US 12,228,286 B1
Combustion section with a primary combustion chamber and a secondary combustion chamber
Pradeep Naik, Bengaluru (IN); Hiranya Kumar Nath, Bengaluru (IN); Perumallu Vukanti, Bengaluru (IN); Clayton S. Cooper, Loveland, OH (US); Steven C. Vise, Loveland, OH (US); Michael A. Benjamin, Cincinnati, OH (US); and R Narasimha Chiranthan, Bengaluru (IN)
Assigned to General Electric Company, Evendale, OH (US)
Filed by GENERAL ELECTRIC COMPANY, Schenectady, NY (US)
Filed on Sep. 29, 2023, as Appl. No. 18/477,597.
Int. Cl. F23R 3/28 (2006.01); F23R 3/34 (2006.01); F23R 3/50 (2006.01)
CPC F23R 3/346 (2013.01) [F23R 3/286 (2013.01); F23R 3/50 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A combustion section for a turbine engine, the combustion section comprising:
a primary combustor liner including an inner liner and an outer liner;
a dome wall extending between the inner liner and the outer liner;
a primary combustion chamber defined at least in part by the inner liner, the outer liner, and the dome wall, wherein the outer liner defines at least one opening aft of the dome wall;
a primary fuel nozzle having an outlet at the dome wall, wherein the outlet of the primary fuel nozzle is fluidly coupled with the primary combustion chamber;
a secondary combustion chamber defined at least in part by a secondary combustor liner, the secondary combustion chamber fluidly coupled to the primary combustion chamber at the at least one opening;
a set of secondary fuel nozzles comprising multiple mixer tubes having outlets at the secondary combustor liner, wherein the outlets of the mixer tubes are fluidly coupled with the secondary combustion chamber;
a first igniter at least partially located in the primary combustion chamber; and
a second igniter at least partially located in the secondary combustion chamber.