| CPC F23R 3/14 (2013.01) [F23R 3/36 (2013.01); F23R 3/002 (2013.01); F23R 3/286 (2013.01)] | 20 Claims |
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1. A fuel nozzle for a gas turbine engine combustor, the fuel nozzle 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 having a liquid swirler inner wall end portion angled radially outward from the nozzle axis;
a liquid swirler outer wall having a liquid swirler outer wall end portion angled radially outward from 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;
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 a contoured outer surface; and
wherein the radiused inner surface is parallel to the RAS inner wall end portion.
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