US 12,416,409 B2
Gas turbine engine having a combustion section with steam provided to second combustor plenum
Pradeep Naik, Bengaluru (IN); Clayton S. Cooper, Loveland, OH (US); Steven C. Vise, Loveland, OH (US); Michael A. Benjamin, Cincinnati, OH (US); Sibtosh Pal, Mason, OH (US); Steven Marakovits, Mason, OH (US); Sripathi Mohan, Bengaluru (IN); and Joseph Zelina, Waynesville, OH (US)
Assigned to GENERAL ELECTRIC COMPANY, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Feb. 8, 2024, as Appl. No. 18/436,180.
Prior Publication US 2025/0257872 A1, Aug. 14, 2025
Int. Cl. F23R 3/28 (2006.01); F02C 3/14 (2006.01); F02C 3/30 (2006.01); F02C 6/18 (2006.01); F02C 7/047 (2006.01); F02C 7/141 (2006.01); F02C 7/143 (2006.01); F02C 9/18 (2006.01); F23R 3/00 (2006.01); F23R 3/04 (2006.01); F23R 3/16 (2006.01); F23R 3/34 (2006.01); F23R 3/42 (2006.01); F23R 3/50 (2006.01)
CPC F23R 3/28 (2013.01) [F02C 3/14 (2013.01); F02C 3/30 (2013.01); F02C 3/305 (2013.01); F02C 6/18 (2013.01); F02C 7/047 (2013.01); F02C 7/141 (2013.01); F02C 7/1435 (2013.01); F02C 9/18 (2013.01); F23R 3/002 (2013.01); F23R 3/04 (2013.01); F23R 3/16 (2013.01); F23R 3/34 (2013.01); F23R 3/346 (2013.01); F23R 3/42 (2013.01); F23R 3/50 (2013.01); F05D 2220/72 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a compressor section having a compressor bleed air system connected thereto;
a steam turbine;
a combustion section, comprising:
a combustor outer casing and a combustor inner casing defining a first combustor pressure plenum therewithin;
a first combustor arranged within the combustor outer casing and the combustor inner casing, and having (a) a first combustor outer liner and a first combustor inner liner that define a first combustion chamber having a primary combustion zone and a secondary combustion zone downstream of the primary combustion zone, and (b) at least one swirler assembly, an outer flow passage being defined between the combustor outer casing and the first combustor outer liner, and an inner flow passage being defined between the combustor inner casing and the first combustor inner liner, the first combustor being arranged to receive a flow of compressed air from the compressor section and to provide a flow of the compressed air into the first combustion chamber; and
a second combustor arranged within one of the outer flow passage or the inner flow passage, the second combustor having a second combustor casing and a second combustor liner defining a second combustion chamber therewithin, a second combustor plenum being defined between the second combustor casing and the second combustor liner, the second combustion liner having an outlet, the second combustor casing being in fluid communication with the compressor bleed air system to receive a flow of compressor bleed air from the compressor bleed air system into the second combustor plenum, and the outlet providing fluid communication between the second combustion chamber and the first combustion chamber of the first combustor;
a first fuel nozzle arranged to provide a first flow of fuel to the at least one swirler assembly of the first combustor;
a second fuel nozzle arranged to provide a second flow of fuel to the second combustion chamber; and
a steam generating system arranged to provide a flow of steam to the second combustor plenum and to the steam turbine.