IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0912119
(2004-08-06)
|
우선권정보 |
DE-103 36 432(2003-08-08) |
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
9 인용 특허 :
6 |
초록
▼
A gas turbine (1), in particular in a power plant, has at least one combustion chamber (2) and an enclosed inner liner (3) which surrounds the combustion chamber (2) and an enclosed outer liner (4), having a stator (5) which has at least one vane row (6) with a plurality of vanes (7), a rotor (8) wh
A gas turbine (1), in particular in a power plant, has at least one combustion chamber (2) and an enclosed inner liner (3) which surrounds the combustion chamber (2) and an enclosed outer liner (4), having a stator (5) which has at least one vane row (6) with a plurality of vanes (7), a rotor (8) which has at least one blade row (9) with a plurality of blades (10), an air cooling arrangement (31) which is designed for cooling parts of the gas turbine (1) with air (L), and a steam cooling arrangement (32) which is designed for cooling parts of the gas turbine (1) with steam (D).
대표청구항
▼
What is claimed is: 1. A gas turbine comprising: at least one combustion chamber, an enclosed inner liner which surrounds the combustion chamber, and an enclosed outer liner; a stator having at least one vane row with a plurality of vanes; a rotor having at least one blade row with a plurality of
What is claimed is: 1. A gas turbine comprising: at least one combustion chamber, an enclosed inner liner which surrounds the combustion chamber, and an enclosed outer liner; a stator having at least one vane row with a plurality of vanes; a rotor having at least one blade row with a plurality of blades; an air cooling arrangement configured and arranged to cool parts of the gas turbine with air; and a steam cooling arrangement configured and arranged to cool parts of the gas turbine by steam, simultaneously with said air cooling arrangement; wherein the vanes comprise hub-side cover elements, and the steam cooling arrangement is configured and arranged at least for cooling the enclosed inner liner, the enclosed outer liner, the vanes, the hub-side cover elements of the vanes, or combinations thereof; further comprising a steam guide configured and arranged at the downstream end of said enclosed inner liner so that a steam film is produced downstream of the vane row, along a rotor lateral surface; or both. 2. The gas turbine as claimed in claim 1, further comprising: heat accumulation elements arranged downstream of the vane row; and wherein the air cooling arrangement is configured and arranged at least for cooling the blades, the heat accumulation elements, or both. 3. The gas turbine as claimed in claim 1, wherein the steam cooling arrangement is configured and arranged for cooling the vanes in a leading region, and the air cooling arrangement is designed for cooling the vanes in a trailing region. 4. The gas turbine as claimed in claim 1, further comprising: means for carrying out sequential combustion; a high-pressure combustion chamber with an enclosed inner liner which surrounds the high-pressure combustion chamber, and an enclosed outer liner; at least one high-pressure vane row having a plurality of high-pressure vanes; and at least one high-pressure blade row having a plurality of high-pressure blades. 5. The gas turbine as claimed in claim 4: wherein the high-pressure vanes comprise hub-side cover elements, and the steam cooling arrangement is configured and arranged at least for cooling the high-pressure vanes, the hub-side cover elements of the high-pressure vanes, the high-pressure blades, or combinations thereof; further comprising a steam guide configured and arranged so that a steam film is produced downstream of the high-pressure vane row along a rotor lateral surface; or both. 6. The gas turbine as claimed in claim 4, further comprising: heat accumulation elements arranged downstream of the high-pressure vane row; and wherein the air cooling arrangement is configured and arranged at least for cooling the enclosed inner liner of the high-pressure combustion chamber, the enclosed outer liner of the high-pressure combustion chamber, the trailing edge of the high-pressure vanes, the heat accumulation elements arranged downstream of the high-pressure vane row, or combinations thereof. 7. The gas turbine as claimed in claim 4, further comprising: a high-pressure compressor; and wherein the steam cooling arrangement is configured and arranged at least for partly cooling the high-pressure compressor. 8. The gas turbine as claimed in claim 4, further comprising: a steam turbine including a heat recovery boiler, the steam turbine being coupled to the gas turbine; and wherein the steam cooling arrangement is connected to the heat recovery boiler, for the extraction of steam. 9. A method of cooling a gas turbine, the gas turbine including: a combustion chamber having an enclosed inner liner which surrounds the combustion chamber, and an enclosed outer liner, a stator which has at least one vane row with a plurality of vanes, and a rotor which has at least one blade row with a plurality of blades, wherein the vanes comprise hub-side cover elements, and the steam cooling arrangement is configured and arranged at least for cooling the enclosed inner liner, the enclosed outer liner, the vanes, the hub-side cover elements of the vanes, or combinations thereof, further comprising a steam guide configured and arranged at the downstream end of said enclosed inner liner so that a steam film is produced downstream of the vane row, along a rotor lateral surface; or both, the method comprising: cooling parts of the gas turbine with air with an air cooling arrangement; and simultaneously cooling other parts of the gas turbine with steam with a steam cooling arrangement. 10. A power plant comprising a gas turbine as claimed in claim 1. 11. The method as claimed in claim 9, wherein the gas turbine is in a power plant.
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