Turbine frame cooling systems and methods of assembly for use in a gas turbine engine
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-025/14
F01D-011/00
F01D-017/08
F01D-017/10
F01D-017/14
F01D-025/12
F01D-025/24
F01D-009/06
F01D-025/16
F02C-007/12
출원번호
US-0041524
(2016-02-11)
등록번호
US-10151217
(2018-12-11)
발명자
/ 주소
Lipinski, Thomas
LaChapelle, Donald George
Moore, Kenneth Jay
Tracey, Bradford
Waymeyer, Stephen Joseph
출원인 / 주소
General Electric Company
대리인 / 주소
General Electric Company
인용정보
피인용 횟수 :
0인용 특허 :
14
초록▼
A turbine frame cooling system for use with a gas turbine engine includes an outer ring defining a cavity and a hub positioned radially inward of the outer ring. The turbine frame cooling system also includes a plurality of circumferentially-spaced first fairings coupled between the outer ring and t
A turbine frame cooling system for use with a gas turbine engine includes an outer ring defining a cavity and a hub positioned radially inward of the outer ring. The turbine frame cooling system also includes a plurality of circumferentially-spaced first fairings coupled between the outer ring and the hub and a plurality of circumferentially-spaced second fairings coupled between the outer ring and the hub, wherein the first and second fairings are alternatingly positioned about the hub. The turbine frame cooling system also includes a plurality of circumferentially-spaced air scoops coupled to the outer ring. The plurality of air scoops extend into a bypass stream and are configured to channel a bypass air cooling flow into the cavity of the outer ring.
대표청구항▼
1. A turbine frame cooling system for use with a gas turbine engine, said turbine frame cooling system comprising: an outer ring defining a cavity;a hub positioned radially inward of said outer ring;a plurality of circumferentially-spaced first fairings coupled between said outer ring and said hub;a
1. A turbine frame cooling system for use with a gas turbine engine, said turbine frame cooling system comprising: an outer ring defining a cavity;a hub positioned radially inward of said outer ring;a plurality of circumferentially-spaced first fairings coupled between said outer ring and said hub;a plurality of circumferentially-spaced second fairings coupled between said outer ring and said hub, wherein said pluralities of first and second fairings are alternatingly positioned about said hub;a plurality of circumferentially-spaced air scoops coupled to said outer ring, wherein said plurality of air scoops extend into a bypass stream and are configured to channel a bypass air cooling flow into the cavity; andfurther comprising a plurality of independent cooling circuits, wherein each cooling circuit comprises:an air scoop of said plurality of air scoops;a first fairing of said plurality of first fairings; anda second fairing of said plurality of second fairings, wherein said first fairing is positioned adjacent said second fairing. 2. The turbine frame cooling system in accordance with claim 1, wherein each cooling circuit of said plurality of cooling circuits comprises a seal coupled within the cavity and configured to define a plurality of independent circuit cavities within said outer ring, wherein each circuit cavity corresponds to a cooling circuit of said plurality of cooling circuits. 3. The turbine frame cooling system in accordance with claim 2, wherein each seal is positioned at a circumferentially downstream end of each cooling circuit. 4. The turbine frame cooling system in accordance with claim 1, wherein each air scoop is configured to channel a first portion of the cooling flow radially through said first fairing and a second portion of the cooling flow through said second fairing. 5. The turbine frame cooling system in accordance with claim 4, wherein the first portion of cooling air is at a first temperature and the second portion of cooling air is at a second temperature greater than the first temperature. 6. The turbine frame cooling system in accordance with claim 1, further comprising a plurality of struts coupled between said hub and said outer ring, wherein each strut is positioned within a corresponding second fairing of said plurality of second fairings. 7. The turbine frame cooling system in accordance with claim 1, further comprising a plurality of groups of fluid lines coupled between said hub and said outer ring, wherein each group of fluid lines is positioned within a corresponding first fairing of said plurality of first fairings. 8. The turbine frame cooling system in accordance with claim 1, further comprising a control system configured to control the cooling airflow through said plurality of air scoops. 9. The turbine frame cooling system in accordance with claim 8, wherein said control system comprises: at least one temperature sensor coupled to at least one of said first fairing, said second fairing, and said outer ring;at least one valve coupled to each air scoop of said plurality of air scoops, wherein said at least one valve controls entry of the cooling air into said air scoop; anda controller operatively coupled to said at least one sensor and said at least one valve, wherein said controller is configured to open said at least one valve upon receiving a signal from said at least one sensor representative of a predetermined temperature. 10. The turbine frame cooling system in accordance with claim 1, further comprising a plurality of circumferentially-spaced seals coupled within the cavity defined in said outer ring, wherein said plurality of seals are configured to limit the circumferential flow of the cooling air within the cavity. 11. A method of cooling a turbine frame of a gas turbine engine, said method comprising: channeling a cooling flow from a bypass duct through a plurality of air scoops coupled to an outer ring of a frame, wherein the plurality of scoops extend into the bypass duct;channeling a first portion of the cooling flow through a plurality of first fairings, wherein the plurality of first fairings are coupled between the outer ring and an inner hub;channeling a second portion of the cooling flow through a plurality of second fairings, wherein the plurality of second fairings are coupled between the outer ring and the inner hub and are alternatingly positioned with the plurality of first fairings; andfurther comprising coupling a plurality of seals with the outer ring to define a plurality of cooling circuits therein. 12. The method according to claim 11, wherein channeling the first portion of cooling flow comprises channeling the first portion of cooling flow along a plurality of fluid lines extending between the outer ring and the hub. 13. The method according to claim 12, wherein channeling the second portion of cooling flow comprises channeling the second portion of cooling flow along a plurality of struts extending between the outer ring and the hub. 14. The method according to claim 13, wherein channeling the first portion of cooling flow along a plurality of fluid lines comprises channeling the first portion of cooling flow along a plurality of fluid lines at a first temperature, and wherein channeling the second portion of cooling flow along a plurality of struts comprises channeling the second portion of cooling flow along a plurality of struts at a second temperature that is greater than the first temperature. 15. The method according to claim 11, wherein each cooling circuit includes: an air scoop of the plurality of air scoops;a first fairing of the plurality of first fairings; anda second fairing of the plurality of second fairings, wherein the first fairing is positioned adjacent the second fairing. 16. The method according to claim 15, further comprising channeling the cooling airflow through each cooling circuit such that the first portion of cooling flow in the circuit is channeled through the first fairing of the circuit and the second portion of cooling flow in the circuit is channeled through the second fairing of the circuit. 17. The method according to claim 11, further comprising controlling the cooling flow through the plurality of air scoops with a control system. 18. The method according to claim 17, wherein controlling the cooling flow comprises: measuring, using a sensor, a temperature of at least one of the first fairing, the second fairing, and the outer ring;operating, with a controller coupled to the sensor, a plurality of valves coupled to a corresponding air scoop of the plurality of air scoops based on the measured temperature.
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이 특허에 인용된 특허 (14)
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