GAS TURBINE COMBUSTOR AND ITS IGNITION METHOD

摘要

A gas turbine combustor burns a fuel mixture at a high combustion efficiency and a low NO x emission, is simple in construction and exercises improved ignition performance, and an ignition method can efficiently igniting a fuel mixture in the gas turbine combustor. A gas turbine combustor 1 provided with fuel nozzles 2A each having a pilot fuel injection nozzle 4 and a main fuel injection nozzle 7A, and fuel nozzles 2B each having a pilot fuel injection nozzle 4 and a main fuel injection nozzle 7B. The fuel nozzle 2A disposed close to an igniter 8 is provided with a local fuel injection port 19a through which fuel F is jetted out from a predetermined position in an air passage 24 in the main fuel injection nozzle 7A to create a combustible fuel mixture zone S3 in the vicinity of the igniter at least while the igniter is in an ignition operation.