Patent ID: 8099940

Claim:
A pilot assembly for a fuel injector of a gas turbine engine, comprising: a longitudinal passageway having an outlet end, a mass flow in the longitudinal passageway generally flowing towards the outlet end during operation of the engine; a liquid fuel nozzle positioned radially outwardly of the longitudinal passageway and configured to direct a mixture of liquid fuel and air around the outlet end of the longitudinal passageway; a compressed air inlet, the compressed air inlet being configured to direct air compressed by a compressor of the engine to a compressor discharge pressure into the longitudinal passageway without a substantial loss of pressure; a flow restriction section, the flow restriction section being a narrowed section of the longitudinal passageway, wherein an upstream side of the flow restriction section includes compressed air at substantially the compressor discharge pressure and a downstream side includes air at a lower pressure and a higher velocity; a gas fuel nozzle configured to inject a gaseous fuel into the longitudinal passageway at the flow restriction section; and an air assist nozzle configured to direct assist air into the longitudinal passageway upstream of the flow restriction section.