A gas turbine engine (10) fuel nozzle (100) includes an axis of symmetry (143) extending therethrough, the nozzle body (110) including a first passage (142) extending coaxially therethrough, a second passage (152), and a third passage (162), the second passage circumscribing the first passage, the third passage formed radially outward of the second passage, and a nozzle tip (112) coupled to the nozzle body, the nozzle tip including at least one primary discharge opening (170) in flow communication with the first passage, at least one secondary discharge opening (172) in flow communication with the second passage, and at least one tertiary discharge opening in flow communication with the third passage.