# US 11,906,165 B2 · Gas turbine nozzle having an inner air swirler passage and plural exterior fuel passages > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,906,165 B2 - Document ID: US11906165B2 - Status: Granted - Kind: B2 - Application number: 17/717,739 - Filed: 2022-04-11 - Published: 2023-06-22 - Granted: 2024-02-20 - Earliest claimed: 2021-12-21 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Michael T. Bucaro; Ajoy Patra; Pradeep Naik; Perumallu Vukanti; R Narasimha Chiranthan; Clayton S. Cooper; Michael A. Benjamin; Steven C. Vise; Manampathy G. Giridharan; Krishnakumar Venkatesan - Web page: https://patentgrep.com/patent/US11906165B2 ## CPC - F23R 3/14: by using swirl vanes - F23R 3/28: characterised by the fuel supply (burners F23D) - F23R 3/283: {Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances} - F23R 3/286: {having fuel-air premixing devices (F23R3/30 takes precedence)} - F23R 3/36: Supply of different fuels - 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 An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. The fuel nozzle can include both a primary and secondary fuel passage, and an additional air passage to provide for greater flame control, fuel provision, or local fuel and air mixing prior to combustion. ## Claims ### Claim 1 A turbine engine comprising: a compressor section, combustor section, and turbine section in serial flow arrangement, with the combustor section including a fuel nozzle assembly comprising: an annular swirler; and a fuel nozzle having an outer wall and an outlet, the fuel nozzle defining a longitudinal axis and extending through the swirler, the fuel nozzle comprising: an inner air passage terminating at an aft end, the inner air passage having a first constant cross-sectional area extending forward from the aft end; and a first fuel passage circumscribing the inner air passage, terminating at a first fuel passage outlet, and having a second constant cross-sectional area extending forward from the first fuel passage outlet; and a second fuel passage circumscribing the first fuel passage, terminating at a second fuel passage outlet, and having a third constant cross-sectional area extending forward from the second fuel passage outlet; wherein the first fuel passage and the second fuel passage terminate aft of the inner air passage. ### Claim 2 (depends on 1) The turbine engine of claim 1 further comprising a swirler provided within the inner air passage. ### Claim 3 (depends on 1) The turbine engine of claim 1 wherein the fuel nozzle is a hydrogen fuel nozzle or a hydrogen-based fuel nozzle. ### Claim 4 (depends on 1) The turbine engine of claim 1 wherein the second fuel passage is arranged as a set of discrete passages in annular arrangement about the first fuel passage. ### Claim 5 (depends on 1) The turbine engine of claim 1 wherein the second fuel passage terminates aft of the first fuel passage. ### Claim 6 (depends on 1) The turbine engine of claim 1 wherein the inner air passage is fluidly isolated from the first fuel passage and the second fuel passage upstream of the outlet. ### Claim 7 (depends on 1) The turbine engine of claim 1 wherein the inner air passage includes a rounded profile at the aft end. ### Claim 8 (depends on 7) The turbine engine of claim 7 wherein the first constant cross-sectional area for the inner air passage is positioned forward of the rounded profile. ### Claim 9 (depends on 1) The turbine engine of claim 1 wherein at least a portion of the annular swirler includes a fourth constant cross-sectional area. ### Claim 10 (depends on 9) The turbine engine of claim 9 wherein the fourth constant cross-sectional area of the annular swirler radially overlaps at least one of the inner air passage, the first fuel passage, or the second fuel passage defined perpendicular to the longitudinal axis. ### Claim 11 (depends on 1) The turbine engine of claim 1 wherein the second fuel passage is immediately exterior of the first fuel passage. ### Claim 12 A fuel nozzle assembly comprising: an annular swirler; and a fuel nozzle having an outer wall, defining a longitudinal axis, and extending through the swirler, the fuel nozzle comprising: an inner air passage terminating at an aft end, the inner air passage having a first constant cross-sectional area extending forward from the aft end; a first fuel passage in annular arrangement about the inner air passage terminating at a first fuel passage outlet, and having a second constant cross-sectional area extending forward from the first fuel passage outlet; and a second fuel passage in annular arrangement about the first fuel passage terminating at a second fuel passage outlet, and having a third constant cross-sectional area extending forward from the second fuel passage outlet; wherein the first fuel passage and the second fuel passage terminate aft of the inner air passage. ### Claim 13 (depends on 12) The fuel nozzle assembly of claim 12 wherein the second fuel passage is arranged as a set of discrete passages in annular arrangement about the first fuel passage. ### Claim 14 (depends on 12) The fuel nozzle assembly of claim 12 further comprising a set of openings extending through the outer wall and fluidly coupled to the inner air passage. ### Claim 15 (depends on 14) The fuel nozzle assembly of claim 14 wherein the second fuel passage is arranged as a set of discrete outer passages, and the set of openings extend between the set of discrete outer passages.