Gas turbine and gas-turbine plant having the same
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/30
F02C-007/232
F01D-025/12
F02C-003/30
F02C-009/40
F23R-003/34
F23R-003/36
F02C-007/14
F02C-007/22
F02C-007/228
F23R-003/28
출원번호
US-0806961
(2011-10-27)
등록번호
US-9347377
(2016-05-24)
우선권정보
JP-2010-242397 (2010-10-28)
국제출원번호
PCT/JP2011/074853
(2011-10-27)
§371/§102 date
20121226
(20121226)
국제공개번호
WO2012/057282
(2012-05-03)
발명자
/ 주소
Murakami, Masayuki
Higashi, Kazuya
Nakamoto, Yukimasa
Fujii, Satoko
Shimizu, Takeyuki
Matsumoto, Keigo
출원인 / 주소
MITSUBISHI HITACHI POWER SYSTEMS, LTD.
대리인 / 주소
Westerman, Hattori, Daniels & Adrian, LLP
인용정보
피인용 횟수 :
0인용 특허 :
8
초록▼
The invention provides a gas-turbine fuel nozzle that includes a plurality of fuel supply channels to which fuel is supplied, a plurality of fuel/sweep-fluid supply channels to which fuel or a sweep fluid for sweeping the fuel is supplied, and a plurality of injection holes that are provided at down
The invention provides a gas-turbine fuel nozzle that includes a plurality of fuel supply channels to which fuel is supplied, a plurality of fuel/sweep-fluid supply channels to which fuel or a sweep fluid for sweeping the fuel is supplied, and a plurality of injection holes that are provided at downstream ends of the fuel supply channels or the fuel/sweep-fluid supply channels and that inject the fuel guided from the fuel supply channels or the fuel/sweep-fluid supply channels; a sweep-fluid supply channel that is connected to the fuel/sweep-fluid supply channels to guide the sweeping; and sweep-fluid cooling means for cooling the sweep-fluid to a temperature lower than a self-ignition temperature of the fuel.
대표청구항▼
1. A gas turbine comprising: a gas-turbine fuel nozzle that includes a plurality of fuel supply channels to which fuel gas is supplied, a plurality of fuel/sweep-fluid supply channels which are separated from the fuel supply channels and to which one of fuel gas and a sweep fluid for sweeping the fu
1. A gas turbine comprising: a gas-turbine fuel nozzle that includes a plurality of fuel supply channels to which fuel gas is supplied, a plurality of fuel/sweep-fluid supply channels which are separated from the fuel supply channels and to which one of fuel gas and a sweep fluid for sweeping the fuel gas is selectively and switchably supplied, and a plurality of injection holes that are provided at downstream ends of the fuel supply channels and the fuel/sweep-fluid supply channels and that inject the fuel gas or the sweep fluid guided from the fuel supply channels or the fuel/sweep-fluid supply channels; anda sweep-fluid supply channel that is connected to the fuel/sweep-fluid supply channels and guides the sweep fluid;wherein the gas turbine is configured to continuously supply the sweep fluid to the fuel/sweep-fluid supply channels while the fuel gas is not supplied to the fuel/sweep-fluid supply channels,the gas turbine further comprising sweep-fluid cooling means for cooling the sweep fluid to a temperature lower than a self-ignition temperature of the fuel gas. 2. The gas turbine according to claim 1, wherein the sweep-fluid supply channel is for connecting the fuel/sweep-fluid supply channels and a casing of the gas turbine, and configured to guide, as the sweep fluid, air in the casing to the fuel/sweep-fluid supply channels; andthe sweep-fluid cooling means is a plurality of projections that are provided around the sweep-fluid supply channel. 3. The gas turbine according to claim 2, wherein the plurality of projections are provided adjacent to suction ports for ventilation fans provided on a gas-turbine outer case that encloses the gas turbine. 4. The gas turbine according to claim 1, wherein the sweep-fluid supply channel is connected to the fuel/sweep-fluid supply channels and to a casing of the gas turbine and guides, as the sweep fluid, a fluid extracted from the casing; andthe sweep-fluid cooling means is heat-exchange means that is provided in the sweep-fluid supply channel and that performs heat exchange between a cooling medium and the sweep fluid. 5. The gas turbine according to claim 4, wherein the heat-exchange means is a gas-turbine cooling-air cooler; andthe sweep fluid is part of the fluid cooled by the gas-turbine cooling-air cooler. 6. The gas turbine according to claim 4, wherein the heat-exchange means is of a water cooling type that uses water as the cooling medium. 7. A gas turbine according to claim 1, wherein the sweep-fluid cooling means is a compressor that supplies compressed air at a temperature lower than a self-ignition temperature of the fuel gas to the sweep-fluid supply channel as the sweep-fluid. 8. The gas turbine according to claim 1, further comprising a fuel-flow-rate control valve that is provided on a channel which is provided at an upstream side of the fuel/sweep-fluid supply channels and that controls the flow rate of the fuel gas, a fuel-pressure control valve that is provided on the channel and that controls the pressure of the fuel gas, atmospheric discharge pipe branching out from the pipe at a portion between the fuel-flow-rate control valve and the fuel-pressure control valve, and a vent valve provided on the atmospheric discharge pipe. 9. The gas turbine according to claim 1, wherein the sweep-fluid supply channel comprises a sweep-fluid supply on-off valve on a downstream side of the sweep-fluid cooling means and a sweep-fluid discharge channel that extends from a portion between the sweep-fluid cooling means and the sweep-fluid supply on-off valve;the sweep-fluid discharge channel comprises a sweep-fluid discharge on-off valve; andwhen the gas turbine is started-up, the sweep-fluid supply on-off valve is completely closed, and the sweep-fluid discharge on-off valve is completely opened. 10. The gas turbine according to claim 9, wherein the sweep-fluid supply on-off valves are provided with two on-off valves located at two positions on the downstream side relative to the sweep-fluid discharge channel,wherein the gas turbine further comprises a sweep-fluid depressurizing channel branching off from a portion of the sweep-fluid supply channel at a position between the two sweep-fluid supply on-off valves,wherein the sweep-fluid depressurizing channel comprises a sweep-fluid depressurizing on-off valve that is operated in conjunction with actuation of at least one of the two sweep-fluid supply on-off valves; andwherein the sweep-fluid depressurizing on-off valve is completely opened when at least one of the two sweep-fluid supply on-off valves is completely closed. 11. The gas turbine according to claim 9, further comprising: a control device that has a load reduction function for reducing an operating load on the gas turbine and an emergency stop function for stopping the operation of the gas turbine,wherein the control device is configured to receive a signal which indicates degrees-of-opening of the sweep-fluid supply on-off valve,wherein the control device activates the emergency stop function and/or the load reduction function when the control device determines that the sweep-fluid supply on-off valves are in abnormal states based on the received signal indicating degrees-of-opening. 12. The gas turbine according to claim 10, wherein an orifice is provided on a downstream side of the sweep-fluid discharge on-off valve or on a downstream side of the sweep-fluid depressurizing on-off valve. 13. The gas turbine according to claim 1, further comprising: a temperature sensor that is provided on the downstream side of the sweep-fluid cooling means and detects the temperature of the sweep fluid taken out from the sweep-fluid cooling means; anda control device that has a load reduction function for reducing the operating load on the gas turbine,wherein the control device operates the load reduction function when the control device determines that the temperature of the sweep fluid detected by the temperature sensor is equal to or higher than a self-ignition temperature of the fuel gas. 14. The gas turbine according to claim 13, wherein, at a period of load rejection, the control device stops the supply of the sweep fluid and increases the flow rate of the fuel gas that is combusted by a premix method and that is supplied to the fuel supply channels. 15. The gas turbine according to claim 1, wherein the gas-turbine fuel nozzle is a pilot nozzle to which the fuel gas is guided, the fuel gas that is combusted by a diffusion method is supplied to the fuel/sweep-fluid supply channels, and the fuel gas that is combusted by a premix method is supplied to the fuel supply channels. 16. The gas turbine according to claim 1, wherein the gas-turbine fuel nozzle is a dual-fuel firing pilot nozzle to which the fuel gas or liquid fuel is guided, the fuel gas that is combusted by a diffusion method is supplied to the fuel/sweep-fluid supply channels, and the liquid fuel that is combusted by the diffusion method is supplied to the fuel supply channels. 17. The gas turbine according to claim 1, wherein the gas-turbine fuel nozzle is a main nozzle in which the fuel gas that is combusted by a premix method is supplied to the fuel/sweep-fluid supply channels, or the sweep fluid is supplied to the fuel/sweep-fluid supply channels; anda plurality of the main nozzles are provided, and the sweep fluid is supplied to some of the main nozzles according to the operation of the gas turbine. 18. A gas-turbine plant comprising a gas turbine according to claim 1. 19. A gas-turbine plant according to claim 18, further comprising a gas-turbine outer case that encloses the gas turbine.
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