IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0628025
(2005-05-20)
|
등록번호 |
US-7780400
(2010-09-13)
|
우선권정보 |
DE-10 2004 026 366(2004-05-29) |
국제출원번호 |
PCT/DE2005/001042
(2005-05-20)
|
§371/§102 date |
20070424
(20070424)
|
국제공개번호 |
WO05/116406
(2005-12-08)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
3 인용 특허 :
14 |
초록
▼
An arrangement is provided for detecting a shaft break on a rotor of a first turbine, especially a medium pressure turbine, of a gas turbine machine, especially an aircraft engine. A second turbine (11), especially a low pressure turbine, is positioned downstream from the first turbine. An actuating
An arrangement is provided for detecting a shaft break on a rotor of a first turbine, especially a medium pressure turbine, of a gas turbine machine, especially an aircraft engine. A second turbine (11), especially a low pressure turbine, is positioned downstream from the first turbine. An actuating element (18) is positioned lying radially inwardly relative to a flow channel, between the rotor of the first turbine and a stator of the second turbine. A transmission element (22) is guided in the stator of the second turbine (11), in order to transmit a shaft break detected by the radially inwardly positioned actuating element (18) to a switching element (23) positioned radially outwardly relative to the flow channel on a housing (14) of the gas turbine.
대표청구항
▼
The invention claimed is: 1. Gas turbine machine comprising at least two compressors, at least one combustion chamber, at least first and second turbines, and an arrangement for the detection of a shaft break on a rotor of the first turbine, wherein the second turbine is positioned downstream from
The invention claimed is: 1. Gas turbine machine comprising at least two compressors, at least one combustion chamber, at least first and second turbines, and an arrangement for the detection of a shaft break on a rotor of the first turbine, wherein the second turbine is positioned downstream from the first turbine, characterized in that an actuating element (18) is positioned between the rotor of the first turbine and a stator of the second turbine (11) and lying radially inwardly adjacent to a rotor disc of the last rotor blade ring, as seen in the flow direction, of the first turbine, and is slidably guided in a radially inwardly lying seal structure (19) of the stator of the second turbine (11) to be slidable in the axial direction or in the flow direction, in that a transmission element (22) is slidably guided in the stator of the second turbine (11) to be slidable in the radial direction, in that the transmission element (22) cooperates at a radially inwardly lying end (25) with the actuating element (18) and cooperates at a radially outwardly lying end (26) with a switching element (23) that is positioned lying radially outwardly on a housing (14) of the gas turbine machine, and in that at least one elastically deformable spring element (21, 27) is arranged for mechanical coupling between the actuating element (18) and the transmission element (22) and/or between the transmission element (22) and the switching element (23). 2. Gas turbine machine according to claim 1, characterized in that the transmission element (22) is guided in a first guide vane ring (10), as seen in the flow direction, of the second turbine (11). 3. The gas turbine machine according to claim 1, wherein said gas turbine machine is an aircraft engine, said first turbine is a medium pressure turbine, and said second turbine is a low pressure turbine. 4. A gas turbine machine comprising: a first turbine including a rotor shaft and a first turbine rotor connected to said rotor shaft; a second turbine including a second turbine stator arranged downstream from said first turbine rotor with respect to a gas flow direction through a gas flow channel of said gas turbine machine; a housing that encloses circumferentially around said gas flow channel, said first turbine and said second turbine; a switching element arranged radially outwardly on said housing; an actuating element that extends from said second turbine stator toward said first turbine rotor, and that is slidably guided in said second turbine stator to be slidable in a first sliding direction having at least a directional component thereof extending parallel to said gas flow direction or parallel to an axis of said first and second turbines; a transmission element that is slidably guided in said second turbine stator to be slidable in a second sliding direction having at least a directional component thereof extending radially relative to said axis, wherein a radially inner end of said transmission element is mechanically coupled directly or indirectly with said actuating element and a radially outer end of said transmission element is mechanically coupled directly or indirectly with said switching element such that if said rotor shaft breaks then said first turbine rotor will strike against and cause a sliding displacement of said actuating element in said first sliding direction which will cause a sliding displacement of said transmission element in said second sliding direction which will cause a switching actuation of said switching element; and at least one elastically deformable spring element interposed between and mechanically coupling said actuating element and said radially inner end of said transmission element, and/or interposed between and mechanically coupling said radially outer end of said transmission element and said switching element. 5. The gas turbine machine according to claim 4, wherein said at least one elastically deformable spring element comprises a first elastically deformable spring element interposed between and mechanically coupling said actuating element and said radially inner end of said transmission element. 6. The gas turbine machine according to claim 5, wherein said first elastically deformable spring element includes a curved spring portion that bears against said radially inner end of said transmission element, and that has a curvature which depends on a sliding displacement position of said actuating element. 7. The gas turbine machine according to claim 5, wherein said at least one elastically deformable spring element further comprises a second elastically deformable spring element interposed between and mechanically coupling said radially outer end of said transmission element and said switching element. 8. The gas turbine machine according to claim 4, wherein said at least one elastically deformable spring element comprises an elastically deformable spring element interposed between and mechanically coupling said radially outer end of said transmission element and said switching element. 9. The gas turbine machine according to claim 8, wherein said elastically deformable spring element is an over-center-snapping spring with two stable oppositely curved positions in opposite directions relative to an unstable center position. 10. The gas turbine machine according to claim 8, wherein said elastically deformable spring element is a cup spring. 11. The gas turbine machine according to claim 4, wherein said switching element is an electrical or electronic switching element. 12. The gas turbine machine according to claim 4, further comprising a combustion chamber, a fuel supply system arranged and adapted to supply a fuel to said combustion chamber, and an electronic control adapted and connected to said fuel supply system so as to control said fuel supply system, wherein said switching element is connected to said electronic control and is adapted to switch said electronic control so as to shut off said fuel supply system upon actuation of said switching element. 13. The gas turbine machine according to claim 4, wherein said actuating element, said transmission element, and said at least one elastically deformable spring element are purely mechanical elements. 14. The gas turbine machine according to claim 4, wherein said actuating element is positioned radially inwardly adjacent to a rotor disc of a last rotor blade ring, as seen in said gas flow direction, of said first turbine. 15. The gas turbine machine according to claim 4, wherein said second turbine stator includes a radially inwardly lying seal structure, and said actuating element is slidably guided in said radially inwardly lying seal structure. 16. The gas turbine machine according to claim 4, wherein said first sliding direction of said actuating element extends parallel to said gas flow direction or parallel to said axis. 17. The gas turbine machine according to claim 4, wherein said second sliding direction of said transmission element extends radially relative to said axis.
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