US 12,146,662 B2
Fuel-air mixing assembly in a turbine engine
Manampathy G. Giridharan, Evendale, OH (US); Ajoy Patra, Bengaluru (IN); Pradeep Naik, Bengaluru (IN); R Narasimha Chiranthan, Bengaluru (IN); Perumallu Vukanti, Bengaluru (IN); and Michael T. Bucaro, Arvada, CO (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by GENERAL ELECTRIC COMPANY, Schenectady, NY (US)
Filed on Oct. 9, 2023, as Appl. No. 18/482,949.
Application 18/482,949 is a continuation of application No. 17/586,082, filed on Jan. 27, 2022, granted, now 11,815,269.
Claims priority of provisional application 63/294,573, filed on Dec. 29, 2021.
Prior Publication US 2024/0151396 A1, May 9, 2024
Int. Cl. F23R 3/28 (2006.01)
CPC F23R 3/286 (2013.01) 20 Claims
OG exemplary drawing
 
1. A turbine engine comprising:
an engine core comprising at least a compressor section and a combustion section in serial flow arrangement, wherein the combustion section comprises at least one fuel-air mixing assembly comprising:
a center body arranged about a fuel cavity defining a centerline;
a channel arranged within the center body, fluidly coupled to the fuel cavity and arranged exterior of the fuel cavity;
an outer wall spaced from and circumscribing the center body, and defining an annular flow passage between the outer wall and the center body;
a first set of fuel orifices arranged in the center body and fluidly coupling the channel to the annular flow passage; and
a second set of fuel orifices arranged in the center body and fluidly coupling the channel to the annular flow passage, wherein the second set of fuel orifices is axially spaced from the first set of fuel orifices relative to the centerline.