| CPC F23R 3/283 (2013.01) [F23R 3/04 (2013.01)] | 19 Claims |
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1. A nozzle assembly configured to discharge fuel and compressed air into a combustion chamber of a combustor of a gas turbine, the nozzle assembly comprising:
a nozzle body;
a plurality of injection nozzles provided inside the nozzle body and disposed to be spaced apart from each other, the plurality of injection nozzles having inner portions through which an air-fuel mixture of the fuel and a first portion of the compressed air flows; and
a side wall which is connected to a first side of the nozzle body,
wherein a cooling air inlet hole into which a second portion of the compressed air is introduced, as a cooling air, into a space where the plurality of injection nozzles is disposed is formed in the nozzle body, and a cooling air outlet hole through which the cooling air introduced from the cooling air inlet hole is discharged is formed in one region of the side wall,
wherein one side surface of the side wall meets an inside space of the nozzle body and an opposite side surface of the side wall meets the combustion chamber,
wherein the side wall is provided with a guide portion that protrudes toward the inside space of the nozzle body from the side wall meeting the combustion chamber, the guide portion including a contact region being in contact with the plurality of injection nozzles,
wherein the contact region is in a curved shape such that a diameter of the contact region decreases and then increases from an upstream end to a downstream end based on a flow direction of the air-fuel mixture in the plurality of injection nozzles,
wherein a most downstream end of each of the plurality of infection nozzles is disposed at the side wall such that the plurality of injection nozzles do not protrude downstream than the side wall,
wherein a plane at which the most downstream end of each of the plurality of injection nozzles is disposed is aligned with the side wall through which the cooling air is discharged to the combustion chamber.
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