US 11,933,216 B2
Systems and methods for providing output products to a combustion chamber of a gas turbine engine
Honggang Wang, Clifton Park, NY (US); and Michael Anthony Benjamin, Cincinnati, OH (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Jan. 4, 2022, as Appl. No. 17/568,286.
Prior Publication US 2023/0212977 A1, Jul. 6, 2023
Int. Cl. F02C 3/30 (2006.01); F02C 7/232 (2006.01); F02C 9/28 (2006.01); F23R 3/28 (2006.01)
CPC F02C 3/30 (2013.01) [F02C 7/232 (2013.01); F02C 9/28 (2013.01); F23R 3/286 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A propulsion system for an aircraft, the aircraft comprising an aircraft fuel supply, the propulsion system comprising:
a turbomachine defining an axial direction and comprising a compressor section, a combustor, and a turbine section arranged in serial flow order, the combustor defining a combustion chamber and an opening at an upstream end of the combustion chamber, the combustor configured to receive a flow of aviation fuel from the aircraft fuel supply through the opening; and
a plurality of fuel cell stacks extended around the combustion chamber, each fuel cell stack of the plurality of fuel cell stacks having a separate channel that receives air and the aviation fuel being configured to provide output products to the combustion chamber to achieve at least one of late lean injection and a desired combustor gas concentration distribution, the plurality of fuel cell stacks distributed along a length of the combustion chamber in the axial direction;
wherein the plurality of fuel cell stacks are separated by a gap that is different than a gap between adjacent fuel cells within each of the plurality of fuel cell stacks.