IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0758069
(2010-04-12)
|
등록번호 |
US-8613199
(2013-12-24)
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발명자
/ 주소 |
- Kimmel, Keith D.
- Laurello, Vincent P.
- Ebert, Todd
|
출원인 / 주소 |
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
32 |
초록
▼
A gas turbine engine includes a supply of cooling fluid, a rotatable shaft, structure defining at least one bypass passage in fluid communication with the supply of cooling fluid for supplying cooling fluid from the supply of cooling fluid, and metering structure located at an outlet of the at least
A gas turbine engine includes a supply of cooling fluid, a rotatable shaft, structure defining at least one bypass passage in fluid communication with the supply of cooling fluid for supplying cooling fluid from the supply of cooling fluid, and metering structure located at an outlet of the at least one bypass passage. The metering structure includes at least one flow passageway extending therethrough at an angle to a central axis of the engine for permitting cooling fluid in the bypass passage to pass into a turbine rim cavity. The cooling fluid flowing out of the flow passageway has a velocity component in a direction tangential to the circumferential direction in the same direction as a rotation direction of the shaft.
대표청구항
▼
1. A gas turbine engine comprising: a supply of cooling fluid;a rotatable shaft;a plurality of passages that deliver a first portion of cooling fluid from said supply of cooling fluid to a cooling circuit defined at least partially within blade disc structure associated with a first row of blades in
1. A gas turbine engine comprising: a supply of cooling fluid;a rotatable shaft;a plurality of passages that deliver a first portion of cooling fluid from said supply of cooling fluid to a cooling circuit defined at least partially within blade disc structure associated with a first row of blades in a turbine section of the engine;structure defining a plurality of bypass passages in fluid communication with said supply of cooling fluid for supplying a second portion of cooling fluid from said supply of cooling fluid, said plurality of bypass passages including a first set of bypass passages and a second set of bypass passages, the first and second sets of bypass passages having inlets that are located respectively in separate chambers of the gas turbine engine and in different radial locations; andmetering structure located at outlets of said bypass passages, said metering structure comprising a plurality of flow passageways extending therethrough at an angle to a central axis of the engine for permitting the second portion of cooling fluid in said bypass passages to pass into an enclosed turbine rim cavity upstream from the blade disc structure, wherein the cooling fluid flowing out of said flow passageways has a velocity component in a direction tangential to the circumferential direction in the same direction as a rotation direction of said shaft;wherein the second portion cooling fluid flowing from said supply of cooling fluid through said bypass passages does not interact with the first portion of cooling fluid flowing to the cooling circuit in the blade disc structure of the engine after the second portion of cooling fluid reaches said bypass passages. 2. The gas turbine engine of claim 1, wherein each said bypass passage communicates with a corresponding flow passageway extending through said metering structure for permitting cooling fluid in said respective bypass passage to pass through said corresponding flow passageway into the turbine rim cavity, wherein each said flow passageway diverts the cooling fluid flowing through said respective flow passageway such that the cooling fluid exiting said flow passageway has a velocity component in the direction tangential to the circumferential direction in the same direction as the rotation direction of said shaft. 3. The gas turbine engine of claim 2, wherein said metering structure comprises a ring-shaped metering member that extends circumferentially about said shaft, said metering structure comprising said plurality of flow passageways. 4. The gas turbine engine of claim 2, wherein the turbine rim cavity is enclosed by blade disc structure and stator structure and is located proximate to an engine hot gas flow path, wherein a sufficient amount of cooling fluid enters the turbine rim cavity from said flow passageways to adequately cool the blade disc structure and the stator structure and to prevent hot gas ingestion into the turbine rim cavity from the hot gas flow path. 5. The gas turbine engine of claim 4, wherein each said flow passageway has a diameter that is no larger than about half the size of a diameter of a corresponding one of said bypass passages. 6. The gas turbine engine of claim 1, wherein said flow passageways in said metering structure are formed at an angle of at least about 70° relative to the central axis of the engine. 7. The gas turbine engine of claim 1, further comprising a pre-swirl structure disposed about said shaft for supplying the first portion of cooling fluid from said supply of cooling fluid to the cooling circuit in the blade disc structure, said pre-swirl structure located radially inwardly from said metering structure, wherein said supply of cooling fluid supplies the first portion of cooling fluid to said pre-swirl structure such that the cooling fluid exiting said pre-swirl structure has a velocity component in a direction tangential to the circumferential direction in the same direction as the rotation direction of said shaft. 8. The gas turbine engine of claim 7, wherein a swirl ratio defined as the velocity component in the direction tangential to the circumferential direction of the cooling fluid exiting said flow passage outlet to a velocity component of said shaft in the direction tangential to the circumferential direction is greater than one. 9. The gas turbine engine according to claim 7, further comprising particle deflecting structure located downstream from said pre-swirl structure, said particle deflecting structure coupled to and extending radially inwardly from the blade disc structure, wherein said particle deflecting structure separates solid particles from the first portion of cooling fluid after the first portion of cooling fluid exits said pre-swirl structure. 10. The gas turbine engine according to claim 9, further comprising a particle collection chamber upstream from said particle deflecting structure, said particle collection chamber receiving said solid particles separated from the first portion of cooling fluid by said particle deflecting structure. 11. A gas turbine engine comprising: a supply of cooling fluid;a rotatable shaft;a plurality of passages that deliver a first portion of cooling fluid from said supply of cooling fluid to a cooling circuit defined at least partially within blade disc structure associated with a first row of blades in a turbine section of the engine;structure defining a plurality of bypass passages in fluid communication with said supply of cooling fluid for supplying a second portion of cooling fluid from said supply of cooling fluid to an enclosed turbine rim cavity upstream from the blade disc structure, said plurality of bypass passages including a first set of bypass passages and a second set of bypass passages, the first and second sets of bypass passages having inlets that are located respectively in separate chambers of the gas turbine engine and in different radial locations; andmetering structure extending circumferentially about said shaft, said metering structure comprising a plurality of flow passageways extending therethrough for permitting the second portion of cooling fluid in respective ones of said bypass passages to pass into the turbine rim cavity, wherein said flow passageways extend through said metering structure at an angle to a central axis of the engine for permitting cooling fluid in each said bypass passage to pass into the turbine rim cavity, wherein the cooling fluid flowing out of said flow passageways has a velocity component in a direction tangential to the circumferential direction in the same direction as a rotation direction of said shaft;wherein the second portion cooling fluid flowing from said supply of cooling fluid through said bypass passages does not interact with the first portion of cooling fluid flowing to the cooling circuit in the blade disc structure after the second portion of cooling fluid reaches said bypass passages. 12. The gas turbine engine of claim 11, wherein each said flow passageway comprises at least one bore formed through said metering structure, wherein said bores are formed at an angle of at least about 70° relative to the central axis of the engine. 13. The gas turbine engine of claim 11, wherein diameters of at least some of said flow passageways in said metering structure can be changed so as to control the amount of cooling fluid that is able to flow therethrough from respective ones of said bypass passages into the turbine rim cavity. 14. The gas turbine engine of claim 13, wherein each said flow passageway has a diameter that is no larger than about half the size of a diameter of a corresponding one of said bypass passages. 15. The gas turbine engine of claim 11, wherein a shaft cover structure comprises said structure that defines said plurality of bypass passages. 16. The gas turbine engine of claim 15, wherein said metering structure is received and affixed in a circumferentially extending slot formed in said shaft cover structure. 17. The gas turbine engine of claim 16, wherein the turbine rim cavity is enclosed by the blade disc structure and stator structure and is located proximate to an engine hot gas flow path, wherein a sufficient amount of cooling fluid enters the turbine rim cavity from the flow passageways to adequately cool the blade disc structure and the stator structure and to prevent hot gas ingestion into the turbine rim cavity from the hot gas flow path. 18. The gas turbine engine of claim 17, further comprising a pre-swirl structure disposed about said shaft for supplying the first portion of cooling fluid from said supply of cooling fluid to the cooling circuit in the blade disc structure, said pre-swirl structure located radially inwardly from said metering structure, wherein said supply of cooling fluid supplies the first portion of cooling fluid to said pre-swirl structure such that the cooling fluid exiting said pre-swirl structure has a velocity component in a direction tangential to the circumferential direction in the same direction as the rotation direction of said shaft. 19. The gas turbine engine according to claim 18, further comprising: particle deflecting structure located downstream from said pre-swirl structure, said particle deflecting structure coupled to and extending radially inwardly from the blade disc structure, wherein said particle deflecting structure separates solid particles from the first portion of cooling fluid after the first portion of cooling fluid exits said pre-swirl structure; anda particle collection chamber upstream from said particle deflecting structure, said particle collection chamber receiving said solid particles separated from the first portion of cooling fluid by said particle deflecting structure.
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