Doosan Enerbility Co., Ltd.

Young Gun Go

Hyun Soo An

Kyoung Taek Oh

Sang Pil Jo

Sung Gju Kang

Ho Keun Kim

Eun Seong Cho

Song-Hun Cha

SangPil Jo

Joong Hyun Lim

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.

Jet nozzle, combustor, and gas turbine including same

A combustor nozzle includes a plurality of mixing tubes through which air and fuel flow, a plurality of accommodation tubes each accommodating and supporting the plurality of mixing tubes therein, a first fuel tube coupled to each accommodation tube to supply a first fuel into the accommodation tube, a second fuel tube coupled to each accommodation tube to supply a second fuel into the accommodation tube, and a fuel supply member supplying the first fuel accommodated in the accommodation tube into each mixing tube, wherein the accommodation tube has a fuel container combined with the second fuel tube to contain the second fuel therein, and an auxiliary injection member is disposed on the fuel container to inject the second fuel from the accommodation tube.

Combustor nozzle, combustor, and gas turbine including same

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.

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.

Combustor nozzle, combustor, and gas turbine including the same

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.

Hollow nozzle, combustor including hollow nozzle, and gas turbine including combustor

A micromixer configured to prevent auto-ignition and flash-back phenomena, and a combustor including the same are provided. The micromixer includes an inlet flow path configured including an inlet formed on one end and receiving a first fluid and a supply port formed on an inner wall and receiving a second fluid, and the inlet flow path is configured to flow a mixed fluid formed by mixing the first fluid and the second fluid, 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.

Micromixer and combustor having the same

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.

Micro-mixer module and combustor having the same

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.

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.

Injection nozzle, combustor including same nozzle, and gas turbine including same combustor

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.

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.

Micro-mixer bundle assembly, and combustor and gas turbine having same

Disclosed is a hybrid power generation facility. The hybrid power generation facility includes a gas turbine including a compressor configured to compress air introduced from an outside, a combustor configured to mix the compressed air with fuel and to combust the air and fuel mixture, and a turbine configured to produce power with first combustion gas discharged from the combustor, a boiler including a combustion chamber and a burner installed in the combustion chamber and into which the first combustion gas discharged from the turbine of the gas turbine is introduced, a steam turbine through which steam generated in the combustion chamber passes, a first GT (gas turbine) pipeline connected between the turbine of the gas turbine and the burner, a first air pipeline connected to the first GT pipeline to supply oxygen to the burner, a first oxygen sensor installed at an inlet of the burner to measure an oxygen concentration of a fluid flowing into the burner, and a first GT damper installed in the first GT pipeline to control a flow rate of the fluid flowing through the first GT pipeline according to the oxygen concentration measured by the first oxygen sensor.

Hybrid power generation equipment and control method thereof

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.

Growing community of inventors

Yongin, South Korea

Young Gun Go