US 12,492,819 B2
Gas turbine engine fuel nozzle having a secondary fuel passage through 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, Evendale, OH (US)
Filed by General Electric Company, Evendale, OH (US)
Filed on Aug. 15, 2024, as Appl. No. 18/805,691.
Application 18/805,691 is a continuation of application No. 18/350,205, filed on Jul. 11, 2023, granted, now 12,085,281.
Application 18/350,205 is a continuation of application No. 17/682,373, filed on Feb. 28, 2022, granted, now 11,725,819, issued on Aug. 15, 2023.
Claims priority of application No. 202111059707 (IN), filed on Dec. 21, 2021.
Prior Publication US 2024/0401809 A1, Dec. 5, 2024
Int. Cl. F23R 3/14 (2006.01); F23R 3/28 (2006.01)
CPC F23R 3/14 (2013.01) [F23R 3/286 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A turbine engine comprising:
a compressor section, combustor section, and turbine section in serial flow arrangement, defining a rotational axis and extending from forward to aft, with the combustor section including a fuel nozzle assembly comprising:
a fuel nozzle including an outer wall defining a fuel passage and a longitudinal axis;
a swirler circumscribing the fuel nozzle and defining a first swirler air passage and a second swirler air passage;
a vane extending across the first swirler air passage; and
a secondary fuel passage passing through the vane and exhausting into the second swirler air passage.