Abstract: A fuel nozzle assembly and a gas turbine combustor including the same are provided. The fuel nozzle assembly may include an end plate coupled to one end of an annular casing, and a fuel nozzle configured such that one end thereof is supported by the end plate and the other end thereof extends outward. The fuel nozzle may include a center fuel nozzle and a plurality of side fuel nozzles arranged annularly to surround the center fuel nozzle. The side fuel nozzle may include a nozzle body located at a center thereof, a shroud spaced outward from the nozzle body, and a plurality of swirlers located between the nozzle body and the shroud. Each of the swirlers may include a leading edge directed toward the end plate and a trailing edge located opposite the leading edge. In each of the side fuel nozzles, distances between the leading edges are different from each other.

Abstract: 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.

Abstract: A combustor has an axial fuel staging system to allow a fuel-air mixture to be injected from two axially spaced stages using an injector for injection of a secondary fuel-air mixture. The combustor includes a liner defining a combustion chamber; a transition piece coupled to a rear end of the liner; a flow sleeve defining an annular channel by surrounding the liner and the transition piece; and at least one injector disposed on a circumferential position of the flow sleeve to inject a mixture of fuel and air into the combustion chamber. Each of the at least one injector includes an injection pipe extending radially and passing through both the flow sleeve and either of the liner and the transition piece; a plate coupled to the injection pipe; and a plurality of mixing passages formed through the plate. The combustor improves fuel-air mixing and prevents flash back.

Abstract: 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.

Abstract: A fuel nozzle assembly and a gas turbine combustor including the same are provided. The fuel nozzle assembly may include an end plate coupled to one end of an annular casing, and a fuel nozzle configured such that one end thereof is supported by the end plate and the other end thereof extends outward. The fuel nozzle may include a center fuel nozzle and a plurality of side fuel nozzles arranged annularly to surround the center fuel nozzle. The side fuel nozzle may include a nozzle body located at a center thereof, a shroud spaced outward from the nozzle body, and a plurality of swirlers located between the nozzle body and the shroud. Each of the swirlers may include a leading edge directed toward the end plate and a trailing edge located opposite the leading edge. In each of the side fuel nozzles, distances between the leading edges are different from each other.

Abstract: A fuel nozzle assembly and a gas turbine combustor including the same are provided. The fuel nozzle assembly may include an end plate coupled to one end of an annular casing, and a fuel nozzle configured such that one end thereof is supported by the end plate and the other end thereof extends outward. The fuel nozzle may include a center fuel nozzle and a plurality of side fuel nozzles arranged annularly to surround the center fuel nozzle. The side fuel nozzle may include a nozzle body located at a center thereof, a shroud spaced outward from the nozzle body, and a plurality of swirlers located between the nozzle body and the shroud. Each of the swirlers may include a leading edge directed toward the end plate and a trailing edge located opposite the leading edge. In each of the side fuel nozzles, distances between the leading edges are different from each other.

Abstract: A fuel nozzle assembly and a gas turbine combustor including the same are provided. The fuel nozzle assembly may include an end plate coupled to one end of an annular casing, and a fuel nozzle configured such that one end thereof is supported by the end plate and the other end thereof extends outward. The fuel nozzle may include a center fuel nozzle and a plurality of side fuel nozzles arranged annularly to surround the center fuel nozzle. The side fuel nozzle may include a nozzle body located at a center thereof, a shroud spaced outward from the nozzle body, and a plurality of swirlers located between the nozzle body and the shroud. Each of the swirlers may include a leading edge directed toward the end plate and a trailing edge located opposite the leading edge. In each of the side fuel nozzles, distances between the leading edges are different from each other.

Abstract: A combustor includes a flow guide installed in an air channel to simultaneously implement collision cooling and convection cooling of a combustor liner and a transition piece. The air channel is formed by an inner casing and an outer casing which are spaced apart from each other by a predetermined distance, through which combustion air is introduced to the combustor in order to produce a fuel-air mixture. The flow guide is attached to an inner surface of the outer casing and extending a predetermined length towards the inner casing so as to guide the combustion air flowing through the air channel toward a surface of the inner casing. The flow guide includes a channel inlet formed on an upstream side; a channel outlet formed on a lower surface facing the inner casing; and a guide channel communicating with each of the channel inlet and the channel outlet.

Abstract: A combustor has an axial fuel staging system to allow a fuel-air mixture to be injected from two axially spaced stages using an injector for injection of a secondary fuel-air mixture. The combustor includes a liner defining a combustion chamber; a transition piece coupled to a rear end of the liner; a flow sleeve defining an annular channel by surrounding the liner and the transition piece; and at least one injector disposed on a circumferential position of the flow sleeve to inject a mixture of fuel and air into the combustion chamber. Each of the at least one injector includes an injection pipe extending radially and passing through both the flow sleeve and either of the liner and the transition piece; a plate coupled to the injection pipe; and a plurality of mixing passages formed through the plate. The combustor improves fuel-air mixing and prevents flash back.

Abstract: A combustor includes a nozzle casing; a head end plate coupled to one end of the nozzle casing and having a plurality of supply holes through which fuel and air are respectively supplied; a nozzle assembly provided inside the nozzle casing and having a plurality of nozzles fixed to the nozzle end plate to receive the fuel and air from the supply holes and a nozzle cap having a plurality of through-holes surrounding the nozzles; and a plurality of fuel pegs disposed at predetermined intervals along an inner circumferential surface of the nozzle casing to inject the fuel into an air channel between the nozzles and the nozzle cap. The fuel peg includes a support mounted on an inner surface of the nozzle casing; and an extension extending a predetermined length inside an air channel and having a fuel injection hole formed on one side.

Abstract: A combustor includes a flow guide installed in an air channel to simultaneously implement collision cooling and convection cooling of a combustor liner and a transition piece. The air channel is formed by an inner casing and an outer casing which are spaced apart from each other by a predetermined distance, through which combustion air is introduced to the combustor in order to produce a fuel-air mixture. The flow guide is attached to an inner surface of the outer casing and extending a predetermined length towards the inner casing so as to guide the combustion air flowing through the air channel toward a surface of the inner casing. The flow guide includes a channel inlet formed on an upstream side; a channel outlet formed on a lower surface facing the inner casing; and a guide channel communicating with each of the channel inlet and the channel outlet.

Abstract: A supporting device for a gas turbine includes a base frame; a fixing member installed on the base frame so as to support one end of a gas turbine; and an absorbing member installed on the base frame so as to support the other end of the gas turbine. The absorbing member having lower stiffness than the fixing member so as to deform in first and second directions when the gas turbine thermally expands.

Abstract: A supporting device for a gas turbine includes a base frame; a fixing member installed on the base frame so as to support one end of a gas turbine; and an absorbing member installed on the base frame so as to support the other end of the gas turbine. The absorbing member having lower stiffness than the fixing member so as to deform in first and second directions when the gas turbine thermally expands.