Gas turbine combustor and method for operating same

摘要

Gas turbine combustor includes a double-swirling burner with an inner swirler 201 and an outer swirler 202, the burner 300 taking a basic configuration with gas fuel injection holes and air injection holes arranged at alternate positions in the inner swirler 201 and with gas injection holes arranged in the outer swirler 202 external to the inner swirler 201. In addition, fuel injection holes for enhancing flame stability are provided at positions radially inward of the inner swirler 201. In the inner swirler 201, the gas injection holes 401 and air injection holes 402 arranged at alternate positions contribute to raising a temperature of the inner flame to a level required for flame stabilization, and thus to enhancing combustion stability. Tthe fuel injection holes 404 provided for enhancing flame stability contribute to generating a high flame temperature in a circulating gas region formed centrally in a radial direction of the burner 300. The gas turbine combustor can thus stably burn low-Btu gases.