CPC F23R 3/34 (2013.01) [F23R 3/06 (2013.01); F23R 3/14 (2013.01); F23R 3/36 (2013.01); F02C 7/22 (2013.01); F23R 3/28 (2013.01); F23R 3/346 (2013.01)] | 20 Claims |
1. A turbine engine defining a longitudinal axis, the turbine engine comprising:
a compressor section, a combustion section, and a turbine section in serial flow arrangement, and the combustion section having a combustor comprising:
a combustor liner at least partially defining a combustion chamber;
a deflector coupled to the combustor liner;
a fuel supply fluidly coupled to the combustion chamber; and
a set of fuel nozzle assemblies arranged as a first ring of fuel nozzle assemblies radially spaced from a second ring of fuel nozzle assemblies, relative to the longitudinal axis, with each fuel nozzle assembly of the set of fuel nozzle assemblies comprising:
a body having a nozzle outlet arranged on the deflector and the nozzle outlet fluidly coupled to the combustion chamber;
an air flow passage located within the body and having an air outlet at least partially defining the nozzle outlet; and
a fuel flow passage located within the air flow passage and having a fuel outlet at least partially defining the nozzle outlet;
wherein the set of fuel nozzle assemblies in the first ring of fuel nozzle assemblies are radially unaligned with the second ring of fuel nozzle assemblies.
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