US 12,339,006 B1
Turbine engine having a combustion section with a fuel nozzle assembly
Pradeep Naik, Bengaluru (IN); Clayton Stuart Cooper, Loveland, OH (US); Sibtosh Pal, Mason, OH (US); Michael T. Bucaro, Arvada, CO (US); Michael A. Benjamin, Cincinnati, OH (US); Steven C. Vise, Loveland, OH (US); Karthikeyan Sampath, Bengaluru (IN); and Andrew Joseph Wickersham, Liberty Township, OH (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by GENERAL ELECTRIC COMPANY, Schenectady, NY (US)
Filed on Dec. 22, 2023, as Appl. No. 18/394,407.
Int. Cl. F23R 3/12 (2006.01); F02C 3/22 (2006.01); F23R 3/04 (2006.01); F23R 3/28 (2006.01)
CPC F23R 3/286 (2013.01) [F02C 3/22 (2013.01); F23R 3/045 (2013.01); F23R 3/12 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A combustion section for a turbine engine comprising a compression section, the combustion section, and a turbine section in serial flow arrangement, the combustion section comprising:
a dome wall and a combustor liner collectively forming at least a portion of a combustion chamber; and
a fuel nozzle assembly, fluidly coupled to the combustion chamber, and comprising:
a compressed air tube having a compressed air outlet exhausting into the combustion chamber thereby supplying a flow of compressed air to the combustion chamber, the compressed air tube defining a tube centerline axis;
a body defining a gaseous fuel channel exhausting into the combustion chamber at a set of gaseous fuel orifices thereby supplying a flow of gaseous fuel to the combustion chamber, the set of gaseous fuel orifices surrounding at least a portion of the compressed air outlet; and
a set of vortex generators located within the compressed air tube, the set of vortex generators configured to direct the flow of compressed air such that at least a portion of the flow of compressed air forms a set of vortices used to capture the flow of gaseous fuel from the set of gaseous fuel orifices to define a mixture of compressed air and gaseous fuel within the combustion chamber.