US 11,774,100 B2
Combustor fuel nozzle assembly
Nayan Vinod Patel, Liberty Township, OH (US); and Michael A. Benjamin, Cincinnati, OH (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by GENERAL ELECTRIC COMPANY, Schenectady, NY (US)
Filed on Apr. 21, 2022, as Appl. No. 17/725,895.
Claims priority of provisional application 63/299,619, filed on Jan. 14, 2022.
Prior Publication US 2023/0228424 A1, Jul. 20, 2023
Int. Cl. F23R 3/34 (2006.01); F23R 3/14 (2006.01); F23R 3/36 (2006.01); F23R 3/06 (2006.01); F02C 7/22 (2006.01); F23R 3/28 (2006.01)
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
OG exemplary drawing
 
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.