US 11,725,819 B2
Gas turbine fuel nozzle having a fuel passage within a swirler
Perumallu Vukanti, Bengaluru (IN); Pradeep Naik, Bengaluru (IN); Clayton S. Cooper, Evendale, OH (US); Michael A. Benjamin, Cincinnati, OH (US); Michael T. Bucaro, Arvada, CO (US); Manampathy G. Giridharan, Evendale, OH (US); Steven C. Vise, West Chester, OH (US); Ajoy Patra, Bengaluru (IN); Saket Singh, Bengaluru (IN); and R Narasimha Chiranthan, Bengaluru (IN)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Feb. 28, 2022, as Appl. No. 17/682,373.
Claims priority of application No. 202111059707 (IN), filed on Dec. 21, 2021.
Prior Publication US 2023/0194091 A1, Jun. 22, 2023
Int. Cl. F23R 3/14 (2006.01); F23R 3/28 (2006.01)
CPC F23R 3/14 (2013.01) [F23R 3/286 (2013.01)] 19 Claims
OG exemplary drawing
 
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:
a fuel nozzle including an outer wall surrounding a fuel passage and defining a longitudinal axis;
a swirler circumscribing the fuel nozzle, the swirler including a forward wall and an aft wall, defining a swirler passage between the forward wall and the aft wall;
a set of vanes provided within the swirler passage, each vane of the set of vanes extending between the forward wall and the aft wall;
a splitter extending from the set of vanes, separating the swirler passage into a radially interior passage and a radially exterior passage; and
a secondary fuel passage extending at least partially within the outer wall of the fuel nozzle, and including an outlet on the splitter.