Patent ID: 7536862

Claim:
A method for delivering fuel in a gas turbine engine including at least one fuel nozzle including a nozzle body having an axis of symmetry extending therethrough, the nozzle body comprising a first passage extending coaxially therethrough, a second passage, and a third passage, the second passage circumscribing the first passage, the third passage formed radially outward of the second passage, the third passage substantially circumscribing the second passage, and a nozzle tip coupled to the nozzle body, the nozzle tip comprising at least one primary discharge opening in flow communication with the first passage, at least one secondary discharge opening in flow communication with the second passage, and at least one tertiary discharge opening in flow communication with the third passage, said method comprising: channeling fuel through the first passage such that fuel is discharged through the nozzle tip at least one primary discharge opening; channeling fuel through the second passage such that fuel is discharged through the nozzle tip at least one secondary discharge opening; channeling steam through the third passage such that steam is discharged through the nozzle tip at least one tertiary discharge opening in a first operational mode; and channeling cooling air through a plurality of fourth discharge openings and into the third passage such that the cooling air is discharged through the at least one tertiary discharge opening during a second operational mode wherein the plurality of fourth discharge openings is in flow communication with the third passage, the plurality of fourth discharge openings formed upstream from the at least one tertiary discharge opening.