IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0409641
(2009-03-24)
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등록번호 |
US-8186933
(2012-05-29)
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발명자
/ 주소 |
- Doss, Jeyamani M.
- Deodhar, Subodh D.
- Meka, Hari K.
|
출원인 / 주소 |
|
대리인 / 주소 |
Sutherland Asbill & Brennan LLP
|
인용정보 |
피인용 횟수 :
4 인용 특허 :
15 |
초록
▼
Systems, methods and apparatus for passive purge flow control in a turbine are provided. Various embodiments of the invention include providing a path for air to flow to a bore of a rotor with a plurality of stacked wheels. The air flow path includes at least one inlet hole on a rotor structure and
Systems, methods and apparatus for passive purge flow control in a turbine are provided. Various embodiments of the invention include providing a path for air to flow to a bore of a rotor with a plurality of stacked wheels. The air flow path includes at least one inlet hole on a rotor structure and a plurality of holes in at least some of the stacked wheels. The method further involves control of air flow to the at least one inlet hole based at least in part on axial deflection between the rotor and an associated stator during the gas turbine operation. Additionally, a portion of the air flowing into the inlet hole is directed through the plurality of holes in the at least some of the stacked wheels to purge the rotor.
대표청구항
▼
1. A method of controlling radial temperature gradients in a rotor of a gas turbine, the method comprising: providing a path for air to flow to a bore of the rotor comprising a plurality of stacked wheels, wherein the path comprises at least one inlet hole on a rotor structure and a plurality of hol
1. A method of controlling radial temperature gradients in a rotor of a gas turbine, the method comprising: providing a path for air to flow to a bore of the rotor comprising a plurality of stacked wheels, wherein the path comprises at least one inlet hole on a rotor structure and a plurality of holes in at least some of the stacked wheels, andbased at least in part on axial deflection between the rotor and an associated stator during operation of the gas turbine, controlling air flow to the at least one inlet hole, wherein at least a portion of the air flow is directed through the plurality of holes in the stacked wheels. 2. The method of claim 1, wherein the stacked wheels comprise solid and annular wheels, and wherein the air flow is directed through a path around the annular wheels and through the solid wheels. 3. The method of claim 2, wherein the plurality of holes in the stacked wheels are located between about 0.2*R and about 0.65*R from a central axis of each wheel, where R is equal to the rim radius of the solid wheels. 4. The method of claim 1, wherein the axial deflection is between about 0.01 and about 0.5 inches. 5. The method of claim 1, wherein the air flow to the at least one inlet hole is controlled by a sealing device. 6. The method of claim 5, wherein the sealing device held from stator can relatively move with respect to rotor and cover at least a portion of the at least one inlet hole. 7. The method of claim 5, wherein the sealing device comprises one or more bristles mounted to an inner circumference of a sealing hub, wherein an outer circumference of the sealing hub mounts to one or more spokes, wherein the one or more spokes mount to an inner circumference of the stator, and wherein openings between the spokes permit axial air flow between the stator and rotor. 8. A system for controlling radial temperature gradients in a rotor of a gas turbine, the system comprising: an air flow path to a bore of the rotor comprising a plurality of stacked wheels, wherein the path comprises at least one inlet hole on a rotor structure and a plurality of holes in the stacked wheels; anda sealing device for controlling air flow to the at least one inlet hole based at least in part on axial deflection between the rotor and an associated stator during operation of the gas turbine, wherein at least a portion of the air flow is directed to purge at least one wheel through the plurality of holes in the stacked wheels. 9. The system of claim 8, wherein the stacked wheels comprise solid and annular wheels, and wherein the air flow is directed through a path around the annular wheels and through the solid wheels. 10. The system of claim 9, wherein the plurality of holes in the stacked wheels are located between about 0.2*R and about 0.65*R from a central axis of each wheel, where R is equal to the rim radius of the solid wheels. 11. The system of claim 8, wherein the at least one inlet hole on the rotor structure is in communication with a cavity defined within the rotor, wherein the cavity is in communication with a plurality of holes in the stacked wheels. 12. The system of claim 8, wherein the axial deflection is between about 0.01 and about 0.5 inches. 13. The system of claim 8, wherein the sealing device held from stator can relatively move with respect to rotor and cover at least a portion of the at least one inlet hole. 14. The system of claim 8, wherein the sealing device comprises one or more bristles mounted to an inner circumference of a sealing hub, wherein an outer circumference of the sealing hub mounts to one or more spokes, wherein the one or more spokes mount to an inner circumference of the stator, and wherein openings between the spokes permit axial air flow between the stator and rotor. 15. An apparatus for controlling radial temperature gradients in a rotor of a gas turbine, the apparatus comprising: an air flow path to a bore of the rotor comprising a plurality of stacked wheels, wherein the path comprises at least one inlet hole on a rotor structure and a plurality of holes in the stacked wheels; anda sealing device for controlling air flow to the at least one inlet hole based at least in part on axial deflection between the rotor and an associated stator during operation of the gas turbine, wherein at least a portion of the air flow is directed to purge at least one wheel through the plurality of holes in the stacked wheels. 16. The apparatus of claim 15, wherein the at least one inlet hole on the rotor structure is in communication with a cavity defined within the rotor, wherein the cavity is in communication with a plurality of holes in the stacked wheels. 17. The apparatus of claim 15, wherein the axial deflection is between about 0.01 and about 0.5 inches. 18. The apparatus of claim 15, wherein the sealing ring axial width is between approximately 0.06 and 0.5 inches. 19. The apparatus of claim 15, wherein the sealing device held from stator can relatively move with respect to rotor and cover at least a portion of the at least one inlet hole. 20. The apparatus of claim 15, wherein the sealing device comprises one or more bristles mounted to an inner circumference of a sealing hub, wherein an outer circumference of the sealing hub mounts to one or more spokes, wherein the one or more spokes mount to an inner circumference of the stator and wherein openings between the spokes permit axial air flow between the stator and rotor.
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