Abstract: A gas turbine combustor and a gas turbine include a pilot burner, a plurality of main burners, and a flame stabilizer. A first air ejection portion is adapted to eject first air toward a tip end portion side between the main burners and the flame stabilizer, a second air ejection portion is adapted to circulate second air toward a tip end portion side outside the flame stabilizer and eject the second air toward a radially outward direction, and a change member is adapted to change an ejecting direction of the second air ejected through the second air ejection portion to an axial center direction of the flame stabilizer.

Abstract: A gas turbine combustor forms a combustion region R1 therein by burning a premixed gas obtained by previously mixing a fuel and combustion air. The gas turbine combustor includes: a burner cylinder (51) in which the premixed gas passes; a film air supply port (61) that is provided on the burner cylinder 51, and supplies a film air formed into a film shape and flowing along the inner wall surface (the inner circumferential surface) of the burner cylinder (51); and a cooling passage (71) in which a cooling air passes. The cooling air cools a back-step surface (65) facing the formed combustion region R1. The cooling passage (71) includes a side from which the cooling air flows out, and the side is connected to the film air supply port (61).

Abstract: A combustor (10) according to the invention includes: a combustor basket (14) in which compressed air and fuel are mixed with each other and the mixture is combusted; a transition piece (17) in which a tip portion of the combustor basket (14) is inserted with a gap (C) therebetween; a spring clip (19) that seals the gap between the combustor basket (14) and the transition piece (17); a throttle section (21) that is provided in an opening portion (Ck) of the gap (C) that is opened to the transition piece (17) on the tip side of the combustor basket (14), and narrows an opening area of the opening portion (Ck), compared to the base end side; and cooling device (22) for cooling the throttle section (21).

Abstract: A combustor includes: a pilot burner; a plurality of main burners, each of which is provided radially and outwardly along a circumferential direction about the pilot burner, and including a main nozzle disposed in a main burner cylinder; and an extension tube provided to extend toward a downstream side from the main burner cylinder of each of the main burners. The extension tube has a circular inlet communicating with the main burner cylinder, and an outlet at the downstream side comprising two radial edges parallel to the radial direction and two circumferential edges formed along the circumferential direction so as to connect both ends of the radial edges. The combustor further includes an air passage formed outside of the main burner cylinder; and an inner communication hole (formed at the side of the inlet of the extension tube and at a position corresponding to the radially and inwardly circumferential edge for allowing communication between the air passage and the inside of the extension tube.

Abstract: A combustor includes a nozzle, a burner cylinder surrounding the outer circumference of the nozzle, and an outside flow path cylinder surrounding the outer circumference of a downstream end portion of the burner cylinder. A purge air flow path through which air flows is formed between the inner circumferential side of the outside flow path cylinder and the outer circumferential side of the burner cylinder. A tapered surface is formed in the downstream end portion of the burner cylinder such that the plate thickness of a burner cylinder-forming plate that forms the burner cylinder gradually thins toward the downstream side.

Abstract: A sound attenuator includes part of a plate forming a combustion liner and an acoustic cover defining, in conjunction with this part of the plate, a space on the outer circumferential side of the combustion liner. A restrictor that reduces a gas flow path is provided inside the combustion liner. At least one through-hole penetrating from inside the combustion liner to the space is defined in the part of the plate. At least one of the through-holes in the sound attenuator is present within a region spanning from a position of a minimum restrictor diameter of the restrictor to positions, on an upstream side and a downstream side, at a distance equivalent to a minimum restrictor radius.

Abstract: Provided is a gas turbine combustor capable of reducing the size of a low-temperature air layer of pilot air formed between a pilot flame and a premixed flame and of improving the flame stability of the premixed flame. A gas turbine combustor, which is provided with a pilot burner that is provided at the center portion of a combustor main body formed in a cylindrical shape to form a pilot flame, and a plurality of main burners arranged so as to surround the outer periphery of the pilot burner to form a premixed flame, includes, as the ignition improving part, a channel blocking member that reduces the size of the low-temperature air layer of the pilot air formed between the pilot flame and the premixed flame.

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: 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 fuel pipes, wherein the water supplier varies a supply amount of water for each of the nozzles to which the water is supplied.

Abstract: In a gas turbine combustor and a gas turbine, a pilot burner, a plurality of main burners, and a pilot cone are provided, and an air passage that ejects air toward a tip end portion side outside the main burner, air passages that circulate the air toward a tip end portion side outside a pilot cone and ejects the air toward an outside in a radial direction, and an eaves portion (change member) that changes an ejecting direction of the air ejected through the air passages to a direction of a central axis center O of the pilot cone are provided.

Abstract: Provided is a gas turbine combustor capable of reducing the size of a low-temperature air layer of pilot air formed between a pilot flame and a premixed flame and of improving the flame stability of the premixed flame. A gas turbine combustor, which is provided with a pilot burner that is provided at the center portion of a combustor main body formed in a cylindrical shape to form a pilot flame, and a plurality of main burners arranged so as to surround the outer periphery of the pilot burner to form a premixed flame, includes, as the ignition improving part, a channel blocking member that reduces the size of the low-temperature air layer of the pilot air formed between the pilot flame and the premixed flame.

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 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: The liquid fuel-using gas turbine combustor prevents the generation of combustion oscillation. The gas turbine combustor is provided with a pilot burner disposed on the central position of the combustion casing, main burners disposed so as to surround the pilot burner. The main burners are configured such that a main nozzle is installed in the central portion of a cylindrical premixing nozzle, with a liquid fuel being injected from fuel injection holes (provided at the periphery of the main nozzle) toward the inner surface of an elongated nozzle connected to the downstream side of the premixing nozzle, and with the injection pattern of the fuel being set so as to differ among the multiple main burners. For example, different injection patterns can be provided by setting different liquid fuel injection angles (?1, ?2) for the fuel injection holes on the multiple main burners.

Abstract: An injector includes: an upstream support plate (11) into which a fuel gas (F) is introduced and which has the shape of a tapered cylinder whose diameter gradually enlarges; a downstream support plate (12) that defines a plenum at an inner side along with the upstream support plate (11); and premixing tubes (13), each of which is supported by the upstream and downstream supporting plates (11 and 12) and introduces air. The plurality of premixing tubes (13) are disposed in a plurality of circular rows at equal intervals in a circumferential direction, and portions of the premixing tubes (13) which are located in the plenum are formed with fuel introducing holes (13a).

Abstract: A combustor is equipped with a burner case, and a base plate spreading from a downstream end of the burner case in a radial direction. The base plate defines a purging air space at an upstream side of the base plate. The combustor is formed with a purging air flow passage that injects purging air in the purging air space to a downstream side relative to the base plate. An outflow opening of the purging air flow passage is formed within an opening formation range. The opening formation range is made up of a range from the downstream end of the burner case to a plate thickness dimension of the base plate toward the upstream side, and a range from an inner circumferential surface of the burner case to the plate thickness dimension of the base plate in the radial direction.

Abstract: A combustor of the present invention includes: a pilot burner; a plurality of main burners (36), each of which is provided radially and outwardly along a circumferential direction about the pilot burner, and including a main nozzle (36a) disposed in a main burner cylinder (36A); an extension tube (36B) provided to extend toward a downstream side from the main burner cylinder of each of the main burners, the extension tube having a circular inlet (36Ba) communicating with the main burner cylinder, and an outlet (36Bb) at the downstream side comprising two radial edges (36Bc) parallel to the radial direction and two circumferential edges (36Bd) formed along the circumferential direction so as to connect both ends of the radial edges; an air passage (36E) formed outside of the main burner cylinder; and an inner communication hole (H1).

Abstract: Provided is a fuel spray nozzle provided with: a liquid fuel channel (15) which is a channel for liquid fuel; a liquid fuel injection hole (19) which is a hole for communicating the liquid fuel channel (15) and the inside of a combustion burner, and injecting the liquid fuel into the combustion burner; an additive channel (14) which is a channel for an additive; and an additive injection hole (18a) which is a hole for communicating the additive channel (14) and the inside of the combustion burner, and injecting the additive into the combustion burner at an angle at which the additive collides with the liquid fuel injected from the liquid fuel injection hole (19); therefore, NOx reduction can be accomplished at low cost.

Abstract: A gas turbine combustor forms a combustion region R1 therein by burning a premixed gas obtained by previously mixing a fuel and combustion air. The gas turbine combustor includes: a burner cylinder 51 in which the premixed gas passes; a film air supply port 61 that is provided on the burner cylinder 51, and supplies a film air formed into a film shape and flowing along the inner wall surface (the inner circumferential surface) of the burner cylinder 51; and a cooling passage 71 in which a cooling air passes. The cooling air cools a back-step surface 65 facing the formed combustion region R1. The cooling passage 71 includes a side from which the cooling air flows out, and the side is connected to the film air supply port 61.