# US 8,770,944 B2 · Turbine airfoil component and method for making > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 8,770,944 B2 - Document ID: US8770944B2 - Status: Granted - Kind: B2 - Application number: 13/077,475 - Filed: 2011-03-31 - Published: 2012-10-04 - Granted: 2014-07-08 - Earliest claimed: 2011-03-31 - Assignees: General Electric Company - Applicants: Akane Suzuki; Stephen Francis Rutkowski; Michale Francis Xavier Gigliotti, Jr. - Inventors: Akane Suzuki; Stephen Francis Rutkowski; Michale Francis Xavier Gigliotti, Jr. - Web page: https://patentgrep.com/patent/US8770944B2 ## CPC - F01D 5/147: {Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18)} - B22D 27/045: {Directionally solidified castings} - B33Y 80/00: Products made by additive manufacturing - F05D 2300/606: Directionally-solidified crystalline structures - F05D 2300/607: Monocrystallinity - F05D 2300/609: Grain size - Y10T 29/49336: Blade making - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - B22D: CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES (shaping of plastics or substances in a plastic state B29C; metallurgical processing, selection of substances to be added to metal C21, C22) - 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 - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION ## Abstract A component such as a turbine bucket or blade, and method for making the component, are presented. One embodiment is an article that comprises an airfoil casting portion comprising a plurality of integral regions, wherein the plurality of integral regions comprises a single-crystalline region and a columnar-grained region. Another embodiment is a method for fabricating an article. The method comprises providing a quantity of molten metal; providing a mold defining an airfoil portion having an axial direction and a transverse direction, wherein the airfoil portion of the mold comprises a single-crystal growth region and a columnar growth region disposed along the transverse direction from the single crystal growth region; introducing the molten metal into the mold; and solidifying the metal such that a solidification front progresses in the axial direction to produce an airfoil casting portion comprising a single-crystalline region and a columnar-grained region. ## Claims ### Claim 1 An article, comprising: an airfoil casting portion comprising: a plurality of integral regions comprising a single-crystalline region and a columnar-grained region; a leading edge section comprising a leading edge of the airfoil casting portion; and a trailing edge section comprising a trailing edge of the airfoil casting portion, wherein the single-crystalline region comprises a single-crystalline material; and the single-crystalline material is disposed at least at the leading edge of the airfoil casting portion or at the trailing edge of the airfoil casting portion. ### Claim 2 (depends on 1) The article of claim 1, wherein the single-crystalline region forms at least 10 percent of a solid cross-sectional area of airfoil casting portion, as measured at a midpoint between a base and a tip of the airfoil. ### Claim 3 (depends on 1) The article of claim 1, wherein the single-crystalline region has a grain orientation of [001] along an axial direction of the airfoil casting portion. ### Claim 4 (depends on 3) The article of claim 3, wherein the single-crystalline region has a grain orientation of [100] or [010] along a transverse direction of the airfoil casting portion. ### Claim 5 (depends on 1) The article of claim 1, wherein the airfoil casting portion comprises a leading edge section and a trailing edge section, and a first single-crystalline region and a second single-crystalline region, wherein the leading edge section comprises the first single-crystalline region and the trailing edge section comprises the second single-crystalline region, wherein the columnar-grained region is interposed between the first and second single-crystalline regions. ### Claim 6 (depends on 1) The article of claim 1, further comprising a platform portion adjoining a base section of the airfoil casting portion. ### Claim 7 (depends on 6) The article of claim 6, wherein the platform portion comprises columnar-grained material. ### Claim 8 (depends on 6) The article of claim 6, wherein the platform portion is integral with the airfoil casting portion. ### Claim 9 (depends on 1) The article of claim 1, further comprising a shroud portion attached to the airfoil casting portion at a tip section of the airfoil casting portion. ### Claim 10 (depends on 9) The article of claim 9, wherein the shroud portion comprises columnar-grained material. ### Claim 11 (depends on 10) The article of claim 10, wherein the shroud portion is integral with the airfoil casting portion. ### Claim 12 (depends on 1) The article of claim 1, wherein the columnar-grained region comprises material having a plurality of grains having a grain orientation of [001] along an axial direction of the airfoil casting portion. ### Claim 13 (depends on 1) The article of claim 1, wherein the columnar-grained region comprises at least 5 grains disposed along a half-height cross-section of the airfoil casting portion. ### Claim 14 (depends on 1) The article of claim 1, wherein the columnar-grained region comprises at least 10 grains disposed along a half-height cross-section of the airfoil casting portion. ### Claim 15 (depends on 1) The article of claim 1, wherein the airfoil casting portion comprises a nickel alloy, a cobalt alloy, or a nickel-iron alloy. ### Claim 16 An article comprising: an airfoil casting portion comprising a base section, a tip section opposite the base section in an axial direction along the airfoil casting portion, a leading edge section comprising a leading edge of the airfoil casting portion, and a trailing edge section comprising a trailing edge of the airfoil casting portion, opposite the leading edge section in a transverse direction along the airfoil casting portion; a shroud portion comprising columnar-grained material, the shroud portion disposed at the tip section and integral with the airfoil casting portion; and a platform portion comprising columnar-grained material, the platform section disposed at the base section and integral with the airfoil casting portion; wherein the airfoil casting portion further comprises a single-crystalline region comprising a single-crystalline material; and a columnar-grained region, the single-crystalline material is disposed at the leading edge of the airfoil casting portion, or at the trailing edge of the airfoil casting portion, or at both the leading edge and the trailing edge of the airfoil casting portion, and at least 10 percent of a solid cross-sectional area of airfoil casting portion, as measured at a midpoint between a base and a tip of the airfoil, comprises the single-crystalline material. ### Claim 17 A method for fabricating an article, the method comprising: providing a quantity of molten metal; providing a mold defining an airfoil portion having an axial direction; a transverse direction; a leading edge section; and a trailing edge section, wherein the airfoil portion of the mold comprises a single-crystal growth region and a columnar growth region disposed along the transverse direction from the single crystal growth region; introducing the molten metal into the mold; and solidifying the metal such that a solidification front progresses in the axial direction to produce an airfoil casting portion comprising a single-crystalline region comprising a single-crystalline material; and a columnar-grained region, wherein the single-crystalline material is disposed at least at a leading edge of the airfoil casting portion, at a trailing edge of the airfoil casting portion, or both the leading edge and trailing edge of the airfoil casting portion. ### Claim 18 (depends on 17) The method of claim 17, wherein the mold further comprises a preliminary solidification region wherein the single-crystal region and the columnar growth region are separated from one another, and a junction region wherein the single-crystal region and the columnar growth region are integral; wherein solidifying further comprises controlling the solidification front within the junction region to be substantially perpendicular to the axial direction. ### Claim 19 (depends on 17) The method of claim 17, wherein solidifying comprises controlling grain orientation of solidified metal to be [001] along the axial direction within the single-crystal growth region, the columnar growth region, or both of these regions. ### Claim 20 (depends on 17) The method of claim 17, wherein solidifying further comprises solidifying the metal to produce an airfoil casting portion having a single-crystalline region that forms at least 10 percent of a solid cross-sectional area of airfoil casting portion, as measured at a midpoint between a base and a tip of the airfoil. ### Claim 21 (depends on 17) The method of claim 17, wherein the provided mold further defines a platform portion disposed at a base section of the airfoil portion, a shroud portion disposed at a tip section of the airfoil portion, or both the platform portion and the shroud portion, and wherein solidifying further comprises solidifying columnar-grained material within the platform portion, the shroud portion, or within both of these portions. ### Claim 22 (depends on 17) The method of claim 17, wherein solidifying comprises transferring heat from the molten metal via conduction through a liquid metal cooling medium.