Abstract: A capacitive sensor has: one or more front-side electrodes including at least one detection electrode; an elastic dielectric body disposed below the front-side electrodes; a shield electrode disposed below the elastic dielectric body; a first, second, and third voltage output unit that respectively outputs a first, second, and third AC voltage; and a detection unit that detects a proximity, a contact, and pressing of a detection target to the detection electrode. The first, second, and third AC voltages have substantially the same frequency. The amplitude of the first AC voltage is larger than or equal to the amplitude of the second AC voltage. The amplitude of the third AC voltage is smaller than the amplitude of the second AC voltage. The first AC voltage is output to a driving unit coupled to the detection electrode with capacitances intervening between them. The second AC voltage is applied to the detection electrode.

Abstract: In an input device capable of reliably detecting, when an operator brings an operating body close to or into contact with an operation plane, absolute position information irrespective of a contact area size, third electrode arrays are disposed closer to the operation plane relative to second electrode arrays in a normal direction of the operation plane, the second electrode arrays have a portion protruding from the corresponding third electrode arrays when viewed in the normal direction, and assuming that a change amount of electrostatic capacitance between first and third electrode arrays occurred by an operation of the operating body is denoted by ?C1 and a change amount of electrostatic capacitance between the first and second electrode arrays occurred by an operation of the operating body is denoted by ?C2, a position of the operating body in the normal direction is calculated based on a ratio ?C1/?C2.

Abstract: In an input device capable of reliably detecting, when an operator brings an operating body close to or into contact with an operation plane, absolute position information irrespective of a contact area size, third electrode arrays are disposed closer to the operation plane relative to second electrode arrays in a normal direction of the operation plane, the second electrode arrays have a portion protruding from the corresponding third electrode arrays when viewed in the normal direction, and assuming that a change amount of electrostatic capacitance between first and third electrode arrays occurred by an operation of the operating body is denoted by ?C1 and a change amount of electrostatic capacitance between the first and second electrode arrays occurred by an operation of the operating body is denoted by ?C2, a position of the operating body in the normal direction is calculated based on a ratio ?C1/?C2.

Abstract: A capacitive sensor has: an electrode link that has a plurality of second transparent electrodes arranged in a predetermined direction; a first wiring part electrically connected to one end of the electrode link; a second wiring part electrically connected to another end of the electrode link; a central linking part that electrically connects a plurality of second transparent electrodes placed at the central portion of the detection area in the predetermined direction; and a peripheral linking part that electrically connects a plurality of second transparent electrodes placed in other than the central portion in the predetermined direction. The first wiring part and second wiring part are electrically connected to each other in a non-detection area. The electric resistance value of the central linking part is higher than the electric resistance value of the peripheral linking part.

Abstract: In a gas turbine in which a seal member seals a gap between a transition piece and a nozzle end wall in a turbine first stage, the transition piece and the nozzle end wall has a seal groove. The seal member includes a hook portion that slides in the turbine radial direction with respect to the flange and a seal plate portion inserted in the groove. The groove and the portion are configured to include a surface contact region in which a surface of the groove and the portion are in surface contact with each other, a non-contact region disposed on a side closer to the transition piece than the region, and a hole provided at the portion so as to face the surface in the groove across a gap in the region.

Abstract: A turbine blade includes cooling passages formed inside the blade and extending in a blade height direction, blade surfaces on a suction side and a pressure side being covered with thermal barrier coating, a design point on a suction side being set on the blade surface on the suction side of each blade section perpendicular to the blade height direction within a range from a position on a back side of and including a throat position, and to a position in front of and not including a tailing end of a final cooling passage. Thickness distribution of the thermal barrier coating on the suction side of each blade section is configured such that a thickness of the thermal barrier coating is uniform from a blade leading edge to the design point and gradually reduces from the design point toward the back side up to the blade trailing edge.

Abstract: A capacitive sensor has: an electrode link that has a plurality of second transparent electrodes arranged in a predetermined direction; a first wiring part electrically connected to one end of the electrode link; a second wiring part electrically connected to another end of the electrode link; a central linking part that electrically connects a plurality of second transparent electrodes placed at the central portion of the detection area in the predetermined direction; and a peripheral linking part that electrically connects a plurality of second transparent electrodes placed in other than the central portion in the predetermined direction. The first wiring part and second wiring part are electrically connected to each other in a non-detection area. The electric resistance value of the central linking part is higher than the electric resistance value of the peripheral linking part.

Abstract: The object of the invention is to suppress development of a secondary current whirl in the vicinity of a rotor blade front edge of a gas turbine even when a cooling refrigerant is mixed in from the front edge of an end wall section of the rotor blade.

Abstract: In a gas turbine in which a seal member seals a gap between a transition piece and a nozzle end wall in a turbine first stage, the transition piece and the nozzle end wall has a seal groove. The seal member includes a hook portion that slides in the turbine radial direction with respect to the flange and a seal plate portion inserted in the groove. The groove and the portion are configured to include a surface contact region in which a surface of the groove and the portion are in surface contact with each other, a non-contact region disposed on a side closer to the transition piece than the region, and a hole provided at the portion so as to face the surface in the groove across a gap in the region.

Abstract: A nuclear reactor control rod with SiC fiber reinforced structure comprises wing sections and a central joint section. Each of the wing sections is a flat plate spreading axially and radially, and includes storage tubes and a wing surface structural member. The storage tubes are arranged in parallel in a flat plane and contain a neutron absorbing member containing the neutron absorbing material. The wing surface structural member is formed by molding of SiC/SiC composite material as to cover surfaces of the storage tubes and formed to have an outward shape of a flat plate. The central joint section and storage tubes are made of SiC/SiC composite material. The central joint section bundles the wing sections together at center. The storage tubes are bundled together with fibers made of SiC or a textile made of SiC.

Abstract: A turbine rotor blade is provided that can reduce a total pressure loss at a blade cross-section on a tip side of the blade and suppress degradation in performance even if cooling air mixes in toward the blade. The rotor blade is mounted to a rotor to form a turbine blade row rotating in a stationary member that includes a platform forming a gas passage through which a mainstream gas flows and an airfoil extending from a gas passage plane in a radial direction vertical to the rotational axis of the rotor, the gas passage plane being a plane of the platform and forming the gas passage. A clearance between the tip-side end face, which is a leading end-side end face of the airfoil, and the stationary member facing the tip-side end face is smaller on the downstream side than on the upstream side.

Abstract: A turbine blade includes cooling passages formed inside the blade and extending in a blade height direction, blade surfaces on a suction side and a pressure side being covered with thermal barrier coating, a design point on a suction side being set on the blade surface on the suction side of each blade section perpendicular to the blade height direction within a range from a position on a back side of and including a throat position, and to a position in front of and not including a tailing end of a final cooling passage. Thickness distribution of the thermal barrier coating on the suction side of each blade section is configured such that a thickness of the thermal barrier coating is uniform from a blade leading edge to the design point and gradually reduces from the design point toward the back side up to the blade trailing edge.

Abstract: A two-shaft gas turbine having a steam injection mechanism, comprising: a compressor having an inlet guide vane, a combustor, turbines, a heat recovery steam generator, a steam valve to control a flow rate of steam to be supplied to the combustor, a fuel valve to control a flow rate of fuel to be supplied to the combustor, characterized in that, the two-shaft gas turbine further comprising: a rotational frequency meter, a flow rate meter to measure the flow rate of the steam to be supplied to the combustor from the heat recovery steam generator, an inlet guide vane position gauge provided to the compressor, a steam valve position gauge, and a control system calculates and outputs command signals to operate openings of the fuel valve, the steam valve, and the inlet guide vane based on measurement signals obtained by the rotational frequency meter, the inlet guide vane position gauge, or the steam valve position gauge, and an output increase command value to the gas turbine.

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: A method of providing an end-capped tubular ceramic composite for containing nuclear fuel (34) in a nuclear reactor involves the steps of providing a tubular ceramic composite (40), providing at least one end plug (14, 46, 48), applying (42) the at least one end plug material to the ends of the tubular ceramic composite, applying electrodes to the end plug and tubular ceramic composite and applying current in a plasma sintering means (10, 50) to provide a hermetically sealed tube (52). The invention also provides a sealed tube made by this method.

Abstract: Provided is a sensor panel including a transparent electrode layer formed on a transparent substrate, a wiring layer formed in the vicinity of the transparent electrode layer, on the substrate, an opaque decorative layer facing the wiring layer, and a cover layer located between the substrate and the decorative layer. The cover layer is configured such that an operation region corresponding to at least the transparent electrode layer is transparent, and a shielding layer configured to shield an optical path leading to the wiring layer is provided between the wiring layer and the decorative layer.

Abstract: A gas turbine stator vane is effective for suppressing a secondary flow in a region sandwiched between a suction surface side and a pressure surface side, as well as for suppressing augmentation of a horseshoe-shaped vortex occurring near a leading edge of the vane. The stator vane includes a vane profile portion having a pressure surface concaved to a chord line of the vane, and a suction surface convexed to the chord line; an outer-circumferential end wall positioned at an outer circumferential side of the vane profile portion; and an inner-circumferential end wall positioned at an inner circumferential side of the vane profile portion. An outer-circumferential end wall inner surface that is an inner-circumferential surface of the outer-circumferential end wall has an inward convexed shape and an outward convexed shape, at the suction surface side of the vane profile portion.

Abstract: A touch panel includes a transparent panel, a transparent electrode which is formed in a transparent input region on a first surface of the transparent panel, a decorative layer which is formed in a decorative region on the first surface, a wiring layer which is formed on a surface of the decorative layer, and a transparent conductive connection layer which electrically connects the wiring layer and the transparent electrode.

Abstract: A reactor control rod for nuclear reactor according to an embodiment has: a plurality of wing sections arranged radially around an axis extending in vertical direction in such a way as to be spaced out each other in a circumferential direction; and a central joint section bundling the plurality of wing sections together at center, wherein at least part of the central joint section and wing surface structural member is made of SiC-fiber-reinforced SiC composite material. The wing surface structural member of side of the central joint section may be sealed with the SiC-fiber-reinforced SiC composite material. Orientation directions of SiC fibers in the SiC-fiber-reinforced SiC composite material may be such that arithmetic mean of cos2? for all SiC fibers may be ½ or greater, where ? is an angle formed of each fiber with the longitudinal direction of the wing section.

Abstract: The object of the invention is to suppress development of a secondary current whirl in the vicinity of a rotor blade front edge of a gas turbine even when a cooling refrigerant is mixed in from the front edge of an end wall section of the rotor blade.