Turbine engine having a fuel nozzle assembly

A turbine engine, comprising:

• a compressor section, a combustion section, and a turbine section in serial flow arrangement, with the combustion section comprising:
• a combustion chamber;
• and
• a fuel nozzle assembly fluidly coupled with the combustion chamber at a fuel nozzle assembly outlet, wherein the fuel nozzle assembly comprises:
• a centerbody having an outer surface and a nose confronting the combustion chamber;
• a gaseous fuel supply passage located within the centerbody and having at least one gaseous fuel outlet including a first gaseous fuel outlet on the outer surface of the centerbody emitting a gaseous fuel;
• a plurality of air supply passages circumscribing the centerbody, including at least a first air supply passage and a second air supply passage circumscribing the first air supply passage with one of the first air supply passage or the second air supply passage emitting air at a lower velocity than the other of the first air supply passage or the second air supply passage to generate a set of vortices circumscribing the gaseous fuel emitted from the first gaseous fuel outlet,
• at least one splitter configured to separate at least two air supply passages of the plurality of air supply passages;
• and
• a second gaseous fuel outlet disposed downstream of the at least one splitter and the first gaseous fuel outlet.