# US 2016/0258296 A1 · Airfoil for a gas turbine engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2016/0258296 A1 - Document ID: US20160258296A1 - Status: Published application - Kind: A1 - Application number: 14/635,243 - Filed: 2015-03-02 - Published: 2016-09-08 - Earliest claimed: 2015-03-02 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Russell J. Bergman; Jess J. Parkin - Web page: https://patentgrep.com/patent/US20160258296A1 ## 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)} - F01D 5/143: {Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour} - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F05D 2220/32: in gas turbines - F05D 2230/50: Building or constructing in particular ways - F05D 2240/12: Fluid guiding means, e.g. vanes - F05D 2240/121: related to the leading edge of a stator vane - F05D 2240/122: related to the trailing edge of a stator vane - F05D 2240/30: Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor - F05D 2240/303: related to the leading edge of a rotor blade - F05D 2240/304: related to the trailing edge of a rotor blade - F05D 2240/80: Platforms for stationary or moving blades - F05D 2250/71: curved - F05D 2260/941: particularly aimed at mechanical or thermal stress reduction - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A component for a gas turbine engine includes an airfoil that has a first end. A first platform is located at the first end of the airfoil. A compound fillet includes a first fillet portion tangent to the first platform and an airfoil offset. A second fillet portion is tangent to a surface of the airfoil and the first fillet portion. ## Claims ### Claim 1 A component for a gas turbine engine comprising: an airfoil having a first end; a first platform located at the first end of the airfoil; and a compound fillet including a first fillet portion tangent to the first platform and an airfoil offset and a second fillet portion tangent to a surface of the airfoil and the first fillet portion. ### Claim 2 (depends on 1) The component of claim 1, wherein the airfoil offset is a surface extending generally parallel to the airfoil. ### Claim 3 (depends on 1) The component of claim 1, wherein the first fillet portion has a first radius and the second fillet portion has a second radius that is greater than the first radius. ### Claim 4 (depends on 1) The component of claim 1, wherein the first fillet portion includes a radius of approximately 0.125 inches, the second fillet portion includes a radius of approximately 0.700 inches, and the airfoil offset is spaced from the airfoil approximately 0.022 inches. ### Claim 5 (depends on 1) The component of claim 1, further comprising a single fillet located at an intersection of the first end and the first platform and spaced from the compound fillet. ### Claim 6 (depends on 5) The component of claim 5, further comprising a transition fillet located at the intersection of the first end and the first platform axially between the compound fillet and the single fillet. ### Claim 7 (depends on 5) The component of claim 5, wherein the compound fillet extends from approximately 23% to 32% of the axial chord length from the leading edge of the airfoil on a pressure side of the airfoil around the leading edge of the airfoil and to approximately 15% to 25% of the axial chord length from the leading edge on a suction side of the airfoil. ### Claim 8 (depends on 7) The component of claim 7, wherein the compound fillet extends from approximately 28% of the axial chord length from the leading edge on the pressure side around the leading edge of the airfoil and to approximately 20% of the axial chord length from the leading edge on the suction side. ### Claim 9 (depends on 7) The component of claim 7, wherein the single fillet extend from approximately 48% of the axial chord length from the leading edge on the pressure side around the trailing edge of the airfoil to approximately 50% of the axial chord length from the leading edge on the suction side. ### Claim 10 (depends on 1) The component of claim 1, wherein the airfoil is a vane and includes a second platform located at a second end of the airfoil and a second compound fillet located at an intersection of the second end and the second platform. ### Claim 11 (depends on 1) The component of claim 1, wherein the first fillet portion is tangent to a radially outer surface of the first platform. ### Claim 12 A gas turbine engine comprising: an airfoil located in one of a compressor section or a turbine section; a first platform attached to the airfoil; a compound fillet including a first fillet portion tangent to the first platform and an airfoil offset and a second fillet portion tangent to a surface of the airfoil and the first fillet portion. ### Claim 13 (depends on 12) The gas turbine engine of claim 12, wherein the airfoil offset is a surface extending generally parallel to the airfoil. ### Claim 14 (depends on 12) The gas turbine engine of claim 12, wherein the first fillet portion has a first radius and the second fillet portion has a second radius that is greater than the first radius. ### Claim 15 (depends on 12) The gas turbine engine of claim 12, further comprising a single fillet located at an intersection of the airfoil and the first platform and spaced from the compound fillet. ### Claim 16 (depends on 12) The gas turbine engine of claim 12, wherein the airfoil is a vane and includes a second platform attached to the airfoil and a second compound fillet located at an intersection of the airfoil and the second platform. ### Claim 17 A method of forming an airfoil comprising: locating a platform relative to an airfoil; forming a first fillet portion tangent to the platform and an airfoil offset; and forming a second fillet portion tangent to the first fillet portion and a surface of the airfoil. ### Claim 18 (depends on 17) The method of claim 17, wherein the airfoil offset is a surface extending generally parallel to the airfoil. ### Claim 19 (depends on 17) The method of claim 17, wherein the first fillet portion has a first radius and the second fillet portion has a second radius that is greater than the first radius. ### Claim 20 (depends on 17) The method of claim 17, further comprising a single fillet located at an intersection of the airfoil and the first platform and spaced from the compound fillet.