IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0425293
(2009-04-16)
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등록번호 |
US-8333075
(2012-12-18)
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발명자
/ 주소 |
- York, William David
- Johnson, Thomas Edward
- Lacy, Benjamin Paul
- Stevenson, Christian Xavier
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출원인 / 주소 |
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
1 인용 특허 :
10 |
초록
▼
A system that includes a turbine fuel nozzle comprising an air-fuel premixer. The air-fuel premixed includes a swirl vane configured to swirl fuel and air in a downstream direction, wherein the swirl vane comprises an internal coolant path from a downstream end portion in an upstream direction throu
A system that includes a turbine fuel nozzle comprising an air-fuel premixer. The air-fuel premixed includes a swirl vane configured to swirl fuel and air in a downstream direction, wherein the swirl vane comprises an internal coolant path from a downstream end portion in an upstream direction through a substantial length of the swirl vane.
대표청구항
▼
1. A system, comprising: a fuel nozzle, comprising: a central body;an outer tube disposed about the central body;an air path disposed between the central body and the outer tube;a vane disposed in the air path, wherein the vane comprises: a fuel inlet;a fuel outlet; anda divider disposed in the vane
1. A system, comprising: a fuel nozzle, comprising: a central body;an outer tube disposed about the central body;an air path disposed between the central body and the outer tube;a vane disposed in the air path, wherein the vane comprises: a fuel inlet;a fuel outlet; anda divider disposed in the vane axially between a downstream cavity having the fuel inlet and an upstream cavity having the fuel outlet; anda fuel path extending through the central body to the fuel inlet into the vane, wherein the fuel path extends through the vane in a non-straight direction about the divider from the fuel inlet to the fuel outlet, wherein the upstream cavity comprises a bypass adapted to channel fuel from the fuel path extending through the central body directly into the upstream cavity. 2. The system of claim 1, wherein the downstream cavity comprises another bypass adapted to channel fuel from the fuel path extending through the central body directly into the downstream cavity. 3. The system of claim 1, wherein the divider comprises a crossover passage through the divider, wherein the crossover passage is adapted to channel fuel from the downstream cavity directly into the upstream cavity. 4. The system of claim 1, wherein the vane is curved to create swirl in the air path. 5. The system of claim 1, wherein the central body comprises a fuel passage extending in a downstream axial direction and a reverse flow passage extending in an upstream axial direction, wherein the central body extends axially downstream away from the vane. 6. The system of claim 1, wherein the fuel outlet is angularly positioned on an outer surface of the vane. 7. The system of claim 1, comprising a combustor having the fuel nozzle, a turbine engine having the fuel nozzle, or a combination thereof. 8. The system of claim 1, wherein the fuel path extends through a substantial length of the vane in an upstream direction from the fuel inlet to the fuel outlet, and the upstream direction is generally opposite from a downstream direction of air flow along the air path. 9. A gas turbine fuel nozzle, comprising: a central body comprising: a multi-directional flow passage having a first flow passage configured to channel fuel in a first axial direction, anda second flow passage configured to channel fuel in a second axial direction opposite from the first axial direction;an outer tube disposed about the central body;an air path disposed between the central body and the outer tube;a vane disposed in the air path, wherein the vane comprises: a fuel inlet disposed in a downstream cavity of the vane relative to the first axial direction;a fuel outlet disposed in an upstream cavity of the vane relative to the first axial direction;a fuel path from the downstream cavity to the upstream cavity; anda bypass configured to channel fuel to the upstream cavity independent from the fuel path. 10. The gas turbine fuel nozzle of claim 9, wherein the bypass is configured to channel fuel from the multi-directional flow passage extending through the central body directly into the downstream cavity. 11. The gas turbine fuel nozzle of claim 9, wherein the bypass is configured to channel fuel from the multi-directional flow passage extending through the central body directly into the upstream cavity. 12. The gas turbine fuel nozzle of claim 11, comprising a second bypass configured to channel fuel from the multi-directional flow passage extending through the central body directly into the downstream cavity. 13. The gas turbine fuel nozzle of claim 9, comprising a divider disposed in the vane axially between the downstream cavity having the fuel inlet and the upstream cavity having the fuel outlet, wherein the divider routes the fuel path in a non-linear direction from the fuel inlet to the fuel outlet. 14. The gas turbine fuel nozzle of claim 13, wherein the divider comprises a crossover passage through the divider, wherein the crossover passage is adapted to channel fuel from the downstream cavity directly into the upstream cavity. 15. The gas turbine fuel nozzle of claim 9, wherein the vane comprises an airfoil shaped hollow body having the fuel inlet leading into the downstream cavity near a downstream tip of the vane, and the fuel path extends through the vane in the second axial direction along a substantial length of the vane. 16. A system, comprising: a turbine fuel nozzle, comprising: an air path through the turbine fuel nozzle;a fuel path through the turbine fuel nozzle;an air-fuel premixer disposed along the air path, wherein the air-fuel premixer comprises a swirl vane configured to swirl fuel and air in a downstream direction, wherein the swirl vane comprises:a fuel inlet;a fuel outlet; anda divider disposed in the swirl vane axially between a downstream cavity having the fuel inlet and an upstream cavity having the fuel outlet; anda fuel path extending through the turbine fuel nozzle to the fuel inlet into the swirl vane, wherein the fuel path extends through the swirl vane in a non-straight direction about the divider from the fuel inlet to the fuel outlet, wherein the turbine fuel nozzle comprises at least one of:an upstream bypass adapted to channel fuel from the fuel path extending through the turbine fuel nozzle directly into the upstream cavity; ora downstream bypass adapted to channel fuel from the fuel path extending through the turbine fuel nozzle directly into the downstream cavity; ora crossover passage extending through the divider and adapted to channel fuel from the downstream cavity directly into the upstream cavity. 17. The system of claim 16, comprising at least one of the upstream bypass or the downstream bypass. 18. The system of claim 16, comprising the crossover passage. 19. A system, comprising: a fuel nozzle, comprising: a central body;an outer tube disposed about the central body;an air path disposed between the central body and the outer tube;a vane disposed in the air path, wherein the vane comprises: a fuel inlet;a fuel outlet; anda divider disposed in the vane axially between a downstream cavity having the fuel inlet and an upstream cavity having the fuel outlet; anda fuel path extending through the central body to the fuel inlet into the vane, wherein the fuel path extends through the vane in a non-straight direction about the divider from the fuel inlet to the fuel outlet, wherein the downstream cavity comprises a bypass adapted to channel fuel from the fuel path extending through the central body directly into the downstream cavity. 20. The system of claim 19, wherein the vane is curved to create swirl in the air path. 21. The system of claim 19, wherein the central body comprises a fuel passage extending in a downstream axial direction and a reverse flow passage extending in an upstream axial direction, wherein the central body extends axially downstream away from the vane. 22. The system of claim 19, wherein the fuel outlet is angularly positioned on an outer surface of the vane. 23. The system of claim 19, comprising a combustor having the fuel nozzle, a turbine engine having the fuel nozzle, or a combination thereof. 24. The system of claim 19, wherein the fuel path extends through a substantial length of the vane in an upstream direction from the fuel inlet to the fuel outlet, and the upstream direction is generally opposite from a downstream direction of air flow along the air path. 25. A system, comprising: a fuel nozzle, comprising: a central body;an outer tube disposed about the central body;an air path disposed between the central body and the outer tube;a vane disposed in the air path, wherein the vane comprises: a fuel inlet;a fuel outlet; anda divider disposed in the vane axially between a downstream cavity having the fuel inlet and an upstream cavity having the fuel outlet, wherein the divider comprises: a crossover passage through the divider, and the crossover passage is adapted to channel fuel from the downstream cavity directly into the upstream cavity; anda fuel path extending through the central body to the fuel inlet into the vane, wherein the fuel path extends through the vane in a non-straight direction about the divider from the fuel inlet to the fuel outlet. 26. The system of claim 25, wherein the vane is curved to create swirl in the air path. 27. The system of claim 25, wherein the central body comprises a fuel passage extending in a downstream axial direction and a reverse flow passage extending in an upstream axial direction, wherein the central body extends axially downstream away from the vane. 28. The system of claim 25, wherein the fuel outlet is angularly positioned on an outer surface of the vane. 29. The system of claim 25, comprising a combustor having the fuel nozzle, a turbine engine having the fuel nozzle, or a combination thereof. 30. The system of claim 25, wherein the fuel path extends through a substantial length of the vane in an upstream direction from the fuel inlet to the fuel outlet, and the upstream direction is generally opposite from a downstream direction of air flow along the air path. 31. The system of claim 25, wherein the vane comprises a bypass adapted to channel fuel from the fuel path extending through the central body directly into the vane. 32. The system of claim 25, wherein the upstream cavity comprises the bypass adapted to channel fuel from the fuel path extending through the central body directly into the upstream cavity.
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