US 12,228,282 B2
Gas turbine fuel nozzle having an inner air passage and plural outer 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 Stuart Cooper, Loveland, 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, Evendale, OH (US)
Filed by GENERAL ELECTRIC COMPANY, Schenectady, NY (US)
Filed on Jan. 10, 2024, as Appl. No. 18/409,690.
Application 18/409,690 is a continuation of application No. 17/717,739, filed on Apr. 11, 2022, granted, now 11,906,165.
Claims priority of application No. 202111059813 (IN), filed on Dec. 21, 2021.
Prior Publication US 2024/0183536 A1, Jun. 6, 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, with the combustor section including a fuel nozzle assembly comprising:
an annular swirler;
a fuel nozzle circumscribed by the annular swirler, the fuel nozzle comprising:
an outer wall defining a longitudinal axis and defining an inner air passage;
a middle fuel passage extending through the outer wall and circumscribing the inner air passage;
an outer fuel passage extending through the outer wall and circumscribing the middle fuel passage; and
an orifice extending through the outer wall from the middle fuel passage to the inner air passage or from the outer fuel passage to the annular swirler.