (548.2° C.) which can be extended further by rapid solidification processing. Copper provides considerable amounts of precipitation strengthening in aluminum by precipitation of fine second phases. The present invention is focused on hypoeutectic alloy composition ranges. - The aluminum magnesium phase diagram is shown in
FIG. 3 . The binary system is a eutectic alloy system with a eutectic reaction at 36 weight percent magnesium and 842° F. (450° C.). Magnesium has maximum solid solubility of 16 weight percent in aluminum at 842° F. (450° C.) which can extended further by rapid solidification processing. Magnesium provides substantial solid solution strengthening in aluminum. In addition, magnesium provides precipitation strengthening through precipitation of Zn2Mg (η′) and Al2CuMg (S′) phases. - The alloys of this invention contain aluminum solid solutions containing at least one element selected from zinc, copper and magnesium. These alloys also contain precipitates consisting of fine dispersions of Zn2Mg (ζ′) and Al2CuMg (S′) phases by decomposition of supersaturated solid solutions. In the solid solutions are dispersions of Al3X having an L12 structure where X is at least one element selected from scandium, erbium, thulium, ytterbium, and lutetium and at least one element selected from gadolinium, yttrium, zirconium, titanium, hafnium, and niobium.
- Exemplary aluminum alloys of this invention include, but are not limited to (in weight percent):
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-0.5)Sc-(0.1-4.0)Gd;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-6)Er-(0.1-4.0)Gd;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-10)Tm-(0.1-4.0)Gd;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-15)Yb-(0.1-4.0)Gd;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-12)Lu-(0.1-4.0)Gd;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-0.5)Sc-(0.1-4.0)Y;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-6)Er-(0.1-4.0)Y;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-10)-Tm-(0.1-4.0)Y;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-15)Yb-(0.1-4.0)Y;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-12)Lu-(0.1-4.0)Y;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-0.5)Sc-(0.05-1.0)Zr;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-6)Er-(0.05-1.0)Zr;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-10)Tm-(0.05-1.0)Zr;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-15)Yb-(0.05-1.0)Zr;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-12)Lu-(0.05-1.0)Zr;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-0.5)Sc-(0.05-2.0)Ti;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-6)Er-(0.05-2.0)Ti;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-10)Tm-(0.05-2.0)Ti;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-15)Yb-(0.05-2.0)Ti;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-12)Lu-(0.05-2.0)Ti;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-0.5)Sc-(0.05-2.0)Hf;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-6)Er-(0.05-2.0)Hf;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-10)Tm-(0.05-2.0)Hf;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-15)Yb-(0.05-2.0)Hf;
- about Al-(3-12)Zn-(0.5-3.5)Mg-((0.1-12)Lu-(0.05-2.0)Hf;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-0.5)Sc-(0.05-1.0)Nb;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-6)Er-(0.05-1.0)Nb;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-10)Tm-(0.05-1.0)Nb;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-15)Yb-(0.05-1.0)Nb;
- about Al-(3-12)Zn-(0.5-3.5)Mg-(0.1-12)Lu-(0.05-1.0)Nb;
- about Al-(3-12)Zn-(0.2-3)Cu-(0.5-3.5)Mg-(0.1-0.5)Sc-(0.1-4.0)Gd;
- about Al-(3-12)Zn-(0.2-3)Cu-(0.5-3.5)Mg-(0.1-6)Er-(0.1-4.0)Gd;
- about Al-(3-12)Zn-(0.2-3)Cu-(0.5-3.5)Mg-(0.1-10)Tm-(0.1-4.0)Gd;
- about Al-(3-12)Zn-(0.2-3)Cu-(0.5-3.5)Mg-(0.1-15)Yb-(0.1-4.0)Gd;
- about Al-(3-12)Zn-(0.2-3)Cu-(0.5-3.5)Mg-(0.1-12)Lu-(0.1-4.0)Gd;
- about Al-(3-12)Zn-(0.2-3)Cu-(0.5-3.5)Mg-(0.1-0.5)Sc-(0.1-4.0)Y;
- about Al-(3-12)Zn-(0.2-3)Cu-(0.5-3.5)Mg-(0.1-6)Er-(0.1-4.0)Y;
- about Al-(3-12)Zn-(0.2-3)Cu-(0.5-3.5)Mg-(0.1-10)-Tm-(0.1-4.0)Y;
- about Al-(3-12)Zn-(0.2-3)Cu-(0.5-3.5)Mg-(0.1-15)Yb-(0.1-4.0)Y;
- about Al-(3-12)Zn-(0.2-3)Cu-(0.5-3.5)Mg-(0.1-12)Lu-(0.1-4.0)Y;
- about Al-(3-12)Zn-(0.2-3)Cu -(0.5-3.5)Mg-(0.1-0.5)Sc-(0.05-1.0)Zr;
- about Al-(3-12)Zn-(0.2-3)Cu -(0.5-3.5)Mg-(0.1-6)Er-(0.05-1.0)Zr;
- about Al-(3-12)Zn-(0.2-3)Cu -(0.5-3.5)Mg-(0.1-10)Tm-(0.05-1.0)Zr;
- about Al-(3-12)Zn-(0.2-3)Cu -(0.5-3.5)Mg-(0.1-15)Yb-(0.05-1.0)Zr;
- about Al-(3-12)Zn-(0.2-3)Cu -(0.5-3.5)Mg-(0.1-12)Lu-(0.05-1.0)Zr;
- about Al-(3-12)Zn-(0.2-3)Cu -(0.5-3.5)Mg-(0.1-0.5)Sc-(0.05-2.0)Ti;
- about Al-(3-12)Zn-(0.2-3)Cu -(0.5-3.5)Mg-(0.1-6)Er-(0.05-2.0)Ti;
- about Al-(3-12)Zn-(0.2-3)Cu -(0.5-3.5)Mg-(0.1-10)Tm-(0.05-2.0)Ti;
- about Al-(3-12)Zn-(0.2-3)Cu -(0.5-3.5)Mg-(0.1-15)Yb-(0.05-2.0)Ti;
- about Al-(3-12)Zn-(0.2-3)Cu -(0.5-3.5)Mg-(0.1-12)-Lu-(0.05-2.0)Ti;
- about Al-(3-12)Zn-(0.2-3)Cu -(0.5-3.5)Mg-(0.1-0.5)Sc-(0.05-2.0)Hf;
- about Al-(3-12)Zn-(0.2-3)Cu -(0.5-3.5)Mg-(0.1-6)Er-(0.05-2.0)Hf;
- about Al-(3-12)Zn-(0.2-3)Cu -(0.5-3.5)Mg-(0.1-10)Tm-(0.05-2.0)Hf;
- about Al-(3-12)Zn-(0.2-3)Cu -(0.5-3.5)Mg-(0.1-15)Yb-(0.05-2.0)Hf;
- about Al-(3-12)Zn-(0.2-3)Cu -(0.5-3.5)Mg-(0.1-12)Lu-(0.05-2.0)Hf;
- about Al-(3-12)Zn-(0.2-3)Cu -(0.5-3.5)Mg-(0.1-0.5)Sc-(0.05-1.0)Nb;
- about Al-(3-12)Zn-(0.2-3)Cu -(0.5-3.5)Mg-(0.1-6)Er-(0.05-1.0)Nb;
- about Al-(3-12)Zn-(0.2-3)Cu -(0.5-3.5)Mg-(0.1-10)Tm-(0.05-1.0)Nb;
- about Al-(3-12)Zn-(0.2-3)Cu -(0.5-3.5)Mg-(0.1-15)Yb-(0.05-1.0)Nb; and
- about Al-(3-12)Zn-(0.2-3)Cu -(0.5-3.5)Mg-(0.1-12)Lu-(0.05-1.0)Nb.
- In the inventive aluminum based alloys disclosed herein, scandium, erbium, thulium, ytterbium, and lutetium are potent strengtheners that have low diffusivity and low solubility in aluminum. All these elements form equilibrium Al3X intermetallic dispersoids where X is at least one of scandium, erbium, ytterbium, lutetium, that have an L12 structure that is an ordered face centered cubic structure with the X atoms located at the corners and aluminum atoms located on the cube faces of the unit cell.
- Scandium forms Al3Sc dispersoids that are fine and coherent with the aluminum matrix. Lattice parameters of aluminum and Al3Sc are very close (0.405 nm and 0.410 nm respectively), indicating that there is minimal or no driving force for causing growth of the Al3Sc dispersoids. This low interfacial energy makes the Al3Sc dispersoids thermally stable and resistant to coarsening up to temperatures as high as about 840° F. (450° C.). In the alloys of this invention these Al3Sc dispersoids are made stronger and more resistant to coarsening at elevated temperatures by adding suitable alloying elements such as gadolinium, yttrium, zirconium, titanium, hafnium, niobium, or combinations thereof, that enter Al3Sc in solution.
- Erbium forms Al3Er dispersoids in the aluminum matrix that are fine and coherent with the aluminum matrix. The lattice parameters of aluminum and Al3Er are close (0.405 nm and 0.417 nm respectively), indicating there is minimal driving force for causing growth of the Al3Er dispersoids. This low interfacial energy makes the Al3Er dispersoids thermally stable and resistant to coarsening up to temperatures as high as about 842° F. (450° C.). Addition of magnesium in solid solution in aluminum increases the lattice parameter of the aluminum matrix, and decreases the lattice parameter mismatch further increasing the resistance of the Al3Er to coarsening. Additions of zinc and copper in aluminum provide significant precipitation strengthening through precipitation of fine second phases Zn2Mg (η′) and Al2CuMg (S′). In the alloys of this invention, these Al3Er dispersoids are made stronger and more resistant to coarsening at elevated temperatures by adding suitable alloying elements such as gadolinium, yttrium, zirconium, titanium, hafnium, niobium, or combinations thereof that enter Al3Er in solution.
- Thulium forms metastable Al3Tm dispersoids in the aluminum matrix that are fine and coherent with the aluminum matrix. The lattice parameters of aluminum and Al3Tm are close (0.405 nm and 420 nm respectively), indicating there is minimal driving force for causing growth of the Al3Tm dispersoids. This low interfacial energy makes the Al3Tm dispersoids thermally stable and resistant to coarsening up to temperatures as high as about 842° F. (450° C.). Addition of magnesium in solid solution in aluminum increases the lattice parameter of the aluminum matrix and decreases the lattice parameter mismatch further increasing the resistance to coarsening of the dispersoid. Additions of zinc and copper in aluminum provide significant precipitation strengthening through precipitation of fine second phases Zn2Mg (η′) and Al2CuMg (S′). In the alloys of this invention these Al3Tm dispersoids are made stronger and more resistant to coarsening at elevated temperatures by adding suitable alloying elements such as gadolinium, yttrium, zirconium, titanium, hafnium, niobium, or combinations thereof that enter Al3Tm in solution.
- Ytterbium forms Al3Yb dispersoids in the aluminum matrix that are fine and coherent with the aluminum matrix. The lattice parameters of Al and Al3Yb are close (0.405 nm and 0.420 nm respectively), indicating there is minimal driving force for causing growth of the Al3Yb dispersoids. This low interfacial energy makes the Al3Yb dispersoids thermally stable and resistant to coarsening up to temperatures as high as about 842° F. (450° C.). Addition of magnesium in solid solution in aluminum increases the lattice parameter of the aluminum matrix and decreases the lattice parameter mismatch further increasing the resistance to coarsening of the Al3Yb. Additions of zinc and copper in aluminum provide significant precipitation strengthening through precipitation of fine second phases Zn2Mg (η′) and Al2CuMg (S′). In the alloys of this invention, these Al3Yb dispersoids are made stronger and more resistant to coarsening at elevated temperatures by adding suitable alloying elements such as gadolinium, yttrium, zirconium, titanium, hafnium, niobium, or combinations thereof that enter Al3Yb in solution.
- Lutetium forms Al3Lu dispersoids in the aluminum matrix that are fine and coherent with the aluminum matrix. The lattice parameters of Al and Al3Lu are close (0.405 nm and 0.419 nm respectively), indicating there is minimal driving force for causing growth of the Al3Lu dispersoids. This low interfacial energy makes the Al3Lu dispersoids thermally stable and resistant to coarsening up to temperatures as high as about 842° F. (450° C.). Addition of magnesium in solid solution in aluminum increases the lattice parameter of the aluminum matrix and decreases the lattice parameter mismatch further increasing the resistance to coarsening of Al3Lu. Additions of zinc and copper in aluminum provide significant precipitation strengthening through precipitation of fine second phases Zn2Mg (η′) and Al2CuMg (S′). In the alloys of this invention, these Al3Lu dispersoids are made stronger and more resistant to coarsening at elevated temperatures by adding suitable alloying elements such as gadolinium, yttrium, zirconium, titanium, hafnium, niobium, or mixtures thereof that enter Al3Lu in solution.
- Gadolinium forms metastable Al3Gd dispersoids in the aluminum matrix that are stable up to temperatures as high as about 842° F. (450° C.) due to their low diffusivity in aluminum. The Al3Gd dispersoids have a D019 structure in the equilibrium condition. Despite its large atomic size, gadolinium has fairly high solubility in the Al3X intermetallic dispersoids (where X is scandium, erbium, thulium, ytterbium or lutetium). Gadolinium can substitute for the X atoms in Al3X intermetallic, thereby forming an ordered L12 phase which results in improved thermal and structural stability.
- Yttrium forms metastable Al3Y dispersoids in the aluminum matrix that have an L12 structure in the metastable condition and a D09 structure in the equilibrium condition. The metastable Al3Y dispersoids have a low diffusion coefficient which makes them thermally stable and highly resistant to coarsening. Yttrium has a high solubility in the Al3X intermetallic dispersoids allowing large amounts of yttrium to substitute for X in the Al3X L12 dispersoids which results in improved thermal and structural stability.
- Zirconium forms Al3Zr dispersoids in the aluminum matrix that have an L12 structure in the metastable condition and D023 structure in the equilibrium condition. The metastable Al3Zr dispersoids have a low diffusion coefficient which makes them thermally stable and highly resistant to coarsening. Zirconium has a high solubility in the Al3X dispersoids allowing large amounts of zirconium to substitute for X in the Al3X dispersoids, which results in improved thermal and structural stability.
- Titanium forms Al3Ti dispersoids in the aluminum matrix that have an L12 structure in the metastable condition and D022 structure in the equilibrium condition. The metastable Al3Ti dispersoids have a low diffusion coefficient which makes them thermally stable and highly resistant to coarsening. Titanium has a high solubility in the Al3X dispersoids allowing large amounts of titanium to substitute for X in the Al3X dispersoids, which results in improved thermal and structural stability.
- Hafnium forms metastable Al3Hf dispersoids in the aluminum matrix that have an L12 structure in the metastable condition and a D023 structure in the equilibrium condition. The Al3Hf dispersoids have a low diffusion coefficient, which makes them thermally stable and highly resistant to coarsening. Hafnium has a high solubility in the Al3X dispersoids allowing large amounts of hafnium to substitute for scandium, erbium, thulium, ytterbium, and lutetium in the above mentioned Al3X dispersoids, which results in stronger and more thermally stable dispersoids.
- Niobium forms metastable Al3Nb dispersoids in the aluminum matrix that have an L12 structure in the metastable condition and a D022 structure in the equilibrium condition. Niobium has a lower solubility in the Al3X dispersoids than hafnium or yttrium, allowing relatively lower amounts of niobium than hafnium or yttrium to substitute for X in the Al3X dispersoids. Nonetheless, niobium can be very effective in slowing down the coarsening kinetics of the Al3X dispersoids because the Al3Nb dispersoids are thermally stable. The substitution of niobium for X in the above mentioned Al3X dispersoids results in stronger and more thermally stable dispersoids.
- Al3X L12 precipitates improve elevated temperature mechanical properties in aluminum alloys for two reasons. First, the precipitates are ordered intermetallic compounds. As a result, when the particles are sheared by glide dislocations during deformation, the dislocations separate into two partial dislocations separated by an anti-phase boundary on the glide plane. The energy to create the anti-phase boundary is the origin of the strengthening. Second, the cubic L12 crystal structure and lattice parameter of the precipitates are closely matched to the aluminum solid solution matrix. This results in a lattice coherency at the precipitate/matrix boundary that resists coarsening. The lack of an interphase boundary results in a low driving force for particle growth and resulting elevated temperature stability. Alloying elements in solid solution in the dispersed strengthening particles and in the aluminum matrix that tend to decrease the lattice mismatch between the matrix and particles will tend to increase the strengthening and elevated temperature stability of the alloy.
- The alloys are based on aluminum zinc copper magnesium systems. Addition of magnesium in solid solution in aluminum increases the lattice parameter of the aluminum matrix and decreases the lattice parameter mismatch further increasing the resistance to coarsening of the L12 Al3X phases where X is at least one element selected from scandium, erbium, thulium, ytterbium, and lutetium and at least on element selected from gadolinium, yttrium, zirconium, titanium, hafnium, and niobium. Additions of zinc and copper in aluminum provide significant precipitation strengthening through precipitation of fine second phases Zn2Mg (η′) and Al2CuMg (S′). The amount of zinc in these alloys ranges from about 3.0 to about 12.0 weight percent, more preferably about 4.0 to about 10.0 weight percent, and even more preferably about 5.0 to about 9.0 weight percent. The amount of magnesium in these alloys ranges from about 0.5 to about 3.5 weight percent, more preferably about 1.0 to about 3.0 weight percent, and even more preferably about 1.5 to about 3.0 weight percent. The amount of copper in these alloys ranges from about 0.2 to about 3.0 weight percent, more preferably about 0.5 to about 2.5 weight percent, and even more preferably about 1.0 to about 2.5 weight percent.
- The amount of scandium present in the alloys of this invention if any may vary from about 0.1 to about 0.5 weight percent, more preferably from about 0.1 to about 0.35 weight percent, and even more preferably from about 0.1 to about 0.25 weight percent. The Al—Sc phase diagram shown in
FIG. 4 indicates a eutectic reaction at about 0.5 weight percent scandium at about 1219° F. (659° C.) resulting in a solid solution of scandium and aluminum and Al3Sc dispersoids. Aluminum alloys with less than 0.5 weight percent scandium can be quenched from the melt to retain scandium in solid solution that may precipitate as dispersed L12 intermetallic Al3Sc following an aging treatment. Alloys with scandium in excess of the eutectic composition (hypereutectic alloys) can only retain scandium in solid solution by rapid solidification processing (RSP) where cooling rates are in excess of about 103° C./second. Alloys with scandium in excess of the eutectic composition cooled normally will have a microstructure consisting of relatively large Al3Sc grains in a finally divided aluminum-Al3Sc eutectic phase matrix. - The amount of erbium present in the alloys of this invention, if any, may vary from about 0.1 to about 6.0 weight percent, more preferably from about 0.1 to about 4.0 weight percent, and even more preferably from about 0.2 to about 2.0 weight percent. The Al—Er phase diagram shown in
FIG. 5 indicates a eutectic reaction at about 6 weight percent erbium at about 1211° F. (655° C.). Aluminum alloys with less than about 6 weight percent erbium can be quenched from the melt to retain erbium in solid solutions that may precipitate as dispersed L12 intermetallic Al3Er following an aging treatment. Alloys with erbium in excess of the eutectic composition can only retain erbium in solid solution by rapid solidification processing (RSP) where cooling rates are in excess of about 103° C./second. Alloys with erbium in excess of the eutectic composition (hypereutectic alloys) cooled normally will have a microstructure consisting of relatively large Al3Er dispersoids in a finely divided aluminum-Al3Er eutectic phase matrix. - The amount of thulium present in the alloys of this invention, if any, may vary from about 0.1 to about 10.0 weight percent, more preferably from about 0.2 to about 6.0 weight percent, and even more preferably from about 0.2 to about 4.0 weight percent. The Al—Tm phase diagram shown in
FIG. 6 indicates a eutectic reaction at about 10 weight percent thulium at about 1193° F. (645° C.). Thulium forms metastable Al3™ dispersoids in the aluminum matrix that have an L12 structure in the equilibrium condition. The Al3™ dispersoids have a low diffusion coefficient which makes them thermally stable and highly resistant to coarsening. Aluminum alloys with less than 10 weight percent thulium can be quenched from the melt to retain thulium in solid solution that may precipitate as dispersed metastable L12 intermetallic Al3™ following an aging treatment. Alloys with thulium in excess of the eutectic composition can only retain Tm in solid solution by rapid solidification processing (RSP) where cooling rates are in excess of about 103° C./second. - The amount of ytterbium present in the alloys of this invention, if any, may vary from about 0.1 to about 15.0 weight percent, more preferably from about 0.2 to about 8.0 weight percent, and even more preferably from about 0.2 to about 4.0 weight percent. The Al—Yb phase diagram shown in
FIG. 7 indicates a eutectic reaction at about 21 weight percent ytterbium at about 1157° F. (625° C.). Aluminum alloys with less than about 21 weight percent ytterbium can be quenched from the melt to retain ytterbium in solid solution that may precipitate as dispersed L12 intermetallic Al3Yb following an aging treatment. Alloys with ytterbium in excess of the eutectic composition can only retain ytterbium in solid solution by rapid solidification processing (RSP) where cooling rates are in excess of about 103° C./second. Alloys with ytterbium in excess of the eutectic composition cooled normally will have a microstructure consisting of relatively large Al3Yb grains in a finally divided aluminum-Al3Yb eutectic phase matrix. - The amount of lutetium present in the alloys of this invention, if any, may vary from about 0.1 to about 12.0 weight percent, more preferably from about 0.2 to about 8.0 weight percent, and even more preferably from about 0.2 to about 4.0 weight percent. The Al—Lu phase diagram shown in
FIG. 8 indicates a eutectic reaction at about 11.7 weight percent Lu at about 1202° F. (650° C.). Aluminum alloys with less than about 11.7 weight percent lutetium can be quenched from the melt to retain Lu in solid solution that may precipitate as dispersed L12 intermetallic Al3Lu following an aging treatment. Alloys with Lu in excess of the eutectic composition can only retain Lu in solid solution by rapid solidification processing (RSP) where cooling rates are in excess of about 103° C./second. Alloys with lutetium in excess of the eutectic composition cooled normally will have a microstructure consisting of relatively large Al3Lu grains in a finely divided aluminum-Al3Lu eutectic phase matrix. - The amount of gadolinium present in the alloys of this invention, if any, may vary from about 0.1 to about 4 weight percent, more preferably from 0.2 to about 2 weight percent, and even more preferably from about 0.5 to about 2 weight percent.
- The amount of yttrium present in the alloys of this invention, if any, may vary from about 0.1 to about 4 weight percent, more preferably from 0.2 to about 2 weight percent, and even more preferably from about 0.5 to about 2 weight percent.
- The amount of zirconium present in the alloys of this invention, if any, may vary from about 0.05 to about 1 weight percent, more preferably from 0.1 to about 0.75 weight percent, and even more preferably from about 0.1 to about 0.5 weight percent.
- The amount of titanium present in the alloys of this invention, if any, may vary from about 0.05 to about 2 weight percent, more preferably from 0.1 to about 1 weight percent, and even more preferably from about 0.1 to about 0.5 weight percent.
- The amount of hafnium present in the alloys of this invention, if any, may vary from about 0.05 to about 2 weight percent, more preferably from 0.1 to about 1 weight percent, and even more preferably from about 0.1 to about 0.5 weight percent.
- The amount of niobium present in the alloys of this invention, if any, may vary from about 0.05 to about 1 weight percent, more preferably from 0.1 to about 0.75 weight percent, and even more preferably from about 0.1 to about 0.5 weight percent.
- In order to have the best properties for the alloys of this invention, it is desirable to limit the amount of other elements. Specific elements that should be reduced or eliminated include no more than about 0.1 weight percent iron, about 0.1 weight percent chromium, about 0.1 weight percent manganese, about 0.1 weight percent vanadium, about 0.1 weight percent cobalt, and about 0.1 weight percent nickel. The total quantity of additional elements should not exceed about 1% by weight, including the above listed impurities and other elements.
- Other additions in the alloys of this invention include at least one of about 0.001 weight percent to about 0.10 weight percent sodium, about 0.001 weight percent to about 0.10 weight calcium, about 0.001 weight percent to about 0.10 weight percent strontium, about 0.001 weight percent to about 0.10 weight percent antimony, about 0.001 weight percent to about 0.10 weight percent barium and about 0.001 weight percent to about 0.10 weight percent phosphorus. These are added to refine the microstructure of the eutectic phase and the primary magnesium or lithium morphology and size.
- These aluminum alloys may be made by any and all consolidation and fabrication processes known to those in the art such as casting (without further deformation), deformation processing (wrought processing), rapid solidification processing, forging, extrusion, rolling, die forging, powder metallurgy and others. The rapid solidification process should have a cooling rate greater that about 1. ° C./second including but not limited to powder processing, atomization, melt spinning, splat quenching, spray deposition, cold spray, plasma spray, laser melting and deposition, ball milling and cryomilling.
- More preferred examples of similar alloys to these are alloys with about 1.0 to about 3.0 weight percent magnesium, alloys with about 4.0 to about 10.0 weight percent zinc, and alloys with about 0.5 to about 2.5 weight percent copper, and include, but are not limited to (in weight percent):
- about Al-(4-10)Zn-(1-3)Mg-(0.1-0.35)Sc-(0.2-2.0)Gd;
- about Al-(4-10)Zn-(1-3)Mg-(0.1-4)Er-(0.2-2.0)Gd;
- about Al-(4-10)Zn-(1-3)Mg-(0.2-6)Tm-(0.2-2.0)Gd;
- about Al-(4-10)Zn-(1-3)Mg-(0.2-8)Yb-(0.2-2.0)Gd;
- about Al-(4-10)Zn-(1-3)Mg-(0.2-8)Lu-(0.2-2.0)Gd;
- about Al-(4-10)Zn-(1-3)Mg-(0.1-0.35)Sc-(0.2-2.0)Y;
- about Al-(4-10)Zn-(1-3)Mg-(0.1-4)Er-(0.2-2.0)Y;
- about Al-(4-10)Zn-(1-3)Mg-(0.2-6)Tm-(0.2-2.0)Y;
- about Al-(4-10)Zn-(1-3)Mg-(0.2-8)Yb-(0.2-2.0)Y;
- about Al-(4-10)Zn-(1-3)Mg-(0.2-8)Lu-(0.2-2.0)Y;
- about Al-(4-10)Zn-(1-3)Mg-(0.1-0.35)Sc-(0.1-0.75)Zr;
- about Al-(4-10)Zn-(1-3)Mg-(0.1-4)Er-(0.1-0.75)Zr;
- about Al-(4-10)Zn-(1-3)Mg-(0.2-6)Tm-(0.1-0.75)Zr;
- about Al-(4-10)Zn-(1-3)Mg-(0.2-8)Yb-(0.1-0.75)Zr;
- about Al-(4-10)Zn-(1-3)Mg-(0.2-8)Lu-(0.1-0.75)Zr;
- about Al-(4-10)Zn-(1-3)Mg-(0.1-0.35)Sc-(0.1-1.0)Ti;
- about Al-(4-10)Zn-(1-3)Mg-(0.1-4)Er-(0.1-1.0)Ti;
- about Al-(4-10)Zn-(1-3)Mg-(0.2-6)Tm-(0.1-1.0)Ti;
- about Al-(4-10)Zn-(1-3)Mg-(0.2-8)Yb-(0.1-1.0)Ti;
- about Al-(4-10)Zn-(1-3)Mg-(0.2-8)Lu-(0.1-1.0)Ti;
- about Al-(4-10)Zn-(1-3)Mg-(0.1-0.35)Sc-(0.1-1.0)Hf;
- about Al-(4-10)Zn-(1-3)Mg-(0.1-4)Er-(0.1-1.0)Hf;
- about Al-(4-10)Zn-(1-3)Mg-(0.2-6)Tb-(0.1-1.0)Hf;
- about Al-(4-10)Zn-(1-3)Mg-(0.2-8)Yb-(0.1-1.0)Hf;
- about Al-(4-10)Zn-(1-3)Mg-(0.2-8)Lu-(0.1-1.0)Hf;
- about Al-(4-10)Zn-(1-3)Mg-(0.1-0.35)Sc-(0.1-0.75)Nb;
- about Al-(4-10)Zn-(1-3)Mg-(0.1-4)Er-(0.1-0.75)Nb;
- about Al-(4-10)Zn-(1-3)Mg-(0.2-6)Tm-(0.1-0.75)Nb;
- about Al-(4-10)Zn-(1-3)Mg-(0.2-8)Yb-(0.1-0.75)Nb;
- about Al-(4-10)Zn-(1-3)Mg-(0.2-8)Lu-(0.1-0.75)Nb;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.1-0.35)Sc-(0.2-2.0)Gd;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.1-4)Er-(0.2-2.0)Gd;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.2-6)Tm-(0.2-2.0)Gd;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.2-8)Yb-(0.2-2.0)Gd;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.2-8)Lu-(0.2-2.0)Gd;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.1-0.35)Sc-(0.2-2.0)Y;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.1-4)Er-(0.2-2.0)Y;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.2-6)-Tm-(0.2-2.0)Y;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.2-8)Yb-(0.2-2.0)Y;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.2-8)Lu-(0.2-2.0)Y;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.1-0.35)Sc-(0.1-0.75)Zr;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.1-4)Er-(0.1-0.75)Zr;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.2-6)Tm-(0.1-0.75)Zr;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.2-8)Yb-(0.1-0.75)Zr;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.2-8)Lu-(0.1-0.75)Zr;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.1-0.35)Sc-(0.1-1.0)Ti;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.1-4)Er-(0.1-1.0)Ti;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.2-6)Tm-(0.1-1.0)Ti;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.2-8)Yb-(0.1-1.0)Ti;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.2-8)Lu-(0.1-1.0)Ti;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.1-0.35)Sc-(0.1-1.0)Hf;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.1-4)Er-(0.1-1.0)Hf;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.2-6)Tb-(0.1-1.0)Hf;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.2-8)Yb-(0.1-1.0)Hf;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.2-8)Lu-(0.1-1.0)Hf;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.1-0.35)Sc-(0.1-0.75)Nb;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.1-4)Er-(0.1-0.75)Nb;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.2-6)Tm-(0.1-0.75)Nb;
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.2-8)Yb-(0.1-0.75)Nb; and
- about Al-(4-10)Zn-(0.5-2.5)Cu-(1-3)Mg-(0.2-8)Lu-(0.1-0.75)Nb.
- Even more preferred examples of similar alloys to these are alloys with about 1.5 to about 3.0 weight percent magnesium, alloys with about 5.0 to about 9.0 weight percent zinc, and alloys with about 1.0 to about 2.5 weight percent copper, and include, but are not limited to (in weight percent):
- about Al-(5-9)Zn-(1.5-3)Mg-(0.1-0.25)Sc-(0.5-2.0)Gd;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.2-2)Er-(0.5-2.0)Gd;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.2-4)Tm-(0.5-2.0)Gd;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.2-4)Yb-(0.5-2.0)Gd;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.2-4)Lu-(0.5-2.0)Gd;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.1-0.25)Sc-(0.5-2.0)Y;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.2-2)Er-(0.5-2.0)Y;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.2-4)Tm-(0.5-2.0)Y;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.2-4)Yb-(0.5-2.0)Y;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.2-4)Lu-(0.5-2.0)Y;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.1-0.25)Sc-(0.1-0.5)Zr;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.2-2)Er-(0.1-0.5)Zr;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.2-4)Tm-(0.1-0.5)Zr;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.2-4)Yb-(0.1-0.5)Zr;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.2-4)Lu-(0.1-0.5)Zr;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.1-0.25)Sc-(0.1-0.5)Ti;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.2-2)Er-(0.1-0.5)Ti;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.2-4)Tm-(0.1-0.5)Ti;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.2-4)Yb-(0.1-0.5)Ti;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.2-4)-Lu-(0.1-0.5)Ti;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.1-0.25)Sc-(0.1-0.5)Hf;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.2-2)Er-(0.1-0.5)Hf;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.2-4)Tm-(0.1-0.5)Hf;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.2-4)Yb-(0.1-0.5)Hf;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.2-4)Lu-(0.1-0.5)Hf;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.1-0.25)Sc-(0.1-0.5)Nb;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.2-2)Er-(0.1-0.5)Nb;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.2-4)Tm-(0.1-0.5)Nb;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.2-4)Yb-(0.1-0.5)Nb;
- about Al-(5-9)Zn-(1.5-3)Mg-(0.2-4)Lu-(0.1-0.5)Nb;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.1-0.25)Sc-(0.2-2.0)Gd;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.2-2)Er-(0.2-2.0)Gd;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.2-4)Tm-(0.2-2.0)Gd;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.2-4)Yb-(0.2-2.0)Gd;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.2-4)Lu-(0.2-2.0)Gd;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.1-0.25)Sc-(0.5-2.0)Y;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.2-2)Er-(0.5-2.0)Y;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.2-4)Tm-(0.5-2.0)Y;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.2-4)Yb-(0.5-2.0)Y;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.2-4)Lu-(0.5-2.0)Y;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.1-0.25)Sc-(0.1-0.5)Zr;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.2-2)Er-(0.1-0.5)Zr;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.2-4)Tm-(0.1-0.5)Zr;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.2-4)Yb-(0.1-0.5)Zr;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.2-4)Lu-(0.1-0.5)Zr;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.1-0.25)Sc-(0.1-0.5)Ti;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.2-2)Er-(0.1-0.5)Ti;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.2-4)Tm-(0.1-0.5)Ti;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.2-4)Yb-(0.1-0.5)Ti;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.2-4)Lu-(0.1-0.5)Ti;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.1-0.25)Sc-(0.1-0.5)Hf;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.2-2)Er-(0.1-0.5)Hf;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.2-4)Tm-(0.1-0.5)Hf;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.2-4)Yb-(0.1-0.5)Hf;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.2-4)Lu-(0.1-0.5)Hf;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.1-0.25)Sc-(0.1-0.5)Nb;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.2-2)Er-(0.1-0.5)Nb;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.2-4)Tm-(0.1-0.5)Nb;
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.2-4)Yb-(0.1-0.5)Nb; and
- about Al-(5-9)Zn-(1-2.5)Cu-(1.5-3)Mg-(0.2-4)Lu-(0.1-0.5)Nb.
- Although the present invention has been described with reference to preferred embodiments, workers skilled in the art will recognize that changes may be made in form and detail without departing from the spirit and scope of the invention.
Claims (22)
1. A heat treatable aluminum alloy comprising:
about 3.0 to about 12.0 weight percent zinc;
about 0.5 to about 3.5 weight percent magnesium;
at least one first element selected from the group comprising about 0.1 to about 0.5 weight percent scandium, about 0.1 to about 6.0 weight percent erbium, about 0.1 to about 10.0 weight percent thulium, about 0.1 to about 15.0 weight percent ytterbium, and about 0.1 to about 12.0 weight percent lutetium;
at least one second element selected from the group comprising about 0.1 to about 4.0 weight percent gadolinium, about 0.1 to about 4.0 weight percent yttrium, about 0.05 to about 1.0 weight percent zirconium, about 0.05 to about 2.0 weight percent titanium, about 0.05 to about 2.0 weight percent hafnium, and about 0.05 to about 1.0 weight percent niobium; and
the balance substantially aluminum.
2. The alloy of claim 1 , wherein the alloy comprises an aluminum solid solution matrix containing a plurality of dispersed Al3X second phases having L12 structures, wherein X includes at least one first element and at least one second element.
3. The alloy of claim 1 , further comprising about 0.2 to 3.0 weight percent copper.
4. The alloy of claim 1 , further comprising at least one of about 0.001 weight percent to about 0.1 weight percent sodium, about 0.001 weight percent to about 0.1 weight calcium, about 0.001 weight percent to about 0.1 weight percent strontium, about 0.001 weight percent to about 0.1 weight percent antimony, about 0.001 weight percent to about 0.1 weight percent barium and about 0.001 weight percent to about 0.1 weight percent phosphorus.
5. The alloy of claim 1 , comprising no more than about 1.0 weight percent total other elements including impurities.
6. The alloy of claim 1 , comprising no more than about 0.1 weight percent iron, about 0.1 weight percent chromium, about 0.1 weight percent manganese, about 0.1 weight percent vanadium, about 0.1 weight percent cobalt, and about 0.1 weight percent nickel.
7. The alloy of claim 1 , wherein the alloy is formed by a process selected from casting, deformation processing, and rapid solidification processing.
8. The alloy of claim 7 , wherein the alloy is heat treated after forming.
9. The alloy of claim 8 , wherein the alloy is heat treated by a solution anneal at a temperature of about 800° F. (426° C.) to about 1100° F. (593° C.) for about 30 minutes to four hours, followed by quenching.
10. The alloy of claim 9 , wherein the quenching is in liquid.
11. The alloy of claim 10 , wherein the alloy is aged after quenching.
12. The alloy of claim 11 , wherein the aging occurs at a temperature of about 200° F. (93° C.) to about 600° F. (316° C.) for about two to forty-eight hours.
13. The heat treatable aluminum alloy of claim 1 , wherein the alloy is capable of being used at temperatures from about −420° F. (−251° C.) up to about 650° F. (343° C.).
14. A heat treatable aluminum alloy comprising:
about 3.0 to about 12.0 weight percent zinc;
about 0.5 to about 3.5 weight percent magnesium;
an aluminum solid solution matrix containing a plurality of dispersed Al3X second phases having L12 structures where X comprises at least one of scandium, erbium, thulium, ytterbium and lutetium, and at least one of gadolinium, yttrium, zirconium, titanium, hafnium and niobium; and
the balance substantially aluminum.
15. The alloy of claim 14 further comprising about 0.2 to about 3.0 weight percent copper.
16. The alloy of claim 14 , wherein the alloy comprises at least one of: about 0.1 to about 0.5 weight percent scandium, about 0.1 to about 6.0 weight percent erbium, about 0.1 to about 10.0 weight percent thulium, about 0.1 to about 15.0 weight percent ytterbium, about 0.1 to about 12.0 weight percent lutetium, about 0.1 to about 4.0 weight percent gadolinium, about 0.1 to about 4.0 weight percent yttrium, about 0.05 to about 1.0 weight percent zirconium, about 0.05 to about 2.0 weight percent titanium, about 0.05 to about 2.0 weight percent hafnium, and about 0.05 to about 1.0 weight percent niobium.
17. A method of forming a heat treatable aluminum alloy, the method comprising:
(a) forming a melt comprising:
about 3.0 to about 12.0 weight percent zinc;
about 0.5 to about 3.5 weight percent magnesium;
at least one first element selected from the group comprising about 0.1 to about 0.5 weight percent scandium, about 0.1 to about 6.0 weight percent erbium, about 0.1 to about 10.0 weight percent thulium, about 0.1 to about 15.0 weight percent ytterbium, and about 0.1 to about 12.0 weight percent lutetium;
at least one second element selected from the group comprising about 0.1 to about 4.0 weight percent gadolinium, about 0.1 to about 4.0 weight percent yttrium, about 0.05 to about 1.0 weight percent zirconium, about 0.05 to about 2.0 weight percent titanium, about 0.05 to about 2.0 weight percent hafnium, and about 0.05 to about 1.0 weight percent niobium;
and the balance substantially aluminum;
(b) solidifying the melt to form a solid body; and
(c) heat treating the solid body.
18. The method of claim 17 , wherein the melt further comprises about 0.2 to about 3.0 weight percent copper.
19. The method of claim 17 , further comprising:
refining the structure of the solid body by deformation processing comprising at least one of: extrusion, forging and rolling.
20. The method of claim 17 , wherein solidifying comprises a casting process.
21. The method of claim 17 , wherein solidifying comprises a rapid solidification process in which the cooling rate is greater than about 103° C./second and comprising at least one of: powder processing, atomization, melt spinning, splat quenching, spray deposition, cold spray, plasma spray, laser melting, laser deposition, ball milling and cryomilling.
22. The method of claim 17 wherein the heat treating comprises:
solution heat treatment at about 800° F. (426° C.) to about 1100° F. (593° C.) for about thirty minutes to four hours;
quenching; and
aging at about 200° F. (93° C.) to about 600° F. (316° C.) for about two to forty-eight hours.
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Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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Citations (90)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3619181A (en) * | 1968-10-29 | 1971-11-09 | Aluminum Co Of America | Aluminum scandium alloy |
US3816080A (en) * | 1971-07-06 | 1974-06-11 | Int Nickel Co | Mechanically-alloyed aluminum-aluminum oxide |
US4041123A (en) * | 1971-04-20 | 1977-08-09 | Westinghouse Electric Corporation | Method of compacting shaped powdered objects |
US4259112A (en) * | 1979-04-05 | 1981-03-31 | Dwa Composite Specialties, Inc. | Process for manufacture of reinforced composites |
US4463058A (en) * | 1981-06-16 | 1984-07-31 | Atlantic Richfield Company | Silicon carbide whisker composites |
US4469537A (en) * | 1983-06-27 | 1984-09-04 | Reynolds Metals Company | Aluminum armor plate system |
US4499048A (en) * | 1983-02-23 | 1985-02-12 | Metal Alloys, Inc. | Method of consolidating a metallic body |
US4597792A (en) * | 1985-06-10 | 1986-07-01 | Kaiser Aluminum & Chemical Corporation | Aluminum-based composite product of high strength and toughness |
US4626294A (en) * | 1985-05-28 | 1986-12-02 | Aluminum Company Of America | Lightweight armor plate and method |
US4647321A (en) * | 1980-11-24 | 1987-03-03 | United Technologies Corporation | Dispersion strengthened aluminum alloys |
US4661172A (en) * | 1984-02-29 | 1987-04-28 | Allied Corporation | Low density aluminum alloys and method |
US4667497A (en) * | 1985-10-08 | 1987-05-26 | Metals, Ltd. | Forming of workpiece using flowable particulate |
US4689090A (en) * | 1986-03-20 | 1987-08-25 | Aluminum Company Of America | Superplastic aluminum alloys containing scandium |
US4710246A (en) * | 1982-07-06 | 1987-12-01 | Centre National De La Recherche Scientifique "Cnrs" | Amorphous aluminum-based alloys |
US4713216A (en) * | 1985-04-27 | 1987-12-15 | Showa Aluminum Kabushiki Kaisha | Aluminum alloys having high strength and resistance to stress and corrosion |
US4755221A (en) * | 1986-03-24 | 1988-07-05 | Gte Products Corporation | Aluminum based composite powders and process for producing same |
US4832741A (en) * | 1986-08-12 | 1989-05-23 | Bbc Brown Boveri Ag | Powder-metallurgical process for the production of a green pressed article of high strength and of low relative density from a heat-resistant aluminum alloy |
US4834810A (en) * | 1988-05-06 | 1989-05-30 | Inco Alloys International, Inc. | High modulus A1 alloys |
US4834942A (en) * | 1988-01-29 | 1989-05-30 | The United States Of America As Represented By The Secretary Of The Navy | Elevated temperature aluminum-titanium alloy by powder metallurgy process |
US4853178A (en) * | 1988-11-17 | 1989-08-01 | Ceracon, Inc. | Electrical heating of graphite grain employed in consolidation of objects |
US4865806A (en) * | 1986-05-01 | 1989-09-12 | Dural Aluminum Composites Corp. | Process for preparation of composite materials containing nonmetallic particles in a metallic matrix |
US4874440A (en) * | 1986-03-20 | 1989-10-17 | Aluminum Company Of America | Superplastic aluminum products and alloys |
US4915605A (en) * | 1989-05-11 | 1990-04-10 | Ceracon, Inc. | Method of consolidation of powder aluminum and aluminum alloys |
US4923532A (en) * | 1988-09-12 | 1990-05-08 | Allied-Signal Inc. | Heat treatment for aluminum-lithium based metal matrix composites |
US4927470A (en) * | 1988-10-12 | 1990-05-22 | Aluminum Company Of America | Thin gauge aluminum plate product by isothermal treatment and ramp anneal |
US4933140A (en) * | 1988-11-17 | 1990-06-12 | Ceracon, Inc. | Electrical heating of graphite grain employed in consolidation of objects |
US4946517A (en) * | 1988-10-12 | 1990-08-07 | Aluminum Company Of America | Unrecrystallized aluminum plate product by ramp annealing |
US4964927A (en) * | 1989-03-31 | 1990-10-23 | University Of Virginia Alumini Patents | Aluminum-based metallic glass alloys |
US4988464A (en) * | 1989-06-01 | 1991-01-29 | Union Carbide Corporation | Method for producing powder by gas atomization |
US5032352A (en) * | 1990-09-21 | 1991-07-16 | Ceracon, Inc. | Composite body formation of consolidated powder metal part |
US5053084A (en) * | 1987-08-12 | 1991-10-01 | Yoshida Kogyo K.K. | High strength, heat resistant aluminum alloys and method of preparing wrought article therefrom |
US5055257A (en) * | 1986-03-20 | 1991-10-08 | Aluminum Company Of America | Superplastic aluminum products and alloys |
US5059390A (en) * | 1989-06-14 | 1991-10-22 | Aluminum Company Of America | Dual-phase, magnesium-based alloy having improved properties |
US5066342A (en) * | 1988-01-28 | 1991-11-19 | Aluminum Company Of America | Aluminum-lithium alloys and method of making the same |
US5076865A (en) * | 1988-10-15 | 1991-12-31 | Yoshida Kogyo K. K. | Amorphous aluminum alloys |
US5076340A (en) * | 1989-08-07 | 1991-12-31 | Dural Aluminum Composites Corp. | Cast composite material having a matrix containing a stable oxide-forming element |
US5130209A (en) * | 1989-11-09 | 1992-07-14 | Allied-Signal Inc. | Arc sprayed continuously reinforced aluminum base composites and method |
US5133931A (en) * | 1990-08-28 | 1992-07-28 | Reynolds Metals Company | Lithium aluminum alloy system |
US5198045A (en) * | 1991-05-14 | 1993-03-30 | Reynolds Metals Company | Low density high strength al-li alloy |
US5211910A (en) * | 1990-01-26 | 1993-05-18 | Martin Marietta Corporation | Ultra high strength aluminum-base alloys |
US5226983A (en) * | 1985-07-08 | 1993-07-13 | Allied-Signal Inc. | High strength, ductile, low density aluminum alloys and process for making same |
US5256215A (en) * | 1990-10-16 | 1993-10-26 | Honda Giken Kogyo Kabushiki Kaisha | Process for producing high strength and high toughness aluminum alloy, and alloy material |
US5308410A (en) * | 1990-12-18 | 1994-05-03 | Honda Giken Kogyo Kabushiki Kaisha | Process for producing high strength and high toughness aluminum alloy |
US5312494A (en) * | 1992-05-06 | 1994-05-17 | Honda Giken Kogyo Kabushiki Kaisha | High strength and high toughness aluminum alloy |
US5318641A (en) * | 1990-06-08 | 1994-06-07 | Tsuyoshi Masumoto | Particle-dispersion type amorphous aluminum-alloy having high strength |
US5397403A (en) * | 1989-12-29 | 1995-03-14 | Honda Giken Kogyo Kabushiki Kaisha | High strength amorphous aluminum-based alloy member |
US5458700A (en) * | 1992-03-18 | 1995-10-17 | Tsuyoshi Masumoto | High-strength aluminum alloy |
US5462712A (en) * | 1988-08-18 | 1995-10-31 | Martin Marietta Corporation | High strength Al-Cu-Li-Zn-Mg alloys |
US5480470A (en) * | 1992-10-16 | 1996-01-02 | General Electric Company | Atomization with low atomizing gas pressure |
US5532069A (en) * | 1993-12-24 | 1996-07-02 | Tsuyoshi Masumoto | Aluminum alloy and method of preparing the same |
US5597529A (en) * | 1994-05-25 | 1997-01-28 | Ashurst Technology Corporation (Ireland Limited) | Aluminum-scandium alloys |
US5624632A (en) * | 1995-01-31 | 1997-04-29 | Aluminum Company Of America | Aluminum magnesium alloy product containing dispersoids |
US5882449A (en) * | 1997-07-11 | 1999-03-16 | Mcdonnell Douglas Corporation | Process for preparing aluminum/lithium/scandium rolled sheet products |
US6139653A (en) * | 1999-08-12 | 2000-10-31 | Kaiser Aluminum & Chemical Corporation | Aluminum-magnesium-scandium alloys with zinc and copper |
US6149737A (en) * | 1996-09-09 | 2000-11-21 | Sumitomo Electric Industries Ltd. | High strength high-toughness aluminum alloy and method of preparing the same |
US6248453B1 (en) * | 1999-12-22 | 2001-06-19 | United Technologies Corporation | High strength aluminum alloy |
US6254704B1 (en) * | 1998-05-28 | 2001-07-03 | Sulzer Metco (Us) Inc. | Method for preparing a thermal spray powder of chromium carbide and nickel chromium |
US6258318B1 (en) * | 1998-08-21 | 2001-07-10 | Eads Deutschland Gmbh | Weldable, corrosion-resistant AIMG alloys, especially for manufacturing means of transportation |
US6309594B1 (en) * | 1999-06-24 | 2001-10-30 | Ceracon, Inc. | Metal consolidation process employing microwave heated pressure transmitting particulate |
US6312643B1 (en) * | 1997-10-24 | 2001-11-06 | The United States Of America As Represented By The Secretary Of The Air Force | Synthesis of nanoscale aluminum alloy powders and devices therefrom |
US6315948B1 (en) * | 1998-08-21 | 2001-11-13 | Daimler Chrysler Ag | Weldable anti-corrosive aluminum-magnesium alloy containing a high amount of magnesium, especially for use in automobiles |
US6331218B1 (en) * | 1994-11-02 | 2001-12-18 | Tsuyoshi Masumoto | High strength and high rigidity aluminum-based alloy and production method therefor |
US20010054247A1 (en) * | 2000-05-18 | 2001-12-27 | Stall Thomas C. | Scandium containing aluminum alloy firearm |
US6355209B1 (en) * | 1999-11-16 | 2002-03-12 | Ceracon, Inc. | Metal consolidation process applicable to functionally gradient material (FGM) compositons of tungsten, nickel, iron, and cobalt |
US6368427B1 (en) * | 1999-09-10 | 2002-04-09 | Geoffrey K. Sigworth | Method for grain refinement of high strength aluminum casting alloys |
US6506503B1 (en) * | 1998-07-29 | 2003-01-14 | Miba Gleitlager Aktiengesellschaft | Friction bearing having an intermediate layer, notably binding layer, made of an alloy on aluminium basis |
US6517954B1 (en) * | 1998-07-29 | 2003-02-11 | Miba Gleitlager Aktiengesellschaft | Aluminium alloy, notably for a layer |
US6524410B1 (en) * | 2001-08-10 | 2003-02-25 | Tri-Kor Alloys, Llc | Method for producing high strength aluminum alloy welded structures |
US6531004B1 (en) * | 1998-08-21 | 2003-03-11 | Eads Deutschland Gmbh | Weldable anti-corrosive aluminium-magnesium alloy containing a high amount of magnesium, especially for use in aviation |
US6562154B1 (en) * | 2000-06-12 | 2003-05-13 | Aloca Inc. | Aluminum sheet products having improved fatigue crack growth resistance and methods of making same |
US6630008B1 (en) * | 2000-09-18 | 2003-10-07 | Ceracon, Inc. | Nanocrystalline aluminum metal matrix composites, and production methods |
US20030192627A1 (en) * | 2002-04-10 | 2003-10-16 | Lee Jonathan A. | High strength aluminum alloy for high temperature applications |
US6702982B1 (en) * | 1995-02-28 | 2004-03-09 | The United States Of America As Represented By The Secretary Of The Army | Aluminum-lithium alloy |
US20040046402A1 (en) * | 2002-09-05 | 2004-03-11 | Michael Winardi | Drive-in latch with rotational adjustment |
US20040055671A1 (en) * | 2002-04-24 | 2004-03-25 | Questek Innovations Llc | Nanophase precipitation strengthened Al alloys processed through the amorphous state |
US20040089382A1 (en) * | 2002-11-08 | 2004-05-13 | Senkov Oleg N. | Method of making a high strength aluminum alloy composition |
US20040170522A1 (en) * | 2003-02-28 | 2004-09-02 | Watson Thomas J. | Aluminum base alloys |
US20040191111A1 (en) * | 2003-03-14 | 2004-09-30 | Beijing University Of Technology | Er strengthening aluminum alloy |
US20050013725A1 (en) * | 2003-07-14 | 2005-01-20 | Chung-Chih Hsiao | Aluminum based material having high conductivity |
US6902699B2 (en) * | 2002-10-02 | 2005-06-07 | The Boeing Company | Method for preparing cryomilled aluminum alloys and components extruded and forged therefrom |
US20050147520A1 (en) * | 2003-12-31 | 2005-07-07 | Guido Canzona | Method for improving the ductility of high-strength nanophase alloys |
US20060011272A1 (en) * | 2004-07-15 | 2006-01-19 | Lin Jen C | 2000 Series alloys with enhanced damage tolerance performance for aerospace applications |
US20060093512A1 (en) * | 2003-01-15 | 2006-05-04 | Pandey Awadh B | Aluminum based alloy |
US20060172073A1 (en) * | 2005-02-01 | 2006-08-03 | Groza Joanna R | Methods for production of FGM net shaped body for various applications |
US20060269437A1 (en) * | 2005-05-31 | 2006-11-30 | Pandey Awadh B | High temperature aluminum alloys |
US20070048167A1 (en) * | 2005-08-25 | 2007-03-01 | Yutaka Yano | Metal particles, process for manufacturing the same, and process for manufacturing vehicle components therefrom |
US20070062669A1 (en) * | 2005-09-21 | 2007-03-22 | Song Shihong G | Method of producing a castable high temperature aluminum alloy by controlled solidification |
US7241328B2 (en) * | 2003-11-25 | 2007-07-10 | The Boeing Company | Method for preparing ultra-fine, submicron grain titanium and titanium-alloy articles and articles prepared thereby |
US7344675B2 (en) * | 2003-03-12 | 2008-03-18 | The Boeing Company | Method for preparing nanostructured metal alloys having increased nitride content |
US20080066833A1 (en) * | 2006-09-19 | 2008-03-20 | Lin Jen C | HIGH STRENGTH, HIGH STRESS CORROSION CRACKING RESISTANT AND CASTABLE Al-Zn-Mg-Cu-Zr ALLOY FOR SHAPE CAST PRODUCTS |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1995032074A2 (en) | 1994-05-25 | 1995-11-30 | Ashurst Corporation | Aluminum-scandium alloys and uses thereof |
WO1996010099A1 (en) | 1994-09-26 | 1996-04-04 | Ashurst Technology Corporation (Ireland) Limited | High strength aluminum casting alloys for structural applications |
JP3594272B2 (en) | 1995-06-14 | 2004-11-24 | 古河スカイ株式会社 | High strength aluminum alloy for welding with excellent stress corrosion cracking resistance |
FR2838135B1 (en) | 2002-04-05 | 2005-01-28 | Pechiney Rhenalu | CORROSIVE ALLOY PRODUCTS A1-Zn-Mg-Cu WITH VERY HIGH MECHANICAL CHARACTERISTICS, AND AIRCRAFT STRUCTURE ELEMENTS |
FR2838136B1 (en) | 2002-04-05 | 2005-01-28 | Pechiney Rhenalu | ALLOY PRODUCTS A1-Zn-Mg-Cu HAS COMPROMISED STATISTICAL CHARACTERISTICS / DAMAGE TOLERANCE IMPROVED |
US20040099352A1 (en) | 2002-09-21 | 2004-05-27 | Iulian Gheorghe | Aluminum-zinc-magnesium-copper alloy extrusion |
ATE474070T1 (en) * | 2003-01-15 | 2010-07-15 | United Technologies Corp | ALUMINUM-BASED ALLOY |
CN1203200C (en) * | 2003-03-14 | 2005-05-25 | 北京工业大学 | Al-Zn-Mg-Er rare earth aluminium alloy |
-
2008
- 2008-04-18 US US12/148,387 patent/US20090263273A1/en not_active Abandoned
-
2009
- 2009-03-31 EP EP09251028.8A patent/EP2112244B1/en active Active
Patent Citations (95)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3619181A (en) * | 1968-10-29 | 1971-11-09 | Aluminum Co Of America | Aluminum scandium alloy |
US4041123A (en) * | 1971-04-20 | 1977-08-09 | Westinghouse Electric Corporation | Method of compacting shaped powdered objects |
US3816080A (en) * | 1971-07-06 | 1974-06-11 | Int Nickel Co | Mechanically-alloyed aluminum-aluminum oxide |
US4259112A (en) * | 1979-04-05 | 1981-03-31 | Dwa Composite Specialties, Inc. | Process for manufacture of reinforced composites |
US4647321A (en) * | 1980-11-24 | 1987-03-03 | United Technologies Corporation | Dispersion strengthened aluminum alloys |
US4463058A (en) * | 1981-06-16 | 1984-07-31 | Atlantic Richfield Company | Silicon carbide whisker composites |
US4710246A (en) * | 1982-07-06 | 1987-12-01 | Centre National De La Recherche Scientifique "Cnrs" | Amorphous aluminum-based alloys |
US4499048A (en) * | 1983-02-23 | 1985-02-12 | Metal Alloys, Inc. | Method of consolidating a metallic body |
US4469537A (en) * | 1983-06-27 | 1984-09-04 | Reynolds Metals Company | Aluminum armor plate system |
US4661172A (en) * | 1984-02-29 | 1987-04-28 | Allied Corporation | Low density aluminum alloys and method |
US4713216A (en) * | 1985-04-27 | 1987-12-15 | Showa Aluminum Kabushiki Kaisha | Aluminum alloys having high strength and resistance to stress and corrosion |
US4626294A (en) * | 1985-05-28 | 1986-12-02 | Aluminum Company Of America | Lightweight armor plate and method |
US4597792A (en) * | 1985-06-10 | 1986-07-01 | Kaiser Aluminum & Chemical Corporation | Aluminum-based composite product of high strength and toughness |
US5226983A (en) * | 1985-07-08 | 1993-07-13 | Allied-Signal Inc. | High strength, ductile, low density aluminum alloys and process for making same |
US4667497A (en) * | 1985-10-08 | 1987-05-26 | Metals, Ltd. | Forming of workpiece using flowable particulate |
US4689090A (en) * | 1986-03-20 | 1987-08-25 | Aluminum Company Of America | Superplastic aluminum alloys containing scandium |
US5055257A (en) * | 1986-03-20 | 1991-10-08 | Aluminum Company Of America | Superplastic aluminum products and alloys |
US4874440A (en) * | 1986-03-20 | 1989-10-17 | Aluminum Company Of America | Superplastic aluminum products and alloys |
US4755221A (en) * | 1986-03-24 | 1988-07-05 | Gte Products Corporation | Aluminum based composite powders and process for producing same |
US4865806A (en) * | 1986-05-01 | 1989-09-12 | Dural Aluminum Composites Corp. | Process for preparation of composite materials containing nonmetallic particles in a metallic matrix |
US4832741A (en) * | 1986-08-12 | 1989-05-23 | Bbc Brown Boveri Ag | Powder-metallurgical process for the production of a green pressed article of high strength and of low relative density from a heat-resistant aluminum alloy |
US5053084A (en) * | 1987-08-12 | 1991-10-01 | Yoshida Kogyo K.K. | High strength, heat resistant aluminum alloys and method of preparing wrought article therefrom |
US5066342A (en) * | 1988-01-28 | 1991-11-19 | Aluminum Company Of America | Aluminum-lithium alloys and method of making the same |
US4834942A (en) * | 1988-01-29 | 1989-05-30 | The United States Of America As Represented By The Secretary Of The Navy | Elevated temperature aluminum-titanium alloy by powder metallurgy process |
US4834810A (en) * | 1988-05-06 | 1989-05-30 | Inco Alloys International, Inc. | High modulus A1 alloys |
US5462712A (en) * | 1988-08-18 | 1995-10-31 | Martin Marietta Corporation | High strength Al-Cu-Li-Zn-Mg alloys |
US4923532A (en) * | 1988-09-12 | 1990-05-08 | Allied-Signal Inc. | Heat treatment for aluminum-lithium based metal matrix composites |
US4946517A (en) * | 1988-10-12 | 1990-08-07 | Aluminum Company Of America | Unrecrystallized aluminum plate product by ramp annealing |
US4927470A (en) * | 1988-10-12 | 1990-05-22 | Aluminum Company Of America | Thin gauge aluminum plate product by isothermal treatment and ramp anneal |
US5076865A (en) * | 1988-10-15 | 1991-12-31 | Yoshida Kogyo K. K. | Amorphous aluminum alloys |
US4853178A (en) * | 1988-11-17 | 1989-08-01 | Ceracon, Inc. | Electrical heating of graphite grain employed in consolidation of objects |
US4933140A (en) * | 1988-11-17 | 1990-06-12 | Ceracon, Inc. | Electrical heating of graphite grain employed in consolidation of objects |
US4964927A (en) * | 1989-03-31 | 1990-10-23 | University Of Virginia Alumini Patents | Aluminum-based metallic glass alloys |
US4915605A (en) * | 1989-05-11 | 1990-04-10 | Ceracon, Inc. | Method of consolidation of powder aluminum and aluminum alloys |
US4988464A (en) * | 1989-06-01 | 1991-01-29 | Union Carbide Corporation | Method for producing powder by gas atomization |
US5059390A (en) * | 1989-06-14 | 1991-10-22 | Aluminum Company Of America | Dual-phase, magnesium-based alloy having improved properties |
US5076340A (en) * | 1989-08-07 | 1991-12-31 | Dural Aluminum Composites Corp. | Cast composite material having a matrix containing a stable oxide-forming element |
US5130209A (en) * | 1989-11-09 | 1992-07-14 | Allied-Signal Inc. | Arc sprayed continuously reinforced aluminum base composites and method |
US5397403A (en) * | 1989-12-29 | 1995-03-14 | Honda Giken Kogyo Kabushiki Kaisha | High strength amorphous aluminum-based alloy member |
US5211910A (en) * | 1990-01-26 | 1993-05-18 | Martin Marietta Corporation | Ultra high strength aluminum-base alloys |
US5318641A (en) * | 1990-06-08 | 1994-06-07 | Tsuyoshi Masumoto | Particle-dispersion type amorphous aluminum-alloy having high strength |
US5133931A (en) * | 1990-08-28 | 1992-07-28 | Reynolds Metals Company | Lithium aluminum alloy system |
US5032352A (en) * | 1990-09-21 | 1991-07-16 | Ceracon, Inc. | Composite body formation of consolidated powder metal part |
US5256215A (en) * | 1990-10-16 | 1993-10-26 | Honda Giken Kogyo Kabushiki Kaisha | Process for producing high strength and high toughness aluminum alloy, and alloy material |
US5308410A (en) * | 1990-12-18 | 1994-05-03 | Honda Giken Kogyo Kabushiki Kaisha | Process for producing high strength and high toughness aluminum alloy |
US5198045A (en) * | 1991-05-14 | 1993-03-30 | Reynolds Metals Company | Low density high strength al-li alloy |
US5458700A (en) * | 1992-03-18 | 1995-10-17 | Tsuyoshi Masumoto | High-strength aluminum alloy |
US5312494A (en) * | 1992-05-06 | 1994-05-17 | Honda Giken Kogyo Kabushiki Kaisha | High strength and high toughness aluminum alloy |
US5480470A (en) * | 1992-10-16 | 1996-01-02 | General Electric Company | Atomization with low atomizing gas pressure |
US5532069A (en) * | 1993-12-24 | 1996-07-02 | Tsuyoshi Masumoto | Aluminum alloy and method of preparing the same |
US5597529A (en) * | 1994-05-25 | 1997-01-28 | Ashurst Technology Corporation (Ireland Limited) | Aluminum-scandium alloys |
US5620652A (en) * | 1994-05-25 | 1997-04-15 | Ashurst Technology Corporation (Ireland) Limited | Aluminum alloys containing scandium with zirconium additions |
US6331218B1 (en) * | 1994-11-02 | 2001-12-18 | Tsuyoshi Masumoto | High strength and high rigidity aluminum-based alloy and production method therefor |
US5624632A (en) * | 1995-01-31 | 1997-04-29 | Aluminum Company Of America | Aluminum magnesium alloy product containing dispersoids |
US6702982B1 (en) * | 1995-02-28 | 2004-03-09 | The United States Of America As Represented By The Secretary Of The Army | Aluminum-lithium alloy |
US6149737A (en) * | 1996-09-09 | 2000-11-21 | Sumitomo Electric Industries Ltd. | High strength high-toughness aluminum alloy and method of preparing the same |
US5882449A (en) * | 1997-07-11 | 1999-03-16 | Mcdonnell Douglas Corporation | Process for preparing aluminum/lithium/scandium rolled sheet products |
US6312643B1 (en) * | 1997-10-24 | 2001-11-06 | The United States Of America As Represented By The Secretary Of The Air Force | Synthesis of nanoscale aluminum alloy powders and devices therefrom |
US6254704B1 (en) * | 1998-05-28 | 2001-07-03 | Sulzer Metco (Us) Inc. | Method for preparing a thermal spray powder of chromium carbide and nickel chromium |
US6517954B1 (en) * | 1998-07-29 | 2003-02-11 | Miba Gleitlager Aktiengesellschaft | Aluminium alloy, notably for a layer |
US6506503B1 (en) * | 1998-07-29 | 2003-01-14 | Miba Gleitlager Aktiengesellschaft | Friction bearing having an intermediate layer, notably binding layer, made of an alloy on aluminium basis |
US6531004B1 (en) * | 1998-08-21 | 2003-03-11 | Eads Deutschland Gmbh | Weldable anti-corrosive aluminium-magnesium alloy containing a high amount of magnesium, especially for use in aviation |
US6258318B1 (en) * | 1998-08-21 | 2001-07-10 | Eads Deutschland Gmbh | Weldable, corrosion-resistant AIMG alloys, especially for manufacturing means of transportation |
US6315948B1 (en) * | 1998-08-21 | 2001-11-13 | Daimler Chrysler Ag | Weldable anti-corrosive aluminum-magnesium alloy containing a high amount of magnesium, especially for use in automobiles |
US6309594B1 (en) * | 1999-06-24 | 2001-10-30 | Ceracon, Inc. | Metal consolidation process employing microwave heated pressure transmitting particulate |
US6139653A (en) * | 1999-08-12 | 2000-10-31 | Kaiser Aluminum & Chemical Corporation | Aluminum-magnesium-scandium alloys with zinc and copper |
US6368427B1 (en) * | 1999-09-10 | 2002-04-09 | Geoffrey K. Sigworth | Method for grain refinement of high strength aluminum casting alloys |
US6355209B1 (en) * | 1999-11-16 | 2002-03-12 | Ceracon, Inc. | Metal consolidation process applicable to functionally gradient material (FGM) compositons of tungsten, nickel, iron, and cobalt |
US6248453B1 (en) * | 1999-12-22 | 2001-06-19 | United Technologies Corporation | High strength aluminum alloy |
US20010054247A1 (en) * | 2000-05-18 | 2001-12-27 | Stall Thomas C. | Scandium containing aluminum alloy firearm |
US6562154B1 (en) * | 2000-06-12 | 2003-05-13 | Aloca Inc. | Aluminum sheet products having improved fatigue crack growth resistance and methods of making same |
US7097807B1 (en) * | 2000-09-18 | 2006-08-29 | Ceracon, Inc. | Nanocrystalline aluminum alloy metal matrix composites, and production methods |
US6630008B1 (en) * | 2000-09-18 | 2003-10-07 | Ceracon, Inc. | Nanocrystalline aluminum metal matrix composites, and production methods |
US6524410B1 (en) * | 2001-08-10 | 2003-02-25 | Tri-Kor Alloys, Llc | Method for producing high strength aluminum alloy welded structures |
US20030192627A1 (en) * | 2002-04-10 | 2003-10-16 | Lee Jonathan A. | High strength aluminum alloy for high temperature applications |
US6918970B2 (en) * | 2002-04-10 | 2005-07-19 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | High strength aluminum alloy for high temperature applications |
US20040055671A1 (en) * | 2002-04-24 | 2004-03-25 | Questek Innovations Llc | Nanophase precipitation strengthened Al alloys processed through the amorphous state |
US20040046402A1 (en) * | 2002-09-05 | 2004-03-11 | Michael Winardi | Drive-in latch with rotational adjustment |
US6902699B2 (en) * | 2002-10-02 | 2005-06-07 | The Boeing Company | Method for preparing cryomilled aluminum alloys and components extruded and forged therefrom |
US20040089382A1 (en) * | 2002-11-08 | 2004-05-13 | Senkov Oleg N. | Method of making a high strength aluminum alloy composition |
US7048815B2 (en) * | 2002-11-08 | 2006-05-23 | Ues, Inc. | Method of making a high strength aluminum alloy composition |
US20060093512A1 (en) * | 2003-01-15 | 2006-05-04 | Pandey Awadh B | Aluminum based alloy |
US6974510B2 (en) * | 2003-02-28 | 2005-12-13 | United Technologies Corporation | Aluminum base alloys |
US20040170522A1 (en) * | 2003-02-28 | 2004-09-02 | Watson Thomas J. | Aluminum base alloys |
US7344675B2 (en) * | 2003-03-12 | 2008-03-18 | The Boeing Company | Method for preparing nanostructured metal alloys having increased nitride content |
US20040191111A1 (en) * | 2003-03-14 | 2004-09-30 | Beijing University Of Technology | Er strengthening aluminum alloy |
US20050013725A1 (en) * | 2003-07-14 | 2005-01-20 | Chung-Chih Hsiao | Aluminum based material having high conductivity |
US7241328B2 (en) * | 2003-11-25 | 2007-07-10 | The Boeing Company | Method for preparing ultra-fine, submicron grain titanium and titanium-alloy articles and articles prepared thereby |
US20050147520A1 (en) * | 2003-12-31 | 2005-07-07 | Guido Canzona | Method for improving the ductility of high-strength nanophase alloys |
US20060011272A1 (en) * | 2004-07-15 | 2006-01-19 | Lin Jen C | 2000 Series alloys with enhanced damage tolerance performance for aerospace applications |
US20060172073A1 (en) * | 2005-02-01 | 2006-08-03 | Groza Joanna R | Methods for production of FGM net shaped body for various applications |
US20060269437A1 (en) * | 2005-05-31 | 2006-11-30 | Pandey Awadh B | High temperature aluminum alloys |
US20070048167A1 (en) * | 2005-08-25 | 2007-03-01 | Yutaka Yano | Metal particles, process for manufacturing the same, and process for manufacturing vehicle components therefrom |
US20070062669A1 (en) * | 2005-09-21 | 2007-03-22 | Song Shihong G | Method of producing a castable high temperature aluminum alloy by controlled solidification |
US20080066833A1 (en) * | 2006-09-19 | 2008-03-20 | Lin Jen C | HIGH STRENGTH, HIGH STRESS CORROSION CRACKING RESISTANT AND CASTABLE Al-Zn-Mg-Cu-Zr ALLOY FOR SHAPE CAST PRODUCTS |
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