Abstract: A gas turbine plant is provided with a gas turbine, a heating device, a decomposition gas line, and a decomposition gas compressor. The heating device heats ammonia and thermally decomposes the ammonia to convert the ammonia into decomposition gas including hydrogen gas and nitrogen gas. The decomposition gas line sends the decomposition gas PG from the heating device to the gas turbine. The decomposition gas compressor increases the pressure of the decomposition gas to a pressure equal to or higher than a feed pressure at which the decomposition gas is allowed to be fed to the gas turbine.

Abstract: A combustor nozzle includes a nozzle main body extending along an axis. The nozzle main body includes a first fuel passage which is formed along the axis and through which first fuel flows, a first fuel ejection passage which extends to an outer circumferential surface of the nozzle main body toward a distal end side thereof from the first fuel passage and ejects the first fuel from the outer circumferential surface, an air flow passage which extends in an axial direction on a radial outer side of the first fuel passage with respect to the axis and through which purge air flows, and an air ejection passage which extends from the air flow passage toward a center of a distal end of the nozzle main body and ejects the purge air from the center of the distal end.

Abstract: A hydrogen/oxygen stoichiometric combustion turbine system includes: a high-pressure steam turbine (2); a low-pressure steam turbine (3); and a heater (5) disposed between the high-pressure and low-pressure steam turbines. The heater (5) has a combustion portion (53) in which stoichiometric combustion of hydrogen and oxygen is caused, and a mixing portion (55) configured to mix discharged steam (S4) from the high-pressure steam turbine (2) with combustion gas (R) from the combustion portion (53) and to supply the obtained product to the low-pressure steam turbine (3).

Abstract: There is provided a CNTs wire capable of materializing a low resistivity and improving the electroconductivity. The CNT wire is formed from a single CNT aggregate constituted of a plurality of CNTs . . . having a single- or multi-walled structure, or formed by bundling a plurality of the CNT aggregates. The proportion of the total number of the CNTs having a double-walled or triple-walled structure based on the number of the plurality of CNTs constituting the CNT wire is 75% or higher; the proportion of the total number of the CNTs having an average diameter of the innermost wall of 1.7 nm or smaller based on the number of the CNTs constituting the CNT wire is 75% or higher; and the full-width at half maximum ?? in azimuth angle in azimuth intensity distribution by SAXS indicating orientation of the plurality of CNT aggregates is 60° or smaller.

Abstract: An ice maker 1 includes an ice making tray 5, a driving unit 6 configured to flip the ice making tray 5 around a predetermined axis, a water supply mechanism 8, and a control unit 19 configured to control driving of the driving unit 6 and the water supply mechanism 8, and a setting switch 22 configured to set a water supply time of water to be supplied from the water supply mechanism 8 to the ice making tray 5. If the water supply time is set to a first water supply time, a second water supply time, or a third water supply time by the operation on the setting switch 22 (steps ST20, ST25, ST28), the ice maker 1 performs a setting confirmation operation to swing the ice making tray 5 the number of times corresponding to the set water supply time (steps ST21, ST26, ST29).

Abstract: A low-resistivity carbon nanotube aggregate includes a plurality of carbon nanotubes each having one or more walls, wherein a ratio of a total number of carbon nanotubes that have two or three walls relative to a total number of said plurality of carbon nanotubes is 75% or greater, and wherein, in a G band of a Raman spectrum in the Raman spectroscopy of the plurality of carbon nanotubes, a G+/Gtotal ratio that is indicative of an amount of semiconductor carbon nanotubes relative to metallic carbon nanotubes is 0.70 or greater.

Abstract: An ice making machine may include an ice tray, a drive unit which is provided at one end of the ice tray and is structured to turn the ice tray, a frame body which supports the ice tray and the drive unit, and a cold air duct which connects an opening formed in the frame body with the cold air supply port. The frame body is provided with a wall part which faces the drive unit at the other end of the ice tray and the opening is formed in the wall part. The cold air duct is provided with an inclined flow passage part inclined with respect to a direction where an ice making recessed part in the ice tray is opened, and the inclined flow passage part is provided with a cold air blowing outlet which faces the ice making recessed part.

Abstract: An ice making machine may include an ice tray, a drive unit that turns the ice tray, a frame body supporting the ice tray and the drive unit, a cold air guide part integrally formed with the frame body, and a cold air duct connecting an opening in the frame body with a cold air supply port. The frame body includes a wall part at an end of the ice tray, the wall part is formed with the opening and the cold air guide part, and the cold air guide part flows cold air through the opening toward the ice tray. The cold air guide part is a frame body side inclined wall and the cold air duct includes a duct side inclined wall facing the frame body side inclined wall and a cold air blowing outlet includes the frame body side inclined wall and the duct side inclined wall.

Abstract: A burner assembly for a combustor includes: a plurality of first nozzles arranged in a circumferential direction of the combustor; a plurality of first burner cylinders accommodating the respective first nozzles; and a middle-flow-passage forming portion which is connected to a downstream end of the plurality of first burner cylinders and which forms a middle flow passage through which a combustion chamber of the combustor is in communication with an interior space of each of the plurality of first burner cylinders. The middle-flow-passage forming portion includes an inner peripheral wall disposed on a radially inner side of the combustor and formed such that a distance from a center axis of the combustor to the inner peripheral wall is uneven with respect to the circumferential direction.

Abstract: Provided are an ice making device and a method of inspecting the same. In the ice making device, signal lines extending from a temperature sensor are connected to a drive unit. The drive unit performs an ice removal process of removing ice from an ice making tray when a temperature detected by the temperature sensor is equal to or lower than a set temperature. The drive unit performs a sensor inspection process of automatically inspecting whether the temperature sensor is abnormal based on an inspection execution command issued by an operation of a test switch during general processes including supplying water to the ice making tray and an ice making process. Thus, inspection of a drive mechanism of the drive unit and inspection of the temperature sensor can be performed in a series of operations.

Abstract: An ice making device is provided. In an ice making device, a convex part reflecting the shape of a recessed part for water storage is formed on a bottom surface of the ice making tray. A temperature sensor is in contact with a side wall of the convex part. The temperature sensor is covered with a flexible member. In addition, a cover member pressing the temperature sensor against the ice making tray is fixed to the bottom surface of the ice making tray through the flexible member. In the temperature sensor, a sealing coating layer is provided to cover a temperature detection chip, but an exterior case is not used.

Abstract: A gas turbine combustor and a gas turbine; wherein inclined surfaces are provided on inner surfaces of side walls neighboring in a circumferential direction at downstream end portions of transition pieces of combustors, the inclined surfaces being configured to increase a passage area of the transition pieces, a ratio (S/P) is from 0 to 0.2, where (P) is a pitch dimension of first stage vanes, and (S) is a circumferential dimension from an intermediate point between neighboring transition pieces to an upstream end of a first stage vane closest in the circumferential direction; and a ratio (L/P) is from 0.3 to 0.55, where (P) is the pitch dimension, and (L) is an axial dimension from a downstream end of the transition piece to the upstream end of the first stage vane.

Abstract: Provided is a combustor that is made compact and achieves NOx reduction.

Abstract: In a damping device according to the present invention, a damping device 63 is mounted on a bypass pipe 61 that supplies an amount of high-pressure air to a combustor transition piece 33. The damping device 63 includes a fluid introducing unit 71 that forms a fluid introduction space B by covering an outer peripheral portion of the bypass pipe 61, a plurality of acoustic boxes 73a and 73b that forms resonance spaces Da and Db with the base portions connected to the fluid introducing unit 71 and the end portions extending along the outer peripheral portion of the bypass pipe 61 in the circumferential direction, and partition plates 74a and 74b that form resonance ducts Ea and Eb of a predetermined length by partitioning the resonance spaces Da and Db.

Abstract: A fuel control method for a gas turbine with a combustor being formed of at least two groups of a pluralities of main nozzles for supplying fuel, and that supplies fuel from the main nozzles of all groups upon ignition of the combustor (S1), and supplies fuel from three main nozzles of a group A during subsequent acceleration of the gas turbine (S3). Because fuel is injected from a small number of the main nozzles during acceleration, the fuel flow rate per one main nozzle is increased, thereby increasing the fuel-air ratio (fuel flow rate/air flow rate) in a combustion region and improving the combustion characteristics. Accordingly, the generation of carbon monoxide and unburned hydrocarbon is reduced, whereby no bypass valve is required and manufacturing costs are reduced.

Abstract: A cylinder for a combustor provided with a cylindrical member, a first cooling passage and a second cooling passage formed in the cylindrical member, and a supply port extended portion. The first cooling passage includes a supply port that opens to an outer peripheral surface of the cylindrical member. The second cooling passage includes a discharge port that opens to the outer peripheral surface of the cylindrical member downstream of the supply port. The supply port extended portion includes a first wall portion disposed between the supply port and the discharge port extending away from the outer peripheral surface of the cylindrical member and a second wall portion disposed upstream of the supply port extending away from the outer peripheral surface of the cylindrical member.

Abstract: A combustion burner including a fuel nozzle, a burner tube that surrounds the fuel nozzle to form an air passage between the burner tube and the fuel nozzle, swirler vanes that are arranged in a plurality of positions in a circumferential direction on an external circumferential surface of the fuel nozzle, each of which extends along an axial direction of the fuel nozzle, and gradually curves from upstream to downstream, a liquid fuel injecting hole that is formed on the fuel nozzle, and from which a liquid fuel is injected to a vane pressure surface of each of the swirler vanes, and a cooling unit that cools a part of the vane pressure surface on which the liquid fuel hits. The cooling unit injects a mixed fuel prepared by mixing water and the liquid fuel evenly from the liquid fuel injecting hole to the vane pressure surface of the swirler vane.

Abstract: A combustion burner including a fuel nozzle, a burner tube that surrounds the fuel nozzle to form an air passage between the burner tube and the fuel nozzle, swirler vanes that are arranged in a circumferential direction on an external circumferential surface of the fuel nozzle, a liquid fuel injecting hole that is formed on the fuel nozzle, and from which a liquid fuel is injected to a vane pressure surface of each of the swirler vanes, and a cooling unit that cools a part of the vane pressure surface on which the liquid fuel hits. The cooling unit includes a multi-purpose injecting hole that is arranged on the vane pressure surface of each of the swirler vanes, and from which a gas fuel is injected during gas combustion, and water is injected to the vane pressure surface of the swirler vane during combustion of the liquid fuel.

Abstract: A combustion burner including a fuel nozzle, a burner tube that surrounds the fuel nozzle to form an air passage between the burner tube and the fuel nozzle, swirler vanes that are arranged a circumferential direction on an external circumferential surface of the fuel nozzle, each of which extends along an axial direction of the fuel nozzle, and gradually curves from upstream to downstream so as to swirl air flowing in the air passage from the upstream to the downstream, a liquid fuel injecting hole that is formed on the fuel nozzle, and from which a liquid fuel is injected to a vane surface of each of the swirler vanes, and a cooling unit that cools a part of the vane surface on which the liquid fuel hits. The cooling unit includes a water cooling circuit formed inside the swirler vane.

Abstract: In a damping device according to the present invention, a damping device 63 is mounted on a bypass pipe 61 that supplies an amount of high-pressure air to a combustor transition piece 33. The damping device 63 includes a fluid introducing unit 71 that forms a fluid introduction space B by covering an outer peripheral portion of the bypass pipe 61, a plurality of acoustic boxes 73a and 73b that forms resonance spaces Da and Db with the base portions connected to the fluid introducing unit 71 and the end portions extending along the outer peripheral portion of the bypass pipe 61 in the circumferential direction, and partition plates 74a and 74b that form resonance ducts Ea and Eb of a predetermined length by partitioning the resonance spaces Da and Db.