Turbine engine having a combustion section with a fuel nozzle having a gaseous fuel supply channel

A turbine engine comprising:

• a compression section, a combustion section, and a turbine section in serial flow arrangement, the combustion section having a combustor centerline, the combustion section comprising:
• a combustor liner having an inner combustor liner and an outer combustor liner, and a dome wall, the combustor liner and the dome wall collectively defining a combustion chamber, the dome wall having a fuel nozzle opening;
• a casing at least partially enclosing the combustor liner, the casing having at least one opening defining a fuel port extending therethrough;
• a fuel nozzle provided within the fuel nozzle opening, the fuel nozzle having:
• a first body defining a centerline axis and a gaseous fuel channel, the gaseous fuel channel including a gaseous fuel outlet exhausting into the combustion chamber;
• and
• a second body, radially spaced from the first body to define a compressed air channel therebetween, the compressed air channel including a compressed air outlet exhausting into the combustion chamber;
• and
• a gaseous fuel supply channel extending through the fuel port and to the gaseous fuel channel, with at least a portion of the gaseous fuel supply channel being formed with the dome wall, the gaseous fuel supply channel comprising:
• a first circumferential gaseous fuel manifold;
• a second circumferential gaseous fuel manifold formed within the second body;
• and
• a third circumferential gaseous fuel manifold formed within the first body, the third circumferential gaseous fuel manifold provided radially inward from the second circumferential gaseous fuel manifold, the second circumferential gaseous fuel manifold provided radially inward from the first circumferential gaseous fuel manifold.