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A fuel nozzle for a turbine engine has a central body member with a pilot, a surrounding barrel housing, a mixing duct and an air inlet duct. The fuel nozzle additionally has a main fuel injection device located between the air inlet duct and the mixing duct. The main fuel injection device is config

A fuel nozzle for a turbine engine has a central body member with a pilot, a surrounding barrel housing, a mixing duct and an air inlet duct. The fuel nozzle additionally has a main fuel injection device located between the air inlet duct and the mixing duct. The main fuel injection device is configured to introduce a flow of fuel into the barrel member to create a fuel/air mixture which is then premixed with a swirler. The fuel/air mixture then further mixes in the mixing duct and exits the nozzle into a combustor for combustion. The geometry of the fuel nozzle ensures that pressure waves from the combustor do not create a time varying fuel to air equivalence ratio in the flow through the nozzle that achieves a resonance with the pressure waves.

대표청구항 ▼

1. A fuel nozzle for a turbine engine having a compressor section and a combustion chamber, the fuel nozzle comprising: a central body comprising a pilot fuel injector injecting a pilot stream of fuel through a tip end of central body and into the combustion chamber;an air inlet duct and a mixing du

1. A fuel nozzle for a turbine engine having a compressor section and a combustion chamber, the fuel nozzle comprising: a central body comprising a pilot fuel injector injecting a pilot stream of fuel through a tip end of central body and into the combustion chamber;an air inlet duct and a mixing duct positioned about the central body helping to define an annular flow passageway between the air inlet duct and the mixing duct and the central body that in use communicates a flow of compressed air from the compressor section through the fuel nozzle out through the exit of the mixing duct and into the combustion chamber;a swirler positioned between the air inlet duct and the mixing duct that swirls the compressed air passing in the annular flow passageway between the air inlet duct and the mixing duct;a plurality of fuel jets to inject fuel into the compressed air passing though the annular flow passageway; anda plurality of circumferentially spaced air jets formed through the fuel nozzle between the swirler and the exit of the mixing duct, the air jets communicating additional compressed air from the compressor section into the annular flow passageway. 2. A fuel nozzle according to claim 1 wherein the plurality of fuel jets are formed in the swirler. 3. A fuel nozzle according to claim 2 wherein the plurality of fuel jets comprises a plurality of liquid fuel jets and a plurality of gaseous fuel jets. 4. A fuel nozzle according to claim 1 wherein the swirler comprises a plurality of vanes that extend outward from the central body and into the annular flow passageway. 5. A fuel nozzle according to claim 1 wherein the fuel jets comprises a restriction to the fuel exiting therefrom. 6. A fuel nozzle according to claim 1 wherein the air inlet duct further comprises a flow restrictor defining a central opening through which the compressed air entering air inlet duct passes, and the central opening and the air jets are sized so that a greater portion of the compressed air from the compressor section is passed through the air inlet duct than through the air jets. 7. A fuel nozzle according to claim 6 wherein the air jets direct compressed air radially inward toward the central body. 8. A fuel nozzle according to claim 7 wherein the plurality of fuel jets are formed in the swirler. 9. A fuel nozzle according to claim 8 wherein the plurality of fuel jets comprises both a plurality of liquid fuel jets and a plurality of gaseous fuel jets. 10. A fuel nozzle according to claim 1 wherein each of the plurality of circumferentially spaced air jets are positioned at the same axial position along the fuel nozzle. 11. A fuel nozzle for a turbine engine having a compressor section and a combustion chamber, the fuel nozzle comprising: a central body comprising a pilot fuel injector injecting a pilot stream of fuel through a tip end of central body and into the combustion chamber;an air inlet duct and a mixing duct positioned about the central body helping to define an annular flow passageway between the air inlet duct and the mixing duct and the central body that in use communicates a flow of compressed air from the compressor section through the fuel nozzle out through an exit of the mixing duct and into the combustion chamber;a swirler positioned between the air inlet duct and the mixing duct that swirls the compressed air passing in the annular flow passageway between the air inlet duct and the mixing duct;a plurality of fuel jets to inject fuel into the compressed air passing though the annular flow passageway; anda plurality of circumferentially spaced air jets formed through the fuel nozzle between the swirler and the exit of the mixing duct, the air jets communicating additional compressed air from the compressor section into the annular flow passageway;wherein the air inlet duct and the plurality of fuel jets are configured such that a time varying change in the flow rate of compressed air flowing through the air inlet duct and a time varying change in the flow rate of fuel flowing through the plurality of fuel jets result in a substantially constant fuel/air ratio in a premixed fuel flow and air flow exiting the mixing duct. 12. A fuel nozzle according to claim 11 wherein the plurality of fuel jets are formed in the swirler. 13. A fuel nozzle according to claim 12 wherein the plurality of fuel jets comprises a plurality of liquid fuel jets and a plurality of gaseous fuel jets. 14. A fuel nozzle according to claim 11 wherein the air inlet duct further comprises a flow restrictor defining a central opening through which the compressed air entering air inlet duct passes, and the central opening and the air jets are sized so that a greater portion of the compressed air from the compressor section is passed through the air inlet duct than through the air jets. 15. A fuel nozzle according to claim 14 wherein the air jets direct compressed air radially inward toward the central body. 16. A fuel nozzle according to claim 15 wherein the plurality of fuel jets are formed in the swirler. 17. A fuel nozzle for a turbine engine having a compressor section and a combustion chamber, the fuel nozzle comprising: a central body comprising a pilot fuel injector injecting a pilot stream of fuel through a tip end of central body and into the combustion chamber;an air inlet duct and a mixing duct positioned about the central body helping to define an annular flow passageway between the air inlet duct and the mixing duct and the central body that in use communicates a flow of compressed air from the compressor section through the fuel nozzle out through an exit of the mixing duct and into the combustion chamber;a swirler positioned between the air inlet duct and the mixing duct that swirls the compressed air passing in the annular flow passageway between the air inlet duct and the mixing duct;a plurality of fuel jets to inject fuel into the compressed air passing though the annular flow passageway; anda plurality of circumferentially spaced air jets formed through the fuel nozzle between the swirler and the exit of the mixing duct, the air jets communicating additional compressed air from the compressor section into the annular flow passageway;wherein the air inlet duct is spaced from the air jets such that a time varying flow rate of compressed air entering the fuel nozzle through the air inlet duct is out of phase with a time varying flow rate of compressed air entering through the air jets. 18. A fuel nozzle according to claim 17 wherein each of the plurality of circumferentially spaced air jets are positioned at the same axial position along the fuel nozzle. 19. A fuel nozzle according to claim 17 wherein each of the plurality of fuel jets are formed at substantially the same axial position along the fuel nozzle. 20. A fuel nozzle according to claim 19 wherein the plurality of fuel jets are formed in the swirler.