Patent ID: 8511097
Filing Date: 2013-08-20
Classification: F23C,F23D,F23R

Abstract:
1. A gas turbine combustor comprising one or plural fuel nozzles each having a pilot fuel injection nozzle working for diffusion combustion only during an operation in a low-output operation mode including an ignition operation, and a main fuel injection nozzle working for premixed combustion during operation in a middle- and a high-output operation mode and surrounding the pilot fuel injection nozzle, wherein the one or plural fuel nozzles is provided with a normal fuel injection port for jetting out fuel from a predetermined position in a premixing passage in the main fuel injection nozzle to create a combustible fuel mixture zone, the pilot fuel injection nozzle including a duct forming a central fuel/air passage in fluid communication with a fuel supply passage of the pilot fuel injection nozzle and having an outlet at a downstream end, the normal fuel injection port is in fluid communication with a fuel supply passage which is in fluid communication with a fuel supply passage of the main fuel injection nozzle, and a projection provided with a single opening in a radially outward direction toward an igniter is projected downstream from the downstream end of the duct included in the pilot fuel injection nozzle, the projection surrounding the outlet of the central passage and disposed close to the igniter to jet fuel from the central passage toward the igniter only during an operation in a low-output operation mode including an ignition operation.