Fuel nozzle for hydrogen-based fuel operation

A gas turbine engine comprising:

• a combustor having a plurality of circumferentially distributed fuel nozzles, each of the plurality of fuel nozzles comprising:
• a fuel nozzle assembly comprising:
• an inflow tube disposed along and a nozzle axis, the inflow tube defining an inner air passage;
• a liquid swirler concentrically disposed about the inflow tube, the liquid swirler comprising:
• a liquid swirler inner wall;
• a liquid swirler outer wall having a liquid swirler outer wall end portion angled radially inward toward the nozzle axis;
• and
• an annular liquid passage defined therebetween;
• and
• a radial air swirler (RAS) concentrically disposed about the liquid swirler outer wall, the RAS comprising:
• an RAS inner wall having an RAS inner wall end portion angled radially inward toward the nozzle axis such that it is parallel to the liquid swirler outer wall end portion;
• an RAS outer wall having an end cap at a downstream-most position;
• and
• an annular gas passage defined therebetween,
• wherein the end cap comprises a radiused inner surface and an outer surface.