IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0146595
(2005-06-07)
|
등록번호 |
US-7506512
(2009-03-24)
|
발명자
/ 주소 |
- Schumacher,Jurgen C.
- Zupanc,Frank J.
- Dudebout,Rodolphe
|
출원인 / 주소 |
- Honeywell International Inc.
|
대리인 / 주소 |
Ingrassia Fisher & Lorenz, P.C.
|
인용정보 |
피인용 횟수 :
13 인용 특허 :
11 |
초록
▼
A cooling scheme for a dome comprises an effusion array drilled directly through a single walled dome. In one embodiment, the layout of the holes comprises two regions, a region close to the fuel injector where the holes follow a tangential path around the injector, and a second region where the dir
A cooling scheme for a dome comprises an effusion array drilled directly through a single walled dome. In one embodiment, the layout of the holes comprises two regions, a region close to the fuel injector where the holes follow a tangential path around the injector, and a second region where the direction of the holes is radially outward from the injector axis. A film of cooling air may be applied on the interior side of the combustor dome via an air swirler, which projects air radially outward from the injector axis. The first series of cooling holes supplement this air supply so that cooling efficacy is extended along the dome surface and is directed in a counter-rotating manner with respect to the main air swirler. The second series of dome cooling holes infuse further cooling flux that reduces the temperature in the corner regions between fuel injectors.
대표청구항
▼
We claim: 1. A cooling scheme for a combustor dome comprising: a plurality of tangential effusion holes positioned in said combustor dome and adapted to direct a first portion of cooling flow in a tangential direction around an injector axis of said combustor dome; and a plurality of radial effusio
We claim: 1. A cooling scheme for a combustor dome comprising: a plurality of tangential effusion holes positioned in said combustor dome and adapted to direct a first portion of cooling flow in a tangential direction around an injector axis of said combustor dome; and a plurality of radial effusion holes positioned in said combustor dome and adapted to direct a second portion of cooling flow radially outward from said injector axis. 2. The cooling scheme of claim 1, wherein said tangential effusion holes are positioned in a radially inward area of said combustor dome. 3. The cooling scheme of claim 2, wherein said radial effusion holes are positioned in a radially outward area of said combustor dome. 4. The cooling scheme of claim 3, further comprising a plurality of transitional effusion holes positioned in a transition area between and adjacent to said radially inward area and said radially outward area. 5. The cooling scheme of claim 1, wherein said combustor dome includes at least one air swirler and said first portion of cooling flow is supplemented by a swirler air flow from said air swirler. 6. The cooling scheme of claim 5, wherein said tangential direction of said first portion of cooling flow is counter to a swirl of said swirler air flow. 7. The cooling scheme of claim 1, wherein at least one of the tangential effusion holes forms a tangential angle of between about 75�� and about 90��. 8. The cooling scheme of claim 1, wherein each said radial effusion hole has a diameter between about 0.01 and about 0.04 inches. 9. The cooling scheme of claim 1, wherein said tangential effusion holes are positioned in a radially outward area of said combustor dome. 10. The cooling scheme of claim 9, wherein said radial effusion holes are positioned in a radially inward area of said combustor dome. 11. The cooling scheme of claim 10, further comprising a plurality of transitional effusion holes positioned in a transition area between and adjacent to said radially inward area and said radially outward area. 12. The cooling scheme of claim 1, wherein at least one of the tangential effusion holes forms an axial angle between about 15�� and about 30��. 13. The cooling scheme of claim 1, wherein said combustor dome comprises an annular combustor dome. 14. A cooling scheme for a combustor dome comprising: a plurality of effusion holes through said combustor dome, said plurality of effusion holes comprising at least one tangential effusion hole positioned in a radially inward area and at least one radial effusion hole positioned in a radially outward area. 15. The cooling scheme of claim 14, wherein said tangential effusion hole has a diameter between about 0.01 and about 0.04 inches. 16. The cooling scheme of claim 14, wherein said plurality of effusion holes includes at least one row of tangential effusion holes positioned around a fuel injector of said combustor dome. 17. The cooling scheme of claim 14, wherein an angle formed by a centerline of said radial effusion hole and a surface of said combustor dome is between about 15�� and about 30��. 18. The cooling scheme of claim 14, wherein an angle formed by a centerline of said tangential effusion hole and a surface of said combustor dome is between about 15�� and about 30��. 19. The cooling scheme of claim 14, wherein said tangential effusion hole is positioned in an area towards a fuel injector of said combustor dome. 20. The cooling scheme of claim 14, wherein said combustor dome is an annular combustor dome comprising a plurality of fuel injectors and wherein said plurality of effusion holes comprises at least one tangential effusion hole positioned towards each fuel injector. 21. The cooling scheme of claim 14, further comprising at least one transitional effusion hole positioned in a transition area between said tangential effusion hole and said radial effusion hole. 22. The cooling scheme of claim 14, wherein a density of said effusion holes is between about 10 and about 100 holes/in2. 23. The cooling scheme of claim 14, wherein said radial effusion hole is aligned at an angle of from about 75�� to about 90�� with respect to said tangential effusion hole. 24. A cooling scheme for a combustor dome comprising: a plurality of tangential effusion holes positioned through said combustor dome, said tangential effusion holes adapted to provide a tangential flow; a plurality of radial effusion holes positioned through said combustor dome and radially outward from said tangential effusion holes, said radial effusion holes adapted to provide a radial flow; and a plurality of transitional effusion holes positioned through said combustor dome, said transitional effusion holes adapted to direct a cooling flow such that the angle of the cooling flow transitions from the tangential flow of the tangential effusion holes to the radial flow of the radial effusion holes. 25. The cooling scheme of claim 24, wherein said tangential effusion holes are adapted to direct a swirl of cooling flow around an injector axis of said combustor dome. 26. The cooling scheme of claim 25, wherein said swirl of cooling flow is in a direction counter to a swirler air flow of said combustor dome. 27. A combustor for a gas turbine engine comprising: an inner liner; an outer liner positioned radially outward from said inner liner; and a combustor dome positioned between and connected to said inner liner and said outer liner, said combustor dome having a plurality of tangential effusion holes and a plurality of radial effusion holes. 28. The combustor of claim 27, wherein said combustor dome is an annular combustor dome comprising a plurality of fuel injectors and wherein said plurality of tangential effusion holes comprises at least one row of tangential effusion holes positioned around each fuel injector. 29. The combustor of claim 27, wherein at least one radial effusion hole is directed towards a corner region of an annular combustor segment of said combustor dome. 30. The combustor of claim 27, wherein each tangential effusion hole forms a tangential angle of between about 75�� and about 90��. 31. The combustor of claim 27, wherein said tangential effusion holes are positioned in a radially outward area of said combustor dome. 32. The combustor of claim 31, wherein said radial effusion holes are positioned in a radially inward area of said combustor dome. 33. An effusion array for an annular combustor dome having at least one air swirler comprising: at least one row of tangential effusion holes positioned around said air swirler, said tangential effusion holes adapted to direct a swirl of cooling flow in a counter-rotating manner with respect to said air swirler, each tangential effusion hole forming a tangential angle of between about 75�� and about 90�� and forming an axial angle of between about 15�� and about 30��, each tangential effusion hole having a diameter between about 0.01 and about 0.04 inches; a plurality of radial effusion holes positioned radially outward from said tangential effusion holes, said radial effusion holes adapted to direct a cooling flow radially outward from said air swirler, each radial effusion hole forming an axial angle of between about 15�� and about 30�� and having a diameter between about 0.01 and about 0.04 inches; and a plurality of transitional effusion holes positioned between said tangential effusion holes and said radial effusion holes, said transitional effusion holes adapted to direct a cooling flow such that the angle of the cooling flow transitions from the tangential flow of the tangential effusion holes to the radial flow of the radial effusion holes.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.