Abstract: A gas turbine blade includes a hollow-blade-form portion formed by a leading edge on an upstream side of an working fluid of a gas turbine in a flow direction, a trailing edge on a downstream side of the working fluid in the flow direction, and a suction surface and a pressure surface reaching the trailing edge from the leading edge, and a shank portion for supporting the blade form portion. The blade also includes a partition for connecting the suction surface and the pressure surface in a hollow region of the blade-form portion, coolant paths formed by the partition, the suction surface, and the pressure surface, an impingement cooling hole formed in the partition for dividing the first path that is a flow path nearest to the leading edge side among the coolant paths and the second path adjacent to the first path, and first and second converter portions.

Abstract: Methods and apparatus are provided for inhibiting data writing to an optical disc drive connected to a computer. A BIOS confirms presence of a security function of an optical disc drive. When the optical disc drive possesses the security function, the BIOS delivers a command to the optical disc drive to set it to a read-only mode. The optical disc drive that has received the command sets the drive per se to operate in the read-only mode. Since a command for setting it to the read-only mode and a command for releasing it are delivered to the optical disc drive only by the BIOS, when a control is transferred to an Operating System (OS), setting of the read-only mode cannot be released by the OS and other OS's, or application software.

Abstract: Motive power supply equipment for a natural gas liquefaction plant includes gas turbine equipment having a compressor for compressing air, a combustor for generating combustion gases by burning a fuel and the compressed air from the compressor, and a turbine rotated by the combustion gases from the combustor. A low-temperature heat source supply system is provided which, during rated load operation of the gas turbine equipment, supplies carbon dioxide as a cooling medium to the gas turbine equipment in order to cool the gas turbine equipment. The carbon dioxide supplied is generated by separation from the natural gas in the natural gas purification equipment.

Abstract: Provided is a member having an internal cooling passage 7c formed therein and having opposed partition walls 6b, 6c between which a medium flows to cool a parent material, including a first heat transfer rib 25a which extends from almost the center between the opposed partition walls 6b, 6c to one partition wall 6c and slants in a downstream direction of the medium, and a second heat transfer rib 25b which extends from almost the center between the opposed partition walls 6b, 6c to the other partition wall 6b and slants in the downstream direction of the medium, wherein a slit 70a or 70b which passes through between an upstream side of the cooling passage 7c and a downstream side thereof is formed in the first heat transfer rib 70a or the second heat transfer rib 70b.

Abstract: A material having an internal cooling passage is provided which reduces a recirculation area to perform effective cooling. In the internal cooling passage formed in the material there is a wall surface provided with cooling ribs thereon to allow a cooling medium to flow along the wall surface, and the cooling ribs are arranged so that a portion of the cooling medium flowing in the vicinity of the center of the wall surface included in the cooling passage is allowed to flow toward both side edges of the wall surface and so that a portion of the cooling medium flowing on a surface of the cooling ribs moves to conform to the surface of the cooling ribs and flows to the wall surface.

Abstract: There is provided a shroud structure for gas turbines capable of suppressing a drop in the amount of cooling air for cooling the inner shroud by reducing the amount of cooling air leakage that occurs along the cooling air path when feeding cooling air from the one-piece outer shroud to the inner shroud of the gas turbine and ensure more reliable cooling of the inner shroud. The gas turbine shroud structure contains a one-piece outer shroud, and an inner shroud retained on the inner circumferential side of the outer shroud in a structure divided into multiple inner shrouds along the periphery. An inner seal plate groove is formed on the outer circumference of the hook formed on the inner shroud, a seal plate is inserted in the inner seal plate groove, and the seal plate is mounted so that a section of the seal plate protrudes in the gap between the hook mechanism of the outer shroud and the inner shroud.

Abstract: A thin flat heat pipe capable of transporting heat even if it is bent is provided. The flat heat pipe comprises: a working fluid to be evaporated when heated and to be condensed when the heat dissipates; and a wick, which is formed by bundling a plurality of thin wires while twisting along a center axis thereof, and which is adapted to create a capillary pressure for returning the liquid phase working fluid to a portion where evaporation takes place. The wick is arranged over the entire length of the flat container while being in contact with both upper and lower inner faces of the container or with an inner side face of the container in a manner such that an inner space of the container for letting through an evaporated working fluid is not closed, and a contact portion between the wick and the container is fixed by sintering over the entire length of the wick.

Abstract: Provided is a member having an internal cooling passage 7c formed therein and having opposed partition walls 6b, 6c between which a medium flows to cool a parent material, including a first heat transfer rib 25a which extends from almost the center between the opposed partition walls 6b, 6c to one partition wall 6c and slants in a downstream direction of the medium, and a second heat transfer rib 25b which extends from almost the center between the opposed partition walls 6b, 6c to the other partition wall 6b and slants in the downstream direction of the medium, wherein a slit 70a or 70b which passes through between an upstream side of the cooling passage 7c and a downstream side thereof is formed in the first heat transfer rib 70a or the second heat transfer rib 70b.

Abstract: Provided is a member having an internal cooling passage 7c formed therein and having opposed partition walls 6b, 6c between which a medium flows to cool a parent material, including a first heat transfer rib 25a which extends from almost the center between the opposed partition walls 6b, 6c to one partition wall 6c and slants in a downstream direction of the medium, and a second heat transfer rib 25b which extends from almost the center between the opposed partition walls 6b, 6c to the other partition wall 6b and slants in the downstream direction of the medium, wherein a slit 70a or 70b which passes through between an upstream side of the cooling passage 7c and a downstream side thereof is formed in the first heat transfer rib 70a or the second heat transfer rib 70b.

Abstract: A gas turbine includes a nozzle vane and a sealing unit engaged with the nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel. The nozzle vane and the sealing unit are disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path. A plurality of engagement portions between the sealing unit and the nozzle vane are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, and a downstream one of the plurality of engagement portions has a contact interface formed in a direction across a turbine rotary shaft. A reduction in the thermal efficiency of the gas turbine can be suppressed.

Abstract: A gas turbine includes a nozzle vane and a sealing unit engaged with the nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel. The nozzle vane and the sealing unit are disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path. A plurality of engagement portions between the sealing unit and the nozzle vane are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, and a downstream one of the plurality of engagement portions has a contact interface formed in a direction across a turbine rotary shaft. A reduction in the thermal efficiency of the gas turbine can be suppressed.

Abstract: A power supply equipment (71) for natural gas liquefaction plant that supplies power to a natural gas liquefaction plant for liquefying the natural gas having impurities separated by a natural gas purification equipment (70). The power supply equipment comprises an air compressor (74); a combustion unit (75) for burning fuel with compressed air from the compressor to thereby generate a combustion gas; a gas turbine equipment (72) having a turbine rotated by the combustion gas from the combustion unit; and a cold heat source supply system (85) for, during the rated load operation of the gas turbine equipment, supplying carbon dioxide separated from the natural gas by the natural gas purification equipment to the gas turbine equipment as a cooling medium for the gas turbine equipment.

Abstract: An advanced humid air turbine power plant capable of suppressing condensation of moisture in a cooling channel, which is provided to cool a high-temperature component of a gas turbine, in a start up stage, a coast down stage, and a load varying state of the gas turbine. In the advanced humid air turbine power plant comprising a compressed air supply line for supplying compressed air generated by a compressor to the high-temperature component of the gas turbine, and a humidified air supply line for supplying humidified air generated in a humidifying tower to the high-temperature component of the gas turbine, the power plant further comprises valves capable of adjusting respective air flow rates in the compressed air supply line and the humidified air supply line.

Abstract: An advanced humid air turbine power plant capable of suppressing condensation of moisture in a cooling channel, which is provided to cool a high-temperature component of a gas turbine, in a start up stage, a coast down stage, and a load varying state of the gas turbine. In the advanced humid air turbine power plant comprising a compressed air supply line for supplying compressed air generated by a compressor to the high-temperature component of the gas turbine, and a humidified air supply line for supplying humidified air generated in a humidifying tower to the high-temperature component of the gas turbine, the power plant further comprises valves capable of adjusting respective air flow rates in the compressed air supply line and the humidified air supply line.

Abstract: A gas turbine includes a nozzle vane and a sealing unit engaged with the nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel. The nozzle vane and the sealing unit are disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path. A plurality of engagement portions between the sealing unit and the nozzle vane are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, and a downstream one of the plurality of engagement portions has a contact interface formed in a direction across a turbine rotary shaft. A reduction in the thermal efficiency of the gas turbine can be suppressed.

Abstract: A gas turbine includes a nozzle vane and a sealing unit engaged with the nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel. The nozzle vane and the sealing unit are disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path. A plurality of engagement portions between the sealing unit and the nozzle vane are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, and a downstream one of the plurality of engagement portions has a contact interface formed in a direction across a turbine rotary shaft. A reduction in the thermal efficiency of the gas turbine can be suppressed.

Abstract: A gas turbine includes a nozzle vane and a sealing unit engaged with the nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel. The nozzle vane and the sealing unit are disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path. A plurality of engagement portions between the sealing unit and the nozzle vane are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, and a downstream one of the plurality of engagement portions has a contact interface formed in a direction across a turbine rotary shaft. A reduction in the thermal efficiency of the gas turbine can be suppressed.

Abstract: Methods and apparatus are provided for inhibiting data writing to an optical disc drive connected to a computer. A BIOS confirms presence of a security function of an optical disc drive. When the optical disc drive possesses the security function, the BIOS delivers a command to the optical disc drive to set it to a read-only mode. The optical disc drive that has received the command sets the drive per se to operate in the read-only mode. Since a command for setting it to the read-only mode and a command for releasing it are delivered to the optical disc drive only by the BIOS, when a control is transferred to an Operating System (OS), setting of the read-only mode cannot be released by the OS and other OS's, or application software.

Abstract: An injector includes a boosting mechanism and a nozzle. The boosting mechanism boosts fuel, and the nozzle injects and supplies the fuel boosted by the boosting mechanism. The boosting mechanism includes a tubular piston and a column piston. The tubular piston has a bore, which extends through the tubular piston in a direction of a longitudinal axis of the tubular piston. The column piston is loosely received by the tubular piston and has an end portion, which projects from the tubular piston, and which is engaged with the tubular piston. The tubular piston is slidably received by a first cylinder. The end portion of the column piston is slidably received by a second cylinder, which is provided generally coaxially to the first cylinder, and which has a diameter different from that of the first cylinder.

Abstract: An injector includes a boosting mechanism and a nozzle. The boosting mechanism boosts fuel, and the nozzle injects and supplies the fuel boosted by the boosting mechanism. The boosting mechanism includes a tubular piston and a column piston. The tubular piston has a bore, which extends through the tubular piston in a direction of a longitudinal axis of the tubular piston. The column piston is loosely received by the tubular piston and has an end portion, which projects from the tubular piston, and which is engaged with the tubular piston. The tubular piston is slidably received by a first cylinder. The end portion of the column piston is slidably received by a second cylinder, which is provided generally coaxially to the first cylinder, and which has a diameter different from that of the first cylinder.