[미국특허]
Method and apparatus for cooling and dilution tuning a gas turbine combustor liner and transition piece interface
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-001/00
F02G-003/00
출원번호
US-0153020
(2008-05-13)
등록번호
US-8096133
(2012-01-17)
발명자
/ 주소
Hessler, William K.
Popovic, Predrag
Nyberg, Charles
출원인 / 주소
General Electric Company
대리인 / 주소
Nixon & Vanderhye, P.C.
인용정보
피인용 횟수 :
2인용 특허 :
36
초록▼
A combustor liner includes a forward end and an aft end, the aft end having a reduced diameter portion and a cooling and dilution sleeve overlying the reduced diameter portion thereby establishing a cooling plenum therebetween. A plurality of cooling and dilution air entry holes are formed in the co
A combustor liner includes a forward end and an aft end, the aft end having a reduced diameter portion and a cooling and dilution sleeve overlying the reduced diameter portion thereby establishing a cooling plenum therebetween. A plurality of cooling and dilution air entry holes are formed in the cooling and dilution sleeve and a plurality of cooling and dilution air exit holes formed adjacent an aft edge of the liner such that, in use, cooling and dilution air flows through the cooling and dilution air entry holes, and through the plenum, exiting the cooling and dilution air exit holes, thereby cooling and dilution tuning the aft end of the combustor liner without having to remove the transition piece.
대표청구항▼
1. A combustor liner comprising a forward end and an aft end, the aft end having a reduced diameter portion and a cooling and dilution sleeve overlying the reduced diameter portion thereby establishing a cooling plenum therebetween; a plurality of cooling and dilution air entry holes formed in said
1. A combustor liner comprising a forward end and an aft end, the aft end having a reduced diameter portion and a cooling and dilution sleeve overlying the reduced diameter portion thereby establishing a cooling plenum therebetween; a plurality of cooling and dilution air entry holes formed in said cooling sleeve and a plurality of cooling and dilution air exit holes formed in said combustor liner adjacent an aft edge of said combustor liner such that, in use, cooling air flows through said cooling and dilution air entry holes and through said plenum, exiting said plenum via said cooling and dilution air exit holes thereby cooling said aft end of said combustor liner. 2. The combustor liner of claim 1 wherein a compression seal is secured to an exterior surface of said cooling and dilution sleeve, directly radially outwardly of said plenum. 3. The combustor liner of claim 1 wherein said aft end includes an inwardly tapered portion leading to said reduced diameter portion, and an outwardly tapered portion leading to an annular collar, and further wherein a forward edge of said cooling and dilution sleeve engages said inwardly tapered portion and an aft edge of said cooling and dilution sleeve is secured to said collar. 4. The combustor liner of claim 1 wherein said aft end includes an inwardly tapered portion leading to said reduced diameter portion, and an outwardly tapered portion leading to an annular collar, and further wherein said cooling and dilution sleeve has a forward sleeve end engaged with the liner at a location upstream of said inwardly tapered portion and an aft sleeve end fixed to said collar. 5. The combustor liner of claim 3 wherein said cooling and dilution air entry holes are formed in an annular array adjacent said forward edge of said cooling and dilution sleeve. 6. The combustor liner of claim 5 wherein said cooling and dilution air exit holes are formed in an annular array in said outwardly tapered portion of said combustor liner. 7. The combustor liner of claim 4 wherein said cooling and dilution sleeve has an inwardly tapered portion proximate a forward edge thereof, and further wherein said cooling and dilution air entry holes are formed in an annular array in said inwardly tapered portion of said cooling and dilution sleeve, and said cooling and dilution air exit holes are formed in said outwardly tapered portion of said combustor liner. 8. The combustor of claim 7 wherein a compression seal is secured to an exterior surface of said cooling and dilution sleeve, directly radially outwardly of said plenum. 9. The combustor liner of claim 7 wherein said forward end of said cooling sleeve forms a slip joint with said combustor liner. 10. A combustor liner comprising a liner forward end and a liner aft end, the liner aft end having a reduced diameter portion and a cooling and dilution sleeve overlying the reduced diameter portion thereby establishing a cooling plenum therebetween; a plurality of cooling and dilution air entry holes formed in said cooling and dilution sleeve and a plurality of cooling and dilution air exit holes formed adjacent an aft liner edge such that, in use, cooling air flows through said cooling and dilution air entry holes, and through said plenum, exiting said cooling and dilution air exit holes thereby cooling said aft liner end; wherein a compression seal is secured to an exterior surface of said cooling and dilution sleeve, directly radially outwardly of said plenum; andwherein said combustor liner aft end includes an inwardly tapered portion leading to said reduced diameter portion, and an outwardly tapered portion leading to an annular collar, said cooling and dilution sleeve having a forward sleeve end engaged with the liner at a location upstream of said inwardly tapered portion, and an aft sleeve end fixed to said collar. 11. The combustor liner of claim 10 wherein said cooling and dilution air exit holes are located in said outwardly tapered portion of said combustor liner. 12. The combustor liner of claim 10 wherein said cooling and dilution sleeve has an inwardly tapered portion proximate a forward edge thereof, and further wherein said cooling and dilution air entry holes are formed in an annular array in said inwardly tapered portion of said cooling and dilution sleeve, and said cooling and dilution air exit holes are formed in said outwardly tapered portion of said liner. 13. The combustor liner of claim 10 wherein said forward end of said cooling and dilution sleeve forms a slip joint with said combustor liner. 14. A method of cooling and dilution tuning an aft end of a combustor liner and associated annular seal comprising: forming an aft end portion of the liner with a reduced diameter portion;locating a cooling and dilution sleeve about said reduced diameter portion, in radially spaced relationship thereto so as to create an annular plenum;forming cooling and dilution air entry holes in an upstream end of said cooling and dilution sleeve and cooling and dilution air exit holes in said combustor liner, proximate an aft edge thereof, such that, in use, cooling air flows through said cooling and dilution air entry holes into said plenum and through said cooling and dilution air exit holes. 15. The method of claim 14 wherein said cooling and dilution air entry holes are formed in an inwardly tapered transition region of said liner that leads to said reduced diameter portion. 16. The method of claim 15 wherein said cooling and dilution air exit holes are located in an outwardly tapered surface of said combustor liner, leading to said aft edge. 17. The method of claim 14 wherein a compression seal is supported on said cooling and dilution sleeve radially outwardly of said plenum. 18. The method of claim 14 including locating a rotatable collar in close-fitting relationship about a portion of said cooling and dilution sleeve said collar having holes therein that are selectively alignable with said cooling and dilution air entry holes to thereby achieve desired cooling and dilution tuning characteristics.
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