Doosan Heavy Industries & Construction Co., Ltd

Other

Ujin Roh

Junhyeong Park

Dongsik Han

Jongho Uhm

Jae Won Seo

Youngsam Shim

Young Bong Kim

Jinhoon Choe

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.

Fuel nozzle assembly and gas turbine having the same

The combustor of a gas turbine may include: a burner, including a plurality of nozzles, to eject fuel and air; and a duct assembly, coupled to one side of the burner, to combust the fuel and the air therein and transfer combustion gas to a turbine, where the burner may include a flow guide member to guide a flow of air to be drawn into the nozzles, and a plurality of holes may be formed in the flow guide member.

Combustor, and gas turbine including the same

A fuel nozzle assembly includes an inner fuel nozzle; a plurality of outer fuel nozzles disposed radially around the inner fuel nozzle, each outer fuel nozzle including a central body for fuel injection, a shroud spaced apart from and surrounding the central body, the shrouds forming an outer periphery of the fuel nozzle assembly, and an inlet formed at one end of the shroud; and a peripheral rim formed at the inlets and disposed to cover at least a portion of the outer periphery. The fuel nozzle assembly is connected to an end plate of a combustion chamber. The one end of a corresponding shroud is disposed at a set distance from an end plate of a combustion chamber, the set distance depending on at least one of relative positions of the inner fuel nozzle and the plurality of outer fuel nozzles and an inlet radius of the corresponding shroud.

Fuel nozzle assembly, and combustor and gas turbine including the same

A fuel supply nozzle for injecting fuel into a combustor in a shape of a pipe having an outer peripheral wall and an inner peripheral wall extended from a route to a tip. The fuel supply nozzle includes a first fuel discharge passage formed at the inside of the inner peripheral wall extending from the route to the tip, at least one or more vanes disposed on the outer peripheral wall spaced apart from the tip by a given distance and having vane fuel outlets communicating with the first fuel discharge passage, and a burning section formed on a given area adjacent to the tip to allow a thickness between the outer peripheral wall and the inner peripheral wall to be lower than the other section thereof.

Fuel supply nozzle for minimizing burning damage

A gas turbine combustor includes a liner and a transmission piece. Fuel injected in the liner from a fuel nozzle of a gas turbine mixes with compressed air. High temperature gas produced in the liner is transmitted through the transmission piece. The liner is disposed in a flow sleeve in which cooling holes are formed. The transition piece is disposed in a perforated sleeve. Compressed air supplied through holes formed in the perforated sleeve collides with the transition piece. The liner includes a cooling sleeve disposed thereon that divides the air supplied through the cooling holes of the flow sleeve and the compressed air flowing to a space portion between the liner and the flow sleeve.

Growing community of inventors

Changwon-si, South Korea

Ujin Roh