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 injecto
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.
대표청구항▼
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 cen
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.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (147)
Graves,Charles B.; DeSalle,Stephanie, Air assist fuel injector for a combustor.
Angel Paul R. ; Caldwell James M. ; Joshi Narendra D. ; Marakovits Steven ; Foresman Kelley A. ; Goebel Steven G. ; Warren ; Jr. Richard E., Air fuel mixer for gas turbine combustor.
Joshi Narendra D. (Cincinnati OH) Epstein Michael J. (West Chester OH), Air fuel mixer for gas turbine combustor having slots at downstream end of mixing duct.
Halvorsen Robert M. (Birmingham MI) Bradley Jerome R. (Sterling Heights MI) Long Gregory F. (Canton MI), Airblast fuel injector tip with integral cantilever spring fuel metering valve and method for reducing vapor lock from h.
Horner Michael W. (West Chester OH) Ekstedt Edward E. (Cincinnati OH) Campbell Thomas C. (Cincinnati OH) Badeer Gilbert H. (Loveland OH), Apparatus and method for atomizing water in a combustor dome assembly.
Burrus David L. ; Johnson Arthur W. ; Mongia Hukam C., Apparatus and method for rich-quench-lean (RQL) concept in a gas turbine engine combustor having trapped vortex cavity.
Beebe Kenneth W. ; Hung Stephen L. ; Cutrone Martin B., Catalytic combustor with lean direct injection of gas fuel for low emissions combustion and methods of operation.
Jean-Herve Le Gal FR; Patrick Flament FR; Gerard Martin FR; Guy Grienche FR; Gerard Schott FR, Combustion chamber of a gas turbine working on liquid fuel.
McMasters, Marie Ann; Cooper, James Neil; Vermeersch, Michael Louis; Thomsen, Duane Douglas; Danis, Allen Michael; Cimmarusti, Gregory Allen, Combustor dome assembly of a gas turbine engine having a contoured swirler.
Heberling Paul V. (Cincinnati OH) Kelsey Mark P. (Cincinnati OH) Dodds Willard J. (West Chester OH), Cyclonic prechamber with a centerbody for a gas turbine engine combustor.
Borkowicz Richard (Westminster MD) Foss David T. (Schenectady NY) Popa Daniel M. (Schenectady NY) Mick Warren J. (Altamont NY) Lovett Jeffery A. (Scotia NY), Dry low NOx single stage dual mode combustor construction for a gas turbine.
Joshi Narendra D. (Cincinnati OH) Angel Paul R. (Fairfield OH) Caldwell James M. (Alexandria KY) Heberling Paul V. (Cincinnati OH) Dean Anthony J. (Scotia NY), Dual fuel mixer for gas turbine combustor.
Lemon Donald T. (Palm Beach Gardens FL) Hu Aaron S. (Hartford CT) Schlein Barry C. (Wethersfield CT) Fox Theodore G. (Newington CT), Fuel injector and method of operating the fuel injector.
Lee Fei P. (Novi MI) Guzowski Mike (Canton MI), Fuel injector assembly with first and second fuel injectors and inner, outer, and intermediate air discharge chambers.
Caruel Jacques Emile Jules (Dammarie-les-Lys FR) Bedue Jean Robert (Creteil FR) Cantaloube Bernard Andre (Chennevieres FR), Fuel injector for atomizing and vaporizing fuel.
Faucher Joseph E. (East Hartford CT) Wright Richard R. (Willimantic CT) Pane ; Jr. Francis C. (South Windsor CT) Kwoka David (Windsor CT) Striebel Edmund E. (South Windsor CT), Fuel nozzle for gas turbine engine.
Pane ; Jr. Francis C. (South Windsor CT) Matthews John A. (Melrose CT) Wright Richard R. (Willimantic CT) Sarnik John M. (Marlborough CT) Frasca Thomas (Wethersfield CT), Fuel nozzle for gas turbine engine.
Barbier Grard Y. G. (Morangis FRX) Beule Frdric B. (Charenton Le Pont FRX) Desaulty Michel A. A. (Vert Saint Denis FRX) Latour Jean M. C. M. P. (La Chaussee Saint Victor FRX) Masse Bruno R. H. (Vaux , Gas turbine combustion chamber wall structure for minimizing cooling film disturbances.
Koshoffer John M. (Forest Park OH) Ekstedt Edward E. (Montgomery OH) Samuel Billy P. (Madeira OH) Stamm Edward I. (Madeira OH), Gas turbine engine carburetor.
Cowell Luke H. (San Diego CA) Roberts Peter B. (Encinitas CA), Gas turbine engine catalytic and primary combustor arrangement having selective air flow control.
Willis Jeffrey D. (Coventry GB2) Deacon Norman E. (Rugby GB2) Pollard Richard E. (Coventry GB2) Toon Ian J. (Leicester GB2) Boyce Bernard W. (Leicester GB2), Gas turbine engine fuel burner.
Toqan Majed A. ; Borio Richard W. ; Duby Thomas G. ; LaFlesh Richard C. ; Nicholson Julie A. ; Thornock David E., Method for effecting control over a radially stratified flame core burner.
Joshi Mahendra L. (Altamonte Spring FL) Broadway Lee (Eustis FL) Mohr Patrick J. (Mims FL) Nitzman Jack L. (Altamonte Spring FL), Oxy-liquid fuel combustion process and apparatus.
Ansart Denis R. H. (Bois le Roi FRX) Commaret Patrice A. (Maincy FRX) David Etienne S. R. (Bois le Roi FRX) Desaulty Michel A. A. (Vert Saint Denis FRX) Quinquenneau Bruno M. M. (Massy FRX) Sandelis , Pre-mixing injection system for a turbojet engine.
Hammond ; Jr. Dean C. (Warren MI) Quinn Ronald E. (Indianapolis IN), Premix combustor with flow constricting baffle between combustion and dilution zones.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.