Abstract: A cooling wall includes: a wall surface defined by arrangement of central axes of a plurality of cooling tubes; and an opening formed in a part of the wall surface in which a burner is installable, each of the plurality of cooling tubes forming the opening has a straight portion and a curved portion, the plurality of cooling tubes include a first cooling tube whose first virtual axis extending in an axial direction of the straight portion overlaps the opening, and a second cooling tube whose second virtual axis extending in an axial direction of the straight portion is located outside an outer circumference of the opening in a radial direction, the curved portion of the first cooling tube is arranged so as to form a curve along the outer circumference surface of the opening and on a surface along the wall surface.

Abstract: A turbine stator blade (21) includes a pressure side (21P) extending in a radial direction intersecting a flow direction of steam, and facing upstream in the flow direction. A slit (5) extending in the radial direction and capturing a liquefied component of the steam is formed on a downstream side of the pressure side (21P). A hydrophilic uneven region (6) having a liquid film capacity greater than that of the pressure side (21P) by being recessed in a depth direction intersecting the pressure side (21P) is formed in a further upstream position than the slit (5). The hydrophilic uneven region (6) has a depth in the depth direction increasing and a flow resistance decreasing toward downstream and toward the slit (5).

Abstract: A transition piece includes a first flow passage group formed by arranging a plurality of intra-wall flow passages, a second flow passage group, and a plurality of dilution holes that penetrate a plate, and establish communication between a compressed air main flow passage and a combustion gas flow passage, each intra-wall flow passage of the first flow passage group and the second flow passage group having an inlet facing the compressed air main flow passage at an end portion on a side near the gas turbine, and having an outlet facing the combustion gas flow passage at an end portion on a side near the combustor liner, a dilution hole being located nearer to the inlet of an intra-wall flow passage of the second flow passage group than to the outlet of the intra-wall flow passage of the second flow passage group.

Abstract: A method and system for measuring a turbine shape is provided in which an appropriate measurement accuracy can be achieved that is sufficient to prevent a failure to recognize features of shape of a measurement object, with extension of a measurement time suppressed. In a turbine including casings, recesses and protrusions on flange surfaces of the casings are measured at measurement intervals M set on the basis of the entire length L of flange portions in an axial direction, the number of bolts N joining the flange portions, and intervals between the bolts in the axial direction of the flange portions.

Abstract: A steam turbine includes an outer casing (19) that is provided with a first steam outlet port (54), through which exhaust steam flowing through the entire length of a flow path (21) defined between an inner casing main body (45) and an outer casing main body (51) in a direction along an axis (O1) is discharged to the outside of the outer casing (19), and a second steam outlet port (55), which is provided in the outer casing main body (51) and through which the exhaust steam passing through a portion of the flow path (21) or the exhaust steam not passing through the flow path (21) is discharged to the outside of the outer casing (19); a first valve (28) that adjusts opening of the first steam outlet port (54); and a second valve (32) that adjusts opening of the second steam outlet port (55).

Abstract: A fuel cell system includes: a fuel cell including a fuel electrode and an air electrode; a fuel electrode fuel line configured to supply fuel gas to the fuel electrode; a polluted exhaust line configured to supply polluted exhaust containing contaminants discharged from a facility to the air electrode; and an air electrode fuel line configured to supply fuel gas to the air electrode.

Abstract: A partial oxidative coupling catalyst has a structure in which a component represented by M2ZrO3 is supported on a support, where M represents an alkali metal.

Abstract: A control device for an inspection device including a long flexible robot that is formed by connecting a plurality of units and bendable at each unit with a desired curvature, and a posture actuator that adjusts a posture of the unit includes a target posture specifying unit that specifies a target posture including positions of representative points of the respective units traveling along a predetermined route, and an operation amount determination unit that determines an operation amount for bringing the unit to the target posture using a learning model with the target posture of the unit as an input and an operation amount of the posture actuator as an output.

Abstract: A drain removal monitoring equipment for monitoring, in a steam turbine, drain removal performed by drawing a fluid outside at least one hollow stator vane including an internal space into the internal space via a slit formed in a surface of the stator vane includes: a gas-liquid separation device for separating the fluid drawn into the internal space into a liquid phase and a gas phase; a liquid-phase flow measurement device for measuring a flow rate of the liquid phase separated by the gas-liquid separation device; a gas-phase flow measurement device for measuring a flow rate of the gas phase separated by the gas-liquid separation device; a liquid-phase return line through which the liquid-phase flow measurement device and the steam turbine communicate with each other, and a gas-phase return line through which the gas-phase flow measurement device and the steam turbine communicate with each other.

Abstract: An impeller includes a hub having a circular plate shape with an axial line as a center, a shroud disposed to face the hub in a direction of the axial line, and a plurality of blades disposed with a space from each other in a circumferential direction between the hub and the shroud. A meridian plane shape of the impeller differs in the circumferential direction.

Abstract: Provided is a gas turbine system that is used for a moving body including a thrust generator configured to generate thrust from electric power and includes: a compressor that compresses external air to generate compressed air; a combustor that burns the compressed air generated by the compressor together with fuel to generate a combustion gas; a turbine driven by the combustion gas generated by the combustor; a first generator that is coupled to the turbine to generate electric power by driving of the turbine and supplies electric power to the thrust generator; and a second generator that is arranged downstream of the turbine in a flow direction of a combustion gas and converts kinetic energy and/or thermal energy of a combustion gas that passed through the turbine into electric power.

Abstract: A metal powder production apparatus capable of easily preventing an oxide in a molten metal from entering a liquid nozzle is provided. The metal powder apparatus includes a first crucible heating and melting a melting material to generate molten metal, a first heating device heating and melting the metal in the first crucible, a stopper opening and closing a first opening provided on the bottom surface of the first crucible, an introduction pipe having one end connected to the first opening of the first crucible and leading a molten metal in the first crucible to the outside of the first crucible, a second crucible receiving the molten metal flowing out of the introduction pipe, a second heating device heating the second crucible, and a liquid nozzle provided on the bottom surface of the second crucible.

Abstract: A turbine blade including an airfoil portion having a leading edge, a trailing edge, and a pressure surface and a suction surface extending between the leading edge and the trailing edge. The airfoil portion internally forming a cooling passage, which includes first and second cooling passages, and a plurality of outflow passages each having one end which opens to a merging portion formed by connecting an end portion of the first cooling passage on a side of the trailing edge and an end portion of the second cooling passage on the side of the trailing edge, and another end which opens to the trailing edge. The first cooling passage and the second cooling passage are divided by a partition member disposed in the airfoil portion. The cooling passage includes pressure side pin fins in the first cooling passage, and suction side pin fins in the second cooling passage.

Abstract: A bumper is provided on an outer side of a structural body of a spacecraft with a predetermined gap between the bumper and the structural body. The bumper includes: a first layer that is provided on the outer side and that is formed from an impact resistant material; a second layer that is provided on an inner side being on a side of the structural body with respect to the first layer, the second layer having holes; and a third layer that is provided on the inner side with respect to the second layer, the third layer including a resin.

Abstract: Provided is a plant that includes: a boiler; a device connected to the boiler; a water supply source that is configured to pool water; a water supply line that supplies water from the water supply source to the boiler; a cooler that transfers heat from a medium to be cooled to supply-water, which is the water flowing along the water supply line; a thermometer that determines a temperature of the medium to be cooled or the supply-water; and a temperature regulator that is configured to regulate the temperature of the medium to be cooled on the basis of the temperature determined by the thermometer.

Abstract: A gas turbine including a turbine driven by a combustion gas, a gas turbine casing that includes an exhaust casing having an inner tube and an outer tube, a bearing that rotatably supports a shaft of the turbine, a bearing casing that holds the bearing, a support leg that supports the gas turbine casing, struts that connect the inner tube and the outer tube, and a first support and a second support that support the bearing casing on the inner tube. The first support is located on a side same as the support leg relative to the struts in a flow direction of the combustion gas. The struts are located between the first support and the second support. The first support is fixed to the inner tube and the bearing casing. The second support is fixed to the inner tube and is in slidable contact with the bearing casing.

Abstract: A condition monitoring device for a wind turbine power generating apparatus provided with an auxiliary motor power supply system including a power-supply-side line connected to a power supply and a plurality of auxiliary-motor-side lines diverging from the power-supply-side line and connected to a plurality of auxiliary motors, respectively, comprises: a current measurement device for measuring a current flowing through the power-supply-side line; and a control device for controlling the plurality of auxiliary motors. The control device is configured to, when a generator of the wind turbine power generating apparatus is in a standby state where power generation is stopped at a low wind speed, execute a single sequential operation mode in which each of the plurality of auxiliary motors is singly and sequentially operated. The current measurement device is configured to measure a current flowing through the power-supply-side line during execution of the single sequential operation mode by the control device.

Abstract: A workpiece material is fed between rollers to bend the workpiece material while rolling, wherein the workpiece has a first thickness portion and a second thickness portion connected to each other with a setting angle of 90 degrees. The first thickness portion increases from an inner side toward an outer side, and a thickness on an outer peripheral side of the first thickness portion is M, and a thickness of a cross section of the second thickness portion is N. The workpiece material is rolled in such that at a completion of bending, a thickness of a cross section of a first thickness portion is m, an outer radius of the first thickness portion is R, an inner radius of the first thickness portion is r, and a thickness of a cross section of a second thickness portion is n, and M equals to m(R/r), and N equals to n(R/r).

Abstract: A power distribution system 100 is installed in an aircraft, and comprises: a first DC power supply unit 10 including a generator 11; a second DC power source unit 20 including a battery 30, a step-up/down converter 41, a voltage sensor 43, and control unit 44; and a diode 50. When the voltage sensor 43 does not detect regenerative power, the control unit 44 executes a running power processing mode in which generated power generated by the first DC power supply unit 10 is supplied to an electric actuator 80 while charging and discharging the battery 30 using the step-up/down converter 41 so as to keep a charge rate A of the battery 30 within a predetermined range. When the voltage sensor 43 detects regenerative power, the control unit 44 executes a regenerative power processing mode in which the battery 30 is charged with the regenerative power using the step-up/down converter 41.

Abstract: A method for producing a composite material in which a first fabric and a second fabric made from a fiber material are impregnated with a thermosetting resin and integrally molded, wherein a resin flow path through which thermosetting resin flows is provided between the first fabric and the second fabric, and the first fabric and the second fabric are impregnated with thermosetting resin from the resin flow path as well as being impregnated with thermosetting resin from the surface.