A gas turbine combustor comprising a burner (18) including:
a plurality of fuel nozzles (15) to supply a fuel (5); a fuel nozzle plate (14) to supports end portions of the fuel nozzles structurally and being configured to distribute the fuel flowing from an upstream side to the fuel nozzles; and
a swirler (13) including a plurality of air holes (21) to supply combustion air, wherein
the fuel nozzle plate is provided with a fuel nozzle receiving hole to receive the fuel nozzle, and the fuel nozzle plate and the fuel nozzle inserted in the fuel nozzle receiving hole are connected to each other from an upstream side of the fuel nozzle plate by welding.
