# US 2018/0023403 A1 · Turbine vane with coupon having corrugated surface(s) > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2018/0023403 A1 - Document ID: US20180023403A1 - Status: Published application - Kind: A1 - Application number: 15/217,062 - Filed: 2016-07-22 - Published: 2018-01-25 - Earliest claimed: 2016-07-22 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Jeffrey Clarence Jones; Adam John Fredmonski - Web page: https://patentgrep.com/patent/US20180023403A1 ## CPC - F01D 5/187: {Convection cooling} - F01D 5/141: {Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147)} - F01D 5/145: {Means for influencing boundary layers or secondary circulations (for compressors F04D29/68)} - 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 5/186: {Film cooling (F01D5/187 takes precedence)} - F01D 9/065: {Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26)} - 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 2240/303: related to the leading edge of a rotor blade - F05D 2240/304: related to the trailing edge of a rotor blade - F05D 2250/181: ridged - F05D 2250/182: crenellated, notched - F05D 2250/183: zigzag - F05D 2250/184: sinusoidal - F05D 2250/61: corrugated - F05D 2260/204: by the use of microcircuits - F05D 2260/22141: using fins or ribs - 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 turbine vane includes an airfoil body having a leading edge, a trailing edge and a smooth outer surface. A cutout is included within at least one of the leading edge and the trailing edge, the cutout removing a predetermined area of the airfoil body. A coupon is coupled in the cutout to replace the predetermined area of the airfoil body. The coupon includes a first corrugated surface on at least a portion of an outer surface thereof. The coupon allows for the addition of advantageous wake mixing and cooling efficiencies to preexisting vanes. ## Claims ### Claim 1 A turbine vane comprising: an airfoil body having a leading edge, a trailing edge and a smooth outer surface; a cutout within at least one of the leading edge and the trailing edge, the cutout removing a predetermined area of the airfoil body; and a coupon coupled in the cutout to replace the predetermined area of the airfoil body, the coupon including a first corrugated surface on at least a portion of an outer surface thereof. ### Claim 2 (depends on 1) The turbine vane of claim 1, wherein the airfoil body includes an airfoil coolant flow passage therein, the cutout exposing the airfoil coolant flow passage, and wherein the coupon includes a first coupon coolant flow passage configured to fluidly mate with the airfoil coolant flow passage. ### Claim 3 (depends on 2) The turbine vane of claim 2, wherein the coupon includes a plurality of flow passages extending from an interior surface thereof to the outer surface thereof. ### Claim 4 (depends on 2) The turbine vane of claim 2, wherein the cutout is positioned in the trailing edge, and the coupon includes a pin bank within the first coupon coolant flow passage. ### Claim 5 (depends on 2) The turbine vane of claim 2, wherein the airfoil body includes an airfoil radially extending chamber therein and an airfoil rib partitioning the airfoil radially extending chamber to form the airfoil coolant flow passage therein, the cutout exposing the airfoil rib and the airfoil coolant flow passage, and wherein the coupon includes a coupon radially extending chamber therein and a first coupon rib partitioning the coupon radially extending chamber to form the first coupon coolant flow passage. ### Claim 6 (depends on 5) The turbine vane of claim 5, wherein the coupon includes at least one second coupon rib partitioning the coupon radially extending chamber into at least one second coupon coolant flow passage, the at least one second coupon flow passage having a different shape than the first coupon coolant flow passage. ### Claim 7 (depends on 6) The turbine vane of claim 6, wherein the coupon further includes a pin bank within at least one second coupon coolant flow passage. ### Claim 8 (depends on 1) The turbine vane of claim 1, wherein the coupon includes a second corrugated surface on at least a portion of an internal surface thereof, the second corrugated surface parallel to the first corrugated surface. ### Claim 9 (depends on 1) The turbine vane of claim 1, wherein the cutout is positioned in the trailing edge, and the coupon includes a crenulated trailing edge meshing with the first corrugated surface. ### Claim 10 (depends on 9) The turbine vane of claim 9, wherein the coupon includes a first coupon coolant flow passage and a plurality of coolant flow passages passing from the first coupon coolant flow passage through the trailing edge of the coupon. ### Claim 11 (depends on 1) The turbine vane of claim 1, wherein the coupon includes a coupon radially extending chamber therein, and an impingement cooling structure positioned within the coupon radially extending chamber. ### Claim 12 A coupon for replacing a cutout of a predetermined area in an airfoil body of a turbine vane, the airfoil body having a leading edge, a trailing edge and a smooth outer surface, the cutout within at least one of the leading edge and the trailing edge of the airfoil body, the coupon comprising: a first corrugated surface on at least a portion of an outer surface thereof. ### Claim 13 (depends on 12) The coupon of claim 12, further comprising a first coupon coolant flow passage configured to fluidly mate with an airfoil coolant flow passage in the airfoil body exposed by the cutout. ### Claim 14 (depends on 13) The coupon of claim 13, wherein the coupon includes a pin bank within the first coupon coolant flow passage. ### Claim 15 (depends on 13) The coupon of claim 13, wherein the coupon includes: a coupon radially extending chamber therein and a first coupon rib partitioning the coupon radially extending chamber to form the first coupon coolant flow passage, and at least one second coupon rib partitioning the coupon radially extending chamber into at least one second coupon coolant flow passage, the at least one second coupon flow passage having a different shape than the first coupon coolant flow passage. ### Claim 16 (depends on 15) The coupon of claim 15, wherein the coupon further includes a pin bank within at least one second coupon coolant flow passage. ### Claim 17 (depends on 12) The coupon of claim 12, wherein the coupon includes a plurality of flow passages extending from an interior surface thereof to the outer surface thereof. ### Claim 18 (depends on 12) The coupon of claim 12, wherein the coupon includes a second corrugated surface on at least a portion of an internal surface thereof, the second corrugated surface parallel to the first corrugated surface. ### Claim 19 (depends on 12) The coupon of claim 12, wherein the coupon includes: a crenulated trailing edge meshing with the first corrugated surface; a first coupon coolant flow passage therein; and a plurality of coolant flow passages passing from the first coupon coolant flow passage through the crenulated trailing edge of the coupon. ### Claim 20 A non-transitory computer readable storage medium storing code representative of a coupon for replacing a cutout of a predetermined area in one of a leading edge or a trailing edge in an airfoil body of a turbine vane, the coupon physically generated upon execution of the code by a computerized additive manufacturing system, the code comprising: code representing the coupon, the coupon including: a first corrugated surface on at least a portion of an outer surface thereof.