# US 12,007,116 B2 · Dual pressure fuel nozzles > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,007,116 B2 - Document ID: US12007116B2 - Status: Granted - Kind: B2 - Application number: 17/179,829 - Filed: 2021-02-19 - Published: 2022-08-25 - Granted: 2024-06-11 - Earliest claimed: 2021-02-19 - Assignees: Pratt & Whitney Canada Corp. - Applicants: Pratt & Whitney Canada Corp. - Inventors: Oleg Morenko; Sandeep Singh Dhalla - Web page: https://patentgrep.com/patent/US12007116B2 ## CPC - F23C 1/08: liquid and gaseous fuel - F23R 3/286: {having fuel-air premixing devices (F23R3/30 takes precedence)} - F23D 11/107: {at least one of both being subjected to a swirling motion} - F23D 14/58: characterised by the shape or arrangement of the outlet or outlets from the nozzle, e.g. of annular configuration - F23R 3/12: inducing a vortex - F23R 3/36: Supply of different fuels - F02C 9/40: specially adapted to the use of a special fuel or a plurality of fuels - F23C 2900/9901: Combustion process using hydrogen, hydrogen peroxide water or brown gas as fuel - F23D 14/24: at least one of the fluids being submitted to a swirling motion - F23R 2900/00002: Gas turbine combustors adapted for fuels having low heating value [LHV] - F23C: METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN {A CARRIER GAS OR} AIR (burners F23D) - 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 - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) ## Abstract A fuel supply system for a gas turbine engine comprises a housing having a housing interior chamber and a fuel swirler disposed inside the housing interior chamber. The fuel swirler has an upstream end and downstream end relative to a fuel flow direction along a fuel nozzle longitudinal axis. The fuel swirler has a first axial fuel passage along the longitudinal axis in fluid communication with a first fuel supply and terminating at a first fuel outlet at the downstream end, a second axial fuel passage along the longitudinal axis in fluid communication with a second fuel supply and terminating at a second fuel outlet at the downstream end, and a plurality of compressed air outlets at the downstream end. The first fuel outlet is positioned on an outermost surface of the fuel swirler and leads directly to a mixing site downstream of the fuel swirler. ## Claims ### Claim 1 A fuel supply system for a gas turbine engine, comprising: a fuel nozzle including: a housing having a housing interior chamber; and a fuel swirler disposed inside the housing interior chamber, the fuel swirler having a fuel swirler upstream end and a fuel swirler downstream end relative to a fuel flow direction along a longitudinal axis of the fuel nozzle, a first axial fuel passage along the longitudinal axis in fluid communication with a first fuel supply and terminating at a first fuel outlet at the fuel swirler downstream end, a second axial fuel passage along the longitudinal axis in fluid communication with a second fuel supply and terminating at a second fuel outlet at the fuel swirler downstream end, and a plurality of compressed air outlets at the fuel swirler downstream end, the fuel swirler further including an end face at the fuel swirler downstream end, the end face disposed at a furthest downstream axial position of the fuel swirler relative to the longitudinal axis; the fuel swirler further having a swirler core; wherein the first fuel outlet is positioned on the end face, the end face bordering a mixing site downstream of and outside of the fuel swirler, the first fuel outlet leading directly to the mixing site; wherein the first axial fuel passage and the second axial fuel passage are formed on opposite sides of a same annular wall of the fuel swirler, a first radial surface of the same annular wall partially defining the first axial fuel passage and a second radial surface of the same annular wall partially defining the second axial fuel passage; and wherein the plurality of compressed air outlets include a plurality of end face compressed air outlets extending through the end face and circumferentially disposed relative to the longitudinal axis about the end face and a swirler core compressed air outlet at the fuel swirler downstream end. ### Claim 2 (depends on 1) The fuel supply system as defined in claim 1, wherein the fuel swirler includes: an outer fuel swirler disposed inside the housing interior chamber, the outer fuel swirler having an outer fuel swirler interior chamber with an outer fuel swirler upstream end and a frustoconically-shaped outer fuel swirler downstream end, the frustoconically-shaped outer fuel swirler downstream end having the end face; and an inner fuel swirler disposed inside the outer fuel swirler interior chamber, the inner fuel swirler having an inner fuel swirler interior chamber with an inner fuel swirler upstream end and a frustoconically-shaped inner fuel swirler downstream end; wherein the swirler core is disposed inside the inner fuel swirler interior chamber, the swirler core having an internal bore extending between a swirler core upstream end and a swirler core downstream end. ### Claim 3 (depends on 2) The fuel supply system as defined in claim 2, wherein the first axial fuel passage is radially formed relative to the longitudinal axis between the outer fuel swirler and the inner fuel swirler, and the second axial fuel passage is radially formed relative to the longitudinal axis between the swirler core and the inner fuel swirler. ### Claim 4 (depends on 1) The fuel supply system as defined in claim 1, wherein the plurality of end face compressed air outlets include an outer row of circumferentially-arranged end face compressed air outlets and an inner row of circumferentially-arranged end face compressed air outlets, the inner row of circumferentially-arranged end face compressed air outlets disposed radially inward of the outer row of circumferentially-arranged end face compressed air outlets relative to the longitudinal axis. ### Claim 5 (depends on 1) The fuel supply system as defined in claim 1, wherein the housing is a fuel stem for the gas turbine engine. ### Claim 6 (depends on 3) The fuel supply system as defined in claim 3, wherein the swirler core includes a shank portion extending from the swirler core upstream end to the swirler core downstream end, the shank portion having one or more annular protrusions protruding radially outward relative to the longitudinal axis into the second axial fuel passage and having a plurality of fuel-directing apertures. ### Claim 7 (depends on 6) The fuel supply system as defined in claim 6, wherein the plurality of fuel-directing apertures are angled relative to the longitudinal axis. ### Claim 8 (depends on 2) The fuel supply system as defined in claim 2, wherein the swirler core includes a shoulder portion at the swirler core upstream end, the shoulder portion engageable with an interior wall of the inner fuel swirler interior chamber. ### Claim 9 (depends on 1) The fuel supply system as defined in claim 1, wherein the first fuel supply is a gaseous fuel supply and the second fuel supply is a liquid fuel supply. ### Claim 10 (depends on 1) The fuel supply system as defined in claim 1, wherein the first axial fuel passage is disposed radially outward of the second axial fuel passage relative to the longitudinal axis. ### Claim 11 (depends on 1) The fuel supply system as defined in claim 1, wherein the first fuel outlet includes a plurality of circumferentially-arranged outlet holes disposed about the longitudinal axis. ### Claim 12 A fuel supply system for a gas turbine engine, comprising: a fuel nozzle having: a fuel swirler disposed inside a housing interior chamber, the fuel swirler having a fuel swirler upstream end and a fuel swirler downstream end relative to a fuel flow direction along a central longitudinal axis of the fuel nozzle, the fuel swirler including an end face at the fuel swirler downstream end, the end face disposed at a furthest downstream axial position of the fuel swirler relative to the central longitudinal axis; a first axial fuel passage radially formed between an inner fuel swirler and an outer fuel swirler relative to the central longitudinal axis, the first axial fuel passage in fluid communication with a hydrogen fuel supply in a housing having the housing interior chamber and terminating at a first fuel outlet at the fuel swirler downstream end, the first fuel outlet positioned on the end face, the end face bordering a mixing site downstream of and outside of the fuel swirler relative to the central longitudinal axis, and delivering hydrogen fuel directly to the mixing site; a second axial fuel passage radially formed between a swirler core and the inner fuel swirler relative to the central longitudinal axis, the second axial fuel passage in fluid communication with a liquid fuel supply in the housing and terminating at a second fuel outlet at the fuel swirler downstream end; wherein the first axial fuel passage and the second axial fuel passage are formed on opposite sides of an annular wall forming the inner fuel swirler, a first radial surface of the annular wall partially defining the first axial fuel passage and a second radial surface of the annular wall partially defining the second axial fuel passage; a first supply of compressed air through a plurality of end face compressed air outlets extending through the end face and circumferentially disposed relative to the central longitudinal axis about the end face; and a second supply of compressed air through an internal bore of the swirler core terminating at a swirler core compressed air outlet at the fuel swirler downstream end. ### Claim 13 (depends on 12) The fuel supply system as defined in claim 12, wherein the plurality of end face compressed air outlets include an outer row of circumferentially-arranged end face compressed air outlets and an inner row of circumferentially-arranged end face compressed air outlets, the inner row of circumferentially-arranged end face compressed air outlets disposed radially inward of the outer row of circumferentially-arranged end face compressed air outlets relative to the central longitudinal axis. ### Claim 14 (depends on 12) The fuel supply system as defined in claim 12, wherein the outer row of circumferentially-arranged end face compressed air outlets are angled to direct compressed air circumferentially. ### Claim 15 (depends on 12) The fuel supply system as defined in claim 12, wherein the second axial fuel passage includes a plurality of fuel-directing apertures through one or more annular protrusions extending radially outward relative to the central longitudinal axis from a swirler core shank portion of the swirler core. ### Claim 16 (depends on 12) The fuel supply system as defined in claim 12, wherein the housing is a fuel stem for the gas turbine engine. ### Claim 17 (depends on 12) The fuel supply system as defined in claim 12, wherein the liquid fuel supply is a liquid kerosene fuel supply. ### Claim 18 (depends on 12) The fuel supply system as defined in claim 12, wherein the first axial fuel passage is disposed radially outward of the second axial fuel passage relative to the central longitudinal axis. ### Claim 19 (depends on 12) The fuel supply system as defined in claim 12, wherein the first axial fuel passage is operable to thermally insulate the second axial fuel passage as the liquid fuel supply is powered and the hydrogen fuel supply is inactive.