Systems and methods for control of combustion dynamics in combustion system
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F23R-003/34
F23N-005/24
F23R-003/44
출원번호
US-0687866
(2015-04-15)
등록번호
US-10113747
(2018-10-30)
발명자
/ 주소
Crothers, Sarah Lori
Karim, Hasan
Hall, Joel Meador
출원인 / 주소
General Electric Company
대리인 / 주소
Wilson, Charlotte C.
인용정보
피인용 횟수 :
0인용 특허 :
39
초록▼
The present disclosure generally relates to a system with a gas turbine engine. The gas turbine engine includes a first combustor having a first fuel injector and a second combustor having a second fuel injector. The gas turbine engine further includes a first fuel conduit extending from a first ori
The present disclosure generally relates to a system with a gas turbine engine. The gas turbine engine includes a first combustor having a first fuel injector and a second combustor having a second fuel injector. The gas turbine engine further includes a first fuel conduit extending from a first orifice to a first fuel outlet of the first fuel injector. The first fuel conduit has a first acoustic volume between the first orifice and the first fuel outlet. The gas turbine engine further includes a second fuel conduit extending from a second orifice to a second fuel outlet of the second fuel injector. The second fuel conduit has a second acoustic volume between the second orifice and the second fuel outlet, and the first acoustic volume and the second acoustic volume are different from one another.
대표청구항▼
1. A system, comprising: a gas turbine engine, comprising; a first combustor comprising a first liner circumscribing a first primary combustion zone and a first secondary combustion zone downstream of the first primary combustion zone and a first fuel injector disposed along the first liner and conf
1. A system, comprising: a gas turbine engine, comprising; a first combustor comprising a first liner circumscribing a first primary combustion zone and a first secondary combustion zone downstream of the first primary combustion zone and a first fuel injector disposed along the first liner and configured to inject a fuel, via a first fuel outlet, through the first liner into the first secondary combustion zone of the first combustor, the first fuel injector being located at a first distance from a first outlet of the first combustor;a second combustor comprising a second liner circumscribing a second primary combustion zone and a second secondary combustion zone downstream of the second primary combustion zone and a second fuel injector disposed along the second liner and configured to inject the fuel, via a second fuel outlet, through the second liner into the second secondary combustion zone of the second combustor, the second fuel injector being located at a second distance from a second outlet of the second combustor;a first fuel conduit extending axially along a first outer surface of the first liner and supplying the fuel to the first fuel injector;a first pre-orifice installed inside the first fuel conduit, such that a first volume of the first fuel conduit is defined between the first pre-orifice and the first fuel outlet;a second fuel conduit extending axially along a second outer surface of the second liner and supplying the fuel to the second fuel injector; anda second pre-orifice installed inside the second fuel conduit, such that to a second volume of the second fuel conduit is defined between the second pre-orifice and the second fuel outlet, wherein the first volume and the second volume are different from one another; andwherein the first distance is equal to the second distance;wherein the first pre-orifice comprises a first geometry, and the second pre-orifice comprises a second geometry, wherein one or more first geometric differences between the first geometry of the first pre-orifice and the second geometry of the second pre-orifice reduce coherence between the first combustor and the second combustor or alter a phase between the first combustor and the second combustor; andwherein the one or more first geometric differences between the first geometry of the first pre-orifice and the second geometry of the second pre-orifice comprises one or more of a number of orifices and an arrangement of a plurality of orifices. 2. The system of claim 1, wherein the first combustor comprises a first fuel nozzle upstream from the first fuel injector, the first fuel nozzle being configured to inject the fuel into the first primary combustion zone of the first combustor; and wherein the second combustor comprises a second fuel nozzle upstream from the second fuel injector, the second fuel nozzle being configured to inject the fuel into the second primary combustion zone of the second combustor. 3. The system of claim 1, wherein the one or more first geometric differences between the first geometry of the first pre-orifice and the second geometry of the second pre-orifice additionally comprises one or more of an orifice shape, an orifice dimension, an axial position, and a cross-sectional area. 4. The system of claim 1, wherein the first fuel conduit comprises a first conduit geometry and the second fuel conduit comprises a second conduit geometry, and wherein one or more second geometric differences between the first conduit geometry and the second conduit geometry alter a phase and/or reduce coherence between the first combustor and the second combustor. 5. The system of claim 4, wherein the one or more second geometric differences between the first conduit geometry and the second conduit geometry comprises one or more of a length, a width, a diameter, an inner surface, and a shape. 6. A system, comprising: a first combustor of a gas turbine system, comprising:a first liner circumscribing a first primary combustion zone and a first secondary combustion zone downstream of the first primary combustion zone;a first fuel injector disposed along the first liner and comprising a first fuel outlet configured to inject a fuel through the first liner into the first secondary combustion zone, the first fuel injector being located at a first distance from a first outlet of the first combustor;a second fuel injector disposed along the first liner and comprising a second fuel outlet configured to inject the fuel through the first liner into the first secondary combustion zone, the second fuel injector being located at a second distance from the first outlet of the first combustor;a first fuel conduit extending axially along an outer surface of the first liner and supplying the fuel to the first fuel injector;a first pre-orifice installed inside the first fuel conduit, wherein the first fuel conduit has a first conduit geometry between the first pre-orifice and the first fuel outlet, and wherein the first pre-orifice has a first pre-orifice geometry;a second fuel conduit extending axially along the first outer surface of the first liner and supplying the fuel to the second fuel injector; anda second pre-orifice installed inside the second fuel conduit, wherein the second fuel conduit has a second conduit geometry between the second pre-orifice and the second fuel outlet, and wherein the second pre-orifice has a second pre-orifice geometry;wherein the first conduit geometry and the second conduit geometry are different from one another, or the first pre-orifice geometry and the second pre-orifice geometry are different from one another, or a combination thereof; and wherein the first distance is equal to the second distance; andwherein one or more first geometric differences between the first pre-orifice geometry of the first pre-orifice and the second pre-orifice geometry of the second pre-orifice comprise differences in a number of orifices or an arrangement of a plurality of orifices. 7. The system of claim 6, wherein the one or more first geometric differences between the first pre-orifice geometry of the first pre-orifice and the second pre-orifice geometry of the second pre-orifice additionally comprise differences in an orifice shape, an orifice dimension, an axial position, or a cross-sectional area. 8. The system of claim 6, wherein the first fuel outlet comprises a third orifice geometry and the second fuel outlet comprises a fourth orifice geometry, wherein the third orifice geometry is different from the fourth orifice geometry. 9. The system of claim 6, wherein the first conduit geometry between the first pre-orifice and the first fuel outlet corresponds to a first volume between the first pre-orifice and the first fuel outlet; wherein the second conduit geometry between the second pre-orifice and the second fuel outlet corresponds to a second volume between the second pre-orifice and the second fuel outlet; and wherein the second volume is different from the first volume. 10. The system of claim 9, wherein one or more differences between the first volume and the second volume reduce combustion dynamics amplitudes between the first fuel injector and the second fuel injector of the first combustor. 11. The system of claim 6, wherein the system comprises a second combustor comprising a second liner circumscribing a second primary combustion zone and a second secondary combustion zone; and wherein the second combustor is equipped with a third fuel injector in fluid communication with a third fuel conduit, the third fuel injector being disposed along the second liner and configured to inject the fuel through the second liner into the second secondary combustion zone, the third fuel injector being located at a third distance from a second outlet of the second combustor; andwherein the third fuel conduit extends axially along a second outer surface of the second liner and has one or more second geometric differences relative to the first fuel conduit or the second fuel conduit of the first combustor, and the third distance is equal to the first distance. 12. A gas turbine engine comprising: a first combustor comprising;a first liner circumscribing a first primary combustion zone and a first secondary combustion zone downstream of the first primary combustion zone;a first fuel injector disposed along the first liner and configured to inject a fuel, via a first fuel outlet, through the first liner into the first secondary combustion zone of the first combustor, the first fuel injector being located at a first distance from a first outlet of the first combustor;a first fuel conduit extending axially along a first outer surface of the first liner and supplying the fuel to the first fuel injector, the first fuel conduit having a first cross-sectional diameter; anda first pre-orifice installed inside the first fuel conduit, such that a first volume of the first fuel conduit is defined between the first pre-orifice and the first fuel outlet;a second combustor comprising:a second liner circumscribing a second primary combustion zone and a second secondary combustion zone downstream of the second primary combustion zone;a second fuel injector disposed along the second liner and configured to inject the fuel, via a second fuel outlet, through the second liner into the second secondary combustion zone of the second combustor, the second fuel injector being located at a second distance from a second outlet of the second combustor, wherein the second distance is equal to the first distance;a second fuel conduit extending axially along a second outer surface of the second liner and supplying the fuel to the second fuel injector, the second fuel conduit having a second cross-sectional diameter different from the first cross-sectional diameter;a second pre-orifice installed inside the second fuel conduit, such that a second volume of the second fuel conduit is defined between the second pre-orifice and the second fuel outlet;wherein the first volume is different from the second volume; andwherein the first pre-orifice has at least one first geometric difference from the second pre-orifice, the at least one first geometric difference being a difference in a number of orifices and a difference in a arrangement of a plurality of orifices. 13. The gas turbine engine of claim 12, wherein the first fuel conduit and the second fuel conduit have at least one second geometric difference in addition to a difference between the first cross-sectional diameter and the second cross-sectional diameter, the at least one second geometric difference comprising a difference in length, a difference in an inner surface, and a difference in conduit shape. 14. The gas turbine engine of claim 12, wherein the at least one first geometric difference additionally comprises a difference in an orifice shape, a difference in an orifice dimension, a difference in a cross-sectional area, and a difference in an axial position of a respective pre-orifice within a respective fuel conduit.
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