GAS TURBINE COMBUSTOR

PROBLEM TO BE SOLVED: To provide a gas turbine combustor which reduces a pressure loss in coaxial nozzles and reduces NOx emission by promoting the mixure of fuel and air. SOLUTION: The gas turbine combustor includes burners in which the plurality of rows of coaxial nozzles comprising a plurality of fuel nozzles and a plurality of air holes formed on an air hole plate and coaxial with the fuel nozzles are arranged annularly. A member for generating a turbulence of an air current is provided either at a tip of the fuel nozzle constituting the coaxial nozzle or within a flow passage of the air hole formed on the air hole plate where the tip of the fuel nozzle is positioned, so as to define the minimum flow passage cross sectional area of the air hole of the coaxial nozzle. The minimum flow passage cross sectional area of the air hole of the coaxial nozzle positioned in the burner arranged on the outer peripheral side out of the plurality of rows of burners is formed wider than the minimum flow passage cross sectional area of the air hole of the coaxial nozzle positioned in the burner arranged on the central side. COPYRIGHT: (C)2011,JPO&INPIT