A combustor includes: a nozzle main body having a shaft body and a swirl vane; a first fuel flow path configured to supply fuel to a first fuel injection hole defined in the nozzle main body; a second fuel flow path configured to supply fuel to a second fuel injection hole defined in the nozzle main body on a radial outer side of the first fuel injection hole; a first regulating valve provided in the first fuel flow path and configured to regulate a flow rate of the fuel in the first fuel flow path; a temperature sensor-configured to detect a temperature on a downstream side of the swirl vane; and a control device configured to control the first regulating valve so that the flow rate of the fuel in the first fuel flow path is lowered when the temperature detected by the temperature sensor satisfies a predetermined condition.

A combustor and a gas turbine capable of uniformly supplying air into a burner are provided. The combustor may include a burner including a tubular nozzle casing, a head plate coupled to an end of the nozzle casing, and a plurality of nozzles to inject fuel and air, and a duct assembly coupled to the burner, a mixture of the fuel and the air being burned in the duct assembly to produce combustion gas. Each of the nozzles may include outer nozzles and an inner nozzle installed inside the outer nozzles, each of the outer nozzles may include a nozzle tube configured to provide a channel through which air and fuel flow and a nozzle shroud configured to surround the nozzle tube, and a flow distribution member may be installed between the head plate and the nozzle shroud to distribute a flow rate of air introduced into the outer nozzle.

A fuel nozzle assembly and a gas turbine having the fuel nozzle assembly includes a fuel nozzle guide disposed in a compressed air channel formed between a body and a housing of a gas turbine and includes a nozzle body disposed in the housing, a shroud mounted on an outer side of the nozzle body, and two or more flow guides arranged at predetermined distances from each other between the shroud and the outer side of the nozzle body and formed to correspond to the shape of an end of the shroud and the shape of the outer surface of the nozzle body.

A combustor and a gas turbine capable of uniformly supplying air into a burner are provided. The combustor may include a burner including a tubular nozzle casing, a head plate coupled to an end of the nozzle casing, and a plurality of nozzles to inject fuel and air, and a duct assembly coupled to the burner, a mixture of the fuel and the air being burned in the duct assembly to produce combustion gas. Each of the nozzles may include outer nozzles and an inner nozzle installed inside the outer nozzles, each of the outer nozzles may include a nozzle tube configured to provide a channel through which air and fuel flow and a nozzle shroud configured to surround the nozzle tube, and a flow distribution member may be installed between the head plate and the nozzle shroud to distribute a flow rate of air introduced into the outer nozzle.

A combustor nozzle capable of injecting fuel uniformly, a combustor including the combustor nozzle, and a gas turbine including the combustor are provided. The combustor nozzle includes a premix passage in which air and fuel are mixed, wherein the premix passage includes a plurality of pegs configured to inject fuel and guide an air flow and a plurality of mixing bars configured to mix air and fuel injected from the plurality of pegs, the mixing bar having a twisted structure.

A fuel injector for a combustor of a gas turbine engine is disclosed herein. The fuel injector includes a fuel stem assembly for receiving and distributing fuel and an injector head receiving fuel from the fuel stem assembly. The injector head can include an injector body, swirler vanes, a pilot assembly, passages, and fuel galleries. The pilot assembly can include pilot struts and a pilot tube. The swirler vanes and pilot struts can include passages to transport the pilot fuel from the fuel stem assembly to the pilot tube.

The fuel nozzle for the gas turbine includes a radial swirler and an axial swirler. The radial swirler is arranged to swirl a first flow of a first oxidant-fuel mixture and the axial swirler is arranged to swirl a second flow of a second oxidant-fuel mixture. The first flow may be fed by a central conduit and the second flow may be fed by an annular conduit surrounding the central conduit.

A multi-fueled impulse initiator that includes a fuel source equipped with a control valve, an air source equipped with a control valve, a removable air flow insert having opposing inlet and outlet faces, an air expansion chamber fluidly connected to both the air source and the inlet face of the removable air flow insert, and an igniter assembly having a sparking tip. The removable air flow insert includes channels traversing from the inlet face to the outlet face of the air flow insert.

A combustor nozzle capable of injecting fuel uniformly, a combustor including the combustor nozzle, and a gas turbine including the combustor are provided. The combustor nozzle includes a premix passage in which air and fuel are mixed, wherein the premix passage includes a plurality of pegs configured to inject fuel and guide an air flow and a plurality of mixing bars configured to mix air and fuel injected from the plurality of pegs, the mixing bar having a twisted structure.

A swirler for creating a swirling fuel/air mix having vanes extending radially around a central axis of the swirler and positioned on an annular base. The swirler has mixing channels for mixing the fuel and the air. At least one mixing channel is defined by opposing walls of two adjacent vanes. At least one of the opposing walls includes a primary side injection opening for ejecting a stream of fuel into the mixing channel; and a secondary side injection opening which corresponds to the primary side injection opening and is for ejecting a jet of fuel into the mixing channel. The secondary side injection opening is positioned on the wall such that the jet from the secondary side injection opening creates turbulence, within the mixing channel, in the stream from the primary side injection opening. The turbulence increases mixing of fuel and air.