[특허]Gas turbine combustor having a fuel nozzle for flame anchoring

General Electric Company

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특허 상세정보

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Gas turbine combustor having a fuel nozzle for flame anchoring

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-007/22 F23R-003/28 F23D-014/22
미국특허분류(USC)	060/740; 060/742; 060/746
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 : 1 인용 특허 : 74

초록
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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.

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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.

이 특허에 인용된 특허 (74)

이 특허를 인용한 특허 피인용횟수: 1

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. USP2018019863267.

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Gas turbine combustor having a fuel nozzle for flame anchoring

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Gas turbine combustor having a fuel nozzle for flame anchoring

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