# US 11,898,754 B2 · Combustor nozzle, combustor, and gas turbine including the same > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,898,754 B2 - Document ID: US11898754B2 - Status: Granted - Kind: B2 - Application number: 17/704,008 - Filed: 2022-03-25 - Published: 2023-07-06 - Granted: 2024-02-13 - Earliest claimed: 2022-01-06 - Assignees: Doosan Enerbility Co., Ltd. - Applicants: Doosan Enerbility Co., Ltd - Inventors: Ho Keun Kim - Web page: https://patentgrep.com/patent/US11898754B2 ## CPC - F23R 3/286: {having fuel-air premixing devices (F23R3/30 takes precedence)} - F23R 3/12: inducing a vortex - F23R 3/14: by using swirl vanes - F23R 3/16: with devices inside the flame tube or the combustion chamber to influence the air or gas flow - F23R 3/343: {Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion (ignition in gas-turbine plants F02C7/264; pilot flame igniters F23Q9/00)} - F23R 2900/00002: Gas turbine combustors adapted for fuels having low heating value [LHV] - F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16) ## Abstract A combustor nozzle using fuel containing hydrogen, a combustor and gas turbine including the same are provided. The nozzle for a combustor configured to burn fuel containing hydrogen includes a fuel supply duct including a plurality of injection tubes through which air and fuel flow and a fuel passage through which fuel flows, a plurality of swirlers formed on a side surface of each of the plurality of injection tubes to guide air outside the injection tube to be introduced thereinto for swirling, and a plurality of fuel inlet holes formed radially through the injection tube to communicate with the fuel passage and allow fuel to flow through the fuel passage to the injection tube. ## Claims ### Claim 1 A nozzle for a combustor configured to burn fuel containing hydrogen, comprising: a fuel supply duct comprising a plurality of injection tubes through which air and the fuel flow and a fuel passage through which the fuel flows; a plurality of swirlers formed on a side surface of each of the plurality of injection tubes to guide the air outside an injection tube of the plurality of injection tubes to be introduced thereinto for swirling; and a plurality of fuel inlet holes formed radially through the injection tube to communicate with the fuel passage and allow the fuel to flow through the fuel passage to the injection tube, wherein the plurality of swirlers are tube swirlers formed on the side surface of the injection tube to guide the air introduced through the plurality of swirlers in a circumferential direction, wherein each of the plurality of swirlers comprises a swirl guide hole and a swirl guide, the swirl guide hole being formed on the side surface of the injection tube, the swirl guide having one circumferential end and other circumferential end, wherein the one circumferential end of the swirl guide is connected to one side of the swirl guide hole and the other circumferential end of the swirl guide forms an air inlet between the side surface of the injection tube and swirl guide, and the swirl guide has a curved shape from the one circumferential end to the other circumferential end such that the swirl guide becomes gradually farther from a center of the injection tube toward the other circumferential end, and wherein the swirl guide hole is formed through the side surface of the injection tube at an angle of 80 to 180 degrees in the circumferential direction to generate swirl of the air entering the injection tube. ### Claim 2 (depends on 1) The nozzle according to claim 1, wherein the tube swirler is disposed between one end of the injection tube for introducing the air and the fuel inlet holes. ### Claim 3 (depends on 1) The nozzle according to claim 1, wherein the fuel inlet holes are arranged between one end of the injection tube for introducing the air and the tube swirlers. ### Claim 4 (depends on 2) The nozzle according to claim 2, wherein the fuel supply duct further comprises a plurality of diffusion nozzle tubes arranged between the plurality of injection tubes, each of the diffusion nozzle tubes having an end cap formed at an end, the end cap having a plurality of diffusion injection holes formed therein. ### Claim 5 (depends on 4) The nozzle according to claim 4, wherein the plurality of diffusion injection holes of the each of the diffusion nozzle tubes are exclusively formed on an chamfered edge, the plurality of diffusion injection holes being formed in an inclined direction with respect to a longitudinal direction of the injection tube. ### Claim 6 (depends on 5) The nozzle according to claim 5, wherein the plurality of diffusion injection holes are formed perpendicular to the chamfered edge of the end cap. ### Claim 7 (depends on 1) The nozzle according to claim 1, wherein the plurality of swirlers are hole swirlers formed through the side surface of the injection tube to contact with an inner peripheral surface and configured to guide the air introduced through the plurality of swirlers in a circumferential direction. ### Claim 8 (depends on 7) The nozzle according to claim 7, wherein the plurality of fuel inlet holes are formed radially through the side surface of the injection tube to communicate with the fuel passage and allow the fuel to flow through the fuel passage to the injection tube, and the plurality of fuel inlet holes are arranged between one end of the injection tube for introducing the air and the hole swirlers. ### Claim 9 (depends on 1) The nozzle according to claim 1, wherein the curved shape of the swirl guide has a larger curvature radius than the side surface of the injection tube. ### Claim 10 (depends on 1) The nozzle according to claim 1, wherein both longitudinal edges of the swirl guide in a longitudinal direction of the injection tube are integrally connected to both longitudinal ends of the swirl guide hole, respectively. ### Claim 11 A combustor comprising: a nozzle assembly having a plurality of nozzles configured to inject fuel and air; and a duct assembly coupled to one side of the nozzle assembly to burn a mixture of the fuel and the air and transmit combustion gas to a turbine, wherein each of the plurality of nozzles comprises: a fuel supply duct comprising a plurality of injection tubes through which the air and the fuel flow and a fuel passage through which the fuel flows; a plurality of swirlers formed on a side surface of each of the plurality of injection tubes to guide the air outside an injection tube of the plurality of injection tubes to be introduced thereinto for swirling; and a plurality of fuel inlet holes formed radially through the injection tube to communicate with the fuel passage and allow the fuel to flow through the fuel passage to the injection tube, wherein the plurality of swirlers are tube swirlers formed on the side surface of the injection tube to guide the air introduced through the plurality of swirlers in a circumferential direction, wherein each of the plurality of swirlers comprises a swirl guide hole and a swirl guide, the swirl guide hole being formed on the side surface of the injection tube, the swirl guide having one circumferential end and other circumferential end, wherein the one circumferential end of the swirl guide is connected to one side of the swirl guide hole and the other circumferential end of the swirl guide forms an air inlet between the side surface of the injection tube and swirl guide, and the swirl guide has a curved shape from the one circumferential end to the other circumferential end such that the swirl guide becomes gradually farther from a center of the injection tube toward the other circumferential end, and wherein the swirl guide hole is formed through the side surface of the injection tube at an angle of 80 to 180 degrees in the circumferential direction to generate swirl of the air entering the injection tube. ### Claim 12 (depends on 11) The combustor according to claim 11, wherein the tube swirler is disposed between one end of the injection tube for introducing the air and the fuel inlet holes. ### Claim 13 (depends on 12) The combustor according to claim 12, wherein the fuel inlet holes are arranged between one end of the injection tube for introducing the air and the tube swirlers. ### Claim 14 (depends on 12) The combustor according to claim 12, wherein the fuel supply duct further comprises a plurality of diffusion nozzle tubes arranged between the plurality of injection tubes, each of the diffusion nozzle tubes having an end cap formed at an end, the end cap having a plurality of diffusion injection holes formed therein. ### Claim 15 (depends on 14) The combustor according to claim 14, wherein the plurality of diffusion injection holes of the each of the diffusion nozzle tubes are exclusively formed on an chamfered edge, the plurality of diffusion injection holes being formed in an inclined direction with respect to a longitudinal direction of the injection tube. ### Claim 16 (depends on 11) The combustor according to claim 11, wherein the plurality of swirlers are hole swirlers formed through the side surface of the injection tube to contact with an inner peripheral surface and configured to guide the air introduced through the plurality of swirlers in a circumferential direction. ### Claim 17 (depends on 16) The combustor according to claim 16, wherein the plurality of fuel inlet holes are formed radially through the side surface of the injection tube to communicate with the fuel passage and allow the fuel to flow through the fuel passage to the injection tube, and the plurality of fuel inlet holes are arranged between one end of the injection tube for introducing the air and the hole swirlers. ### Claim 18 A gas turbine comprising: a compressor configured to compress air introduced from an outside; a combustor configured to mix fuel with the air compressed by the compressor and combust a mixture of the fuel and the air to produce combustion gas; and a turbine having a plurality of turbine blades rotated by the combustion gas produced by the combustor, wherein the combustor comprises a nozzle assembly having a plurality of nozzles configured to inject fuel and air, and a duct assembly coupled to one side of the nozzle assembly to burn the mixture of the fuel and the air and transmit the combustion gas to the turbine, wherein each of the plurality of nozzles comprises: a fuel supply duct comprising a plurality of injection tubes through which the air and the fuel flow and a fuel passage through which the fuel flows; a plurality of swirlers formed on a side surface of each of the plurality of injection tubes to guide the air outside an injection tube of the plurality of injection tubes to be introduced thereinto for swirling; and a plurality of fuel inlet holes formed radially through the injection tube to communicate with the fuel passage and allow the fuel to flow through the fuel passage to the injection tube, wherein the plurality of swirlers are tube swirlers formed on the side surface of the injection tube to guide the air introduced through the plurality of swirlers in a circumferential direction, wherein each of the plurality of swirlers comprises a swirl guide hole and a swirl guide, the swirl guide hole being formed on the side surface of the injection tube, the swirl guide having one circumferential end and other circumferential end, wherein the one circumferential end of the swirl guide is connected to one side of the swirl guide hole and the other circumferential end of the swirl guide forms an air inlet between the side surface of the injection tube and swirl guide, and the swirl guide has a curved shape from the one circumferential end to the other circumferential end such that the swirl guide becomes gradually farther from a center of the injection tube toward the other circumferential end, and wherein the swirl guide hole is formed through the side surface of the injection tube at an angle of 80 to 180 degrees in the circumferential direction to generate swirl of the air entering the injection tube.