AIR ATOMIZED DISCRETE JET LIQUID FUEL INJECTOR AND METHOD

摘要

Liquid fuel injector nozzles for gas turbine combustors direct liquid fuel to the combustion chamber in separate jets. The liquid fuel injector nozzle includes a fuel passage terminated with a vortex pilot comprising a plurality of vortex slots for delivering swirl to the liquid fuel. A spin chamber disposed downstream of the vortex pilot delivers liquid fuel to the discharge orifice in a separate jet. Individual fuel streams are concentrated in such a way as to minimize atomization until the fuel has passed through the premixer air stream, resulting in increased efficiency, lower emissions, greater flame stability and Combustion characteristics that lead to improved pattern elements are obtained.