Gas turbine combustor having a fuel nozzle for flame anchoring
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/22
F23R-003/28
F23D-014/22
출원번호
US-0048564
(2011-03-15)
등록번호
US-8365534
(2013-02-05)
발명자
/ 주소
Popovic, Predrag
Baruah, Abinash
Kraemer, Gilbert Otto
Ross, William Thomas
출원인 / 주소
General Electric Company
인용정보
피인용 횟수 :
1인용 특허 :
74
초록▼
A combustor includes an end cover having a nozzle. The nozzle has a front end face and a central axis. The nozzle includes a plurality of fuel passages and a plurality of oxidizer passages. The fuel passages are configured for fuel exiting the fuel passage. The fuel passages are positioned to direct
A combustor includes an end cover having a nozzle. The nozzle has a front end face and a central axis. The nozzle includes a plurality of fuel passages and a plurality of oxidizer passages. The fuel passages are configured for fuel exiting the fuel passage. The fuel passages are positioned to direct fuel in a first direction, where the first direction is angled inwardly towards the center axis. The oxidizer passages are configured for having oxidizer exit the oxidizer passages. The oxidizer passages are positioned to direct oxidizer in a second direction, where the second direction is angled outwardly away from the center axis. The plurality of fuel passages and the plurality of oxidizer passages are positioned in relation to one another such that fuel is in a cross-flow arrangement with oxidizer to create a burning zone in the combustor.
대표청구항▼
1. A combustor for a gas turbine, comprising: an end cover having a nozzle, the nozzle having a front end face and a center axis, the front end face oriented at an inclined end face angle measured with respect to the center axis, the nozzle comprising: a plurality of fuel passages configured for dir
1. A combustor for a gas turbine, comprising: an end cover having a nozzle, the nozzle having a front end face and a center axis, the front end face oriented at an inclined end face angle measured with respect to the center axis, the nozzle comprising: a plurality of fuel passages configured for directing fuel in a first direction, wherein the first direction is angled inwardly towards the center axis, fuel exiting the plurality of fuel passages through respective openings located on the front end face;a plurality of oxidizer passages configured for directing oxidizer in a second direction, wherein the second direction is angled outwardly away from the center axis, and wherein the plurality of fuel passages and the oxidizer passages are positioned in relation to one another such that fuel is in a cross-flow arrangement with oxidizer to create a burning zone in the combustor, oxidizer exiting the plurality of oxidizer passages through respective oxidizer opening located on the front end face,a pilot nozzle positioned at the central axis, the pilot nozzle initiating a flame in the burning zone, andwherein the plurality of oxidizer passages are configured to direct oxidizer to create a recirculation zone in the combustor that anchors the burning zone at the front end face of the nozzle, the recirculation zone being downstream of a point of intersection of the fuel and oxidizer from their respective passages. 2. The combustor of claim 1, wherein the nozzle includes a plurality of cooling flow passages configured for directing working fluid out of the plurality of cooling flow passages and into the combustor. 3. The combustor of claim 2, wherein a working fluid that is an oxygen-deficient working fluid is included with the combustor. 4. The combustor of claim 2, wherein a series of mixing passages are located within the end cover between the plurality of oxidizer passages and the plurality of cooling flow passages, and wherein the plurality of oxidizer passages and the plurality of cooling flow passages are fluidly connected to one another through the mixing passages. 5. The combustor of claim 1, wherein the plurality of oxidizer passages are oriented in an oxidizer angle measured with respect to the front end face of the fuel nozzle, wherein the oxidizer angle is about normal with respect to the front end face. 6. The combustor of claim 1, wherein the end face angle of the front end face ranges from about thirty degrees to about seventy-five degrees when measured from the center axis. 7. The combustor of claim 1, wherein the plurality of fuel passages are positioned at a fuel angle to orient fuel in the first direction, and wherein the fuel angle ranges between about fifteen degrees to about ninety degrees when measured with respect to the front end face of the fuel nozzle. 8. The combustor of claim 1, wherein the plurality of fuel passages are arranged in a staggered configuration with respect to one another along the front end face. 9. The combustor of claim 1, wherein the plurality of oxidizer passages include an outer diameter that ranges from between about 1.3 centimeter to about 3.8 centimeters. 10. A combustor for a gas turbine, the combustor comprising: an end cover having at least one nozzle, the nozzle having a front end face and a center axis, the front end face oriented at an inclined end face angle measured with respect to the center axis, the nozzle comprising: a plurality of fuel passages configured for directing fuel in a first direction, wherein the first direction is angled inwardly towards the center axis, fuel exiting the plurality of fuel passages through respective openings located on the front end face;a plurality of cooling flow passages configured for directing working fluid out of one or more of the plurality of cooling flow passages and into the combustor;a plurality of oxidizer passages configured for directing oxidizer in a second direction, the second direction being angled outwardly away from the center axis, and wherein the plurality of fuel passages and the plurality of oxidizer passages are positioned in relation to one another such that fuel is in a cross-flow arrangement with oxidizer to create a burning zone in the combustor, oxidizer exiting the plurality of oxidizer passages through respective oxidizer opening located on the front end face,a pilot nozzle positioned at the central axis, the pilot nozzle initiating a flame in the burning zone, andwherein the plurality of oxidizer passages are configured to direct oxidizer to create a recirculation zone that anchors the burning zone at the front end face of the nozzle, the recirculation zone being downstream of a point of intersection of the fuel and oxidizer from their respective passages. 11. The combustor of claim 10, wherein a working fluid that is an oxygen-deficient working fluid is included with the combustor. 12. The combustor of claim 10, wherein a series of mixing passages are located within the end cover between the plurality of oxidizer passages and the plurality of cooling flow passages, and wherein the plurality of oxidizer passages and the plurality of cooling flow passages are fluidly connected to one another through the mixing passages. 13. The combustor of claim 10, wherein the end face angle of the front end face ranges from about thirty degrees to about seventy-five degrees when measured from the center axis. 14. The combustor of claim 10, wherein the plurality of oxidizer passages are oriented in an oxidizer angle measured with respect to the front end face of the fuel nozzle, wherein the oxidizer angle is about normal with respect to the front end face. 15. The combustor of claim 10, wherein the plurality of fuel passages are positioned at a fuel angle to orient fuel in the first direction, and wherein the fuel angle ranges between about fifteen to about ninety degrees when measured with respect to the front end face of the fuel nozzle. 16. A gas turbine having a combustor, the combustor comprising: an end cover having at least one nozzle, the nozzle having a front end face and a center axis, wherein the front end face is oriented at an inclined end face angle measured with respect to the center axis, the nozzle comprising: a plurality of fuel passages configured for directing fuel in a first direction, wherein the first direction is angled inwardly towards the center axis, fuel exiting the plurality of fuel passages through respective openings located on the front end face;a plurality of cooling flow passages configured for directing working fluid out of the plurality of cooling flow passages and into the combustor;a plurality of oxidizer passages configured for directing oxidizer in a second direction, wherein the second direction is angled outwardly away from the center axis, and wherein the plurality of oxidizer passages are oriented in an oxidizer angle measured with respect to the front end face of the fuel nozzle, the plurality of fuel passages and the plurality of oxidizer passages being positioned in relation to one another such that fuel supplied to the combustor is in a cross-flow arrangement with oxidizer to create a burning zone in the combustor, oxidizer exiting the plurality of oxidizer passages through respective oxidizer opening located on the front end face,a pilot nozzle positioned at the central axis, the pilot nozzle initiating a flame in the burning zone, andwherein the plurality of oxidizer passages are configured to direct oxidizer to create a recirculation zone that anchors the burning zone at the front end face of the nozzle, the recirculation zone being downstream of a point of intersection of the fuel and oxidizer from their respective passages. 17. The gas turbine of claim 16, wherein the end face angle of the front end face ranges from about thirty degrees to about seventy-five degrees when measured from the center axis. 18. The gas turbine of claim 16, wherein and wherein the fuel angle ranges between about fifteen degrees to about ninety degrees when measured with respect to the front end face of the fuel nozzle.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (74)
Joshi Mahendra L. (Altamonte Springs FL) O\Connor Paul (Ocoee FL), Adjustable atomizing orifice liquid fuel burner.
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.
Angel Paul R. (Fairfield OH) Caldwell James M. (Alexandria KY) Heberling Paul V. (Cincinnati OH) Dean Anthony J. (Scotia NY) Joshi Narendra D. (Cincinnati OH), Dual fuel mixer for gas turbine combustor.
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.
Loprinzo Anthony J. ; Maughan James R. ; Morton H. Lindsay ; Black Stephen Hugh ; Dean Anthony John ; Bechtel ; II William Theodore ; Luts Andrew, Dual-fuel nozzle for inhibiting carbon deposition onto combustor surfaces in a gas turbine.
Harjit Singh Hura ; Paul Edward Sabla ; James Neil Cooper ; Beverly Stephenson Duncan ; Hukam Chand Mongia ; Steven Joseph Lohmueller, Fuel nozzle assembly for reduced exhaust emissions.
Becker Bernard,DEX, Fuel nozzle configuration for a fluid-fuel burner, oil burner using the fuel nozzle configuration and method for regulating the fuel supply of a fluid-fuel burner.
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.
Hayashi,Akinori; Inage,Shinichi; Koizumi,Hiromi; Takehara,Isao; Ito,Kazuyuki; Sasao,Toshifumi; Murata,Hidetaro, Gas turbine combustor, combustion method of the gas turbine combustor, and method of remodeling a gas turbine combustor.
Rajamani Ravi ; Goodman George Charles ; Joshi Narendra Digamber ; Hook Richard Bradford, Method and apparatus for optimizing NOx emissions in a gas turbine.
Hsieh, Shih Yang; Hsiao, George Chia Chun; Li, Shui Chi; Mongia, Hukam Chand, Mixer assembly for combustor of a gas turbine engine having a plurality of counter-rotating swirlers.
Byron Andrew Pritchard, Jr. ; Allen Michael Danis ; Michael Jerome Foust ; Mark David Durbin ; Hukam Chand Mongia, Multiple annular combustion chamber swirler having atomizing pilot.
Hammond ; Jr. Dean C. (Warren MI) Quinn Ronald E. (Indianapolis IN), Premix combustor with flow constricting baffle between combustion and dilution zones.
Prociw Lev A. (Willowdale CAX) Bouchard Alain (St. Charles Borromee CAX) Bolduc Pierre (St. Amable CAX) Stastny Honze (West St. Bruno CAX), Radially mounted air blast fuel injector.
Joshi Mahendra L. ; Borders Harley A. ; Marin Ovidiu ; Charon Olivier, Self-cooled oxygen-fuel for use in high-temperature and high-particulate furnaces.
Ekstedt Edward E. (Montgomery OH) Joshi Narendra D. (Cincinnati OH) Ablett Adrian M. (Cincinnati OH) Gresla Timothy R. (Cincinnati OH) Koshoffer John M. (Cincinnati OH) Burke William F. (Marlborough , Triple annular combustor for gas turbine engine.
Farmer Gilbert ; Groeschen James A. ; Rettig Mark G., Venturi for use in the swirl cup package of a gas turbine combustor having water injected therein.
O'Dea, Dennis M.; Minto, Karl Dean; Huntington, Richard A.; Dhanuka, Sulabh K.; Mittricker, Franklin F., System and method of control for a gas turbine engine.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.