Doosan Heavy Industries & Construction Co., Ltd

Other

Jongho Uhm

Jeongmin Kim

Ujin Roh

Disclosed herein is a combustor capable of improving impingement cooling performance by reducing the influence of a cross-flow on a jet flow. The combustor includes a combustion liner, in which fuel sprayed from fuel nozzles of a gas turbine is mixed with compressed air and the mixture is combusted, a sleeve surrounding the outer surface of the combustion liner while being spaced apart therefrom in order to form a flow passage for compressed air, a cooling hole formed in the sleeve to introduce compressed air discharged from a compressor into the flow passage, and a first auxiliary hole formed upstream of the cooling hole in the airflow direction. Compressed air discharged from the compressor is introduced into the flow passage through the first auxiliary hole, impinges with compressed air flowing through the flow passage, and forms an air column.

Combustor, gas turbine including the same and method of distributing compressed air in combustor

A fuel nozzle with turning guide is included in a gas turbine. The turning guide is disposed in an air inlet of the fuel nozzle to distribute a flow of compressed air and includes at least one of a turning separator, an inner separator, and an outer separator. The fuel nozzle includes a central body having an outer wall; a shroud concentrically disposed with respect to the central body and configured to surround the central body while maintaining a space for an air passage between an inner wall of the shroud and the outer wall of the central body; a rim formed on one end of the shroud and forming an air inlet communicating with the air passage; and a turning guide including a turning separator disposed in the air inlet, to make the air flow uniform, thereby suppressing the creation of an air pocket.

Fuel nozzle with turning guide and gas turbine including the same

Disclosed are a fuel nozzle assembly, and a fuel nozzle module and gas turbine having the same. The fuel nozzle assembly includes a fuel nozzle, a shroud spaced apart from the fuel nozzle and defining a flow path between an inner wall and the fuel nozzle, a rim formed around the shroud to guide air, and a turning guide spaced apart from the rim to distribute the air. The turning guide includes a turning separator spaced apart from the rim to extend in a circumferential direction of the rim, and inner separators extending in a radial direction of the rim to interconnect opposite circumferential ends of the turning separator and an outer surface of the fuel nozzle. The fuel nozzle assembly prevents air pockets, and ensures uniform supply of air, thereby preventing a local increase in combustion temperature inside the fuel nozzle and reducing generation of NOx.

Fuel nozzle assembly, and fuel nozzle module and gas turbine having 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.

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Yongin-si, South Korea

Jongho Uhm