Abstract: The present invention is a downstream plate which is provided on a downstream side of an upstream plate includes an air inlet into which cooling air is introduced from a cooling air introduction pipe and a cooling flow path which extends in a direction along a surface of the downstream plate from the air inlet so as to avoid a premix tube and through which cooling air flows.

Abstract: A combustor includes: a first nozzle which extends along an axis and injects fuel toward a downstream side; a flame stabilizer which covers a downstream-side end portion of the first nozzle from an outer periphery side; and a plurality of second nozzles arranged at intervals in a circumferential direction around the axis on the outer periphery side of the flame stabilizer. The flame stabilizer has a cone portion expanding in diameter toward the downstream side from the upstream side, and a flange portion extending radially outward from a downstream-side end edge of the cone portion, and a penetrating portion which penetrates at least the flange portion in a direction of the axis is formed in the flame stabilizer.

Abstract: There is provided a combustor including a nozzle main body (16) that includes a shaft body (24) which extends along an axis and has, inside the shaft body (24), a purge air flow path (29), which extends along the axis to a tip portion of the shaft body (24) and into which compressed air is introduced, and an air spraying hole (39), which is formed in the tip portion of the shaft body (24) and connects the purge air flow path (29) to an outer surface of the shaft body (24), a swirling blade (26), which overhangs from an outer circumferential surface of the shaft body (24) in a diameter direction of the axis and swirls a fluid flowing to a downstream side of an axial direction around the axis, and a fuel spraying hole (38), and a sealing member (40) that seals the air spraying hole (39) and is formed of a metal having a melting point lower than a melting point of a metal forming the nozzle main body (16).

Abstract: A combustor includes: a nozzle main body having a shaft body and a swirl vane; a first fuel flow path which supplies fuel to a first fuel injection hole formed in the nozzle main body; a second fuel flow path which supplies fuel to a second fuel injection hole formed on a radial outer side of the first fuel injection hole in the nozzle main body; a first regulating valve provided in the first fuel flow path and configured to regulate a flow rate of the fuel flowing through the first fuel flow path; a temperature sensor-which detects a temperature on a downstream side of the swirl vane; and a control device which controls the first regulating valve so that the flow rate of the fuel flowing through the first fuel flow path is lowered when a temperature detected by the temperature sensor satisfies a predetermined condition.

Abstract: A gas turbine combustor provided with: a plurality of swirler tubes that are disposed inside a combustor basket and impart a swirl to a premixed gas, the premixed gas being obtained by premixing a fuel and air for combustion; and an outer ring that is disposed between the plurality of swirler tubes and the combustor basket with a gap provided between the outer ring and the combustor basket, and generates film-shaped air inside a combustor transition piece connected to the combustor basket via injection through the gap into the combustor transition piece, and at a downstream end of the outer ring, the outer ring includes a tapered surface formed such that the outer ring gradually decreases in thickness from an upstream side toward a downstream side.

Abstract: Provided is a combustor that includes a plurality of main burners disposed at intervals in a circumferential direction. The main burners include first main burners (16A) and second main burners (16B) that separately generate fuel-air mixtures. The second main burners (16B) generate fuel-air mixtures that have less evenness in concentration of fuel than the fuel-air mixtures generated by the first main burners (16A).

Abstract: A combustion apparatus includes a nozzle in which a fuel injection port for injecting a fuel is formed on the center of a tip. A plurality of water injection ports are formed with intervals therebetween in a circumferential direction around the fuel injection port of the tip of the nozzle, and the water injection ports are non-uniformly formed in the circumferential direction.

Abstract: A combustor is equipped with first burners each adopted as a main burner circulating a primary air to generate an air-fuel mixture, second burners each adopted as the main burner circulating the primary air in a direction opposite to the first burners to generate another air-fuel mixture. A plurality of main burners are disposed at intervals in a circumferential direction, and the first burner and the second burner are disposed in a non-periodic arrangement pattern over an entire circumference in the circumferential direction.

Abstract: A combustor according to the present invention is provided with: a pilot burner (15) disposed along an axis (P); a plurality of premixing burners (16), each of which has a premixing swirler cylinder (19) and a premixing nozzle (20) disposed inside the premixing swirler cylinder (19) and that are disposed about the axis (P) in the circumferential direction so as to surround the periphery of the pilot burner (15); a substrate (23) through which the pilot burner (15) and the premixing swirler cylinders (19) are individually inserted so as to be supported therein; and stagnation eliminating blocks (27) that are provided so as to fill spaces between the premixing swirler cylinders (19) on a surface of the substrate (23) on the downstream side, wherein air film supplying ports (38) that form air films A on surfaces of the stagnation eliminating blocks (27) are formed in the stagnation eliminating blocks (27).

Abstract: The present invention provides a main nozzle of a combustor, a plurality of the main nozzles are to be installed on an outer peripheral side of a pilot nozzle of the combustor at an interval in a circumferential direction of the pilot nozzle, the main nozzle includes a main nozzle body extending in an axial line; a swirl vane protruded from an outer peripheral surface of the main nozzle body in a radial direction of the axial line, and is configured to allow a fluid flowing downstream in a direction of the axial line to swirl around the axial line; and temperature sensors installed on the main nozzle body so as to be disposed on a tangential line to a mean line of the swirl vane drawn between a vane ventral surface and a vane dorsal surface of the swirl vane, at a downstream end portion of the swirl vane.

Abstract: A gas turbine combustor includes a pilot burner disposed on a central portion of a combustion liner; and a plurality of main burners disposed to surround the pilot burner. The pilot burner includes: a pilot nozzle disposed on the central portion of the combustion liner; and a pilot cone including a widened portion widening downstream from a vicinity of a downstream end of the pilot nozzle, and an annular portion having an annular shape extending outward in a radial direction from a downstream opening end of the widened portion. The annular portion includes a first position in a circumferential direction and a second position different from the first position in the circumferential direction, and the first position and the second position have different widths in the radial direction.

Abstract: A combustor includes: a fuel nozzle extending along an axis; a tubular combustor basket configured to cover the fuel nozzle; and a tubular transition piece configured to form a cooling air passage through which air from the outside is introduced between the transition piece and an outer circumferential surface of a leading end portion in the combustor basket and extending toward the leading end side of the combustor basket, wherein a position in a radial direction of the leading end of the combustor basket partially varies in a circumferential direction. Thus, vortices are formed on the downstream side of the leading end of the combustor basket. This vortex expedites mixing of air supplied through the cooling air passage with a combustion gas.

Abstract: A combustion burner includes a nozzle, a swirl vane having a fuel injection hole, the swirl vane being disposed in an air flow passage of an annular shape extending along an axial direction of the nozzle around the nozzle, and a partition plate having an annular shape and partitioning at least a region of the air flow passage in a radial direction of the nozzle, so as to divide at least the region into an inner flow passage facing an outer peripheral surface of the nozzle and an outer flow passage disposed on an outer side of the inner flow passage with respect to the radial direction. The fuel injection hole is disposed in the outer flow passage of the air flow passage. An end portion on an upstream side of the partition plate is disposed upstream of the fuel injection hole in the axial direction.

Abstract: A combustor having a plurality of nozzles (main nozzles) to supply fuel disposed, includes a water supplier that is connected to all or part of the plurality of nozzles to supply water to each of a plurality of fuel pipes. The water supplier is configured to vary a supply amount of water for each of plurality of nozzles to which the water is supplied.

Abstract: An injector includes: an upstream support plate into which a fuel gas is to be introduced and which has a shape of a tapered cylinder with a diameter which enlarges; a downstream support plate that defines a plenum at an inner side along with the upstream support plate; and premixing tubes, each of which is supported by the upstream support plate and the downstream support plate and is configured to introduce air. The premixing tubes are disposed in circular rows at equal intervals in a circumferential direction, and portions of the premixing tubes which are located in the plenum include fuel introducing holes.

Abstract: An injector includes: an upstream support plate into which a fuel gas is to be introduced and which has a shape of a tapered cylinder with a diameter which enlarges; a downstream support plate that defines a plenum at an inner side along with the upstream support plate; and premixing tubes, each of which is supported by the upstream support plate and the downstream support plate and is configured to introduce air. The premixing tubes are disposed in circular rows at equal intervals in a circumferential direction, and portions of the premixing tubes which are located in the plenum include fuel introducing holes.

Abstract: A combustor includes: a first nozzle which extends along an axis and injects fuel toward a downstream side; a flame stabilizer which covers a downstream-side end portion of the first nozzle from an outer periphery side; and a plurality of second nozzles arranged at intervals in a circumferential direction around the axis on the outer periphery side of the flame stabilizer. The flame stabilizer has a cone portion expanding in diameter toward the downstream side from the upstream side, and a flange portion extending radially outward from a downstream-side end edge of the cone portion, and a penetrating portion which penetrates at least the flange portion in a direction of the axis is formed in the flame stabilizer.

Abstract: A combustion burner includes a nozzle and a swirl vane disposed in an axial flow path extending along an axial direction of the nozzle. The swirl vane includes a tip portion for swirling gas, the gas flowing through a radially-outer region of the axial flow path, and a root portion disposed on an inner side in a radial direction of the nozzle, the root portion having a cutout on a side of a trailing edge. The radially-outer region and a radially-inner region of the axial flow path communicate with each other, at least in a range in the axial direction in which the swirl vane is disposed. The swirl vane has a pressure surface, a downstream region of the pressure surface of the root portion being defined by the cutout as a curved surface which curves in a direction opposite to the swirl direction toward the trailing edge.

Abstract: A gas turbine combustor includes an external cylinder, an inner cylinder disposed in the external cylinder, a first fuel injecting unit disposed in the inner cylinder, an air passage provided between the external cylinder and the inner cylinder to cause compressed air to flow into the inner cylinder, and a second fuel injecting unit disposed in the air passage. The second fuel injecting unit is disposed at a curve communicating with the inner cylinder downstream in the air passage. The second fuel injecting unit is supported by a curved inner surface of the external cylinder in the inner cylinder. The second fuel injecting unit is disposed with a center line in a longitudinal direction inclined in a flow direction of the compressed air flowing through the air passage at a predetermined angle with respect to a perpendicular orthogonal to a tangent to the curved inner surface of the external cylinder.

Abstract: A burner assembly for a combustor includes: a plurality of first nozzles arranged in a circumferential direction of the combustor; a plurality of first burner cylinders accommodating the respective first nozzles; and a middle-flow-passage forming portion which is connected to a downstream end of the plurality of first burner cylinders and which forms a middle flow passage through which a combustion chamber of the combustor is in communication with an interior space of each of the plurality of first burner cylinders. The middle-flow-passage forming portion includes an inner peripheral wall disposed on a radially inner side of the combustor and formed such that a distance from a center axis of the combustor to the inner peripheral wall is uneven with respect to the circumferential direction.