IPC분류정보
| 국가/구분 |
United States(US) Patent
등록
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| 국제특허분류(IPC7판) |
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| 출원번호 |
US-0856592
(2004-05-28)
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발명자
/ 주소 |
- Green,Andrew
- Stuttaford,Peter
- Benoit,Jeffrey Arthur
- Duraibabu,Vamsi
- Rizkalla,Hany
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| 출원인 / 주소 |
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| 인용정보 |
피인용 횟수 :
17 인용 특허 :
11 |
초록
▼
A gas turbine combustion liner is disclosed having an alternate interface region between it and a transition duct where the cooling effectiveness and heat transfer along the aft end of the combustion liner is improved, resulting in extended component life. The region of the combustion liner proximat
A gas turbine combustion liner is disclosed having an alternate interface region between it and a transition duct where the cooling effectiveness and heat transfer along the aft end of the combustion liner is improved, resulting in extended component life. The region of the combustion liner proximate its second end comprises a plurality of first feed holes, a plurality of spring seals that seal against a transition duct, a cooling ring having a plurality of second feed holes, that with the first feed holes pass a cooling fluid into an annulus formed between the cooling ring and combustion liner. The cooling fluid passes over a means for augmenting the heat transfer proximate the combustion liner second end, wherein the heat transfer augmentation preferably comprises a plurality of raised ridges that increases the surface area of the outer liner wall to turbulate the cooling fluid and maximize the cooling effectiveness.
대표청구항
▼
What we claim is: 1. A combustion liner for a gas turbine engine, said combustion liner comprising: a centerline, a first liner end, a second liner end, a first portion proximate said first end, and a second portion fixed downstream to said first portion and extending to said second end, said secon
What we claim is: 1. A combustion liner for a gas turbine engine, said combustion liner comprising: a centerline, a first liner end, a second liner end, a first portion proximate said first end, and a second portion fixed downstream to said first portion and extending to said second end, said second portion comprising: an inner liner wall; an outer liner wall; said second end being a downstream end of said liner; a plurality of first feed holes parallel to said centerline; a cooling ring in fixed relation to said outer liner wall and located radially outward of said outer liner wall to thereby form an annulus therebetween having an annulus height, said cooling ring having a cooling ring inner wall, a cooling ring outer wall, a first cooling ring end, and a second cooling ring end; a first spring seal overlapping said cooling ring outer wall and having a first length and a plurality of first axial slots, with each of said first axial slots having a first width; a second spring seal overlapping said first spring seal and having a second length and a plurality of second axial slots, with each of said second axial slots having a second width; a means for augmenting the heat transfer along said outer liner wall downstream said plurality of first feed holes; said first and second spring seals axially overlapping a region of said means for augmenting the heat transfer; and, wherein said first feed holes terminate at said annulus. 2. The combustion liner of claim 1 wherein said cooling ring is fixed to said outer liner wall proximate said first cooling ring end. 3. The combustion liner of claim 1 wherein said second cooling ring end extends axially beyond said second liner end. 4. The combustion liner of claim 1 further comprising a plurality of second feed holes in said cooling ring wherein said plurality of second feed holes are oriented generally perpendicular to said cooling ring outer wall. 5. The combustion liner of claim 1 wherein said first length is greater than said second length. 6. The combustion liner of claim 1 wherein said first width is substantially equal to said second width. 7. The combustion liner of claim 1 wherein said first and second spring seals are fixed to said combustion liner proximate said second end of said cooling ring. 8. The combustion liner of claim 1 wherein said means for augmenting heat transfer comprises a plurality of raised ridges extending into said annulus. 9. The combustion liner of claim 8 wherein each of said raised ridges comprises at least a first surface and a second surface. 10. The combustion liner of claim 8 wherein said raised ridges extend into said annulus approximately between 5% and 60% of said annulus height. 11. A combustion liner for a gas turbine engine, said combustion liner comprising: a centerline, a first liner end, a second liner end, a first portion proximate said first end, and a second portion fixed downstream to said first portion and extending to said second end, said second portion comprising: an inner liner wall; an outer liner wall; said second end being a downstream end of said liner; a plurality of first feed holes parallel to said centerline; a cooling ring in fixed relation to said outer liner wall and located radially outward of said outer liner wall to thereby form an annulus therebetween having an annulus height, said cooling ring having a cooling ring inner wall, a cooling ring outer wall, a first cooling ring end, and a second cooling ring end; a first spring seal overlapping said cooling ring outer wall and having a first length and a plurality of first axial slots, with each of said first axial slots having a first width; a second spring seal overlapping said first spring seal and having a second length and a plurality of second axial slots, with each of said second axial slots having a second width; a plurality of raised ridges extending into said annulus downstream said plurality of first feed holes, with each of said raised ridges comprising at least a first surface and a second surface; said first and second spring seals axially overlapping a region of said plurality of raised ridges; and, wherein said first feed holes terminate at said annulus. 12. The combustion liner of claim 11 wherein said cooling ring is fixed to said outer liner wall proximate said first cooling ring end. 13. The combustion liner of claim 11 wherein said second cooling ring end extends axially beyond said second liner end. 14. The combustion liner of claim 11 further comprising a plurality of second feed holes in said cooling ring wherein said plurality of second feed holes are oriented generally perpendicular to said cooling ring outer wall. 15. The combustion liner of claim 11 wherein said first length is greater than said second length. 16. The combustion liner of claim 11 wherein said first width is substantially equal to said second width. 17. The combustion liner of claim 11 wherein said first and second spring seals are fixed to said combustion liner proximate said second end of said cooling ring.
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