# US 2021/0277788 A1 · Turbine nozzle airfoil and/or trailing edge profile > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2021/0277788 A1 - Document ID: US20210277788A1 - Status: Published application - Kind: A1 - Application number: 16/812,510 - Filed: 2020-03-09 - Published: 2021-09-09 - Earliest claimed: 2020-03-09 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: John Franklin Ryman; Andrew Bradford Black; Xiaoyong Fu - Web page: https://patentgrep.com/patent/US20210277788A1 ## CPC - F01D 9/02: Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F05D 2220/30: in turbines - F05D 2240/122: related to the trailing edge of a stator vane - F05D 2240/123: related to the pressure side of a stator vane - F05D 2240/124: related to the suction side of a stator vane - F05D 2240/128: Nozzles - F05D 2250/74: given by a set or table of xyz-coordinates - Y02E 20/16: Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT] - 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 - Y02E: REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A turbine nozzle for a turbine includes: an airfoil having a shape having a nominal profile substantially in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance. The X and Y values are connected by smooth continuing arcs to define airfoil profile sections at each distance Z along at least a portion of the airfoil, and the profile sections at the Z distances are joined smoothly with one another to form the nominal profile. A trailing edge profile for a turbine nozzle is also disclosed. ## Claims ### Claim 1 A turbine nozzle comprising: an airfoil having: a suction side, a pressure side opposing the suction side, a leading edge spanning between the pressure side and the suction side, and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and at least one endwall connected with the airfoil along the suction side, the pressure side, the trailing edge and the leading edge, wherein at least one of a suction side or a pressure side of the airfoil has a shape having a nominal profile in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance, and wherein X and Y values connected by smooth continuing arcs define airfoil profile sections at each distance Z along at least a portion of the airfoil, the airfoil profile sections at the Z distances being joined smoothly with one another to form the nominal profile. ### Claim 2 (depends on 1) The turbine nozzle of claim 1, further comprising a fillet connecting a surface of the at least one endwall to a surface of the airfoil. ### Claim 3 (depends on 1) The turbine nozzle of claim 1, wherein the at least one endwall includes an inner endwall or an outer endwall. ### Claim 4 (depends on 1) The turbine nozzle of claim 1, wherein the turbine nozzle includes a third stage nozzle. ### Claim 5 (depends on 1) The turbine nozzle of claim 1, wherein the shape having the nominal profile in accordance with the at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I includes the airfoil profile sections defined within 10% and 90% of the height of the airfoil. ### Claim 6 (depends on 1) The turbine nozzle of claim 1, wherein the shape having the nominal profile in accordance with the at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I includes the airfoil profile sections defined within 5% and 95% of the height of the airfoil. ### Claim 7 A static nozzle section for a turbine, the static nozzle section comprising: a set of static nozzles, the set of static nozzles including at least one nozzle having: an airfoil having: a suction side, a pressure side opposing the suction side, a leading edge spanning between the pressure side and the suction side, and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and at least one endwall connected with the airfoil along the suction side, the pressure side, the trailing edge and the leading edge, wherein at least one of a suction side or a pressure side of the airfoil has a shape having a nominal profile in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance, and wherein X and Y values connected by smooth continuing arcs define airfoil profile sections at each distance Z along at least a portion of the airfoil, the airfoil profile sections at the Z distances being joined smoothly with one another to form the nominal profile. ### Claim 8 (depends on 7) The static nozzle section of claim 7, further comprising a fillet connecting a surface of the at least one endwall to a surface of the airfoil. ### Claim 9 (depends on 7) The static nozzle section of claim 7, wherein the at least one endwall includes an inner endwall or an outer endwall. ### Claim 10 (depends on 7) The static nozzle section of claim 7, wherein the static nozzle section is a third stage nozzle section. ### Claim 11 (depends on 7) The static nozzle section of claim 7, wherein the shape having the nominal profile in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I includes the airfoil profile sections defined within 10% and 90% of the height of the airfoil. ### Claim 12 (depends on 7) The static nozzle section of claim 7, wherein the shape having the nominal profile in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I includes the airfoil profile sections defined within 5% and 95% of the height of the airfoil. ### Claim 13 A turbine nozzle comprising: an airfoil having: a suction side, a pressure side opposing the suction side, a leading edge spanning between the pressure side and the suction side, and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and at least one endwall connected with the airfoil along the suction side, the pressure side, the trailing edge and the leading edge, wherein at least one of a suction side or a pressure side of the airfoil has a trailing edge shape having a nominal profile in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE II, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance, and wherein X and Y values connected by smooth continuing arcs define trailing edge profile sections at each distance Z along at least a portion of the airfoil, the trailing edge profile sections at the Z distances being joined smoothly with one another to form the nominal profile of the trailing edge shape. ### Claim 14 (depends on 13) The turbine nozzle of claim 13, further comprising a fillet connecting a surface of the at least one endwall to a surface of the airfoil. ### Claim 15 (depends on 13) The turbine nozzle of claim 13, wherein the at least one endwall includes an inner endwall or an outer endwall. ### Claim 16 (depends on 13) The turbine nozzle of claim 13, wherein the turbine nozzle includes a third stage nozzle. ### Claim 17 (depends on 13) The turbine nozzle of claim 13, wherein the trailing edge shape having the nominal profile in accordance with the at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE II includes the trailing edge profile sections defined within 10% and 90% of the height of the airfoil. ### Claim 18 (depends on 13) The turbine nozzle of claim 13, wherein the trailing edge shape having the nominal profile in accordance with the at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE II includes the trailing edge profile sections defined within 5% and 95% of the height of the airfoil.