[특허]Gas turbine and fuel injector for the same

Solar Turbines Incorporated

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특허 상세정보

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Gas turbine and fuel injector for the same

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F23R-003/28 F23R-003/36 F23D-011/10 F23D-014/22 F02C-003/30
출원번호	US-0326798 (2011-12-15)
등록번호	US-9182124 (2015-11-10)
발명자 / 주소	Oskam, Gareth W.
출원인 / 주소	Solar Turbines Incorporated
대리인 / 주소	Finnegan, Henderson, Farabow, Garrett & Dunner, LLP
인용정보	피인용 횟수 : 0 인용 특허 : 147

초록
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A fuel injector for a gas turbine engine may include an injector housing having a central cavity configured to be fluidly coupled to a combustor of the turbine engine. The central cavity may also be configured to direct a first fuel into the combustor substantially unmixed with air. The fuel injector may also include an annular air discharge outlet circumferentially disposed about the downstream end of the central cavity. The air discharge outlet may be configured to discharge compressed air into the combustor circumferentially about the first fuel from the central cavity. The fuel injector may also include an annular fuel discharge outlet circumferentially disposed about the air discharge outlet at the downstream end. The fuel discharge outlet may be configured to discharge a second fuel into the combustor circumferentially about the compressed air from the air discharge outlet.

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청구항
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1. A fuel injector for a gas turbine engine comprising: an injector housing including a central cavity extending along a longitudinal axis from an upstream end to a downstream end, the downstream end of the central cavity configured to be fluidly coupled to a combustor of the turbine engine, the central cavity also configured to direct a first fuel into the combustor substantially unmixed with air;an annular air discharge outlet circumferentially disposed about the downstream end of the central cavity, the air discharge outlet being configured to discharge compressed air into the combustor circumferentially about the first fuel from the central cavity;an annular fuel discharge outlet circumferentially disposed about the air discharge outlet at the downstream end, the fuel discharge outlet being configured to discharge a second fuel into the combustor circumferentially about the compressed air from the air discharge outlet;an outer annular passageway extending from the upstream end of the injector housing to the fuel discharge outlet at the downstream end, wherein the outer annular passageway has a first outer diameter at the upstream end;an annular chamber extending around the upstream end of the injector housing and fluidly coupled to the outer annular passageway at the upstream end, wherein the annular chamber has a second outer diameter greater than the first outer diameter of the outer annular passageway; anda plurality of inlet ports radially coupled to an outer wall of the annular chamber, wherein a first inlet port of the plurality of inlet ports is configured to direct the second fuel radially inward into the annular chamber. 2. The fuel injector of claim 1, further including a fuel nozzle at the upstream end of the central cavity, the fuel nozzle being configured to discharge the first fuel into the central cavity. 3. The fuel injector of claim 1, further including an inner annular passageway extending from an annular inlet at the upstream end of the injector housing to the air discharge outlet at the downstream end, the inner annular passageway being disposed symmetrically about the central cavity. 4. The fuel injector of claim 3, wherein at least a portion of the inner annular passageway converges towards the longitudinal axis. 5. The fuel injector of claim 3, wherein the outer annular passageway is disposed symmetrically about the central cavity and radially outwards from the inner annular passageway. 6. The fuel injector of claim 5, wherein at least a portion of the outer annular passageway converges towards the longitudinal axis. 7. The fuel injector of claim 1, wherein the second fuel is a liquid fuel and the plurality of inlet ports includes a second inlet port configured to direct a gaseous fuel into the outer annular passageway. 8. The fuel injector of claim 7, wherein the plurality of inlet ports includes a third inlet port configured to direct steam into the outer annular passageway. 9. The fuel injector of claim 1, wherein the central cavity is a convergent passageway. 10. The fuel injector of claim 1, wherein the central cavity includes only a single inlet, the single inlet being configured to discharge the first fuel into the central cavity. 11. A method of operating a gas turbine engine comprising: directing a gaseous fuel into a combustor of the gas turbine engine through a central cavity of a fuel injector substantially unmixed with compressed air, the central cavity extending longitudinally from an upstream end to a downstream end longitudinally fluidly coupled to the combustor;directing compressed air into the combustor as a shroud around the gaseous fuel;directing a second fuel into the combustor circumferentially about the compressed air, wherein directing the second fuel includes increasing an angular velocity of the second fuel in the fuel injector;providing an outer annular passageway extending from an upstream end to a fuel discharge outlet, wherein the outer annular passageway has a first outer diameter at the upstream end;providing an annular chamber fluidly coupled to the outer annular passageway at the upstream end of the outer annular passageway, wherein the annular chamber has a second outer diameter greater than the first outer diameter of the outer annular passageway; andproviding a plurality of inlet ports radially coupled to an outer wall of the annular chamber, wherein a first inlet port of the plurality of inlet ports directs the second fuel radially inward into the annular chamber. 12. The method of claim 11, further including increasing a linear velocity of the second fuel in the fuel injector prior to directing the second fuel into the combustor, wherein the second fuel is a liquid fuel. 13. The method of claim 11, wherein directing the gaseous fuel, directing the compressed air, and directing the second fuel occurs at a same time. 14. The method of claim 11, further including directing steam into the combustor circumferentially around the compressed air. 15. A gas turbine engine, comprising: a compressor system;a turbine system;a combustor system including a combustor; anda fuel injector extending from an upstream end to a downstream end, the fuel injector being coupled to the combustor at the downstream end, the fuel injector including:a central cavity extending from the upstream end to the downstream end along a longitudinal axis, the central cavity being configured to direct a gaseous fuel into the combustor substantially unmixed with compressed air;an annular air discharge outlet circumferentially disposed about the central cavity, the annular air discharge outlet being configured to direct compressed air into the combustor circumferentially around the gaseous fuel entering the combustor from the central cavity;an outer passageway circumferentially disposed about the central cavity, the outer passageway being configured to selectively direct a gaseous fuel and a liquid fuel into the combustor circumferentially around the compressed air from the air discharge outlet, wherein the outer passageway has a first outer diameter at the upstream end; andan annular chamber, fluidly coupled to the outer passageway, that extends around the fuel injector at the upstream end of the fuel injector, wherein the annular chamber has a second outer diameter greater than the first outer diameter of the outer passageway;a plurality of inlet ports radially coupled to an outer wall of the annular chamber, wherein a first inlet port of the plurality of inlet ports is configured to direct the gaseous or liquid fuel radially inward into the annular chamber. 16. The gas turbine of claim 15, wherein the first inlet port is configured to direct the gaseous fuel radially inward into the annular chamber, a second inlet port of the plurality of inlet ports is configured to direct the liquid fuel radially inward into the annular chamber, and a third inlet port of the plurality of inlet ports is configured to direct steam radially inward into the annular chamber. 17. The gas turbine of claim 15, further including an air swirler circumferentially disposed about the fuel injector. 18. The gas turbine engine of claim 17, wherein the inner passageway and the outer passageway include portions that converge towards the longitudinal axis.

인용문헌 (147)

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Gas turbine and fuel injector for the same

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Gas turbine and fuel injector for the same

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