Patent ID: 11933216
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
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.