US 11,906,165 B2
Gas turbine nozzle having an inner air swirler passage and plural exterior fuel passages
Michael T. Bucaro, Arvada, CO (US); Ajoy Patra, Bengaluru (IN); Pradeep Naik, Bengaluru (IN); Perumallu Vukanti, Bengaluru (IN); R Narasimha Chiranthan, Bengaluru (IN); Clayton S. Cooper, Evendale, OH (US); Michael A. Benjamin, Cincinnati, OH (US); Steven C. Vise, West Chester, OH (US); Manampathy G. Giridharan, Evendale, OH (US); and Krishnakumar Venkatesan, Niskayuna, NY (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Apr. 11, 2022, as Appl. No. 17/717,739.
Claims priority of application No. 202111059813 (IN), filed on Dec. 21, 2021.
Prior Publication US 2023/0194093 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)] 15 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:
an annular swirler; and
a fuel nozzle having an outer wall and an outlet, the fuel nozzle defining a longitudinal axis and extending through the swirler, the fuel nozzle comprising:
an inner air passage terminating at an aft end, the inner air passage having a first constant cross-sectional area extending forward from the aft end; and
a first fuel passage circumscribing the inner air passage, terminating at a first fuel passage outlet, and having a second constant cross-sectional area extending forward from the first fuel passage outlet; and
a second fuel passage circumscribing the first fuel passage, terminating at a second fuel passage outlet, and having a third constant cross-sectional area extending forward from the second fuel passage outlet;
wherein the first fuel passage and the second fuel passage terminate aft of the inner air passage.