Abstract: Proposed are a jet nozzle, and a combustor and a gas turbine including the jet nozzle. The jet nozzle is formed on an inner surface of a combustor to supply fluid into an interior of a liner of the combustor in a direction intersecting with a progress direction of combustion gases primarily combusted in a combustion chamber in the interior of the liner. The jet nozzle includes a fluid inlet, through which fluid is externally introduced, and a fluid outlet including a first fluid outlet member, through which a portion of the fluid introduced through the fluid inlet is discharged so as to be rotated in one direction, and a second fluid outlet member, through which the rest of the fluid is discharged so as to be rotated in a direction different from the rotation direction of the fluid discharged from the first fluid outlet member.

Abstract: A hollow nozzle including a tubular nozzle casing and a plurality of rotary vanes arranged radially along an inner surface of an inlet of the nozzle casing, through which compressed air is introduced, forming a hollow center at the center of the nozzle casing through which the compressed air flows, each of the rotary vanes including a first fuel injection hole through which a first type of fuel having a predetermined flame propagation speed is injected toward the hollow center, and a second fuel injection hole through which a second type of fuel having a higher flame propagation speed than the first type of fuel is injected, a combustor including the hollow nozzle, and a gas turbine including the combustor.

Abstract: Disclosed are a jet nozzle, and a combustor and a gas turbine including the jet nozzle. The jet nozzle is formed on an inner surface of a combustor to supply fluid into an interior of a liner of the combustor in a direction intersecting with a progress direction of combustion gases primarily combusted in a combustion chamber in the interior of the liner. The jet nozzle includes a body section provided with a fluid inlet on one end, through which fluid is introduced, and a fluid outlet on the other end, through which the fluid introduced through the fluid inlet is discharged, and a swirler section provided inside the body section to allow a portion of the fluid introduced into one side of the body section to rotate in a clockwise direction and to allow the rest of the fluid introduced into the other side of the body section to rotate in a counterclockwise direction.

Abstract: Proposed are a jet nozzle, and a combustor and a gas turbine including the jet nozzle. The jet nozzle is formed on an inner surface of a combustor to supply fluid into an interior of a liner of the combustor in a direction intersecting with a progress direction of combustion gases primarily combusted in a combustion chamber in the interior of the liner. The jet nozzle includes a body section provided with a fluid inlet on a first end, through which fluid is introduced, and a fluid outlet on a second end, through which the fluid introduced through the fluid inlet is discharged while generating a vortex, and a baffle section formed on an inner peripheral surface of the second end of the body section and configured to enhance the generation of a counter-rotary shear layer vortex in the fluid discharged out of the fluid outlet through the body section.

Abstract: A micro-mixer bundle assembly and a combustor and a gas turbine having the same are provided. The micro-mixer bundle assembly includes a plurality of micro-mixers, each of the plurality of micro-mixers including an inlet portion formed on one side and through which a first fluid is introduced and a feed hole formed in a circumferential wall and through which a second fluid is fed, wherein the first fluid introduced through the inlet portion and the second fluid fed through the feed hole are mixed to form a fluid mixture which is injected into a combustion chamber, and a plurality of micro-mixer bundles, each of the plurality of micro-mixer bundles including the plurality of micro-mixers arranged therein, wherein a cross-sectional shape of an outlet of the micro-mixers disposed in one of the micro-mixer bundles is different from a cross-sectional shape of an outlet of the micro-mixers disposed in the other micro-mixer bundles.

Abstract: An injection nozzle installed in a combustor of a gas turbine to inject fuel and compressed air to a combustion chamber is provided. The injection nozzle includes an inlet portion into which fuel and compressed air are introduced, an outlet portion installed downstream of the inlet portion in a flow direction of fluid and configured to discharge the fuel and compressed air to the combustion chamber, and an intermediate portion obliquely installed between the inlet portion and the outlet portion and connected to each of the inlet portion and outlet portion.

Abstract: Disclosed herein is a nozzle for a combustor that burns fuel containing hydrogen, which includes a plurality of mixing tubes through which air and fuel flow, and a multi-tube configured to insert the mixing tubes thereinto and support the same, wherein each of the mixing tubes has an inlet formed at a longitudinal end thereof for introduction of a first fluid, and a plurality of supply ports formed on a circumferential surface thereof for introduction of a second fluid, the mixing tube has a plurality of first supply ports formed on a first surface thereof, and a plurality of second supply ports formed on a second surface facing the first surface, and the first supply ports are staggered with the second supply ports.

Abstract: Disclosed is a hybrid power generation facility.

Abstract: An injection nozzle installed in a combustor of a gas turbine to inject fuel and compressed air into a combustion chamber is provided. The injection nozzle includes an inlet portion into which fuel and compressed air are introduced, an outlet portion disposed downstream of the inlet portion in a flow direction of fluid and configured to discharge the fuel and compressed air to the combustion chamber, and an intermediate portion disposed between the inlet portion and the outlet portion and connected obliquely to each of the inlet portion and outlet portion, wherein each of the inlet portion, the outlet portion, and the intermediate portion has a prismatic shape.

Abstract: A micro-mixer bundle assembly and a combustor and a gas turbine having the same are provided. The micro-mixer bundle assembly includes a plurality of micro-mixers, each of the plurality of micro-mixers including an inlet portion formed on one side and through which a first fluid is introduced and a feed hole formed in a circumferential wall and through which a second fluid is fed, wherein the first fluid introduced through the inlet portion and the second fluid fed through the feed hole are mixed to form a fluid mixture which is injected into a combustion chamber, and a plurality of micro-mixer bundles, each of the plurality of micro-mixer bundles including the plurality of micro-mixers arranged therein, wherein a cross-sectional shape of an outlet of the micro-mixers disposed in one of the micro-mixer bundles is different from a cross-sectional shape of an outlet of the micro-mixers disposed in the other micro-mixer bundles.

Abstract: A micro-mixer module and a combustor having the same are provided. The micro-mixer module includes a micro-mixer having an inlet portion formed on one side and through which a first fluid is introduced and a feed hole formed in a circumferential wall and through which a second fluid is fed, wherein the first fluid introduced through the inlet portion and the second fluid fed through the feed hole are mixed to form a fluid mixture which is injected into a combustion chamber, and an air hole formed at a side end of the combustor chamber of the micro-mixer.

Abstract: A micromixer which transfers radiant heat by flame generated in a combustion chamber to a micromixer to prevent auto-ignition and flash-back phenomena occurring in the micromixer, and a combustor including the same are provided. The micromixer includes an inlet flow path configured to include an inlet formed on one end and through which first fluid flows and a supply port formed on an inner wall and through which second fluid, and to flow mixed fluid formed by mixing the first fluid introduced through the inlet and the second fluid supplied through the supply port, an outlet flow path injecting the mixed fluid to a combustion chamber and formed at a position spaced apart from a virtual extension line of the inlet flow path, and an inclined flow path connecting the inlet flow path and the outlet flow path and formed to be inclined at a predetermined angle to reduce transfer of radiant heat by flame generated in the combustion chamber to the inlet flow path.

Abstract: An injection nozzle installed in a combustor of a gas turbine to inject fuel and compressed air into a combustion chamber is provided. The injection nozzle includes an inlet portion through which fuel and compressed air are introduced, an outlet portion disposed downstream of the inlet portion in a flow direction of fluid and configured to discharge the fuel and compressed air to the combustion chamber, and an intermediate portion connected obliquely to each of the inlet portion and the outlet portion, wherein the inlet portion and the intermediate portion are symmetrically formed based on an imaginary central line extending from the outlet portion along the flow direction of fluid and passing through a center of the outlet portion.

Abstract: An injection nozzle installed in a combustor of a gas turbine to inject fuel and compressed air into a combustion chamber is provided. The injection nozzle includes an inlet portion into which fuel and compressed air are introduced, an outlet portion disposed downstream of the inlet portion in a flow direction of fluid and configured to discharge the fuel and compressed air to the combustion chamber, and an intermediate portion disposed between the inlet portion and the outlet portion and connected obliquely to each of the inlet portion and outlet portion, wherein each of the inlet portion, the outlet portion, and the intermediate portion has a prismatic shape.

Abstract: An injection nozzle installed in a combustor of a gas turbine to inject fuel and compressed air to a combustion chamber is provided. The injection nozzle includes an inlet portion into which fuel and compressed air are introduced, an outlet portion installed downstream of the inlet portion in a flow direction of fluid and configured to discharge the fuel and compressed air to the combustion chamber, and an intermediate portion obliquely installed between the inlet portion and the outlet portion and connected to each of the inlet portion and outlet portion.

Abstract: Disclosed is a hybrid power generation facility.