Abstract: A combustor liner used for a gas turbine combustor and forming a combustion chamber includes: an outer side wall made of metal; a panel attached to an inner side of the outer side wall and made of a ceramic matrix composite material, the panel including a panel body facing the combustion chamber, and a connection piece rising from an exterior surface of the panel body at a side portion of the panel body and protruding in a lateral direction; and a connection unit configured to connect the panel to the outer side wall, the connection unit including an elastic member configured to bias at least one of the outer side wall and the connection piece, and a fixation member made of metal and configured to fix at least one of the connection piece and the elastic member to the outer side wall.

Abstract: A combustor liner used for a gas turbine combustor and forming a combustion chamber includes: an outer side wall made of metal; a panel attached to an inner side of the outer side wall and made of a ceramic matrix composite material, the panel including a panel body facing the combustion chamber, and a connection piece rising from an exterior surface of the panel body at a side portion of the panel body and protruding in a lateral direction; and a connection unit configured to connect the panel to the outer side wall, the connection unit including an elastic member configured to bias at least one of the outer side wall and the connection piece, and a fixation member made of metal and configured to fix at least one of the connection piece and the elastic member to the outer side wall.

Abstract: A burner device for supplying a mixture of a fuel gas and a combustion-supporting gas into a combustion region includes: a mixing path configured to inject the mixture from a downstream end portion of the mixing path into the combustion region; a fuel gas injection nozzle configured to inject the fuel gas into the mixing path toward the combustion region; and a combustion-supporting gas supply swirler configured to inject the combustion-supporting gas such that at least a part of the combustion-supporting gas collides directly with the fuel gas injected from the fuel gas injection nozzle, in a direction of a tangent line that is tangent to a fuel injection hole of the fuel gas injection nozzle on a cross-section.

Abstract: A combustor liner used for a gas turbine combustor and forming a combustion chamber includes: an outer side wall made of metal; a panel attached to an inner side of the outer side wall and made of a ceramic matrix composite material, the panel including a panel body facing the combustion chamber, and a connection piece rising from an exterior surface of the panel body at a side portion of the panel body and protruding in a lateral direction; and a connection unit configured to connect the panel to the outer side wall, the connection unit including an elastic member configured to bias at least one of the outer side wall and the connection piece, and a fixation member made of metal and configured to fix at least one of the connection piece and the elastic member to the outer side wall.

Abstract: A main fuel injector of a fuel injection device includes: a main outer air passage including an inlet that is open outward in a radial direction, the main outer air passage taking in compressed air through the inlet; a main inner air passage including an inlet that is open inward in the radial direction, the main inner air passage taking in the compressed air through the inlet; a merged air passage, in which the compressed air taken in by the main outer air passage and the compressed air taken in by the main inner air passage merge together; and a main fuel injection port configured to inject a fuel into the compressed air taken in by the main outer air passage or into the compressed air taken in by the main inner air passage.

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 device for supplying a mixture of a fuel gas and a combustion-supporting gas into a combustion region includes: a mixing path configured to inject the mixture from a downstream end portion of the mixing path into the combustion region; a fuel gas injection nozzle configured to inject the fuel gas into the mixing path toward the combustion region; and a combustion-supporting gas supply swirler configured to inject the combustion-supporting gas such that at least a part of the combustion-supporting gas collides directly with the fuel gas injected from the fuel gas injection nozzle, in a direction of a tangent line that is tangent to a fuel injection hole of the fuel gas injection nozzle on a cross-section.

Abstract: A fuel injection nozzle (31) of the present invention comprises a pre-mixing passage (34) which mixes fuel (103) and air (102) to generate an air-fuel mixture; and an injection port (33) which is located downstream of the pre-mixing passage (34) and injects the air-fuel mixture into a combustion chamber (26). The fuel injection port (33) has a slit shape and a width that is less than a dimension that is twice as large as a quenching distance.

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 combustor liner used for a gas turbine combustor and forming a combustion chamber includes: an outer side wall made of metal; a panel attached to an inner side of the outer side wall and made of a ceramic matrix composite material, the panel including a panel body facing the combustion chamber, and a connection piece rising from an exterior surface of the panel body at a side portion of the panel body and protruding in a lateral direction; and a connection unit configured to connect the panel to the outer side wall, the connection unit including an elastic member configured to bias at least one of the outer side wall and the connection piece, and a fixation member made of metal and configured to fix at least one of the connection piece and the elastic member to the outer side wall.

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 fuel injector (23) comprises a cylindrical passage (32) which opens in a combustion chamber (26), a fuel introduction passage (34) which guides fuel to a region of the cylindrical passage (32) which is closer to the combustion chamber (26), and an air introduction passage (35) which guides compressed air to the cylindrical passage (32) at a location that is upstream of a location at which the fuel is introduced to the cylindrical passage (32), wherein the fuel introduction passage (34) guides the fuel in a tangential direction of the cylindrical passage (32) in a transverse sectional view.

Abstract: A main fuel injector of a fuel injection device includes: a main outer air passage including an inlet that is open outward in a radial direction, the main outer air passage taking in compressed air through the inlet; a main inner air passage including an inlet that is open inward in the radial direction, the main inner air passage taking in the compressed air through the inlet; a merged air passage, in which the compressed air taken in by the main outer air passage and the compressed air taken in by the main inner air passage merge together; and a main fuel injection port configured to inject a fuel into the compressed air taken in by the main outer air passage or into the compressed air taken in by the main inner air passage.

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: Provided are a gas turbine combustor and a gas turbine, with which the amount of NOx exhaust emissions from a diffuse combustion-type duct burner can be reduced. A duct burner is provided with cylindrical fuel injection nozzles and air holes. The fuel injection nozzles are supported by an outside casing along eight axial centers included within a plane orthogonal to a center axis and arranged at equidistant intervals (45-degree intervals) in the circumferential direction. Sets of eight fuel injection nozzles are respectively constituted as single fuel injection nozzle rows, four fuel injection nozzle rows being arrayed at prescribed spacing along a direction of a center axis. The angular positions of the fuel injection nozzles are arrayed so as to be shifted by a half-pitch angle in opposing rows.

Abstract: A fuel injector (23) comprises a cylindrical passage (32) which opens in a combustion chamber (26), a fuel introduction passage (34) which guides fuel to a region of the cylindrical passage (32) which is closer to the combustion chamber (26), and an air introduction passage (35) which guides compressed air to the cylindrical passage (32) at a location that is upstream of a location at which the fuel is introduced to the cylindrical passage (32), wherein the fuel introduction passage (34) guides the fuel in a tangential direction of the cylindrical passage (32) in a transverse sectional view.

Abstract: Provided is a combustor that has an efficient cooling structure. Also provided is a gas turbine engine that is provided with the combustor. A combustor that is for a gas turbine and that is provided with a combustion liner and with a fuel injection part that is provided to one end of the combustion liner so as to pass through the combustion liner. The combustion liner is provided with an inner liner that forms a combustion chamber inside the combustion liner, with a coolant flow path that is an annular space that is formed outside the inner liner, and with a coolant supply means that supplies hydrogen gas to the coolant flow path. In this combustor, the inner liner that is the combustion chamber is cooled by the hydrogen gas that flows in the coolant flow path.

Abstract: A fuel injection nozzle (31) of the present invention comprises a pre-mixing passage (34) which mixes fuel (103) and air (102) to generate an air-fuel mixture; and an injection port (33) which is located downstream of the pre-mixing passage (34) and injects the air-fuel mixture into a combustion chamber (26). The fuel injection port (33) has a slit shape and a width that is less than a dimension that is twice as large as a quenching distance.

Abstract: A gas turbine (100) of the present invention is a gas turbine which uses a hydrogen gas as a fuel, and comprises a combustor (20) which includes a fuel injection nozzle (23), and has a combustion chamber (24) in an interior of the combustor; a steam supply unit (40) which supplies steam to the combustor (20) to decrease a combustion temperature; and an air drier (50) which removes the steam from air to be supplied to the combustor (20) to dry the air.