Gas turbine engine and fuel nozzle assembly therefor

A gas turbine engine, comprising:

• a compressor section, combustion section, and turbine section in serial flow arrangement, with the combustion section comprising:
• a combustor liner that at least partially defines a combustion chamber, the combustion chamber defining a centerline;
• and
• a gaseous fuel nozzle assembly fluidly coupled with the combustion chamber and comprising:
• a rich fuel supply including a rich mixture of gaseous fuel and air;
• a lean fuel supply including a lean mixture of gaseous fuel and air, the lean mixture having a lower equivalence ratio than the rich mixture;
• a rich fluid passage fluidly coupled to the rich fuel supply and emitting the rich mixture in a direction towards the centerline of the combustion chamber into the combustion chamber;
• and
• a lean fluid passage fluidly coupled to the lean fuel supply and emitting the lean mixture in a direction away from the centerline of the combustion chamber into the combustion chamber;
• wherein the combustion section includes a wall coupled to the combustor liner;
• wherein the gaseous fuel nozzle assembly includes at least a portion of the wall;
• and
• wherein the combustor liner includes a height at the wall;
• wherein a ratio of a lean fluid passage diameter of the lean fluid passage to the height of the combustor liner is at least 0.3 and less than or equal to 0.8;
• wherein a ratio of a rich fluid passage diameter of the rich fluid passage to the height of the combustor liner is at least 0.1 and less than or equal to 0.6.