Abstract: A combustor includes a fuel supply unit defining on a radially inner side of an axis an inner peripheral side space into which inert gas is introduced and which is configured to supply the inert gas to a combustion cylinder, and defining on a radially outer side an outer peripheral side space into which the inert gas is introduced and which is configured to supply the inert gas to the combustion cylinder; an inner peripheral side oxygen supply unit that is configured to supply oxygen to the inner peripheral side space; an outer peripheral side oxygen supply unit that is configured to supply oxygen to the outer peripheral side space; and an adjustment unit that is configured to adjust the relative amounts of the oxygen supplied by the inner peripheral side oxygen supply unit and the oxygen supplied by the outer peripheral side oxygen supply unit.

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 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: A combustion tube for a gas turbine including an outlet section having a cross-section of an annular sector-shape. The outlet section includes an outer wall forming an outer peripheral boundary of the annular sector-shape, an inner wall forming an inner peripheral boundary of the annular sector-shape, and a pair of side walls forming boundaries on both sides of the annular sector-shape in a circumferential direction, respectively. The outer wall extends obliquely with respect to the inner wall such that a height of the annular sector-shape decreases toward an outlet opening of the combustion tube. A first side wall extends obliquely with respect to a second side such that a perimeter of the annular sector-shape increases toward the outlet opening of the combustion tube. An inclination angle ?1 of the first side wall with respect to the second side wall satisfies 0<?1?56.

Abstract: To provide a gas turbine combustor that can suppress a generation amount of NOx and maintain a flame holding property, while suppressing burn damage around a pilot nozzle including the pilot nozzle. A gas turbine combustor includes a pilot nozzle that can inject fuel F and cooling air A for cooling a nozzle tip, a flow regulating valve that can adjust a flow rate of cooling air to be supplied to the pilot nozzle, a detection sensor that detects a combustion state of fuel, and a control device that controls the flow regulating valve based on a detection result of the detection sensor.

Abstract: The upstream-side wall portion 54 includes, in the circumferential direction thereof, a first region 31 where air inlets 30 are formed at a lower density, and a second region 32 which is disposed at a position offset from the first region 31 in the circumferential direction, and in which the air inlets 30 are formed at a higher density than in the first region 31.

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 combustor including a transition piece that defines a flow channel therein; a combustor basket inserted in the transition piece from an upstream side of the flow channel that sends a combustion gas through the flow channel and defines a gap through which a compressed air is sent with an inner peripheral surface of the transition piece; wherein the combustor basket includes a notch portion recessed from an end of the combustor basket on a downstream side toward the upstream side, and a purge air introduction hole through which the compressed air in the gap is introduced into the notch portion.

Abstract: A combustor including a combustor main body having a transition piece that defines a flow channel therein, and a combustor basket inserted in the transition piece from an upstream side of the flow channel that defines a gap through which a film air is sent with an inner peripheral surface of the transition piece; a connecting pipe disposed upstream of an outlet of the gap that connects to the combustor main body from an outer peripheral side and communicates with the flow channel via a connection hole; and a flow guide disposed at an identical position to the outlet of the gap on a downstream side of a connecting portion of the connecting pipe and the combustor main body that guides a compressed air introduced from outside the connecting pipe so that a flow rate distribution is made uniform in a circumferential direction of the combustor main body.

Abstract: A resonant sound absorbing device of a gas turbine combustor includes a plurality of resonance chambers independently disposed side by side in an axial direction of the gas turbine combustor so as to communicate with a gas passage of the gas turbine combustor via acoustic holes. The plurality of resonance chambers include n related resonance chambers each satisfying: 0.9 × ? i = 1 n ? F i n ? F i ? 1.1 × ? i = 1 n ? F i n ( A ) where n is an integer of 2 or more, and Fi is a peak frequency corresponding to a maximum sound absorbing ratio of the ith related resonance chamber of the n related resonance chambers.

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: 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 gas turbine (1) including a compressor (2) that generates compressed air, a casing (5) into which the compressed air is introduced, a combustor (3) that generates a combustion gas, a turbine (4) that is driven by the combustion gas, a combustor cooling system (6) that has a sub-compressor (62), which is able to be operated independently of the compressor (2), and a heat exchanger (61), which extracts air in the casing (5) and causes the air to exchange heat after the sub-compressor (62) has increased a pressure of the air, and that introduces the air, which has exchanged heat, into a cooling passage (31) of a cylindrical body (30) of the combustor (3), and a combustor air introducing system that extracts air flowing in the combustor cooling system (6) and introduces the air into the combustor (3).

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.

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 combustor includes: a first cylindrical body which is configured to hold a fuel nozzle extending in an axial line direction and through which air flows toward a downstream side thereof; a second cylindrical body that is connected to a downstream side of the first cylindrical body; and an outer shell that has an inner peripheral surface configured to define an air introduction channel through which air is introduced such that the air reverses course at an upstream end of the first cylindrical body and flows toward the downstream side together with an outer peripheral surface of the first cylindrical body. The inner peripheral surface has an outside narrowing surface that is formed to extend inward in a radial direction toward the upstream end of the first cylindrical body.

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 includes a purging air flow passage configured to inject 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 defined within at least one of a radial range from an inner circumferential surface of the burner case and an axial range from the downstream end of the burner case.

Abstract: An object is to realize combustion flame which can further reduce the amount of NOx generation. A combustor (14) includes a pilot nozzle (40); a plurality of main nozzles (44) arranged apart from the pilot nozzle (40) in the circumferential direction on the outer peripheral side of the pilot nozzle (40) and configured to perform premix combustion; a combustor basket (34) surrounding the pilot nozzle (40) and each main nozzle (44); an outlet outer ring (50) provided at a tip end of the combustor basket (34); and a combustion liner (36) fitted, at an inner surface thereof, onto the outer periphery of the combustor basket (34) and surrounding the outlet outer ring (50). The outlet outer ring (50) is formed parallel to an inner wall surface (66) of the combustion liner (36).

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).