Turbine combustor configured for high-frequency dynamics mitigation and related method
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F23R-003/42
F23D-014/62
F23R-003/28
F23R-003/10
출원번호
US-0021298
(2011-02-04)
등록번호
US-8875516
(2014-11-04)
발명자
/ 주소
Uhm, Jong Ho
Zuo, Baifang
York, William David
Srinivasan, Shivakumar
출원인 / 주소
General Electric Company
대리인 / 주소
Nixon & Vanderhye, P.C.
인용정보
피인용 횟수 :
0인용 특허 :
24
초록▼
A turbomachine combustor includes a combustion chamber; a plurality of micro-mixer nozzles mounted to an end cover of the combustion chamber, each including a fuel supply pipe affixed to a nozzle body located within the combustion chamber, wherein fuel from the supply pipe mixes with air in the nozz
A turbomachine combustor includes a combustion chamber; a plurality of micro-mixer nozzles mounted to an end cover of the combustion chamber, each including a fuel supply pipe affixed to a nozzle body located within the combustion chamber, wherein fuel from the supply pipe mixes with air in the nozzle body prior to discharge into the combustion chamber; and wherein at least some of the nozzle bodies of the plurality of micro-mixer nozzles have axial length dimensions that differ from axial length dimensions of other of the nozzle bodies.
대표청구항▼
1. A turbomachine combustor comprising: a combustion chamber;a plurality of micro-mixer nozzles mounted to an end cover of the combustion chamber, each micro-mixer nozzle including a fuel supply pipe affixed to a nozzle body located within the combustion chamber, each nozzle body comprising a substa
1. A turbomachine combustor comprising: a combustion chamber;a plurality of micro-mixer nozzles mounted to an end cover of the combustion chamber, each micro-mixer nozzle including a fuel supply pipe affixed to a nozzle body located within the combustion chamber, each nozzle body comprising a substantially hollow body formed with an upstream end face, a downstream end face and a peripheral wall extending therebetween, wherein each substantially hollow body is greater in diameter than its respective fuel supply pipe, receives fuel from the respective fuel supply pipe, and is provided with a plurality of pre-mix tubes or passages extending axially through said substantially hollow body, thereby permitting fuel from the supply pipe to mix with air in said nozzle body prior to discharge into said combustion chamber; andwherein at least some nozzle bodies of said plurality of micro-mixer nozzles have axial length dimensions that differ from axial length dimensions of other of said nozzle bodies along an inlet end of the nozzle bodies. 2. The turbomachine combustor of claim 1 wherein said plurality of micro-mixer nozzles comprise a center nozzle and an annular array of radially outer nozzles surrounding said center nozzle. 3. The turbomachine combustor of claim 2 wherein every other nozzle body of said annular array of radially outer nozzles has a first axial length dimension, and wherein remaining nozzle bodies of said annular array of said radially outer nozzles have a second axial length dimension greater or less than said first axial length dimension. 4. The turbomachine combustor of claim 3 wherein the nozzle body of said center nozzle has an axial length dimension equal to, or different than said first and second axial length dimensions. 5. The turbomachine combustor of claim 1 wherein none of said axial length dimensions of said plurality of micro-mixer nozzle bodies are the same. 6. The turbomachine of claim 1 wherein said nozzle body of one or more of said plurality of micro-mixer nozzles is formed to include a radially outer portion of a first diameter, and at least one radially inner portion of a second diameter less than said first diameter, connected by a radially-oriented shoulder, and wherein said radially outer and radially inner portions have differential axial lengths. 7. The turbomachine of claim 6 wherein pre-mix tubes in said radially outer portion have axial length dimensions less than axial length dimension of pre-mix tubes in said at least one radially inner portion. 8. The turbomachine of claim 7 wherein pre-mix tubes in said radially outer portion have axial length dimensions greater than axial length dimensions of pre-mix tubes in said at least one radially inner portion. 9. A turbomachine combustor comprising: a combustion chamber;a plurality of nozzle bodies supported in said combustion chamber, and connected to respective fuel supply pipes, wherein fuel from said supply pipes mixes with air in said nozzle bodies prior to discharge into said combustion chamber; wherein said plurality of nozzle bodies comprise a center nozzle body and an annular array of radially outer nozzle bodies surrounding said center nozzle body, each of said plurality of nozzle bodies and said center nozzle body comprising a substantially hollow body greater in diameter than its respective fuel supply pipe, the hollow body receives fuel from the respective fuel supply pipe, and the hollow body is formed with an upstream end face, a downstream end face and a peripheral wall extending therebetween, wherein each substantially hollow body is provided with a plurality of pre-mix tubes or passages extending axially through said substantially hollow body; said center nozzle body having a first axial length, and said annular array of radially outer nozzle bodies having at least second and third axial lengths that are different from said first axial length along an inlet end of the nozzle bodies. 10. The turbomachine of claim 9 wherein axial length dimensions differ for each of said plurality of nozzle bodies. 11. The turbomachine of claim 9 wherein no adjacent nozzle bodies of said plurality of nozzle bodies have identical axial lengths. 12. A method of mitigating high frequency dynamics in a turbine combustor incorporating plural micro-mixer nozzles arranged substantially in parallel, each micro-mixer nozzle having a nozzle body at an aft end thereof, the method comprising: a. arranging said plural micro-mixer nozzles in an array of radially outer micro-mixer nozzle bodies surrounding a center micro-mixer nozzle body, each of said radially outer micro-mixer nozzle bodies and said center micro-mixer nozzle body comprising a substantially hollow body greater in diameter than a respective fuel supply pipe, the hollow body receiving fuel from the respective fuel supply pipe, and the hollow body is formed with an upstream end face, a downstream end face and a peripheral wall extending therebetween, with a plurality of pre-mix tubes or passages extending axially through said substantially hollow body; andb. forming at least some of said plural micro-mixer nozzles to have nozzle bodies of respectively different axial length dimensions along an inlet end of the nozzle bodies. 13. The method of claim 12 wherein step b. includes forming every other nozzle body of said array of radially outer micro-mixer nozzles to have a first axial length dimension, and forming remaining nozzle bodies of said array of radially outer micro-mixer nozzles to have a second axial length dimension greater to or less than said first axial length dimension. 14. The method of claim 13 wherein step b. includes forming said center nozzle to have a nozzle body with a third axial length dimension different from first and second axial length dimensions. 15. The method of claim 12 wherein axial length dimensions differ for each of said plurality of micro-mixer nozzles. 16. The method of claim 12 wherein said nozzle body of one or more of said plurality of micro-mixer nozzles is formed to include at least first and second axially-extending portions connected by a shoulder, such that said at least first and second axially-extending portions have differential axial lengths. 17. The method of claim 16 wherein a radially outer one of said at least first and second axially-extending portions has an axial length dimension less than an axial length dimension of a radially inner one of said at least first and second axially-extending portions. 18. The method of claim 16 wherein a radially outer one of said at least first and second axially-extending portions has an axial length dimension greater than an axial length dimension of a radially inner one of said at least first and second axially-extending portions. 19. The method of claim 12 wherein no adjacent nozzle bodies of said plurality of nozzle bodies have identical axial lengths. 20. The method of claim 12 wherein each radially outer micro-mixer nozzle body in said array of radially outer micro-mixer nozzle bodies is sector-shaped, and said center micro-mixer nozzle body is round.
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