CPC F23R 3/14 (2013.01) [F23R 3/286 (2013.01)] | 15 Claims |
1. A turbine engine comprising:
a compressor section, combustor section, and turbine section in serial flow arrangement, with the combustor section including a fuel nozzle assembly comprising:
an annular swirler; and
a fuel nozzle having an outer wall and an outlet, the fuel nozzle defining a longitudinal axis and extending through the swirler, the fuel nozzle comprising:
an inner air passage terminating at an aft end, the inner air passage having a first constant cross-sectional area extending forward from the aft end; and
a first fuel passage circumscribing the inner air passage, terminating at a first fuel passage outlet, and having a second constant cross-sectional area extending forward from the first fuel passage outlet; and
a second fuel passage circumscribing the first fuel passage, terminating at a second fuel passage outlet, and having a third constant cross-sectional area extending forward from the second fuel passage outlet;
wherein the first fuel passage and the second fuel passage terminate aft of the inner air passage.
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