# US 2019/0170356 A1 · Fuel nozzle for a gas turbine with radial swirler and axial swirler and gas turbine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2019/0170356 A1 - Document ID: US20190170356A1 - Status: Published application - Kind: A1 - Application number: 16/302,556 - Filed: 2017-05-30 - Published: 2019-06-06 - Earliest claimed: 2016-05-31 - Assignees: Nuovo Pignone Tecnologie Srl - Applicants: Nuovo Pignone Tecnologie Srl - Inventors: Matteo CERUTTI - Web page: https://patentgrep.com/patent/US20190170356A1 ## CPC - F23R 3/286: {having fuel-air premixing devices (F23R3/30 takes precedence)} - F23D 14/08: with axial outlets at the burner head - F23D 14/62: Mixing devices; Mixing tubes - F23D 14/64: with injectors - F23R 3/14: by using swirl vanes - 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)} - F23C 2900/07001: Air swirling vanes incorporating fuel injectors - F23D 2900/14021: Premixing burners with swirling or vortices creating means for fuel or air - F23D 2900/14701: Swirling means inside the mixing tube or chamber to improve premixing - 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) - F23D: BURNERS - F23C: METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN {A CARRIER GAS OR} AIR (burners F23D) ## Abstract The fuel nozzle for the gas turbine includes a radial swirler and an axial swirler. The radial swirler is arranged to swirl a first flow of a first oxidant-fuel mixture and the axial swirler is arranged to swirl a second flow of a second oxidant-fuel mixture. The first flow may be fed by a central conduit and the second flow may be fed by an annular conduit surrounding the central conduit ## Claims ### Claim 1 A fuel nozzle for a gas turbine comprising a radial swirler and an axial swirler, wherein the radial swirler is arranged to swirl a first flow of a first oxidant-fuel mixture and the axial swirler is arranged to swirl a second flow of a second oxidant-fuel mixture. ### Claim 2 (depends on 1) The fuel nozzle of claim 1, wherein a first recirculation zone is associated to the radial swirler, wherein a second recirculation zone is associated to the axial swirler, and wherein the second recirculation zone is at least partially downstream the first recirculation zone. ### Claim 3 (depends on 1) The fuel nozzle of claim 1, developing in an axial direction from an inlet side to an outlet side, comprising a central conduit developing in the axial direction and an annular conduit developing in the axial direction around the central conduit, wherein the central conduit is arranged to feed the first flow and the annular conduit is arranged to feed the second flow. ### Claim 4 (depends on 3) The fuel nozzle of claim 3, wherein the annular conduit comprises a plurality of swirl vanes arranged to axially swirl the second flow. ### Claim 5 (depends on 4) The fuel nozzle of claim 4, wherein the swirl vanes are hollow and are arranged to feed a first component of the first flow radially to the central conduit. ### Claim 6 (depends on 5) The fuel nozzle of claim 5, wherein first feeding channels are located inside the swirl vanes and arranged to feed the first component, wherein the first feeding channels are tangential so to create radially swirling motion in the central conduit around the axial direction. ### Claim 7 (depends on 6) The fuel nozzle of claim 6, being arranged to inject a second component of the first flow to the central conduit and mix it with the first component thereby obtaining the first flow with radially swirling motion. ### Claim 8 (depends on 3) The fuel nozzle of claim 3, wherein the central conduit has a converging section and a diverging section following the converging section. ### Claim 9 (depends on 4) The fuel nozzle of claim 4, wherein second feeding channels are defined between airfoil portions of adjacent swirl vanes and arranged to feed the second flow. ### Claim 10 (depends on 9) The fuel nozzle of claim 9, wherein the fuel nozzle is arranged to mix a first component and a second component of the second flow in the annular conduit upstream the swirl vanes. ### Claim 11 (depends on 9) The fuel nozzle of claim 9, wherein the swirl vanes comprise first portions being essentially straight and second portions being curved, the second portions being located downstream the first portions and arranged to axially swirl the second flow. ### Claim 12 (depends on 11) The fuel nozzle of claim 11, wherein the first feeding channels are located inside the first portions of the swirl vanes. ### Claim 13 (depends on 3) The fuel nozzle of claim 3, comprising further a pilot injector located in the center of the central conduit. ### Claim 14 (depends on 1) The gas turbine comprising at least one fuel nozzle according to claim 1.