A gas turbine combustor

Combustor of a gas turbine, the combustion chamber having a combustion burner comprising: a fuel nozzle, and Swirl vanes which are arranged at a plurality of locations along a circumferential direction of an outer peripheral surface of the fuel nozzle so as to extend along an axial direction of the fuel nozzle, and gradually flowing curve air from an upstream side to a downstream side of a flow of along the axial direction of the fuel nozzle, for swirling the air around the fuel nozzle around, characterized, in that the combustion chamber comprising: Injection holes are formed in each swirl vane for injecting a fuel, Fuel passages for individually supplying the fuel to the swirl formed in each injection holes, in the respective fuel passages provided valves, and a control section for controlling the opening or closing of the valves, wherein the control section enables all valves in an opening state when the gas turbine is in a full load state, and a degree of opening certain valves in accordance with a load ...