Abstract: A liquid ejecting apparatus includes a liquid ejecting head having a first-nozzle-row, a first-tank storing a first-liquid, a first-supply-flow-path for supplying the first-liquid to the first-nozzle-row from the first-tank, a first on-off valve provided in an intermediate portion of the first-supply-flow-path and configured to open and close the first-supply-flow-path, and a first-pressurizing-mechanism configured to pressurize an inside of the first-tank. A pressure inside the first-tank is set to a predetermined positive pressure by driving the first-pressurizing-mechanism in a closed state of the first on-off valve. Thereafter, a discharge process of discharging the first-liquid from the first-nozzle-row is performed by bringing the first on-off valve into an open state. In the discharge process, the first on-off valve is switched from the open state to the closed state at a timing at which the first-liquid is being continuously discharged from the first-nozzle-row.

Abstract: A strut cover for a gas turbine includes: a cylindrical sheet metal member having a hollow portion; and a flare member that is connected to one end of the cylindrical sheet metal member in an axial direction of the cylindrical sheet metal member and includes a curved portion having an outer surface such that a distance from a center axis of the cylindrical sheet metal member to the outer surface increases with increasing a distance from the cylindrical sheet metal member in the axial direction. The flare member has a thickness larger than a minimum thickness of the cylindrical sheet metal member at least in the curved portion.

Abstract: A strut cover for a gas turbine includes: a cylindrical sheet metal member having a hollow portion; and a flare member that is connected to one end of the cylindrical sheet metal member in an axial direction of the cylindrical sheet metal member and includes a curved portion having an outer surface such that a distance from a center axis of the cylindrical sheet metal member to the outer surface increases with increasing a distance from the cylindrical sheet metal member in the axial direction. The flare member has a thickness larger than a minimum thickness of the cylindrical sheet metal member at least in the curved portion.

Abstract: A terminal device which receives command information from a central device in a train information management system, includes a transmission-reception unit which transmits and receives the command information to and from the central device or other terminal device and periodically receives command information from a plurality of central devices, a control unit which determines whether or not management information, which is information on a train composition set by a central device which is a transmission source, regarding the received command information, is normal command information and determines command information to be adopted based on a priority set to the central device which is the transmission source when receiving the normal command information from the plurality of central devices, and a storage unit which stores information on the priorities set to the plurality of central devices.

Abstract: A gas turbine disk material according to the present invention contains: C: from 0.05 to 0.15%; Ni: from 0.25 to 1.50%; Cr: from 9.0 to 12.0%; Mo: from 0.50 to 0.90%; W: from 1.0 to 2.0%; V: from 0.10 to 0.30%; Nb: from 0.01 to 0.10%; Co: from 0.01 to 4.0%; B: from 0.0005 to 0.010%; N: from 0.01 to 0.05%; Mn: 0.40% or less; Si: 0.10% or less; and Al: 0.020% or less. A balance is of Fe and unavoidable impurities. Additionally, as a heat treatment method, a quenching temperature of a forged material having the component composition is set within a range from 1050 to 1150° C.

Abstract: An exhaust system and a gas turbine, in which the exhaust system includes an exhaust casing; an outer diffuser supported inside the exhaust casing; an inner diffuser disposed inside the outer diffuser to form an exhaust gas flow passage between the inner diffuser and the outer diffuser; a strut cover coupled at a first end to the outer diffuser and coupled at a second end to the inner diffuser; and a second cooling air introduction port provided in the exhaust casing, further on the downstream side of the exhaust gas flow passage than the strut cover. Furthermore, a non-perforated partition member having an annular shape is arranged so as to cover the outer side of the outer diffuser and is supported by the exhaust casing to form a cooling air flow passage.

Abstract: An object is to provide an in-train transmission control system which can minimize delay in transmission of command data to devices further than the conventional art, in which a central unit provided in any car of a train formation composed of one or more cars and controlling operation of the entire train formation transmits command data to devices provided in some or all of the cars and in which the devices transmit device data to the central unit. The control system comprises relay device provided in the car, and line concentrator allowing the command data to pass therethrough, and when receiving device data from the devices, transmitting the device data to the relay device. The relay device aggregates the device data received from the line concentrator to transmit the aggregated data to the central unit.

Abstract: A gas turbine combustor comprising a plurality of cooling air passages (27A) through which bled pressurized air flows from downstream of a combustion gas flow toward upstream, the plurality of cooling air passages (27A) being disposed in a wall portion (26) side by side and aligned in a flow direction of a combustion gas; wherein the plurality of cooling air passages (27A) are divided via a passage transition groove portion (33) into upstream cooling air passages (27A1) disposed closer to bled pressurized air inlet holes (30a) and downstream cooling air passages (27A2) disposed closer to bled pressurized air outlet holes (30b), and center lines (C1) of the upstream cooling air passages are non-collinear with center lines (C2) of the downstream cooling air passages.

Abstract: A terminal device which receives command information from a central device in a train information management system, includes a transmission-reception unit which transmits and receives the command information to and from the central device or other terminal device and periodically receives command information from a plurality of central devices, a control unit which determines whether or not management information, which is information on a train composition set by a central device which is a transmission source, regarding the received command information, is normal command information and determines command information to be adopted based on a priority set to the central device which is the transmission source when receiving the normal command information from the plurality of central devices, and a storage unit which stores information on the priorities set to the plurality of central devices.

Abstract: An object is to provide an in-train transmission control system which can minimize delay in transmission of command data to devices further than the conventional art, in which a central unit provided in any car of a train formation composed of one or more cars and controlling operation of the entire train formation transmits command data to devices provided in some or all of the cars and in which the devices transmit device data to the central unit. The control system comprises relay device provided in the car, and line concentrator allowing the command data to pass therethrough, and when receiving device data from the devices, transmitting the device data to the relay device. The relay device aggregates the device data received from the line concentrator to transmit the aggregated data to the central unit.

Abstract: The present invention provides an exhaust system and a gas turbine. The exhaust system includes: an exhaust casing; an outer diffuser supported inside the exhaust casing; an inner diffuser disposed inside the outer diffuser to form an exhaust gas flow passage between the inner diffuser and the outer diffuser; a strut cover coupled at one end to the outer diffuser and coupled at the other end to the inner diffuser; a second cooling air introduction port provided in the exhaust casing, further on the downstream side of the exhaust gas flow passage than the strut cover; a partition member having an annular shape so as to cover the outer side of the outer diffuser and supported by the exhaust casing; and a cooling air flow passage.

Abstract: The purpose of the invention is to provide a rotor blade support structure, wherein the concentration of stress near the rotor blade groove in which the rotor blade is embedded is limited even as increase in production cost is limited. A rotor blade support structure, in which rotor blades (30) are embedded in rotor blade grooves (10) provided on a rotor disc (1), wherein the rotor blade groove (10) is provided with circular direction grooves (13) that extend more in the circular direction of the rotor disc than upward from the bottom (14), and shaft center direction grooves (15) that are provided on the end faces (1a, 1b) of the rotor disc (1) in the center of the bottom (14) in the circular direction of the rotor disc and that extend towards the rotor disc shaft center.

Abstract: A gas turbine combustor comprising a plurality of cooling air passages (27A) through which bled pressurized air flows from downstream of a combustion gas flow toward upstream, the plurality of cooling air passages (27A) being disposed in a wall portion (26) side by side and aligned in a flow direction of a combustion gas; wherein the plurality of cooling air passages (27A) are divided via a passage transition groove portion (33) into upstream cooling air passages (27A1) disposed closer to bled pressurized air inlet holes (30a) and downstream cooling air passages (27A2) disposed closer to bled pressurized air outlet holes (30b), and center lines (C1) of the upstream cooling air passages are non-collinear with center lines (C2) of the downstream cooling air passages.

Abstract: The rotor structure is provided with a rotation shaft body in which a blade groove is formed at an outer circumference part, and extends in a circumferential direction of the axis line, and a plurality of blade bodies which are arrayed in the circumferential direction at the outer circumference part of the rotation shaft body, wherein a blade fixing piece is installed so as to be a positioned between at least one set of adjacent two blade bodies in the circumferential direction inside the blade groove, a projected part is formed at where either an opening wall part or the groove opening side of the blade groove and the blade fixing piece, and a recessed part which is fitted into the projected part is formed at where the other one of them.

Abstract: Disclosed is a compound represented by Formula (I) or a pharmaceutically acceptable salt thereof: wherein R1 is 1: a C3-8 cycloalkyl C1-4 alkyl group, 2: a C7-14 aralkyl group, in which the aryl moiety thereof is optionally substituted with the same or different 1 to 3 groups selected from the group consisting of: (a) halogen, (b) C1-4 alkyl, which is optionally substituted with 1 to 3 fluorine atoms, (c) C1-4 alkoxy, which is optionally substituted with 1 to 3 fluorine atoms, and (d) C1-4 alkylcarbonyl, which is optionally substituted with C1-4 alkoxy, 3: a five-to ten-membered heteroaryl-C1-4 alkyl group, in which the heteroaryl moiety thereof is optionally substituted with the same or different 1 to 3 groups selected from the group consisting of: (a) halogen, and (b) C1-4 alkyl, or 4: a C6-10 aryl C2-6 alkenyl group; and R2 is a cyano group or a nitro group.

Abstract: The purpose of the invention is to provide a rotor blade support structure, wherein the concentration of stress near the rotor blade groove in which the rotor blade is embedded is limited even as increase in production cost is limited. A rotor blade support structure, in which rotor blades (30) are embedded in rotor blade grooves (10) provided on a rotor disc (1), wherein the rotor blade groove (10) is provided with circular direction grooves (13) that extend more in the circular direction of the rotor disc than upward from the bottom (14), and shaft center direction grooves (15) that are provided on the end faces (1a, 1b) of the rotor disc (1) in the center of the bottom (14) in the circular direction of the rotor disc and that extend towards the rotor disc shaft center.

Abstract: The rotor structure is provided with a rotation shaft body in which a blade groove is formed at an outer circumference part, and extends in a circumferential direction of the axis line, and a plurality of blade bodies which are arrayed in the circumferential direction at the outer circumference part of the rotation shaft body, wherein a blade fixing piece is installed so as to be a positioned between at least one set of adjacent two blade bodies in the circumferential direction inside the blade groove, a projected part is formed at where either an opening wall part or the groove opening side of the blade groove and the blade fixing piece, and a recessed part which is fitted into the projected part is formed at where the other one of them.

Abstract: Disclosed is a compound represented by Formula (I) or a pharmaceutically acceptable salt thereof: wherein R1 is 1: a C3-8 cycloalkyl C1-4 alkyl group, 2: a C7-14 aralkyl group, in which the aryl moiety thereof is optionally substituted with the same or different 1 to 3 groups selected from the group consisting of: (a) halogen, (b) C1-4 alkyl, which is optionally substituted with 1 to 3 fluorine atoms, (c) C1-4 alkoxy, which is optionally substituted with 1 to 3 fluorine atoms, and (d) C1-4 alkylcarbonyl, which is optionally substituted with C1-4 alkoxy, 3: a five- to ten-membered heteroaryl-C1-4 alkyl group, in which the heteroaryl moiety thereof is optionally substituted with the same or different 1 to 3 groups selected from the group consisting of: (a) halogen, and (b) C1-4 alkyl, or 4: a C6-10 aryl C2-6 alkenyl group; and R2 is a cyano group or a nitro group.