Gas turbine, load coupling of gas turbine, and cooling method of gas turbine compressor
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-006/08
F04D-029/58
F01D-005/08
F01D-011/00
F02C-007/18
F04D-029/053
출원번호
US-0918606
(2009-01-08)
등록번호
US-9127693
(2015-09-08)
우선권정보
JP-2008-088751 (2008-03-28)
국제출원번호
PCT/JP2009/050135
(2009-01-08)
§371/§102 date
20100820
(20100820)
국제공개번호
WO2009/119127
(2009-10-01)
발명자
/ 주소
Hashimoto, Shinya
Arase, Kenichi
출원인 / 주소
MITSUBISHI HEAVY INDUSTRIES, LTD.
대리인 / 주소
Lowe Hauptman & Ham, LLP
인용정보
피인용 횟수 :
0인용 특허 :
5
초록▼
To include a cooling passage leading from a latter stage of a compressor, via an external cooler, to a hollow part provided in a load coupling that couples a rotor of the compressor and a rotor of a turbine to each other, and also leading from the hollow part to the latter stage of the compressor, a
To include a cooling passage leading from a latter stage of a compressor, via an external cooler, to a hollow part provided in a load coupling that couples a rotor of the compressor and a rotor of a turbine to each other, and also leading from the hollow part to the latter stage of the compressor, and a centrifugal compressor that raises air pressure in the hollow part with rotation of the load coupling, in the hollow part. Therefore, pressure of the air in the hollow part is raised by the centrifugal compressor by using a centrifugal force resulting from the rotation of the load coupling at the time of operating the gas turbine. Cooled air flows from the hollow part to between compressor rotor blades and compressor vanes at the latter stage, and then flows into the hollow part, thereby enabling to efficiently reduce temperature in the hollow part.
대표청구항▼
1. A gas turbine, comprising: a load coupling for coupling a rotor of a compressor and a rotor of the turbine to each other, and extending parallel to a central axis of the rotor;a centrifugal compressor configured by: a flange protruding from and orthogonal to the load coupling and away from the ce
1. A gas turbine, comprising: a load coupling for coupling a rotor of a compressor and a rotor of the turbine to each other, and extending parallel to a central axis of the rotor;a centrifugal compressor configured by: a flange protruding from and orthogonal to the load coupling and away from the central axis into a hollow part so as to divide the hollow part into a rear-side hollow part and a front-side hollow part, the hollow part being defined by the load coupling, a partition wall of the compressor and a disk on which a compressor rotor blade at a latter stage of the compressor is fixed; anda through hole communicating between the rear-side hollow part and the front-side hollow part, the through hole being provided in the flange, and air pressure in the rear-side hollow part being raised via the through hole with rotation of the load coupling; anda cooling passage leading from the latter stage of the compressor, via an outside of the compressor, to the rear-side hollow part, and also leading from the rear-side hollow part, via the through hole, to the latter stage of the compressor. 2. The gas turbine according to claim 1, wherein the through hole is provided to open radially inward on a first side of the flange and radially outward on a second side of the flange, the first and second sides axially opposite to each other. 3. The gas turbine according to claim 2, wherein a wall surface of the flange on the one side is formed in such a mode that an opening of the through hole faces the central axis of the rotor. 4. The gas turbine according to claim 1, wherein overlapping parts extending from opposite directions with ends thereof overlapping on each other are provided in a portion leading from the hollow part to the latter stage of the compressor. 5. The gas turbine according to claim 1, wherein a thermal insulation member having thermal insulation properties is provided on the partition wall present between the hollow part and a compressed air passage leading from the compressor to a combustor. 6. A cooling method of a gas turbine compressor, comprising: bleeding compressed air from a latter stage of a compressor to outside of a gas turbine;injecting cooled compressed air to a hollow part provided in a load coupling that couples a rotor of the compressor and a rotor of a turbine to each other, wherein the load coupling extends parallel to a central axis of the rotor; andcentrifugally compressing injected compressed air by rotation of the load coupling to raise a pressure thereof and by using a centrifugal compressor that includes: a flange protruding from and orthogonal to the load coupling and away from the central axis into the hollow part so as to divide the hollow part into a rear-side hollow part and a front-side hollow part, the hollow part being defined by the load coupling, a partition wall of the compressor and a disk on which a compressor rotor blade at the latter stage is fixed, anda through hole communicating between the rear-side hollow part and the front-side hollow part, the through hole being provided in the flange, and supplying compressed air from the hollow part to a cooling passage leading to the latter stage of the compressor,whereinair pressure in the rear-side hollow part is raised via the through hole with rotation of the load coupling, andthe cooling passage leads from the latter stage of the compressor, via an outside of the compressor, to the rear-side hollow part, and also leads from the rear-side hollow part, via the through hole, to the latter stage of the compressor.
연구과제 타임라인
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이 특허에 인용된 특허 (5)
Lenahan Dean Thomas (Cincinnati OH) Pedersen Poul D. (Cincinnati OH) Plemmons Larry Wayne (Fairfield OH) Glynn Christopher Charles (Hamilton OH) Miller Frederick M. (Cincinnati OH) Stover Curtis W. (, Compressor rotor cooling system for a gas turbine.
Simeone, Peter Andrew; Lenahan, Dean Thomas; Wigon, Jeremy Stephen; St. Hilaire, Alan Patrick; Iglesias, Dennis Centeno; McGovern, James Patrick, Methods and apparatus for cooling gas turbine engine rotor assemblies.
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