Abstract: Provided is a biosensor device including: a signal generating unit for generating a continuous wave signal; an antenna for emitting the continuous wave signal as a radio wave; a variable matching circuit for performing impedance matching between the signal generating unit and the antenna; a detection circuit for outputting a detection signal on the basis of the continuous wave signal generated by the signal generating unit and a reflected signal of a radio wave incident on the antenna; and a control unit for controlling an element value of the variable matching circuit from the detection signal in a predetermined period corresponding to one cycle or more time in which heartbeat and respiration waveforms can be measured on the basis of the detection signal.

Abstract: Provided is a bearing structure that can support a rotary shaft with a small number of components. The bearing structure includes: a cylindrical sleeve (32) provided so as to surround the outer circumference of a rotary shaft (4) that rotates about a center axis line (CL) and configured to rotate together with the rotary shaft (4); thrust collars (34a, 34b) provided so as to abut against both ends in the center axis line (CL) direction of the cylindrical sleeve (32), respectively, having a larger diameter than the cylindrical sleeve (32), and configured to rotate together with the rotary shaft (4); and a compressor-side journal bearing (12) arranged on the outer circumference side of the cylindrical sleeve (32) and between the thrust collars (34a, 34b).

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: Provided is a journal bearing structure including: a journal bearing that supports a rotary shaft by an inner circumferential surface; and a bearing housing that holds an outer circumferential surface of the journal bearing by the inner circumferential surface, the journal bearing has an oil supply hole through which the inner circumferential surface and the outer circumferential surface communicate with each other, the bearing housing has an oil supply hole opened to an inner circumferential surface, and an oil supply groove extending in a circumferential direction about an axis line and configured to guide a lubricant discharged from the oil supply hole to the oil supply hole is formed in the inner circumferential surface of the bearing housing.

Abstract: Provided is a transition piece including: a first flow passage group formed by arranging a plurality of intra-wall flow passages extending within a plate constituting the transition piece from a side near a gas turbine to a side near a combustor liner; a second flow passage group located on a side near the combustor liner with respect to the first flow passage group; and a plurality of dilution holes that penetrate the 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

Abstract: Provided is a gas turbine combustor that can achieve improvement of the combustion stability. A gas turbine combustor includes a pilot burner of the diffusion combustion type, a pilot flow control valve that regulates a flow rate of fuel to be supplied to the pilot burner, a main burner of the premix combustion type arranged on an outer circumference side of the pilot burner, main flow control valves that regulate flow rates of fuel to be individually supplied to burner sectors into which the main burner is sectioned in a circumferential direction, and a controller configured to control the pilot flow control valve and the main flow control valves. The controller controls the main flow control valves such that, when fuel is to be supplied to all the burner sectors, a difference in fuel flow rate occurs between at least one burner sector and the other burner sectors among the burner sectors.

Abstract: A bearing device includes: a bearing housing; a floating metal having a cylindrical shape and disposed in a housing hole of the bearing housing and in which a rotational shaft is inserted; and a positioning pin for positioning the floating metal with respect to the bearing housing, the positioning pin being disposed along a radial direction of the rotational shaft. The positioning pin includes a first oil supply hole formed so as to penetrate the positioning pin and communicating with a first space between an inner peripheral surface of the floating metal and an outer peripheral surface of the rotational shaft, and a second oil supply hole formed inside the positioning pin so as to connect a second space to the first oil supply hole, the second space being disposed between an outer peripheral surface of the floating metal and an inner peripheral surface of the housing hole.

Abstract: A press forming method includes a first process of obtaining a pressing force applied to each portion of a tool by an workpiece material during press forming while independently driving the respective each portion of the tool divided into multiple portions and press forming the workpiece material, and a second process of adjusting at least one of an applied driving force, an applied driving speed, and an applied driving timing for each portion of the tool to cause a processing portion of the workpiece material in which the state approaching an overload state is detected based on the pressing force to flow to other processing portions of the workpiece material.

Abstract: A gas turbine combustor is equipped with a transition piece assembly of the combustor, the transition piece assembly includes a transition piece, a frame which is installed on the downstream side (an outlet part) of the transition piece and a seal member which is installed on a coupled part of the aforementioned frame and a turbine-side stator vane part and blocks flowing of compressed air from a compressor into the aforementioned turbine side through a gap of the coupled part, and a projection member is provided on an outer circumference of the aforementioned frame, a movement suppression mechanism for matching the aforementioned projection member and suppressing possible movement of the aforementioned seal member is provided on the aforementioned seal member, the movement suppression mechanism and the aforementioned projection members fit together and thereby the aforementioned seal member is fixed to the frame.

Abstract: A compression device includes a centrifugal compressor and a silencer. The centrifugal compressor includes a compressor assembly bolt fastening an inlet side of an inlet guide to a scroll casing. The silencer includes: a first side wall extending in a direction intersecting with a rotational axis of an impeller; an annular second side wall provided between the first side wall and the centrifugal compressor and surrounding the rotational axis; at least one silencer element provided in an ambient-air introduction space formed between the first side wall and the second side wall for guiding an ambient air to the inlet guide; and a silencer assembly bolt extending from the first side wall to the scroll casing in a direction along the rotational axis of the impeller and fastening the first side wall, the second side wall, and the scroll casing.

Abstract: Provided is a bearing structure that can support a rotary shaft with a small number of components. The bearing structure includes: a cylindrical sleeve (32) provided so as to surround the outer circumference of a rotary shaft (4) that rotates about a center axis line (CL) and configured to rotate together with the rotary shaft (4); thrust collars (34a, 34b) provided so as to abut against both ends in the center axis line (CL) direction of the cylindrical sleeve (32), respectively, having a larger diameter than the cylindrical sleeve (32), and configured to rotate together with the rotary shaft (4); and a compressor-side journal bearing (12) arranged on the outer circumference side of the cylindrical sleeve (32) and between the thrust collars (34a, 34b).

Abstract: A fuel nozzle including a plurality of fuel lines is provided, which has low thermal stress caused by a temperature difference between fuel and combustion air which are passed through the fuel nozzle, and also a gas turbine combustor using the fuel nozzle is provided. The fuel nozzle includes a plurality of channels including a first channel through which either fuel or combustion air is passed, and a second channel through which either fuel or combustion air is passed and which is distinct from the first channel. Of components of the fuel nozzle, a single-piece component makes up at least a region where the first channel and the second channel are placed.

Abstract: There are provided transition piece cooling holes which make NOx reduction and combustion performance improvement possible while effectively cooling the transition piece end frame and the first-stage stator vane end wall. The transition piece cooling holes include a transition piece which guides combustion gas from a combustor to a turbine, a transition piece end frame which is installed on a turbine-side outlet of the transition piece and is disposed so as to face a first-stage stator vane end wall of the turbine with a predetermined gap being interposed, and a seal member which is fitted on the transition piece end frame and is fitted into the first-stage stator vane end wall so as to seal cooling air which is supplied into the gap. The cooling holes are made in the transition piece end frame so as to directly supply the cooling air to the first-stage stator vane end wall.

Abstract: Provided is a gas turbine combustor that can achieve improvement of the combustion stability. A gas turbine combustor includes a pilot burner of the diffusion combustion type, a pilot flow control valve that regulates a flow rate of fuel to be supplied to the pilot burner, a main burner of the premix combustion type arranged on an outer circumference side of the pilot burner, main flow control valves that regulate flow rates of fuel to be individually supplied to burner sectors into which the main burner is sectioned in a circumferential direction, and a controller configured to control the pilot flow control valve and the main flow control valves. The controller controls the main flow control valves such that, when fuel is to be supplied to all the burner sectors, a difference in fuel flow rate occurs between at least one burner sector and the other burner sectors among the burner sectors.

Abstract: A gas turbine combustor is capable of uniformizing a distribution of fuel concentrations to reduce NOx emissions. The gas turbine combustor includes a main burner of the premixed combustion type and a combustion chamber for burning a fuel and air supplied from the main burner. The main burner includes a fuel nozzle for injecting a fuel supplied from a main fuel system and a premixture passageway for mixing the fuel injected from the fuel nozzle and air supplied from an air passageway and supplying the air-fuel mixture to the combustion chamber. The fuel nozzle includes a tapered portion, a flat portion extending from the tapered portion toward a distal side thereof, a fuel passageway defined in the fuel nozzle, and first and second arrays of fuel injection holes providing fluid communication between the fuel passageway and the outside of the fuel nozzle. The first array of fuel injection holes is defined in the tapered portion.

Abstract: A bearing device includes: a bearing housing; a floating metal having a cylindrical shape and disposed in a housing hole of the bearing housing and in which a rotational shaft is inserted; and a positioning pin for positioning the floating metal with respect to the bearing housing, the positioning pin being disposed along a radial direction of the rotational shaft. The positioning pin includes a first oil supply hole formed so as to penetrate the positioning pin and communicating with a first space between an inner peripheral surface of the floating metal and an outer peripheral surface of the rotational shaft, and a second oil supply hole formed inside the positioning pin so as to connect a second space to the first oil supply hole, the second space being disposed between an outer peripheral surface of the floating metal and an inner peripheral surface of the housing hole.

Abstract: A flame produced within a premixer is promptly extinguished and a reduction in output power of a gas turbine associated with extinguishment is suppressed.

Abstract: The present invention provides a gas turbine combustor configured to form a film-like airflow around a region of a combustion liner, where pressure dynamics damping holes are formed for efficiently cooling the region where the pressure dynamics damping holes are formed without increasing concentration of discharged nitrogen oxides. The gas turbine combustor includes the combustion liner that forms a combustion chamber for receiving supply of fuel and air to generate combustion gas, a liner attached to an outer circumferential surface of the combustion liner for forming space from the outer circumferential surface, and the pressure dynamics damping hole formed in the combustion liner provided with the liner for communication between the space and the combustion chamber. The gas turbine combustor includes a cooling air guide lip disposed on an inner circumferential surface of the combustion liner for forming a film-like airflow around a region where the pressure dynamics damping hole is formed.

Abstract: A method of manufacturing a mechanical part of the present invention includes a first process of forming, by performing a folding processing to an end portion of the material, a portion to be processed having a structure, in which a plurality of layers respectively having a thickness corresponding to a plate thickness of a material overlap each other, in the material such that a plate thickness direction of the layer is orthogonal to a plate thickness direction of the material; and a second process of changing, by performing a forging processing to the portion to be processed, a shape of the portion to be processed to a target shape while press-welding the layers of the portion to be processed to each other by plastic deformation.

Abstract: A compressor-impeller fixing nut has a tubular shape, and includes: a curved-surface shaped portion disposed in a first range from a first end side in an axial direction, the curved-surface shaped portion having an outer diameter which increases toward a second end side in the axial direction and including an outer peripheral surface having a curved shape which protrudes outward in a radial direction in a cross section along the axial direction; and a nut portion disposed in a second range closer to the second end side from the first range in the axial direction, the nut portion having an outer peripheral surface with a nut shape. An expression (D1max?D1min)/2<L is satisfied, where L is a length of the first range in the axial direction, and D1max is a maximum value and D1min is a minimum value of the outer diameter of the curved-surface shaped portion in the first range.