CPC F23R 3/12 (2013.01) [F23R 3/14 (2013.01); F23R 3/28 (2013.01); F23R 2900/00005 (2013.01)] | 20 Claims |
1. A fuel nozzle for a gas turbine engine, the fuel nozzle comprising:
a fuel swirler including a fuel swirler body having an inlet section configured to receive fuel, an outlet section configured to dispense swirled fuel, and at least one fuel flow passage extending from the inlet section to the outlet section that is configured to transport fuel; and
an outer air swirler including an outer air swirler body arranged radially outwardly of the fuel swirler body, the outer air swirler body having a plurality of air swirler vanes that at least partially form respective air flow passages configured to pass and swirl air that interacts with dispensed fuel from the fuel swirler;
wherein the fuel swirler body and the outer air swirler body are additively manufactured together to form a unitary body;
wherein the unitary body includes a radially outer annular wall and a radially inner annular wall that each extend in a longitudinal direction and are radially spaced apart from each other along at least a portion of the unitary body to form an annular gap therebetween; and
wherein the at least one fuel flow passage extends in the longitudinal direction from the inlet section to the outlet section and is completely enclosed by the radially inner annular wall of the unitary body along at least a portion thereof.
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