US20110064599A1 - Direct extrusion of shapes with l12 aluminum alloys - Google Patents

Direct extrusion of shapes with l12 aluminum alloys Download PDF

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US20110064599A1
US20110064599A1 US12/560,000 US56000009A US2011064599A1 US 20110064599 A1 US20110064599 A1 US 20110064599A1 US 56000009 A US56000009 A US 56000009A US 2011064599 A1 US2011064599 A1 US 2011064599A1
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weight percent
powder
aluminum
extrusion
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Awadh B. Pandey
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Raytheon Technologies Corp
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United Technologies Corp
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Priority to EP10251602A priority patent/EP2295609A1/de
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Priority to US13/925,988 priority patent/US20140010700A1/en
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/20—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces by extruding
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/04—Making non-ferrous alloys by powder metallurgy
    • C22C1/0408—Light metal alloys
    • C22C1/0416—Aluminium-based alloys
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/02—Alloys based on aluminium with silicon as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/06—Alloys based on aluminium with magnesium as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/10—Alloys based on aluminium with zinc as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/12—Both compacting and sintering
    • B22F3/14—Both compacting and sintering simultaneously
    • B22F2003/145—Both compacting and sintering simultaneously by warm compacting, below debindering temperature
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • B22F2998/10—Processes characterised by the sequence of their steps
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2999/00—Aspects linked to processes or compositions used in powder metallurgy

Definitions

  • the present invention relates generally to aluminum alloys and more specifically to a method for forming high strength aluminum ally powder having L1 2 dispersoids therein into aluminum parts such as brackets, cases and other components of turbine engines as well as other products fabricated from aluminum alloys.
  • 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 Lu.
  • 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.).
  • U.S. Patent Application Publication No. 2006/0269437 A1 discloses a high strength aluminum alloy that contains scandium and other elements that is strengthened by L1 2 dispersoids.
  • L1 2 strengthened aluminum alloys have high strength and improved fatigue properties compared to commercial aluminum alloys. Fine grain size results in improved mechanical properties of materials. Hall-Petch strengthening has been known for decades where strength increases as grain size decreases. An optimum grain size for optimum strength is in the nano range of about 30 to 100 nm. These alloys also have higher ductility.
  • the present invention is a method for consolidating aluminum alloy powders into useful components such as brackets, cases and other components having improved strength and fracture toughness.
  • powders include an aluminum alloy having coherent L1 2 Al 3 X dispersoids 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 containing at least one alloying element selected from silicon, magnesium, manganese, lithium, copper, zinc, and nickel.
  • the aluminum alloy components and parts are formed by direct extrusion of consolidated billets using a die with the required component shape. Extrusion of these alloys produces considerable improvement in mechanical properties, especially ductility compared to the consolidated billet. Extrusion parameters include billet temperature, billet soak time, extrusion rate, extrusion ratio and die temperature.
  • FIG. 1 is an aluminum scandium phase diagram.
  • FIG. 2 is an aluminum erbium phase diagram.
  • FIG. 3 is an aluminum thulium phase diagram.
  • FIG. 4 is an aluminum ytterbium phase diagram.
  • FIG. 5 is an aluminum lutetium phase diagram.
  • FIG. 6A is a schematic diagram of a vertical gas atomizer.
  • FIG. 6B is a close up view of nozzle 108 in FIG. 6A .
  • FIGS. 7A and 7B are SEM photos of the inventive aluminum alloy powder.
  • FIGS. 8A and 8B are optical micrographs showing the microstructure of gas atomized L1 2 aluminum alloy powder.
  • FIG. 9 is a diagram showing the steps of the gas atomization process.
  • FIG. 10 is a diagram showing the processing steps to consolidate the L1 2 aluminum alloy powder.
  • FIG. 11 is a schematic diagram of blind die compaction.
  • FIG. 12 is a schematic diagram of a direct extrusion process.
  • FIG. 13 A-C are extrusions and examples of products made by sectioning off extrusions.
  • FIG. 14 is a schematic of a hollow extrusion die.
  • FIG. 15 is a photograph of duct produced for a rocket engine.
  • Alloy powders of this invention are formed from aluminum based alloys with high strength and fracture toughness for applications at temperatures from about ⁇ 420° F. ( ⁇ 251° C.) up to about 650° F. (343° C.).
  • the aluminum alloy comprises a solid solution of aluminum and at least one element selected from silicon, magnesium, manganese, lithium, copper, zinc, and nickel strengthened by L1 2 Al 3 X coherent precipitates 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 binary aluminum magnesium system is a simple eutectic at 36 weight percent magnesium and 842° F. (450° C.). There is complete solubility of magnesium and aluminum in the rapidly solidified inventive alloys discussed herein
  • the binary aluminum silicon system is a simple eutectic at 12.6 weight percent silicon and 1070.6° F. (577° C.). There is complete solubility of silicon and aluminum in the rapidly solidified inventive alloys discussed herein.
  • the binary aluminum manganese system is a simple eutectic at about 2 weight percent manganese and 1216.4° F. (658° C.). There is complete solubility of manganese and aluminum in the rapidly solidified inventive alloys discussed herein.
  • the binary aluminum lithium system is a simple eutectic at 8 weight percent lithium and 1105° (596° C.).
  • the equilibrium solubility of 4 weight percent lithium can be extended significantly by rapid solidification techniques. There is complete solubility of lithium in the rapid solidified inventive alloys discussed herein.
  • the binary aluminum copper system is a simple eutectic at 32 weight percent copper and 1018° F. (548° C.). There is complete solubility of copper in the rapidly solidified inventive alloys discussed herein.
  • 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 and 718° 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 processes. Decomposition of the supersaturated solid solution of zinc in aluminum gives rise to spherical and ellipsoidal GP zones, which are coherent with the matrix and act to strengthen the alloy.
  • the aluminum nickel binary system is a simple eutectic at 5.7 weight percent nickel and 1183.8° F. (639.9° C.). There is little solubility of nickel in aluminum. However, the solubility can be extended significantly by utilizing rapid solidification processes.
  • the equilibrium phase in the aluminum nickel eutectic system is L1 2 intermetallic Al 3 Ni.
  • 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, thulium, ytterbium, and 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 842° F. (450° C.).
  • Additions of magnesium in aluminum increase the lattice parameter of the aluminum matrix, and decrease the lattice parameter mismatch further increasing the resistance of the Al 3 Sc to coarsening.
  • Additions of zinc, copper, lithium, silicon, manganese and nickel provide solid solution and precipitation strengthening in the aluminum alloys.
  • 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.
  • 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.).
  • Additions of magnesium in aluminum increase the lattice parameter of the aluminum matrix, and decrease the lattice parameter mismatch further increasing the resistance of the Al 3 Er to coarsening.
  • Additions of zinc, copper, lithium, silicon, manganese and nickel provide solid solution and precipitation strengthening in the aluminum alloys.
  • 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.
  • 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 0.420 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.).
  • Additions of magnesium in aluminum increase the lattice parameter of the aluminum matrix, and decrease the lattice parameter mismatch further increasing the resistance of the Al 3 Tm to coarsening.
  • 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.).
  • Additions of magnesium in aluminum increase the lattice parameter of the aluminum matrix, and decrease the lattice parameter mismatch further increasing the resistance of the Al 3 Yb to coarsening.
  • 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.).
  • Additions of magnesium in aluminum increase the lattice parameter of the aluminum matrix, and decrease the lattice parameter mismatch further increasing the resistance of the Al 3 Lu to coarsening.
  • Additions of zinc, copper, lithium, silicon, manganese and nickel provide solid solution and precipitation strengthening in the aluminum alloys.
  • 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.
  • 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 19 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 despersoids 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 result 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.
  • L1 2 phase strengthened aluminum alloys are important structural materials because of their excellent mechanical properties and the stability of these properties at elevated temperature due to the resistance of the coherent dispersoids in the microstructure to particle coarsening.
  • the mechanical properties are optimized by maintaining a high volume fraction of L1 2 dispersoids in the microstructure.
  • the concentration of alloying elements in solid solution in alloys cooled from the melt is directly proportional to the cooling rate.
  • Exemplary aluminum alloys for this invention include, but are not limited to (in weight percent unless otherwise specified):
  • M is at least one of about (4-25) weight percent silicon, (1-8) weight percent magnesium, (0.1-3) weight percent manganese, (0.5-3) weight percent lithium, (0.2-6) weight percent copper, (3-12) weight percent zinc, and (1-12) weight percent nickel.
  • the amount of silicon present in the fine grain matrix may vary from about 4 to about 25 weight percent, more preferably from about 5 to about 20 weight percent, and even more preferably from about 6 to about 14 weight percent.
  • the amount of magnesium present in the fine grain matrix may vary from about 1 to about 8 weight percent, more preferably from about 3 to about 7.5 weight percent, and even more preferably from about 4 to about 6.5 weight percent.
  • the amount of manganese present in the fine grain matrix may vary from about 0.1 to about 3 weight percent, more preferably from about 0.2 to about 2 weight percent, and even more preferably from about 0.3 to about 1 weight percent.
  • the amount of lithium present in the fine grain matrix may vary from about 0.5 to about 3 weight percent, more preferably from about 1 to about 2.5 weight percent, and even more preferably from about 1 to about 2 weight percent.
  • the amount of copper present in the fine grain matrix may vary from about 0.2 to about 6 weight percent, more preferably from about 0.5 to about 5 weight percent, and even more preferably from about 2 to about 4.5 weight percent.
  • the amount of zinc present in the fine grain matrix may vary from about 3 to about 12 weight percent, more preferably from about 4 to about 10 weight percent, and even more preferably from about 5 to about 9 weight percent.
  • the amount of nickel present in the fine grain matrix may vary from about 1 to about 12 weight percent, more preferably from about 2 to about 10 weight percent, and even more preferably from about 4 to about 10 weight percent.
  • the amount of scandium present in the fine grain matrix may vary from 0.1 to about 4 weight percent, more preferably from about 0.1 to about 3 weight percent, and even more preferably from about 0.2 to about 2.5 weight percent.
  • the Al—Sc phase diagram shown in FIG. 1 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 (hypereutectic alloys) can only retain scandium 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 erbium present in the fine grain matrix may vary from about 0.1 to about 20 weight percent, more preferably from about 0.3 to about 15 weight percent, and even more preferably from about 0.5 to about 10 weight percent.
  • the Al—Er phase diagram shown in FIG. 2 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.
  • RSP rapid solidification processing
  • the amount of thulium present in the alloys may vary from about 0.1 to about 15 weight percent, more preferably from about 0.2 to about 10 weight percent, and even more preferably from about 0.4 to about 6 weight percent.
  • the Al—Tm phase diagram shown in FIG. 3 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 may vary from about 0.1 to about 25 weight percent, more preferably from about 0.3 to about 20 weight percent, and even more preferably from about 0.4 to about 10 weight percent.
  • the Al—Yb phase diagram shown in FIG. 4 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.
  • RSP rapid solidification processing
  • the amount of lutetium present in the alloys may vary from about 0.1 to about 25 weight percent, more preferably from about 0.3 to about 20 weight percent, and even more preferably from about 0.4 to about 10 weight percent.
  • the Al—Lu phase diagram shown in FIG. 5 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.
  • RSP rapid solidification processing
  • the amount of gadolinium present in the alloys may vary from about 0.1 to about 20 weight percent, more preferably from about 0.3 to about 15 weight percent, and even more preferably from about 0.5 to about 10 weight percent.
  • the amount of yttrium present in the alloys may vary from about 0.1 to about 20 weight percent, more preferably from about 0.3 to about 15 weight percent, and even more preferably from about 0.5 to about 10 weight percent.
  • the amount of zirconium present in the alloys may vary from about 0.05 to about 4 weight percent, more preferably from about 0.1 to about 3 weight percent, and even more preferably from about 0.3 to about 2 weight percent.
  • the amount of titanium present in the alloys may vary from about 0.05 to about 10 weight percent, more preferably from about 0.2 to about 8 weight percent, and even more preferably from about 0.4 to about 4 weight percent.
  • the amount of hafnium present in the alloys may vary from about 0.05 to about 10 weight percent, more preferably from about 0.2 to about 8 weight percent, and even more preferably from about 0.4 to about 5 weight percent.
  • the amount of niobium present in the alloys may vary from about 0.05 to about 5 weight percent, more preferably from about 0.1 to about 3 weight percent, and even more preferably from about 0.2 to about 2 weight percent.
  • Gas atomization is a two fluid process wherein a stream of molten metal is disintegrated by a high velocity gas stream. The end result is that the particles of molten metal eventually become spherical due to surface tension and finely solidify in powder form. Heat from the liquid droplets is transferred to the atomization gas by convection.
  • the solidification rates depending on the gas and the surrounding environment, can be very high and can exceed 10 6 ° C./second. Cooling rates greater than 10 3 ° C./second are typically specified to ensure supersaturation of alloying elements in gas atomized L1 2 aluminum alloy powder in the inventive process described herein.
  • FIG. 6A A schematic of typical vertical gas atomizer 100 is shown in FIG. 6A .
  • FIG. 6A is taken from R. Germain, Powder Metallurgy Science Second Edition MPIF (1994) (chapter 3, p. 101) and is included herein for reference.
  • Vacuum or inert gas induction melter 102 is positioned at the top of free flight chamber 104 .
  • Vacuum induction melter 102 contains melt 106 which flows by gravity or gas overpressure through nozzle 108 .
  • FIG. 6B A close up view of nozzle 108 is shown in FIG. 6B . Melt 106 enters nozzle 108 and flows downward till it meets the high pressure gas stream from gas source 110 where it is transformed into a spray of droplets.
  • the droplets eventually become spherical due to surface tension and rapidly solidify into spherical powder 112 which collects in collection chamber 114 .
  • the gas recirculates through cyclone collector 116 which collects fine powder 118 before returning to the input gas stream.
  • cyclone collector 116 collects fine powder 118 before returning to the input gas stream.
  • a large number of processing parameters are associated with gas atomization that affect the final product. Examples include melt superheat, gas pressure, metal flow rate, gas type, and gas purity.
  • gas atomization the particle size is related to the energy input to the metal. Higher gas pressures, higher superheat temperatures and lower metal flow rates result in smaller particle sizes. Higher gas pressures provide higher gas velocities for a given atomization nozzle design.
  • inert gases such as helium, argon, and nitrogen.
  • Helium is preferred for rapid solidification because the high heat transfer coefficient of the gas leads to high quenching rates and high supersaturation of alloying elements.
  • the particle size of gas atomized melts typically has a log normal distribution.
  • ultra fine particles can form that may reenter the gas expansion zone.
  • These solidified fine particles can be carried into the flight path of molten larger droplets resulting in agglomeration of small satellite particles on the surfaces of larger particles.
  • An example of small satellite particles attached to inventive spherical L1 2 aluminum alloy powder is shown in the scanning electron microscopy (SEM) micrographs of FIGS. 7A and 7B at two magnifications. The spherical shape of gas atomized aluminum powder is evident.
  • the spherical shape of the powder is suggestive of clean powder without excessive oxidation. Higher oxygen in the powder results in irregular powder shape. Spherical powder helps in improving the flowability of powder which results in higher apparent density and tap density of the powder.
  • the satellite particles can be minimized by adjusting processing parameters to reduce or even eliminate turbulence in the gas atomization process.
  • the microstructure of gas atomized aluminum alloy powder is predominantly cellular as shown in the optical micrographs of cross-sections of the inventive alloy in FIGS. 8A and 8B at two magnifications. The rapid cooling rate suppresses dendritic solidification common at slower cooling rates resulting in a finer microstructure with minimum alloy segregation.
  • Oxygen and hydrogen in the powder can degrade the mechanical properties of the final part. It is preferred to limit the oxygen in the L1 2 alloy powder to about 1 ppm to 2000 ppm. Oxygen is intentionally introduced as a component of the helium gas during atomization. An oxide coating on the L1 2 aluminum powder is beneficial for two reasons. First, the coating prevents agglomeration by contact sintering and secondly, the coating inhibits the chance of explosion of the powder. A controlled amount of oxygen is important in order to provide good ductility and fracture toughness in the final consolidated material. Hydrogen content in the powder is controlled by ensuring the dew point of the helium gas is low. A dew point of about minus 50° F. (minus 45.5° C.) to minus 100° F. (minus 73.3° C.) is preferred.
  • the powder is classified according to size by sieving.
  • To prepare the powder for sieving if the powder has zero percent oxygen content, the powder may be exposed to nitrogen gas which passivates the powder surface and prevents agglomeration. Finer powder sizes result in improved mechanical properties of the end product. While minus 325 mesh (about 45 microns) powder can be used, minus 450 mesh (about 30 microns) powder is a preferred size in order to provide good mechanical properties in the end product.
  • powder is collected in collection chambers in order to prevent oxidation of the powder. Collection chambers are used at the bottom of atomization chamber 104 as well as at the bottom of cyclone collector 116 . The powder is transported and stored in the collection chambers also. Collection chambers are maintained under positive pressure with nitrogen gas which prevents oxidation of the powder.
  • FIG. 9 A schematic of the L1 2 aluminum powder manufacturing process is shown in FIG. 9 .
  • aluminum 200 and L12 forming (and other alloying) elements 210 are melted in furnace 220 to a predetermined superheat temperature under vacuum or inert atmosphere.
  • Preferred charge for furnace 220 is prealloyed aluminum 200 and L1 2 and other alloying elements before charging furnace 220 .
  • Melt 230 is then passed through nozzle 240 where it is impacted by pressurized gas stream 250 .
  • Gas stream 250 is an inert gas such as nitrogen, argon or helium, preferably helium.
  • Melt 230 can flow through nozzle 240 under gravity or under pressure. Gravity flow is preferred for the inventive process disclosed herein.
  • Preferred pressures for pressurized gas stream 250 are about 50 psi (10.35 MPa) to about 750 psi (5.17 MPa) depending on the alloy.
  • the atomization process creates molten droplets 260 which rapidly solidify as they travel through agglomeration chamber 270 forming spherical powder particles 280 .
  • the molten droplets transfer heat to the atomizing gas by convention.
  • the role of the atomizing gas is two fold: one is to disintegrate the molten metal stream into fine droplets by transferring kinetic energy from the gas to the melt stream and the other is to extract heat from the molten droplets to rapidly solidify them into spherical powder.
  • the solidification time and cooling rate vary with droplet size. Larger droplets take longer to solidify and their resulting cooling rate is lower.
  • the atomizing gas will extract heat efficiently from smaller droplets resulting in a higher cooling rate.
  • Finer powder size is therefore preferred as higher cooling rates provide finer microstructures and higher mechanical properties in the end product. Higher cooling rates lead to finer cellular microstructures which are preferred for higher mechanical properties. Finer cellular microstructures result in finer grain sizes in consolidated product. Finer grain size provides higher yield strength of the material through the Hall-Petch strengthening model.
  • Key process variables for gas atomization include superheat temperature, nozzle diameter, helium content and dew point of the gas, and metal flow rate.
  • Superheat temperatures of from about 150° F. (66° C.) to 200° F. (93° C.) are preferred.
  • Nozzle diameters of about 0.07 in. (1.8 mm) to 0.12 in. (3.0 mm) are preferred depending on the alloy.
  • the gas stream used herein was a helium nitrogen mixture containing 74 to 87 vol. % helium.
  • the metal flow rate ranged from about 0.8 lb/min (0.36 kg/min) to 4.0 lb/min (1.81 kg/min).
  • the oxygen content of the L1 2 aluminum alloy powders was observed to consistently decrease as a run progressed.
  • the powder is then classified by sieving process 290 to create classified powder 300 .
  • Sieving of powder is performed under an inert environment to minimize oxygen and hydrogen pickup from the environment. While the yield of minus 450 mesh powder is extremely high (95%), there are always larger particle sizes, flakes and ligaments that are removed by the sieving. Sieving also ensures a narrow size distribution and provides a more uniform powder size. Sieving also ensures that flaw sizes cannot be greater than minus 450 mesh which will be required for nondestructive inspection of the final product.
  • Powder quality is extremely important to produce material with higher strength and ductility. Powder quality is determined by powder size, shape, size distribution, oxygen content, hydrogen content, and alloy chemistry. Over fifty gas atomization runs were performed to produce the inventive powder with finer powder size, finer size distribution, spherical shape, and lower oxygen and hydrogen contents. Processing parameters of some exemplary gas atomization runs are listed in Table 1. It is suggested that the observed decrease in oxygen content is attributed to oxygen gettering by the powder as the runs progressed.
  • Inventive L1 2 aluminum alloy powder was produced with over 95% yield of minus 450 mesh (30 microns) which includes powder from about 1 micron to about 30 microns.
  • the average powder size was about 10 microns to about 15 microns.
  • finer powder size is preferred for higher mechanical properties. Finer powders have finer cellular microstructures. As a result, finer cell sizes lead to finer grain size by fragmentation and coalescence of cells during powder consolidation. Finer grain sizes produce higher yield strength through the Hall-Petch strengthening model where yield strength varies inversely as the square root of the grain size. It is preferred to use powder with an average particle size of 10-15 microns.
  • Powders with a powder size less than 10-15 microns can be more challenging to handle due to the larger surface area of the powder. Powders with sizes larger than 10-15 microns will result in larger cell sizes in the consolidated product which, in turn, will lead to larger grain sizes and lower yield strengths.
  • Powders with narrow size distributions are preferred. Narrower powder size distributions produce product microstructures with more uniform grain size. Spherical powder was produced to provide higher apparent and tap densities which help in achieving 100% density in the consolidated product. Spherical shape is also an indication of cleaner and lower oxygen content powder. Lower oxygen and lower hydrogen contents are important in producing material with high ductility and fracture toughness. Although it is beneficial to maintain low oxygen and hydrogen content in powder to achieve good mechanical properties, lower oxygen may interfere with sieving due to self sintering. An oxygen content of about 25 ppm to about 500 ppm is preferred to provide good ductility and fracture toughness without any sieving issue. Lower hydrogen is also preferred for improving ductility and fracture toughness.
  • Blending is a preferred step in the consolidation process because it results in improved uniformity of particle size distribution.
  • Gas atomized L1 2 aluminum alloy powder generally exhibits a bimodal particle size distribution and cross blending of separate powder batches tends to homogenize the particle size distribution.
  • Blending is also preferred when separate metal and/or ceramic powders are added to the L1 2 base powder to form bimodal or trimodal consolidated alloy microstructures.
  • the powders are transferred to a can (step 330 ) where the powder is vacuum degassed (step 340 ) at elevated temperatures.
  • the can (step 330 ) is an aluminum container having a cylindrical, rectangular or other configuration with a central axis. Cylindrical configurations are preferred with hydraulic extrusion presses. Vacuum degassing times can range from about 0.5 hours to about 8 days. A temperature range of about 300° F. (149° C.) to about 900° F. (482° C.) is preferred. Dynamic degassing of large amounts of powder is preferred to static degassing. In dynamic degassing, the can is preferably rotated during degassing to expose all of the powder to a uniform temperature. Degassing removes oxygen and hydrogen from the powder.
  • step 340 Following vacuum degassing (step 340 ), the vacuum line is crimped and welded shut (step 350 ). The powder is then fully densified by blind die compaction or closed die forging as the process is sometimes called (step 360 ). At this point the can may be removed by machining (step 380 ) to form a useful billet (step 390 ).
  • FIGS. 11A and 11B A schematic showing blind die compaction (process 400 ) is shown in FIGS. 11A and 11B .
  • the equipment comprises base 410 , die 420 , ram 430 , and means to apply pressure to ram 430 indicated by arrow 450 .
  • billet 440 does not fill die cavity 460 .
  • billet 445 completely fills the die cavity and has taken the shape of die cavity 460 .
  • the die cavities can have any shape provided they have a central symmetrical axis parallel to arrow 450 . Cylindrical shapes adopt well for extrusion billets. Canned L1 2 aluminum alloy powder preforms are easily densified due to the large capacity of modern hydraulic presses.
  • FIG. 12 is a perspective view of a direct extrusion process.
  • a billet of, in this case, L1 2 aluminum alloy is extruded through a die having a cavity with a shape necessary to produce a cross-sectional profile of the final part.
  • the components of extrusion process 500 are illustrated on the FIG. and comprise container 510 , container liner 520 , and ram 540 with dummy block 550 .
  • Dummy block 550 isolates billet 530 from direct contact with ram 540 during extrusion.
  • billet 530 is forced through opening (s) in die 560 by pressure on ram 540 .
  • Ram 540 can be mechanically or hydraulically actuated. Hydraulic extrusion presses are preferred for higher pressure operation.
  • die 560 is held in place against the ram pressure by die backer 570 .
  • Other forms of extrusion are indirect extrusion, hydrostatic extrusion, lateral extrusion, and others known to those in the art.
  • Extrusion 580 in FIG. 12 has a simple circular cross-section.
  • FIG. 13 shows examples of other common shapes.
  • FIG. 13A is an example of how a bracket can be fabricated from an extrusion.
  • FIG. 13B is an example of a gear.
  • FIG. 13C is another exemplary shape.
  • FIGS. 13B and 13C have hollow shapes and are formed by the process of hollow die extrusion.
  • the L1 2 aluminum alloy is divided during extrusion in port sections of a first (interior) hollow die into a plurality of portions, which are again joined (welded) to each other in a second (exterior) die with a welding chamber section, to form a welded portion, thereby producing a hollow section having a complicated profile.
  • FIG. 14 A perspective representation of hollow die system 600 used to form a rectangular tube is shown in FIG. 14 .
  • the die system comprises internal die 660 and external die 665 .
  • Internal die 660 contains a plurality of inlet ports 620 and internal bearing 630 .
  • internal bearing 630 fits inside external bearing 635 such that there is clearance between bearing wall 640 of internal bearing 630 and bearing wall 645 of external bearing 635 .
  • L1 2 alloy billet 610 is forced in direction of arrow 615 in a container (not shown) by a ram (not shown) such that the alloy is forced to flow through port (s) 620 such that it flows around internal bearing 630 .
  • the metal rejoins in welding chamber 665 and flows through the gap between internal bearing 630 and external bearing 635 and is formed into rectangular hollow extrusion 670 with dimensions formed by bearing surfaces 640 and 645 .
  • Die 660 (shown) is termed a porthole die.
  • Other dies used to form extrusions with hollow features are spider and bridge dies and others known to those in the art.
  • L1 2 aluminum alloy parts useful for turbine and rocket engine applications can be rapidly and efficiently made by direct extrusion including brackets, cases, tubes, ducts, beams, spars.
  • Billet soaking time was kept constant at 1.5 hours for all these billets. These billets were compacted at 750 F using vacumm hot pressing resulting in 100% dense billets which were extruded to produce ducts. Lower extrusion temperature of 500 F at ratio of 10:1 and speed of 3 inch per minute resulted in 118 ksi tensile strength, 8% elongation and 16% reduction in area. Higher extrusion temperature of 700 F at ratio of 10:1 and speed of 0.5 inch per minute resulted in 115 ksi tensile strength, 9% elongation and 18.5% reduction in area.
  • extrusion temperature of 650 F at ratio of 6:1 and speed of 0.5 inch per minute resulted in 117 ksi tensile strength, about 7.5% elongation and 15% reduction in area.
  • extrusion temperature of 700 F, ratio of 15:1 and speed of 3:1 resulted in 105 ksi tensile strength, 10% elongation and 20% reduction in area.
  • a number of examples of extrusion demonstrated excellent tensile properties with about 105-120 ksi tensile strength and ductility in terms of reduction in area of about 10 to 20%.
  • Extrusions when carried at very high speeds can result in reduced strength and higher ductility due to adiabatic heating generated during extrusion. Higher the speed larger the adiabatic heat generated due to friction during extrusion. Therefore higher speed is not preferred from strength point of view. Higher speed is preferred from cost point of view since more number of components can be produced in same amount of time. Slower speeds do not produce adiabatic heat and therefore preferred for higher strength extrusions. Slower the speed less adiabatic heat is produced. However, below certain speed extrusion becomes uneconomical and therefore it is not preferred to use too low extrusion speed. Based on all the results produced, extrusion speed of about 0.1 inch per minute to about 20 inch per minute is preferred for present inventive L1 2 aluminum alloys based on balanced mechanical properties resulting in good combination of strength and ductility.
  • FIG. 15 A photograph of a duct produced for a jet engine is shown in FIG. 15 . Products such as this are a significant improvement in the industry.

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