Abstract: A gas turbine combustor according to at least one embodiment, includes: a less combustible fuel flow control part for controlling, independently of each other, amounts of less combustible fuel supplied to a first fuel injector and a second fuel injector; a highly combustible fuel flow control part for controlling, independently of each other, amounts of highly combustible fuel having a higher combustion speed than the less combustible fuel and supplied to the first fuel injector and the second fuel injector; and a controller configured to control the less combustible fuel flow control part and the highly combustible fuel flow control part such that a relative ratio of a first ratio of the highly combustible fuel to whole of first fuel injected by the first fuel injector and a second ratio of the highly combustible fuel to whole of second fuel injected by the second fuel injector changes according to an operating condition of a gas turbine.

Abstract: A combustor for a gas turbine, includes: a first fuel nozzle group and a second fuel nozzle group each of which includes a fuel nozzle capable of supplying a fuel and has an independently controllable fuel supply system; a cylinder inside which a combustion region allowing a combustion gas produced by combustion of the fuel to flow is formed; and a first contraction portion extending partially along a circumferential direction so as to correspond to one of the first fuel nozzle group or the second fuel nozzle group and protruding radially inward from an inner peripheral surface of the cylinder.

Abstract: A high-temperature part of the present disclosure includes: a high-temperature part body which includes a base and a coating layer formed on a part of a surface of the base; and a protective layer which is formed on at least a part of a surface of the coating layer. The protective layer is formed of a material which is allowed to disappear from a surface of the coating layer under an operation environment of a gas turbine.

Abstract: A combustor of the present disclosure includes: a mixing portion which is provided with a plurality of mixing passages passing through the mixing portion so as to be extended from an upstream end surface to a downstream end surface of the mixing portion intersecting an axis of the combustor, air being introduced to the plurality of the mixing passages from the upstream end surface of the mixing portion; and a fuel supply portion which is configured to supply the air introduced to the mixing passages with fuel to generate mixed fluid, wherein flow paths of the mixing passages have different pressure loss coefficients so that the differences in the flow velocity of the mixed fluid flowing through the mixing passages at the downstream end surface of the mixing portion are greater than those of a case where the mixing passages have the same flow path shape.

Abstract: A fuel injector has a body extending in an axial direction. The body includes: an axial passage formed so as to extend in the axial direction; a radial passage formed so as to communicate at one end with the axial passage and to open at another end to an outer surface of the body; and an internal passage including a first opening and a second opening open to the outer surface, and formed so as to extend inside the body from the first opening to the second opening. The first opening and the second opening are located opposite to each other across a third opening, through which the radial passage opens to the outer surface, in a circumferential direction centered on an axis of the body.

Abstract: A tail pipe (50) comprises: a pipe (51); an acoustic attenuator (61) that forms an acoustic space (Ss) on the outer peripheral side of the pipe (51); and a cooling air jacket (65) that forms a cooling air space (Sa) isolated from the outer space (So), which is the space on the outer peripheral side of the pipe (51). The pipe (51) has: a first air flow path (56) that is formed between the outer peripheral surface (55o) and the inner peripheral surface (55i); and an acoustic hole (59) that penetrates from the acoustic space (Ss) to a combustion space (Sc), which is a space on the inner peripheral side of the pipe (51c). The first air flow path (56) has: an inlet (56i) that faces into the cooling air space (Sa) and guides the air in the cooling air space (Sa) into the first air flow path (56); and an outlet (56o) that faces into the acoustic space (Ss) and guides the air passing through the first air flow path (56) into the acoustic space (Ss).

Abstract: A state determining device determines a state of a gas turbine connected to an electric generator. The gas turbine includes a compressor that compresses intake air into compression air, a fuel supply device that supplies fuel, a combustor that mixes the compression air supplied from the compressor and the fuel supplied from the fuel supply device and combusts a resultant mixture to generate combustion gas, and a turbine that is rotated with the generated combustion gas.

Abstract: An IGV opening command value is corrected to calculate an actual opening equivalent value that indicates an approximate value of an actual opening. A temperature estimation value, for a case where a mixture of fuel and in-flowing air is combusted, is calculated using the actual opening equivalent value, atmospheric conditions, and an output from a gas turbine. A fuel distribution command value that indicates distribution of fuel output from a plurality of fuel supply systems is calculated on the basis of the temperature estimation value. The fuel distribution command value and a fuel control signal command value that indicates the total flow rate of fuel to be output to the plurality of fuel supply systems are acquired, and respective valve openings of fuel flow rate regulating valves of the fuel supply systems are calculated on the basis of the fuel distribution command value and the fuel control signal command value.

Abstract: An IGV opening command value is corrected to calculate an actual opening equivalent value that indicates an approximate value of an actual opening. A temperature estimation value, for a case where a mixture of fuel and in-flowing air is combusted, is calculated using the actual opening equivalent value, atmospheric conditions, and an output from a gas turbine. A fuel distribution command value that indicates distribution of fuel output from a plurality of fuel supply systems is calculated on the basis of the temperature estimation value. The fuel distribution command value and a fuel control signal command value that indicates the total flow rate of fuel to be output to the plurality of fuel supply systems are acquired, and respective valve openings of fuel flow rate regulating valves of the fuel supply systems are calculated on the basis of the fuel distribution command value and the fuel control signal command value.

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 according to the invention includes a combustor basket to which air A is supplied from the outside, a plurality of first nozzles that are annularly provided along the inner periphery of the combustor basket and that supply premixed gas M of the air and fuel to the inside of the combustor basket, and a transition piece in which the combustor basket is connected to a base end thereof and which burns the premixed gas supplied from the first nozzles, thereby forming a flame front spread to the outer periphery side toward the leading end in an axial direction, wherein each first nozzle supplies the premixed gas with fuel concentration changed around the center axis of the first nozzle such that the flame front has a uniform temperature in the axial direction.

Abstract: A state determining device determines a state of a gas turbine connected to an electric generator. The gas turbine includes a compressor that compresses intake air into compression air, a fuel supply device that supplies fuel, a combustor that mixes the compression air supplied from the compressor and the fuel supplied from the fuel supply device and combusts a resultant mixture to generate combustion gas, and a turbine that is rotated with the generated combustion gas.

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 fuel control method for a gas turbine with a combustor being formed of at least two groups of a pluralities of main nozzles for supplying fuel, and that supplies fuel from the main nozzles of all groups upon ignition of the combustor (S1), and supplies fuel from three main nozzles of a group A during subsequent acceleration of the gas turbine (S3). Because fuel is injected from a small number of the main nozzles during acceleration, the fuel flow rate per one main nozzle is increased, thereby increasing the fuel-air ratio (fuel flow rate/air flow rate) in a combustion region and improving the combustion characteristics. Accordingly, the generation of carbon monoxide and unburned hydrocarbon is reduced, whereby no bypass valve is required and manufacturing costs are reduced.

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: In a communicating structure between combustors that generates combustion gas inside pipe pieces and a turbine portion that generates a rotational driving force by making the combustion gas sequentially pass through a turbine stage formed of turbine stator vanes and turbine rotor blades, at least some of the first-stage turbine stator vanes closest to the combustor among the turbine stator vanes are disposed downstream of sidewalls of one pipe piece and another pipe piece that are adjacent to each other, and the distance from leading edges of the first-stage turbine stator vanes disposed downstream of the sidewalls of the pipe pieces to end portions of the sidewalls closer to the turbine portion is equal to or less than a spacing between an internal surface of the sidewall of the one pipe piece and an internal surface of the sidewall of the other pipe piece.

Abstract: A combustor includes a combustor external cylinder, a tubular combustor basket installed in the combustor external cylinder, a compressed air channel defined between the combustor external cylinder and the combustor basket, and a plurality of fuel nozzles installed in the combustor basket. Compressed air flowing along the compressed air channel is approximately reversed in the flow direction at an end of the combustor basket, and is introduced into the plurality of fuel nozzles. Fuel injection pegs made up of an upstream side fuel injection peg injecting upstream side fuel and a downstream side fuel injection peg injecting downstream side fuel, are installed in the compressed air channel. Concentration fluctuation of the upstream side fuel caused by pressure fluctuation in the combustor is configured so as to reduce a peak of concentration fluctuation of the downstream side fuel at a combustion start position of the combustor.

Abstract: An acoustic damper of the present invention is objected to obtain a sound absorption effect of a combustor in an extensive range of frequency band. The acoustic damper includes an acoustic pipe body attached to a combustor so as to communicate with an inside of the combustor, and the acoustic pipe body is provided with a plurality of passages whose extension lengths are different from each other inside the acoustic pipe body.

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: A gas turbine is provided with a combustor having a pilot nozzle, a first main nozzle, and a second main nozzle. A combustor control device has a load interruption detector which detects load interruption of the gas turbine, a pilot nozzle flow rate control unit which increases the amount of premixed fuel supplied to the pilot nozzle, based on the detection of the load interruption, a first main nozzle flow rate control unit which reduces the amount of premixed fuel supplied to the first main nozzles, based on the detection of the load interruption, and a second main nozzle flow rate control unit which reduces the amount of premixed fuel supplied to the second main nozzles to a predetermined amount, based on the detection of the load interruption, and then further reduces the amount of premixed fuel supplied after the elapse of a predetermined time.