Turbine engine having a fuel nozzle

A turbine engine, comprising:

• a compressor section, combustor section, and turbine section in serial flow arrangement, with the combustor section including a fuel nozzle defining a longitudinal axis and a radial axis orthogonal thereto, the fuel nozzle including:
• a central body defining a first fuel passage extending axially therethrough terminating at a first orifice,
• an annular first wall circumferentially surrounding the central body and spaced therefrom to define a first airflow passage therebetween;
• and
• a set of first swirler vanes circumferentially spaced about the central body and disposed within the first airflow passage, each first swirler vane extending radially outward from the central body toward the annular first wall, at least one first swirler vane defining a respective second fuel passage extending axially therethrough and terminating at a respective second orifice;
• and
• wherein the first orifice is configured to inject a first flow of fuel toward a combustion zone, and the respective second orifice is configured to inject a respective second flow of fuel toward the combustion zone.