Hanwha Aerospace Co., Ltd.

Hee Ho Park

Su Hyeong Cho

Seung Chai Jung

Chul Ju Ahn

A fuel injection apparatus for a gas turbine includes a fuel supply pipe; a first manifold connected to the fuel supply pipe and comprising a nozzle through which fuel is sprayed; a second manifold at least partially surrounding the first manifold at a predetermined interval apart from the first manifold in a radial direction, the second manifold including: an air inlet through which a first portion of air is introduced into the second manifold; and a fuel outlet where the fuel sprayed through the nozzle collides with the air thereby forming mixed fuel; and a first swirler provided at a predetermined interval apart from the second manifold in the radial direction, the first swirler configured to swirl the air toward the air inlet and the fuel outlet.

Fuel injection apparatus for gas turbine

Provided is a combustor assembly. The combust assembly includes: a plurality of swirlers through which a first fluid that is a part of a fluid discharged from a compressor passes; a base portion, in which the plurality of swirlers are provided, comprising a first through hole formed between one swirler and another swirler from among the plurality of swirlers so that a second fluid that is another part of the fluid discharged from the compressor and different from the first fluid passes through the first through hole; and a deflector provided in the base portion so as to face the first through hole for changing a moving direction of the second fluid.

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Changwon-si, South Korea

Hee Ho Park