摘要:
Provided is turbine plant using methanol as fuel in which working fluid is compressed by compressor 1 and led into combustor 2. A mixture of H2 and CO2 as fuel added with O2 is burned to generate high temperature gas, which works in high temperature turbine 3, flows through heat exchangers 4, 5 and returns partly to the compressor 1 and enters partly low pressure turbine 7 of a bottoming system to work. Condensed water from condenser 9 of the bottoming system is pressurized by pressure pump 10 and flows through the heat exchangers 4, 5 to become high temperature steam and to work in high pressure turbine 6. Exhaust gas thereof is mixed into the combustor 2. A mixture of methanol and water is supplied into reformer 13 to absorb heat from the heat exchanger 4 to be reformed into H2 and CO2, which is supplied into the combustor 2. A high temperature portion of the high temperature turbine 3 is cooled by cooling medium extracted from the compressor 1 outlet and high pressure turbine 6 outlet thereby reliability of the high temperature turbine 3 is enhanced.
摘要:
In a recovery type steam cooled gas turbine, dew condensation is prevented when feeding steam in a starting operation of the gas turbine, and penetration of high temperature combustion gas into a steam cooling passage is prevented. Also, residual steam is removed in the stopping operation of the gas turbine. The gas turbine (1) has moving and stationary blade steam cooling passages (4a, 4b). The steam from steam cooling pipes (9, 10) flows through these passages to cool them. The steam after cooling is recovered. In the starting operation of the gas turbine, air from a compressor (2) flows through a valve (15) and a flow rate regulator (7). Also, a portion of the air is subjected to a temperature adjustment in a temperature adjuster (5) and flows through three-way valves (11, 12) to a steam cooling passage (4a, 4b) to be discharged through three-way valves (13, 14) and a flow rate regulator valve (8) to warm the passages (4a, 4b). Also, valves (15, 16) are closed and a valve (17) is opened so that outside air or inert gas from a medium feed source (6) may flow. After the warming up operation in the starting operation, the three-way valves (11 to 14) are switched to allow the steam to flow from the pipes (9, 10) to the passages (4a, 4b) to perform cooling during regular operation. Furthermore, after the stopping operation, it is possible to purge the residual steam within the passages (4a, 4b) with air.
摘要:
The invention provides a gas turbine combined cycle structured such that an intermediate cooling device for cooling a compression air discharged from a low pressure compressor, so as to reduce a load of a high pressure compressor, is provided. The gas turbine combined cycle in accordance with the invention is structured such as to branch water from a condenser to a steam generating device for generating steam. Exhaust gas discharged from a steam turbine is condensed to water. Compression air discharged from a low pressure compressor is cooled by being supplied to an intermediate cooling device, and is then supplied to a high pressure compressor. Steam which heats and operates the steam turbine is generated by the heat recovered by the cooling of the compression air in the intermediate cooling device. Accordingly, there can be obtained a gas turbine combined cycle having the advantage of the conventional intermediate cooling type gas turbine combined cycle, but exhibiting an improved combined efficiency.
摘要:
A cooling structure around the output shaft of an L-shaped vertical gas turbine, for cooling the output shaft effectively by a natural ventilation. A gas generator 5 is arranged horizontally whereas an output turbine 1 is arranged vertically, and a pump or the like is driven by an output shaft 3. A cylinder 20 is fitted in a space 12 between the output shaft 3 and a cylindrical casing 13 and is fixed at a cylindrical flange 20a. Cooling air 30 is caused to flow upward from between the cylinder 20 and the output shaft 3 by the ejector effect of an exhaust gas from below a baseplate 8 and by the vacuum in the casing and then to flow downward from the upper end of the cylinder 20 between the cylinder 20 and the cylindrical casing 13, so that it flows out from the lower portion into the package. The output shaft of the L-shaped vertical type gas turbine having a compact narrow space is effectively cooled therearound by the natural ventilation without providing any fan or the like.
摘要:
In a recovery type steam-cooled gas turbine, a steam passage leading to a moving blade is provided on a central side of a rotor for reducing leakage of the steam. Cooling steam 70 of a low temperature and high pressure is led into moving blades 1, 2 through supply side steam passages 12, 13 and steam passages 15, 16. After being used for cooling, it flows into a cavity 22 through steam passages 16, 17 to be recovered as recovery steam 71 of a high temperature and low pressure at a rotor end 20 through recovery side steam passages 19, 21. The cooling steam 70 of low temperature and high pressure passes on an inner side of the recovery steam 71 in the rotor, hence there are fewer places from where the high pressure steam leaks outside as compared with the prior art, in which the high pressure steam is supplied from the outer side in the rotor, and the leakage amount of steam is reduced.
摘要:
A method for manufacturing ozone ice that is improved for its storage stability is provided. In the method, ice 11 including oxygen gas g2 as gas bubbles b is produced and the produced ice 11 is irradiated with ultraviolet radiation, then the oxygen gas g2 in the ice 11 is ozonized to manufacture ozone ice 1.
摘要:
A refrigerant supplied from a refrigerant supply pipe flows into a first space, being a passage of the refrigerant, from a space between first stage and second stage rotor disks. The refrigerant supplied to the first space is guided to second, third and forth spaces through a gap between a spindle bolt and a bolt hole, during which the rotor disks are warmed up or cooled. In the second stage rotor disk, a refrigerant through hole axially penetrating this rotor disk is provided near the center thereof. The refrigerant flowing into the first space passes through the refrigerant through hole to flow into the second space, to thereby promote the convection in the first, second, third and fourth spaces and equalization of temperatures in the rotor disks.
摘要:
A first stage rotor disk (50a) and a connecting member (30) on the compressor side are fixed by a spindle bolt (20). The spindle bolt (20) is covered with a tubular member (100), between the first stage rotor disk (50a) and the connecting member (30) on the compressor side.
摘要:
A combined cycle gas turbine system is improved to enhance a gas turbine efficiency and a combined efficiency by effecting steam-cooling of a combustor transition piece and a turbine blade. The combined cycle system has a gas turbine (8) having a generator (1), a compressor (2), a combustor (3), a blade cooling air cooler (4) and a turbine (6), a steam turbine (29) having a high pressure turbine (21), an intermediate pressure turbine (22) and a low pressure turbine (23), and a waste heat recovery boiler (9). Saturated water of a high pressure pump (27) is partially led into a demineralizer (118) and a water sprayer (116) for cooling steam to be supplied into a moving blade (52). The steam, after being used for cooling, is recovered into a reheater (20). Outlet steam of the high pressure turbine (21) is led into a stationary blade (53) for cooling thereof and the steam is then recovered into an inlet of the intermediate pressure turbine (22). Also, steam of an intermediate pressure superheater (16) is led into a combustor transition piece (54) for cooling thereof and the steam is recovered into the inlet of the intermediate pressure turbine (22). Thus, moving blade cooling steam is reduced and the combined efficiency is enhanced.
摘要:
The pressure ratio &Dgr;P4S of a final stage moving blade is reduced. As a result, the Mach number in the final stage moving blade can be suppressed, and in the gas turbine operating at a pressure ratio of 20 or more, therefore, decline of turbine efficiency due to shock wave loss can be prevented securely.