Classifications

• • C—CHEMISTRY; METALLURGY
  • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
  • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
  • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
  • C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
• • 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
  • B22F1/00—Metallic powder; Treatment of metallic powder, e.g. to facilitate working or to improve properties
  • B22F1/06—Metallic powder characterised by the shape of the particles
  • B22F1/068—Flake-like particles
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B33—ADDITIVE MANUFACTURING TECHNOLOGY
  • B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
  • B33Y80/00—Products made by additive manufacturing
• • C—CHEMISTRY; METALLURGY
  • C21—METALLURGY OF IRON
  • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
  • C21D6/00—Heat treatment of ferrous alloys
  • C21D6/004—Heat treatment of ferrous alloys containing Cr and Ni
• • C—CHEMISTRY; METALLURGY
  • C21—METALLURGY OF IRON
  • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
  • C21D6/00—Heat treatment of ferrous alloys
  • C21D6/02—Hardening by precipitation
• • C—CHEMISTRY; METALLURGY
  • C21—METALLURGY OF IRON
  • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
  • C21D8/00—Modifying the physical properties of ferrous metals or ferrous alloys by deformation combined with, or followed by, heat treatment
• • 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
  • C22C1/0433—Nickel- or cobalt-based alloys
• • C—CHEMISTRY; METALLURGY
  • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
  • C22C—ALLOYS
  • C22C19/00—Alloys based on nickel or cobalt
  • C22C19/03—Alloys based on nickel or cobalt based on nickel
  • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
  • C22C19/058—Alloys based on nickel or cobalt based on nickel with chromium without Mo and W
• • C—CHEMISTRY; METALLURGY
  • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
  • C22C—ALLOYS
  • C22C30/00—Alloys containing less than 50% by weight of each constituent
• • C—CHEMISTRY; METALLURGY
  • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
  • C22C—ALLOYS
  • C22C38/00—Ferrous alloys, e.g. steel alloys
• • 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
  • C22F1/002—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working by rapid cooling or quenching; cooling agents used therefor
• • C—CHEMISTRY; METALLURGY
  • C21—METALLURGY OF IRON
  • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
  • C21D2211/00—Microstructure comprising significant phases
  • C21D2211/001—Austenite
• • C—CHEMISTRY; METALLURGY
  • C21—METALLURGY OF IRON
  • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
  • C21D2211/00—Microstructure comprising significant phases
  • C21D2211/004—Dispersions; Precipitations
• • C—CHEMISTRY; METALLURGY
  • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
  • C22C—ALLOYS
  • C22C33/00—Making ferrous alloys
  • C22C33/02—Making ferrous alloys by powder metallurgy
  • C22C33/0257—Making ferrous alloys by powder metallurgy characterised by the range of the alloying elements
  • C22C33/0278—Making ferrous alloys by powder metallurgy characterised by the range of the alloying elements with at least one alloying element having a minimum content above 5%
  • C22C33/0285—Making ferrous alloys by powder metallurgy characterised by the range of the alloying elements with at least one alloying element having a minimum content above 5% with Cr, Co, or Ni having a minimum content higher than 5%

Definitions

• a new material includes at least 27.5 at. % Ni. In yet another embodiment, a new material includes at least 30.0 at. % Ni. In one embodiment, a new material includes not greater than 37.5 at. % Ni. In another embodiment, a new material includes not greater than 35.0 at. % Ni. In yet another embodiment, a new material includes not greater 32.5 at. % Ni.
• incidental elements may be used with the new materials described herein, provided the above-identified requirements relating to nickel, iron, aluminum, and chromium are satisfied.
• up to 15 at. %, in total, of one or more of cobalt (Co), copper (Cu), molybdenum (Mo), manganese (Mn), and tungsten (W) may be used, which elements may, for instance, contribute to solid solution strengthening of the alloy.
• up to 10 at. %, in total, of one or more of niobium (Nb), tantalum (Ta), and titanium (Ti) may be used, which elements may, for instance, facilitate precipitation formation and/or improve stability of precipitates.
• C % of carbon
• C % of carbon
• Si may be used as silicon may, for instance, improve wear resistance and/or lower density.
• V vanadium
• Hf hafnium
• elements may, for instance, facilitate boride and/or carbide formation and/or grain boundary strengthening (e.g., in the case of hafnium).
• B boron
• Zr zirconium
• an alloy includes up to 10 at. % Co, wherein a sufficient amount of cobalt is present to facilitate solid solution strengthening and/or second phase strengthening, as compared to the same alloy without cobalt.
• an alloy includes at least 0.5 at. % Co.
• the alloy includes not greater than 5.0 at. % Co.
• the alloy includes not greater than 1.0 at. % Co.
• the alloy is essentially free of cobalt, containing cobalt only as an impurity.
• an alloy includes up to 10 at. % Mo, wherein a sufficient amount of molybdenum is present to facilitate solid solution strengthening and/or second phase strengthening, as compared to the same alloy without molybdenum. In one embodiment, at least some molybdenum is included within the fee phase of the alloy. In one embodiment, an alloy includes at least 0.5 at. % Mo. In one embodiment, the alloy includes not greater than 5.0 at. % Mo. In another embodiment, the alloy includes not greater than 1.0 at. % Mo. In another embodiment, the alloy is essentially free of molybdenum, containing molybdenum only as an impurity.
• the alloy includes not greater than 3 at. % Ta, wherein a sufficient amount of tantalum is present to facilitate precipitate stability (e.g., high solvus temperatures) / strengthening of bcc.
• an alloy includes at least 0.5 at. % Ta.
• the alloy includes not greater than 2.0 at. % Ta.
• an alloy includes not greater than 1.0 at. % Ta.
• the alloy is essentially free of tantalum, containing tantalum only as an impurity.
• the alloy includes up to 10.0 at. % Ti. Using titanium may reduce density, and may contribute to strengthening of the alloy.
• an "fcc-first" solidification pathway may facilitate the production of products having improved properties, such as, reduced cracking during additive manufacturing and/or casting, and improved tensile properties, among others.
• the amount of aluminum within the alloy is sufficient to realize an fcc-first solidification pathway where fee forms first during solidification of a melt.
• titanium is also used in the alloy and in combination with aluminum in an amount sufficient to realize an fcc-first solidification pathway.
• appropriate amounts of titanium plus aluminum may facilitate the production of alloy products having improved properties, such as, reduced cracking during additive manufacturing and/or casting, and/or improved tensile properties, among others.
• an appropriate amount of titanium may facilitate the realization of an fcc-first solidification pathway.
• the total amount of Al + Ti (in at. %) is sufficient to realize a fcc-first solidification pathway, and is sufficient to avoid embrittlement (e.g., cracking).
• the total amount of Al + Ti (in at. %) is not greater than 20 at. % (i.e., at. % Al + at. % Ti ⁇ 20 at. %).
• the total amount of Al + Ti (in at. %) is not greater than 18 at. %.
• the alloy includes a sufficient amount of carbon to facilitate interstitial solid solution strengthening (hardening).
• the alloy includes a sufficient amount of carbon to facilitate formation of carbides (e.g., MC, M 23 C 6 , M 7 C 3 compounds, where M is a metal, such as any of Fe, Al, and Cr and potentially Mo and Ti, if present in the alloy), where a sufficient volume of carbides is present to provide carbide strengthening (and with or without interstitial solid solution strengthening).
• a sufficient amount of carbon is used to achieve both interstitial solid solution strengthening and carbide precipitation.
• the alloy includes not greater than 6.0 at. % C. In another embodiment, the alloy includes not greater than 5.0 at. % C. In one embodiment, an alloy includes from 1-10 at. % C. In another embodiment, an alloy includes from 2-9 at. % C. In yet another embodiment, an alloy includes 3-9 at. % C. In another embodiment, an alloy includes 3-8 at. % C. In one embodiment, a sufficient amount of carbon is used to restrict/prevent cracking in a bcc-first solidification pathway product. In other embodiments, the alloy is essentially free of carbon, containing carbon only as an impurity.
• the alloy includes up to 2.0 at. % Hf.
• Hafnium may interact with carbon to form hafnium carbides, which may improve high temperature strength and creep resistance.
• the alloy includes up to 1.0 at. % Hf.
• the alloy includes up to 0.5 at. % Hf.
• the alloy is essentially free of hafnium, containing hafnium only as an impurity.
• the alloy includes up to 2.0 at. % B, wherein a sufficient amount of boron is present to facilitate formation of borides (e.g., M 3 B 2 , where M is a metal, such as any of Ni, Fe, or Cr, and potentially Mo and Ti, if present in the alloy), where a sufficient volume of borides is present to provide boride strengthening.
• the alloy includes at least 0.05 at. % of B.
• the alloy includes up to 1.0 at. % B.
• the alloy includes up to 0.75 at. % B.
• the alloy is essentially free of boron, containing boron only as an impurity.
• a new material comprises a sufficient amount of the ceramic material to facilitate production of a crack-free product (e.g., via equiaxed grains), but the amount of ceramic material in the product is limited so that the product retains its strength (e.g., tensile yield strength (TYS) and/or ultimate tensile strength (UTS)).
• the amount of ceramic material may be limited such that the strength of the ceramic-containing product is within 5 ksi (e.g., 1-2 ksi) of its strength without the ceramic.
• the ceramic material is TiB 2 .
• a new material comprises at least 0.1 vol. % of ceramic material. In one embodiment, a new material comprises 0.1 - 10 vol.
• a new material comprises 0.1 - 5 vol. % of ceramic material. In another embodiment, a new material comprises 0.1 - 1.0 vol. % of ceramic material (e.g., 0.05-0.5 wt. % of ceramic material).
• equiaxed grains means grains having an average aspect ratio of not greater than 1.5 to 1 as measured in the XY, YZ, and XZ planes as determined by the "Heyn Lineal Intercept Procedure" method described in ASTM standard El 12-13, entitled, "Standard Test Methods for Determining Average Grain Size”. Ceramic-containing materials that comprise equiaxed grains may realize, for instance, improved ductility and/or strength, among others, relative to the new material without the ceramic. In this regard, equiaxed grains that realize an average grain size of not greater than 20 microns may help facilitate the realization of improved ductility and/or strength, among others.
• a new material comprises equiaxed grains, wherein the average grain size is of from 0.01 to 20 microns.
• a method includes (300) cooling the solid product to below a solvus temperature of a precipitate phase of the mixture (e.g., any one of Ll 2 , L2i, B2, delta, D0 22 , and Laves precipitates of the material), thereby forming one or more precipitate phases within the product, wherein the mixture comprises a sufficient amount of the Ni, the Fe, the Al, and the Cr, with any optional incidental elements (noted above) to realize precipitate phase(s) within the crystalline structure.
• a precipitate phase of the mixture e.g., any one of Ll 2 , L2i, B2, delta, D0 22 , and Laves precipitates of the material
• controlled cooling of the material is employed to facilitate realization of an appropriate end product.
• a method may include the step of (400) cooling the mixture to ambient temperature, and a method may include controlling rates of cooling during at least cooling steps (300) and (400) such that, upon conclusion of step (400), i.e., upon reaching ambient temperature, a crack-free ingot is realized.
• Controlled cooling may be accomplished by, for instance, using an appropriate water cooled casting mold.
• ingot means a cast product of any shape.
• the term “ingot” includes billet.
• crack-free ingot means an ingot that is sufficiently free of cracks such that it can be used as fabricating ingot.
• Fabricating ingot means an ingot suitable for subsequent working into a final product. The subsequent working may include, for instance, hot working and/or cold working via any of rolling, forging, extrusion, as well as stress-relief by compression and/or stretching.
• a crack-free product such as a crack-free ingot
• a crack-free ingot may be processed, as appropriate, to obtain a final wrought product from the material.
• steps (100) - (400) of FIG. 3, described above may be considered a casting step (10), shown in FIG. 4, resulting in the above-described crack-free ingot.
• the crack-free product may be a crack-free preform produced by, for instance, shape casting, additive manufacturing or powder metallurgy.
• the working step (30) generally involves hot working and/or cold working the ingot and/or an intermediate product form.
• the hot working and/or cold working may include rolling, extrusion or forging of the material, for instance.
• the working (30) may occur before and/or after any dissolving step (20).
• the material may be allowed to cool to ambient temperature, and then reheated to an appropriate temperature for hot working.
• the material may be cold worked at around ambient temperatures.
• the material may be hot worked, cooled to ambient, and then cold worked.
• the hot working may commence after a soak of a dissolving step (20) so that reheating of the product is not required for hot working.
• the amount of Laves precipitates in the final product is not greater than 0.5 vol. %.
• the new material is essentially free of Laves precipitates (i.e., Laves precipitates are not detected in the new material when measured by X-ray Diffraction ("XRD")).
• the new materials may realize an improved combination of properties, such as an improved combination of at least two of density, ductility, strength, fracture toughness, oxidation resistance, fatigue resistance, creep resistance, and elevated temperature resistance, among others.
• the new materials may find use in various applications, including use in elevated temperature environments (e.g., 400°C-800°C).
• engine components e.g., disks, turbine blades, compressor components, vanes, airfoils, nozzles, shafts, shrouds, rotors, stators, and the like
• automotive or aerospace structural components land-based turbines
• nuclear applications e.g., reactor materials
• pressure vessels e.g., oil and gas components
• oil and gas components e.g., wellhead components, down-hole tools, safety valves
• components used in the chemical industry e.g., heaters, evaporator tubes, condensers
• the new materials may realize a mixed fcc+bcc crystalline structure, or an fec-only crystalline structure immediately below a solidus temperature of the material.
• the compositions of the new materials may be selected to have an appropriate solidification pathway to facilitate realization of the either the mixed fee + bec crystalline structure, or the fec-only crystalline structure.
• an appropriate solidification pathway may facilitate the realization of improved properties, such as, reduced cracking during additive manufacturing and/or casting, and improved tensile properties, among others.
• a new material forms by a solidification pathway where fee crystalline structures form first from the liquid and prior to the formation of bec crystalline structures (sometimes referred to hereinafter as an "fcc-first" solidification pathway).
• a new material forms by a solidification pathway where bec crystalline structures form first from the liquid prior to the formation of fee crystalline structures (sometimes referred to hereinafter as a "bcc-first” solidification pathway).
• a new material forms by a solidification pathway where fee crystalline structures and bec crystalline structures form from the liquid generally concomitantly (e.g., "near eutectic" or "eutectic-like" solidification).
• an appropriate composition is selected such that fee crystalline structures form first from a liquid melt along the solidification pathway. In another embodiment, an appropriate composition is selected such that bec crystalline structures form first from a liquid melt along the solidification pathway. In yet another embodiment, an appropriate composition is selected such that fee crystalline structures and bec crystalline structures form from the liquid generally concomitantly.
• the solidified material may realize one of a mixed fcc+bcc crystalline structure, or an fee-only crystalline structure. Additionally, the final product may realize the same volumetric percentage of fee and/or bee crystalline structures as the solidified material, or may realize a different volumetric percentage of fee and/or bee crystalline structures as compared to the as solidified material (e.g., due to TMT).
• an alloy matrix of a final product comprises at least 3.0 vol. % of fee crystalline structures.
• an alloy matrix of a final product comprises at least 5.0 vol. % of fee crystalline structures.
• an alloy matrix of a final product comprises at least 10 vol. % of fee crystalline structures.
• an alloy matrix of a final product comprises not greater than 95 vol. % fee crystalline structures.
• an alloy matrix of a final product comprises not greater than 90 vol. % fee crystalline structures.
• an alloy matrix of a final product comprises not greater than 80 vol. % fee crystalline structures.
• an alloy matrix of a final product comprises not greater than 60 vol. % fee crystalline structures.
• an alloy matrix of a final product comprises not greater than 40 vol. % fee crystalline structures.
• a powder comprising (or consisting essentially of) Ni, Fe, Al, and Cr, with any optional incidental elements (noted above), and within the scope of the compositions described above, may be used to produce an additively manufactured body comprising a mixed fcc+bcc crystalline structure, or an fec-only crystalline structure, optionally with precipitate phase(s) therein.
• the powders may be selectively heated above the liquidus temperature of the material, thereby forming a molten pool having the Ni, the Fe, the Al, and the Cr, with any optional incidental elements (noted above), followed by rapid solidification of the molten pool.
• One embodiment of a method of making an additively manufactured body may include (a) dispersing a powder comprising the Ni, Fe, Al, Cr, and with any optional incidental elements (noted above), (b) selectively heating a portion of the powder (e.g., via a laser) to a temperature above the liquidus temperature of the particular body to be formed, (c) forming a molten pool having the Ni, the Fe, the Al, and the Cr, with any optional incidental elements (noted above), and (d) cooling the molten pool at a cooling rate of at least 1000°C per second.
• the cooling rate is at least 10,000°C per second.
• the cooling rate is at least 100,000°C per second.
• the cooling rate is at least 1,000,000°C per second.
• Steps (a)-(d) may be repeated as necessary until the body is completed, i.e., until the final additively manufactured body is formed / completed.
• the final additively manufactured body comprising the fcc+bcc crystalline structure, or fcc-only crystalline structure, optionally with precipitate phase(s) therein may be of a complex geometry, or may be of a simple geometry (e.g., in the form of a sheet or plate).
• the powders used to additively manufacture a new material may be produced by atomizing a material (e.g., an ingot or melt) of the new material into powders of the appropriate dimensions relative to the additive manufacturing process to be used.
• a material e.g., an ingot or melt
• the additively manufactured body may be subject to any appropriate dissolving (20), working (30) and/or precipitation hardening steps (40), as described above. If employed, the dissolving (20) and/or the working (30) steps may be conducted on an intermediate form of the additively manufactured body and/or may be conducted on a final form of the additively manufactured body. If employed, the precipitation hardening step (40) is generally conducted relative to the final form of the additively manufactured body.
• an additively manufactured body consists essentially of the Ni, the Fe, the Al, the Cr, with any optional incidental elements (noted above), optionally with > 0.5 vol. % of precipitate phase(s), such as any of the material compositions described above.
• the new materials may realize an improved combination of properties, such as an improved combination of at least two of castability, machinability, density, ductility, strength fracture toughness, oxidation resistance, fatigue resistance, creep resistance, and elevated temperature resistance, among others.
• the new materials may find use in various applications, including use in elevated temperature environments (e.g., 400°C-800°C).
• a final product e.g., an ingot, a shape cast product, a wrought product, an additively manufactured product
• the final product is crack-free.
• the final product is machinable.
• the final product is both crack-free and machinable.
• the new materials may also realize a room temperature specific yield strength (i.e., a strength to weight ratio) of at least 340 ksi*in 3 /lbs.
• a final product realizes a room temperature specific yield strength of at least 390 ksi*in 3 /lbs.
• a final product realizes a room temperature specific yield strength of at least 440 ksi*in 3 /lbs.
• a final product realizes a room temperature specific yield strength of at least 500 ksi*in 3 /lbs.
• a final product realizes a room temperature specific yield strength of at least 550 ksi*in 3 /lbs.
• the new materials may realize good tensile properties at elevated temperature.
• a final product produced from the new materials may realize a tensile yield strength of at least 65 ksi at 650°C when measured in accordance with ASTM E21-09.
• a final product realizes a tensile yield strength of at least 80 ksi at 650°C.
• a final product realizes a tensile yield strength of at least 95 ksi at 650°C.
• a final product realizes a tensile yield strength of at least 1 10 ksi at 650°C.
• a final product realizes a tensile yield strength of at least 125 ksi at 650°C. In yet another embodiment, a final product realizes a tensile yield strength of at least 130 ksi at 650°C. In another embodiment, a final product realizes a tensile yield strength of at least 135 ksi at 650°C. In yet another embodiment, a final product realizes a tensile yield strength of at least 140 ksi or higher at 650°C.
• a final product realizes an ultimate tensile strength of at least 160 ksi at 650°C. In another embodiment, a final product realizes an ultimate tensile strength of at least 165 ksi at 650°C. In yet another embodiment, a final product realizes an ultimate tensile strength of at least 170 ksi or higher at 650°C.
• the new materials may also realize a high specific yield strength of at least 250 ksi*in 3 /lbs at 650°C.
• a final product realizes a specific yield strength of at least 300 ksi*in 3 /lbs at 650°C.
• a final product realizes a specific yield strength of at least 350 ksi*in 3 /lbs at 650°C.
• a final product realizes a specific yield strength of at least 400 ksi*in 3 /lbs at 650°C.
• a final product realizes a specific yield strength of at least 450 ksi*in 3 /lbs at 650°C.
• the new materials may realize an elongation of at least 15.0% at 650°C when measured in accordance with ASTM E21-09.
• a final product realizes an elongation of at least 20.0% at 650°C.
• a final product realizes an elongation of at least 23.0% at 650°C.
• a final product realizes an elongation of at least 25.0% at 650°C.
• a final product realizes an elongation of at least 28.0% at 650°C.
• a final product realizes an elongation of at least 31.0% at 650°C.
• a final product realizes an elongation of at least 33.0% at 650°C. In yet another embodiment, a final product realizes an elongation of at least 36.0% or higher, at 650°C.
• FIG. 1 is a schematic illustration of bcc, fee, and hep unit cells.
• FIG. 2 is a schematic illustration of a B2 unit cell, wherein X and Y are different elements within the unit cell.
• FIG. 5 is an SEM micrograph of Alloy 2 from Example 1 showing a crack.
• FIG. 6 is an SEM micrograph at 500x magnification of Sample A-14 from Example 2; the microstructure shows a predominantly bcc crystalline structure.
• FIG. 7 is an SEM micrograph at 10,000x magnification of Sample A-15 from Example 2; the microstructure shows a mixed fcc+bcc crystalline structure.
• FIG. 8 is an SEM micrograph at 10,000x magnification of Sample A-16 from Example 2; the microstructure shows fee crystalline structures within the bcc crystalline structures.
• FIG. 9a is an SEM micrograph at 500x magnification of Sample A-17 from Example 2; the microstructure shows a predominantly bcc crystalline structure.
• FIG. 9b is a portion of FIG. 9a at 8,000x magnification; fee crystalline structures are located along the boundaries of the bcc crystalline structures.
• FIG. 10 is an SEM micrograph at 5,000x magnification of Sample A-18 from Example 2; the microstructure shows fee crystalline structures located along the boundaries of the bcc crystalline structures, and fee crystalline structures within the bcc crystalline structures, and generally equiaxed crystalline structures (grains).
• FIG. 11 is an SEM micrograph at 5,000x magnification of Sample A-19 from Example 2; the microstructure shows fee crystalline structures located along the boundaries of the bcc crystalline structures, and fee crystalline structures within the bcc crystalline structures, and generally equiaxed crystalline structures (grains).
• FIG. 12a is an SEM micrograph at 500x magnification of Sample A-20 from Example 2; the microstructure shows a mixed fcc+bcc crystalline structure.
• FIG. 13a is an SEM micrograph at 500x magnification of Sample A-21 from Example 2; the microstructure shows a mixed fcc+bcc crystalline structure.
• FIG. 13b is a portion of FIG. 13a at ⁇ , ⁇ magnification.
• FIG. 15 illustrates the matrix vol. % of fee crystalline structures versus the solidification rate for as-solidified Alloy 6 from Example 1.
• **Bal. the balance of the alloy was nickel.
• Near-eutectic solidification pathway reflects a solidification pathway where fee and bec generally form concomitantly (i.e., neither an fcc-first or bcc-first solidification pathway).
• Alloy C is a prior art alloy from Dong, Y., Lu, Y., Kong, j ' ., Zhang, j., & Li, T. (2013 ). "Microstructure and mechanical properties of m i c -component AlCrFeNiMox high-entropy alloys". Journal of Alloys and Compounds, 5? 3, 96-101 .
• Sample A-9 was evaluated at room temperature in the longitudinal direction and in accordance with ASTM E8 (rev. # 8M-16A). Samples A-10 through A-13 were evaluated in the longitudinal direction at 500°C, 600°C, 650°C, and 700°C, and in accordance with ASTM E21-09. Results from the evaluations are given in Table 2D, below.
• Alloy A was subjected to solidification rates varying from about 10°C/s to about l,000,000°C/s. Following solidification, and in some cases following post-solidification thermal treatment, appropriate micrographs were taken of the solidified materials.
• the solidification rate and conditions e.g., thermal history or as-solidified
• figure numbers of the micrographs are illustrated in FIGS. 6- 13b, are given in Table 2E.
• FIGS. 9a and 9b A-17 As-solidified FIGS. 9a and 9b
• FIGS. 12a and 12a Solidified and then FIGS. 12a and 12a
• FIGS. 13a and 13a are identical to FIGS. 13a and 13a.
• FIGS. 6- 13b The microstructures shown in FIGS. 6- 13b were characterized using Electron Backscatter Diffraction ("EBSD") to determine the volumetric percentage of matrix fee and matrix bcc crystalline structures (i.e., phases other than fcc/bcc were not measured or characterized). Elemental compositions within the fee and bcc crystalline structures were determined using Energy Dispersive X-Ray Spectroscopy (“EDS"). Results from the evaluations are given in Table 2F, below. The micrographs given in FIGS. 6-13b (listed above in Table 2E) were used for the microstructural characterization.
• EBSD Electron Backscatter Diffraction
• Alloy 6 from Example 1 was also evaluated, the results of which are given in Table 2G and FIG. 15. As illustrated, Alloy 6 realizes a microstructure having fee as the predominant matrix phase over the solidification range of from 10-l,000,000°C/s. Thus, Alloy 6 realizes an fcc-first solidification pathway.
• Specimens A-14 through A-21 were also subjected to hardness testing in accordance with ASTM E92. Results for the evaluations (given in Vickers Pyramid Numbers (HV)) are given in Table 2H, below. Values are an average of multiple specimens and corresponding uncertainties reflect a normally distributed, 95% confidence interval (i.e., 2- sigma).
• Table 21 Room Temperature and Elevated Temperature Tensile Properties Room Temp. 450°C 650°C

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• 2017
  • 2017-09-29 EP EP17874461.1A patent/EP3519601A2/de not_active Withdrawn
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