Fuel nozzle assembly for a gas turbine combustor and liquid fuel injection method

摘要

Liquid fuel injector nozzles for gas turbine combustors send liquid fuel to the combustion chamber with individual jets. The liquid fuel injector nozzle includes a fuel passage terminating in a plurality of vortex slotted vortex-type pilots for delivering swirl to the liquid fuel. A spin chamber disposed downstream of the vortex-type pilot transfers the liquid fuel to the ejector orifices as individual jets. The individual fuel streams are concentrated in such a way as to minimize atomization until the fuel passes moderately through the premixer air stream, which results in increased efficiency, lower exhaust gas, greater flame stability, and improved And the combustion characteristic of obtaining the pattern element obtained is obtained.