Patent ID: 11204167

Abstract:
A gas turbine combustor includes a combustion chamber coupled to a nozzle unit that is radially partitioned into plural regions. Each region includes a nozzle casing; a nozzle supplied with fuel and air to produce a mixed gas of the fuel and the air and configured to be inserted into the nozzle casing and to inject the mixed gas into the combustion chamber; a fuel supply section coupled to an outer peripheral surface of the nozzle casing to supply the fuel to the nozzle through the outer peripheral surface; a fuel plenum formed in the nozzle casing to receive the fuel from the fuel supply section; and an air plenum formed in the nozzle casing toward the combustion chamber to receive a portion of the air supplied to the nozzle unit, the portion of air introduced to the air plenum through a first opening formed in the nozzle casing.