Gas turbine fuel nozzle having an inner air passage and plural outer 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;
• a fuel nozzle circumscribed by the annular swirler, the fuel nozzle comprising:
• an outer wall defining a longitudinal axis and defining an inner air passage;
• a middle fuel passage extending through the outer wall and circumscribing the inner air passage;
• an outer fuel passage extending through the outer wall and circumscribing the middle fuel passage;
• and
• an orifice extending through the outer wall from the middle fuel passage to the inner air passage or from the outer fuel passage to the annular swirler.