Abstract: Provided is an optical lens formed by integrally molding a lens part that is an optically effective portion and has a light incidence/emission surface, and a lens edge part that is an optically ineffective portion and has a surface thereof except the light incidence/emission surface. The lens edge part includes a non-transparent region in part or all thereof, the lens part and the lens edge part include a thermoplastic resin, and the non-transparent region in the lens edge part contains a total of 0.1-5 mass % of one or more of a black dye and a black pigment.

Abstract: The present invention provides a burner, a combustor equipped with the burner, and a gas turbine, with which it is possible to premix a first hydrocarbon-based fuel (for example, natural gas), a second fuel (for example, hydrogen gas), and combustion air, and to spray into the combustion chamber of the combustor a thin and uniform concentration distribution of the premixed air, and with which it is possible to suppress the amount of NOx discharged. On the upstream side of the premix flow path, hydrogen gas is sprayed from second fuel spray nozzles, which project into the premix flow path, into the flow of the combustion air flowing toward the center from the outer edge of an outer cylinder, whereby a primary air-fuel mixture having a uniform concentration distribution is generated without affecting a low-speed region of the combustion air.

Abstract: A lid device includes an opening former, a lid, and a connector. The opening former is provided with an opening. The lid opens and closes the opening in the opening former. The connector intervenes between the opening former and the lid, and connects the opening former with the lid. The opening former includes a first gear. The lid includes a second gear. The connector includes a third gear meshing with both of the first gear and the second gear. The opening former and connector are made turnable relatively to one another about the axial center of the first gear. The lid and connector are made turnable relatively to one another about the axial center of the second gear. The connector interlocks the opening former turning relatively to the connector and the lid turning relatively to the connector with one another.

Abstract: A burner injects a mixture of fuel and air from a base end side far from a combustion chamber toward a distal end side close to the combustion chamber. The burner has a fuel passage having a turn-back part turning back and channeling the fuel between the base end side and the distal end side. The burner has a premixed gas passage formed to surround the fuel passage. The burner has a fuel introduction part introducing the fuel channeled through the fuel passage into the premixed gas passage from the base end side to the distal end side. The burner has an air supply part supplying the premixed gas passage with air on the base end side.

Abstract: A lid device includes an opening former, a lid, and a connector. The opening former is provided with an opening. The lid opens and closes the opening in the opening former. The connector intervenes between the opening former and the lid, and connects the opening former with the lid. The opening former includes a first gear. The lid includes a second gear. The connector includes a third gear meshing with both of the first gear and the second gear. The opening former and connector are made turnable relatively to one another about the axial center of the first gear. The lid and connector are made turnable relatively to one another about the axial center of the second gear. The connector interlocks the opening former turning relatively to the connector and the lid turning relatively to the connector with one another.

Abstract: A gas turbine combustor includes a casing coupled to a main housing; a liner having formed inside a combustion chamber that extends in an axial direction, an upstream portion including a head portion of the liner accommodated in the casing, and a downstream portion accommodated in the main housing; a main burner provided at the head portion of the liner; a supplemental burner including an injection port located in an air passage formed between the liner and the casing, the supplemental burner configured to inject an air-fuel mixture in which supplemental burning fuel containing hydrogen and the compressed air taken into the supplemental burner through the space formed between the liner and the casing are mixed; and a duct including an entrance connected to the injection port of the supplemental burner and an exit which opens in the combustion chamber, the duct extends in parallel with the axial direction.

Abstract: A link connecting a lid and a base member of a filler lid structure includes first and second link members. At an opening position, a distance between a distal end of the lid and the base member is larger than a distance between a proximal end of the lid and the base member. The first link member swings about a first support portion in a direction in which a second support portion is moved away from the base member, when the lid shifts from a closing position to the opening position. A distance between a base support point at which the base member or the first link member supports a third support portion at the closing position and an end support point at which the lid supports a fourth support portion at the closing position changes when the lid shifts from the closing position to the opening position.

Abstract: A link connecting a lid and a base member of a filler lid structure includes first and second link members. At an opening position, a distance between a distal end of the lid and the base member is larger than a distance between a proximal end of the lid and the base member. The first link member swings about a first support portion in a direction in which a second support portion is moved away from the base member, when the lid shifts from a closing position to the opening position. A distance between a base support point at which the base member or the first link member supports a third support portion at the closing position and an end support point at which the lid supports a fourth support portion at the closing position changes when the lid shifts from the closing position to the opening position.

Abstract: The present invention provides a burner, a combustor equipped with the burner, and a gas turbine, with which it is possible to premix a first hydrocarbon-based fuel (for example, natural gas), a second fuel (for example, hydrogen gas), and combustion air, and to spray into the combustion chamber of the combustor a thin and uniform concentration distribution of the premixed air, and with which it is possible to suppress the amount of NOx discharged. On the upstream side of the premix flow path, hydrogen gas is sprayed from second fuel spray nozzles, which project into the premix flow path, into the flow of the combustion air flowing toward the center from the outer edge of an outer cylinder, whereby a primary air-fuel mixture having a uniform concentration distribution is generated without affecting a low-speed region of the combustion air.

Abstract: A burner injects a mixture of fuel and air from a base end side far from a combustion chamber toward a distal end side close to the combustion chamber. The burner has a fuel passage having a turn-back part turning back and channeling the fuel between the base end side and the distal end side. The burner has a premixed gas passage formed to surround the fuel passage. The burner has a fuel introduction part introducing the fuel channeled through the fuel passage into the premixed gas passage from the base end side to the distal end side. The burner has an air supply part supplying the premixed gas passage with air on the base end side.

Abstract: To provide a multifuel gas turbine combustor capable of combusting gases containing hydrogen in a high concentration with a low NOx while maintaining a low emission performance brought about by the pre-mixture combustion in the main burner, the gas turbine combustor includes a main burner (12) for supplying to and combusting a premixed gas (M), containing a first fuel (F1), within a first combustion region (S1) of a combustion chamber (10), and a supplemental burner (20) for supplying to and combusting a second fuel (F2) of a composition different from that of the first fuel (F1) within a second combustion region (S2) defined downstream of the first combustion region (S1) within the combustion chamber (10). The first fuel (F1) is of a hydrocarbon system and the second fuel (F2) is a gas containing hydrogen in a concentration exceeding the stable combustion limiting concentration of the hydrogen.

Abstract: To provide a multifuel gas turbine combustor capable of combusting gases containing hydrogen in a high concentration with a low NOx while maintaining a low emission performance brought about by the pre-mixture combustion in the main burner, the gas turbine combustor includes a main burner (12) for supplying to and combusting a premixed gas (M), containing a first fuel (F1), within a first combustion region (S1) of a combustion chamber (10), and a supplemental burner (20) for supplying to and combusting a second fuel (F2) of a composition different from that of the first fuel (F1) within a second combustion region (S2) defined downstream of the first combustion region (S1) within the combustion chamber (10). The first fuel (F1) is of a hydrocarbon system and the second fuel (F2) is a gas containing hydrogen in a concentration exceeding the stable combustion limiting concentration of the hydrogen.

Abstract: To provide a multifuel gas turbine combustor capable of combusting gases containing hydrogen in a high concentration with a low NOx while maintaining a low emission performance brought about by the pre-mixture combustion in the main burner, the gas turbine combustor includes a main burner (12) for supplying to and combusting a premixed gas (M), containing a first fuel (F1), within a first combustion region (S1) of a combustion chamber (10), and a supplemental burner (20) for supplying to and combusting a second fuel (F2) of a composition different from that of the first fuel (F1) within a second combustion region (S2) defined downstream of the first combustion region (S1) within the combustion chamber (10). The first fuel (F1) is of a hydrocarbon system and the second fuel (F2) is a gas containing hydrogen in a concentration exceeding the stable combustion limiting concentration of the hydrogen.

Abstract: To provide a multifuel gas turbine combustor capable of combusting gases containing hydrogen in a high concentration with a low NOx while maintaining a low emission performance brought about by the pre-mixture combustion in the main burner, the gas turbine combustor includes a main burner (12) for supplying to and combusting a premixed gas (M), containing a first fuel (F1), within a first combustion region (S1) of a combustion chamber (10), and a supplemental burner (20) for supplying to and combusting a second fuel (F2) of a composition different from that of the first fuel (F1) within a second combustion region (S2) defined downstream of the first combustion region (S1) within the combustion chamber (10). The first fuel (F1) is of a hydrocarbon system and the second fuel (F2) is a gas containing hydrogen in a concentration exceeding the stable combustion limiting concentration of the hydrogen.

Abstract: A multi-fuel-capable gas turbine combustor is provided which is able to sufficiently utilize various fuels having a characteristic deviating from a premixing characteristic range suitable for generating a premixed gas, even while maintaining favorable low-emission performance by premixed combustion. The gas turbine combustor includes: a main burner configured to supply a premixed gas containing a first fuel for premixing, to a first combustion region within a combustion chamber to cause premixed combustion; and a supplemental burner configured to supply a second fuel for reheating having a different composition from that of the first fuel, to a second combustion region at a location downstream of the first combustion region within the combustion chamber, to cause diffusion combustion. The first fuel has a premixing characteristic range suitable for generating a premixed gas. The second fuel has a characteristic deviating from the premixing characteristic range.

Abstract: Provided is a sealing structure of a fuel inlet box exhibiting good sealing characteristics without deforming a mounting surface of a vehicle body side panel. The fuel inlet box comprises a main body member and a sealing member. The main body member has a box portion, and a storage wall bulging from a side wall of the box portion and having space for storing an arm portion of a lid body. The mounting surface is interposed between a base portion of the storage wall and a flange portion, and faces the flange portion through a gap extending in a planar direction. A seal lip of the sealing member is fixed on the flange portion, extending toward the mounting surface and inclined toward an outer peripheral side of an opening. An outer basing point of a root portion of the seal lip is located in the flange portion.

Abstract: A catalytic combustor (2) in a gas turbine engine (GT) includes a casing (54) for accommodating a catalyst carrier (10) therein, a catalyst retaining body (62) interposed between the casing (54) and the catalyst carrier (10) for retaining an outer peripheral surface of the catalyst carrier (10) to an inner peripheral surface of the casing (54) and also for preventing a gas (G2) from leaking in a downstream direction through an outer periphery of the catalyst carrier (10), a support material (64) disposed on a downstream side of the direction of flow of the gas to be treated in the catalyst carrier (10) for holding the catalyst carrier (10), and a downstream side regulating member (72) disposed on the downstream side of the catalyst retaining body (62) for avoiding a movement of the catalyst retaining body (62) in a direction of flow of the gas (G2).

Abstract: A catalytic combustor (2) for use in a gas turbine engine (GT) includes catalyst units (U1, U2, U3) in a multistage. The catalyst unit (U1, U2, U3) in each stage includes a support material (64) for supporting the respective catalyst unit (U1, U2, U3) against the pressure of a gas. The catalyst unit (U1, U2, U3) in each stage is unitized together with the support material (64) and the catalyst units (U1, U2, U3) are removably fitted to a combustor housing (50).

Abstract: An apparatus for equalizing flow velocity distribution of a fuel gas supplied into a catalytic combustor includes a rectification vane and a rectification plate in an inlet chamber of the catalyst combustor. The inlet chamber has a round transverse sectional shape and includes an inflow port that allows the fuel gas to inflow radially, and an outflow port for discarding the fuel gas axially. The rectification vane has a front edge oriented towards the inflow port, and a rectifying surface ramified from the front edge so as to extend towards a cylindrical inner wall surface of the inlet chamber such that swirling flow of the fuel gas flown into the inlet chamber, that flows towards the inflow port along the cylindrical inner wall surface, is generated. The rectification plate is located at the outflow port and has openings for allowing the fuel gas to flow therethrough.

Abstract: To improve an angular color difference and emit uniform illumination light. According to an embodiment, a light-emitting device in an embodiment includes a light-emitting module (15). The light-emitting module (15) includes a substrate (21), a plurality of light-emitting elements (45) made of semiconductor, and a plurality of sealing members (54). The light-emitting elements (45) are disposed on the substrate (21). The sealing members (54) contain, as a main component, translucent resin mixed with a phosphor. The sealing members (54) are heaped up from the bottom surfaces thereof bonded on the substrate (21) and are each formed to bury a singularity or a plurality of the light-emitting elements (45). A ratio (H/D) of a diameter D of the bottom surfaces to height H of the heaps of the sealing members (54) is set to 0.22 to 1.0.