Patent ID: 6935117

Claim:
A fuel injector for a gas turbine engine comprising: a mounting flange; a stem extending from a proximal portion at the mounting flange to a distal portion; a nozzle proximate the stem distal portion; a first passageway along and through the stem and extending from a first inlet to a first outlet at the nozzle, the first outlet comprising a first plurality of apertures injecting gasified fuel; a second passageway along and through the stem and extending from a second inlet to a second outlet at the nozzle, the second outlet comprising a second plurality of apertures injecting liquid fuel, generally radially inboard of the first plurality of apertures; and a third passageway along and through the stem and extending from a third inlet to a third outlet at the nozzle, the third outlet comprising at least one third aperture injecting liquid fuel, generally radially inboard of the first plurality of apertures; said first, second, and third passageways in fluid communication with one or more liquid fuel tanks; said gas turbine engine being mounted on an aircraft to produce thrust.