Abstract: A vehicle lamp includes a light source provided on one surface of a board and a light guide body that guides light emitted from the light source, the light guide body has an incidence section located on a side of the light guide body facing the one surface of the board, an emitting section located on a side opposite to the side facing the one surface of the board, and a light guide section located between the incidence section and the emitting section, and the light guide section has a portion that extends across inside and outside a region where the light guide body overlaps with the board when seen in a plan view, that extends at an outer side of the region, and that extends from one side toward the other side of the board in at least a thickness direction of the board.

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 vehicle lamp includes a light source provided on one surface of a board and a light guide body that guides light emitted from the light source, the light guide body has an incidence section located on a side of the light guide body facing the one surface of the board, an emitting section located on a side opposite to the side facing the one surface of the board, and a light guide section located between the incidence section and the emitting section, and the light guide section has a portion that extends across inside and outside a region where the light guide body overlaps with the board when seen in a plan view, that extends at an outer side of the region, and that extends from one side toward the other side of the board in at least a thickness direction of the board.

Abstract: A gas turbine combustor that mixes fuel with compressed air guided from a compressor to burn the fuel mixed with the compressed air to generate a combustion gas and supplies the generated combustion gas to a turbine is provided with: an inner cylinder forming a combustion chamber thereinside; an outer cylinder that covers the inner cylinder and forms, between the outer cylinder and the inner cylinder, a cylindrical outer peripheral flow path through which the compressed air flows; an end cover closing the end of the outer cylinder on an opposite side from a side the turbine is located; and a turn guide provided at the end on the end cover side of the inner cylinder, protruding from the outer peripheral surface of the inner cylinder toward the outer cylinder and smoothly connected to the inner peripheral surface of the inner cylinder.

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: 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 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 gas turbine combustor that mixes fuel with compressed air guided from a compressor to burn the fuel mixed with the compressed air to generate a combustion gas and supplies the generated combustion gas to a turbine is provided with: an inner cylinder forming a combustion chamber thereinside; an outer cylinder that covers the inner cylinder and forms, between the outer cylinder and the inner cylinder, a cylindrical outer peripheral flow path through which the compressed air flows; an end cover closing the end of the outer cylinder on an opposite side from a side the turbine is located; and a turn guide provided at the end on the end cover side of the inner cylinder, protruding from the outer peripheral surface of the inner cylinder toward the outer cylinder and smoothly connected to the inner peripheral surface of the inner cylinder.

Abstract: The gas turbine combustor includes a swirler lip on the air hole plate periphery, protruding toward a chamber, and a spring seal in an area for fitting the liner and the plate/lip. The spring seal has an air hole for passage of part of the combustion air introduced in the gap between the outer periphery of the air hole plate and the liner. The swirler lip has an air hole which introduces part of the combustion air passing through the spring seal air hole into the chamber. The liner has an air hole facing the spring seal air hole, to introduce part of air from outside the liner into the gap between the outer periphery of the air hole plate and the liner. A turn guide for rectifying a combustion air flow is provided at the liner end portion on the side for fitting the liner and air hole plate.

Abstract: A multi-directional drive device includes a first drive motor supported by a holding portion and having a first drive shaft, a rotary member integrally connected to the first drive shaft of the first drive motor and configured to rotate together with the first drive shaft, a spherical body supported on the rotary member to be relatively rotatable and configured to rotate about a second rotation center axis different from a first rotation center axis of the first drive shaft, a second drive motor mounted on the rotary member and having a second drive shaft independent of the first drive shaft, and a transmission mechanism provided between the second drive shaft of the second drive motor and the spherical body on the rotary member and configured to transmit power of the second drive shaft to the spherical body and cause the spherical body to slidably rotate about the second rotation center axis with respect to the rotary member, wherein a body to be operated is supported by the spherical body.

Abstract: A multidirectional drive device includes: a driven member that comprises a spherical surface having depressions and protrusions; a rotation driving part that is in contact with the spherical surface of the driven member and rotates the driven member; and a supporting member that is fixed to the driven member and supports an operated body. At least either one of a position and an orientation of the operated body is adjusted by rotation of the driven member.

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: A semiconductor device according to an embodiment of the disclosure includes: a first substrate; a TFT element provided on the first substrate with a first interlayer insulating layer interposed therebetween, and including a semiconductor layer and a gate electrode that is provided on the semiconductor layer with a gate insulating layer interposed therebetween; and a second substrate disposed to face the first substrate. The gate electrode includes a first electroconductive film and a second electroconductive film that has a light-shielding property in order from side of the semiconductor layer. The second electroconductive film extends from a side face to a bottom face of each of a pair of openings that are provided to interpose the semiconductor layer.

Abstract: A semiconductor device according to an embodiment of the disclosure includes: a first substrate; a TFT element provided on the first substrate with a first interlayer insulating layer interposed therebetween, and including a semiconductor layer and a gate electrode that is provided on the semiconductor layer with a gate insulating layer interposed therebetween; and a second substrate disposed to face the first substrate. The gate electrode includes a first electroconductive film and a second electroconductive film that has a light-shielding property in order from side of the semiconductor layer. The second electroconductive film extends from a side face to a bottom face of each of a pair of openings that are provided to interpose the semiconductor layer.

Abstract: A two-shaft gas turbine is provided which includes: a compressor; a combustor having multiple fuel systems and generating combustion gas by combusting fuels from the fuel systems and air compressed by the compressor; a high-pressure turbine coupled coaxially with the compressor and rotated by the combustion gas; a low-pressure turbine having a shaft structure independent of the high-pressure turbine and rotated by exhaust gas from the high-pressure turbine; an air extraction channel for extracting the air compressed by the compressor; an injection flow channel for feeding the air extracted through the air extraction channel back to the combustor; and a controller for controlling the flow rate of the fuel supplied to each of the fuel systems based on the air flow rate of the compressor, on the flow rate of the fuel supplied to the combustor, and on the temperature of the air in the injection flow channel.

Abstract: A multidirectional drive device includes: a driven member that comprises a spherical surface having depressions and protrusions; a rotation driving part that is in contact with the spherical surface of the driven member and rotates the driven member; and a supporting member that is fixed to the driven member and supports an operated body. At least either one of a position and an orientation of the operated body is adjusted by rotation of the driven member.

Abstract: In a perforated coaxial jet burner implemented by a lot of air-fuel coaxial jets, a swirl plate (33) as an end face of the burner on the combustion chamber's side has a lot of air holes for supplying unburned premixed gas of fuel and air to the combustion chamber. Grooves (36) are formed downstream of the air holes of the swirl plate. Adhesion of flame to the swirl plate is inhibited by feeding part of the unburned premixed gas to the grooves. Further, the width of each remaining part (37) between adjacent grooves is set at several millimeters that is approximately equal to the flame quenching distance, by which adhesion of flame to the remaining parts is also prevented. With this configuration, both stable combustion and low NOx combustion can be achieved irrespective of the load condition.

Abstract: A combustor has at least one premixing burner for premixing fuel with air and jetting the mixed gas into a chamber for combustion. A cylinder attached to an outer circumferential portion of an end face of the burner is provided with air supply holes. An interval D1 defined between the adjacent air supply holes and an interval D2 defined between each air supply hole and the end face of the burner are each made narrower than the quenching distance in the premixed gas jetted from the premixing burner.

Abstract: A gas turbine combustor 2 according to the present invention comprises: a combustion chamber 50 in which fuel is burned with air to generate combustion gas; a plurality of fuel nozzles 30 arranged in multiple concentric annular rows; a first plate 32 arranged downstream of the fuel nozzles 30 and having multiple concentric circular air hole rows made up of a plurality of air holes corresponding to the fuel nozzles 30; a second plate 33 arranged downstream of the first plate 32 and having multiple air hole rows corresponding to the air hole rows of the first plate 32; and a partition wall part 37 which partitions a space part 46 between the first plate 32 and the second plate 33 into rooms corresponding to the air hole rows.