Gas turbine nozzle having an inner air swirler passage and plural exterior fuel passages

A turbine engine comprising:

• a compressor section, combustor section, and turbine section in serial flow arrangement, with the combustor section including a fuel nozzle assembly comprising:
• an annular swirler;
• and
• a fuel nozzle having an outer wall and an outlet, the fuel nozzle defining a longitudinal axis and extending through the swirler, the fuel nozzle comprising:
• an inner air passage terminating at an aft end, the inner air passage having a first constant cross-sectional area extending forward from the aft end;
• and
• a first fuel passage circumscribing the inner air passage, terminating at a first fuel passage outlet, and having a second constant cross-sectional area extending forward from the first fuel passage outlet;
• and
• a second fuel passage circumscribing the first fuel passage, terminating at a second fuel passage outlet, and having a third constant cross-sectional area extending forward from the second fuel passage outlet;
• wherein the first fuel passage and the second fuel passage terminate aft of the inner air passage.