Patent ID: 8671690
Filing Date: 2014-03-18
Classification: F23R

Abstract:
1. A combustor of a gas turbine, the combustor having a combustion burner, comprising: a fuel nozzle; and swirl vanes which are arranged at a plurality of locations, along a circumferential direction, on an outer peripheral surface of the fuel nozzle in such a state as to extend along an axial direction of the fuel nozzle, said swirl vanes are progressively curved from an upstream side toward a downstream side of a flow of air flowing along the axial direction of the fuel nozzle in order to swirl the air around the fuel nozzle, wherein the combustor comprises: injection holes, formed at a position on the upstream side of the flow of air on a vane ventral surface and a vane dorsal surface of each swirl vane, for injecting a fuel; fuel passages for supplying the fuel individually to the injection holes formed in each swirl vane; valves provided in the respective fuel passages; and a control section for controlling the valves to open or close, and the control section brings all of the valves to an open state when the gas turbine is in a full load state, and controls an opening of the valves, which are provided in the fuel passages for supplying the fuel to the injection holes formed in a specific number of the swirl vanes of the fuel nozzle arranged adjacently as a group in the circumferential direction, in accordance with a load, and closes valves of the remaining swirl vanes of the fuel nozzle, when the gas turbine is in a partial load state.