US 12,270,340 B2
Gas turbine engine and fuel cell assembly
Honggang Wang, Clifton Park, NY (US); Brandon Wayne Miller, Liberty Township, OH (US); Michael Anthony Benjamin, Cincinnati, OH (US); Richard L. Hart, Broadalbin, NY (US); Randy M. Vondrell, Cincinnati, OH (US); and Ryan St. Pierre, Jacksonville, FL (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Jan. 4, 2024, as Appl. No. 18/404,364.
Claims priority of application No. 202310155818.X (CN), filed on Feb. 23, 2023.
Prior Publication US 2024/0287936 A1, Aug. 29, 2024
Int. Cl. F02C 7/22 (2006.01); H01M 8/04089 (2016.01); H01M 8/04111 (2016.01); H01M 8/0612 (2016.01)
CPC F02C 7/22 (2013.01) [H01M 8/04097 (2013.01); H01M 8/04111 (2013.01); H01M 8/0618 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a turbomachine having a compressor section, a combustor, and a turbine section arranged in serial flow order, the turbomachine further comprising an outer casing and, during operation of the gas turbine engine, an exhaust gas flow from the turbine section; and
a fuel cell assembly positioned within the outer casing of the turbomachine, the fuel cell assembly comprising a fuel cell defining an inlet positioned to receive a portion of the exhaust gas flow, an outlet positioned to provide output products directly to the exhaust gas flow, or both, wherein the fuel cell defines the outlet positioned to provide output products directly to the exhaust gas flow, wherein the fuel cell is a first fuel cell of a plurality of fuel cells of the fuel cell assembly, wherein the plurality of fuel cells further comprises a second fuel cell in series flow communication with the first fuel cell at a location downstream of the first fuel cell and wherein the first fuel cell and the second fuel cell define varying geometries.