System and method for reducing modal coupling of combustion dynamics
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F23R-003/20
F23R-003/46
F02C-007/24
F02C-007/22
F23D-014/02
F23R-003/28
출원번호
US-0048272
(2013-10-08)
등록번호
US-9151502
(2015-10-06)
발명자
/ 주소
Crothers, Sarah Lori
Kraemer, Gilbert Otto
출원인 / 주소
General Electric Company
대리인 / 주소
Wilson, Charlotte C.
인용정보
피인용 횟수 :
7인용 특허 :
3
초록▼
A system and method for reducing combustion dynamics includes first and second combustors, and each combustor includes a fuel nozzle and a combustion chamber downstream from the fuel nozzle. Each fuel nozzle includes an axially extending center body, a shroud that circumferentially surrounds at leas
A system and method for reducing combustion dynamics includes first and second combustors, and each combustor includes a fuel nozzle and a combustion chamber downstream from the fuel nozzle. Each fuel nozzle includes an axially extending center body, a shroud that circumferentially surrounds at least a portion of the axially extending center body, a plurality of vanes that extend radially between the center body and the shroud, a first fuel port through at least one of the plurality of vanes at a first axial distance from the combustion chamber, the plurality of vanes being located at a second axial distance from the combustion chamber. A second fuel port is provided through the center body at a third axial distance from the combustion chamber. The system further includes structure for producing a combustion instability frequency in the first combustor that is different from the combustion instability frequency in the second combustor.
대표청구항▼
1. A system for reducing modal coupling of combustion dynamics, the system comprising: (a) a plurality of combustors arranged in a circumferential array about a common longitudinal axis, each combustor having a liner defining a combustion chamber and a cap assembly having an axial cap length;(b) at
1. A system for reducing modal coupling of combustion dynamics, the system comprising: (a) a plurality of combustors arranged in a circumferential array about a common longitudinal axis, each combustor having a liner defining a combustion chamber and a cap assembly having an axial cap length;(b) at least one fuel nozzle disposed within each combustor upstream of the combustion chamber, each of the at least one fuel nozzles being housed within the cap assembly and a first fuel nozzle of the at least one fuel nozzle comprising an axially extending center body, a shroud circumferentially surrounding at least a portion of the axially extending center body and a plurality of vanes extending radially between the center body and the shroud, the vanes being curved to impart swirl to a working fluid flowing between the shroud and the center body, each vane defining at least a first fuel port located at a first axial distance from a front end of the combustion chamber and further comprising an edge located at a second axial distance from the front end of the combustion chamber; wherein at least one of the first axial distance and the second axial distance of the first fuel nozzle in a first combustor of the plurality of combustors is different from the first axial distance and the second axial distance of the first fuel nozzle in a second combustor of the plurality of combustors, and wherein the plurality of vanes of one of the fuel nozzles is located at an inlet of a corresponding shroud. 2. The system of claim 1, wherein the first axial distance of the first fuel nozzle in the first combustor is different from the first axial distance of the first fuel nozzle in the second combustor; and wherein the second axial distance of the first fuel nozzle in the first combustor is different from the second axial distance of the first fuel nozzle in the second combustor. 3. The system of claim 1, wherein the axially extending center body of the first fuel nozzle in each of the first combustor and the second combustor defines a fuel port located at a third axial distance from the front end of the combustion chamber. 4. The system of claim 3, wherein the third axial distance of the first fuel nozzle in the first combustor is different from the third axial distance of the first fuel nozzle in the second combustor. 5. The system of claim 4, wherein the first axial distance of the first fuel nozzle in the first combustor is different from the first axial distance of the first fuel nozzle in the second combustor; and wherein the third axial distance of the first fuel nozzle in the first combustor is different from the third axial distance of the first fuel nozzle in the second combustor. 6. The system of claim 4, wherein the axial cap length in the first combustor is different from the axial cap length in the second combustor. 7. The system of claim 6, wherein at least three of the first axial distance of the first fuel nozzle, the second axial distance of the first fuel nozzle, the third axial distance of the first fuel nozzle, and the axial cap length in the first combustor are different from the first axial distance of the first fuel nozzle, the second axial distance of the first fuel nozzle, the third axial distance of the first fuel nozzle, and the axial cap length in the second combustor. 8. The system of claim 1, wherein the cap assembly of each combustor further comprises a plurality of second fuel nozzles that circumferentially surround the first fuel nozzle, each second fuel nozzle comprising a plurality of tubes arranged in a tube bundle and each tube in the tube bundle comprising a fuel injector extending therethrough to provide fluid communication into each tube at a fourth axial distance from the front end of the combustion chamber. 9. The system of claim 8, wherein the fourth axial distance of the second fuel nozzles in the first combustor is different from the fourth axial distance of the second fuel nozzles in the second combustor. 10. A method of reducing modal coupling of combustion dynamics in a combustion system comprising a plurality of combustors, the method comprising: (a) providing a first combustor having a first liner defining a first combustion chamber, a first cap assembly, and at least one fuel nozzle housed within the first cap assembly, a first fuel nozzle of the at least one fuel nozzle comprising an axially extending center body, a shroud circumferentially surrounding at least a portion of the axially extending center body and a plurality of vanes extending radially between the center body and the shroud, the vanes being curved to impart swirl to a working fluid flowing between the shroud and the center body, each vane defining at least a first fuel port located at a first axial distance from a front end of the first combustion chamber and further comprising an edge located at a second axial distance from the front end of the first combustion chamber;(b) providing a second combustor having a second liner defining a second combustion chamber, a second cap assembly, and at least one fuel nozzle housed within the second cap assembly, a first fuel nozzle of the at least one fuel nozzle comprising an axially extending center body, a shroud circumferentially surrounding at least a portion of the axially extending center body and a plurality of vanes extending radially between the center body and the shroud, the vanes being curved to impart swirl to a working fluid flowing between the shroud and the center body, each vane defining at least a first fuel port located at a first axial distance from a front end of the second combustion chamber and further comprising an edge located at a second axial distance from the front end of the second combustion chamber; wherein at least one of (i) the first axial distance of the first fuel nozzle in the first combustor is different from the first axial distance of the first fuel nozzle in the second combustor; and (ii) the second axial distance of the first fuel nozzle in the first combustor is different from the second axial distance of the first fuel nozzle in the second combustor, and wherein the plurality of vanes of one of the fuel nozzles is located at an inlet of a corresponding shroud. 11. The method of claim 10, further comprising: providing the axially extending center body of the first fuel nozzle of the first combustor and the second combustor with at least one fuel port, the fuel port being located at a third axial distance from the front end of the combustion chamber; wherein the third axial distance of the first fuel nozzle center body in the first combustor is different from the third axial distance of the first fuel nozzle center body in the second combustor. 12. The method of claim 11, further comprising: providing the first combustor with a first axial cap length and providing the second combustor with a second axial cap length, wherein the first axial cap length of the first combustor is different from the second axial cap length of the second combustor. 13. The method of claim 12, wherein at least three of the first axial distance of the first fuel nozzle, the second axial distance of the first fuel nozzle, the third axial distance of the first fuel nozzle, and the axial cap length in the first combustor are different from the first axial distance of the first fuel nozzle, the second axial distance of the first fuel nozzle, the third axial distance of the first fuel nozzle, and the axial cap length in the second combustor. 14. The method of claim 13, further comprising: providing the first fuel nozzle of the first combustor with the first axial distance, the second axial distance, the third axial distance, all of which are different from the first axial distance, the second axial distance, and the third axial distance of the first fuel nozzle of the second combustor, and wherein the axial cap length of the first combustor is different from the axial cap length of the second combustor. 15. The method of claim 10, further comprising: providing, in the first combustor and the second combustor, a plurality of second fuel nozzles that circumferentially surround the first fuel nozzle, each second fuel nozzle comprising a plurality of tubes arranged in a tube bundle and each tube in the tube bundle comprising a fuel injector extending therethrough to provide fluid communication into each tube at a fourth axial distance from the front end of the combustion chamber; wherein the fourth axial distance of the second fuel nozzles in the first combustor is different from the fourth axial distance of the second fuel nozzles in the second combustor.
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