US 12,351,329 B2
Systems and method of operating a fuel cell assembly
Honggang Wang, Clifton Park, NY (US); Michael Anthony Benjamin, Cincinnati, OH (US); Seung-Hyuck Hong, Clifton Park, NY (US); and Richard L. Hart, Broadalbin, NY (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Jan. 21, 2022, as Appl. No. 17/581,135.
Prior Publication US 2023/0234716 A1, Jul. 27, 2023
Int. Cl. H01M 8/04 (2016.01); B64D 27/10 (2006.01); B64D 27/24 (2006.01); B64D 31/00 (2006.01); B64D 31/18 (2024.01); H01M 8/04223 (2016.01); H01M 8/04225 (2016.01); H01M 8/04302 (2016.01); H01M 8/04701 (2016.01); B64D 27/02 (2006.01)
CPC B64D 31/00 (2013.01) [B64D 27/10 (2013.01); B64D 27/24 (2013.01); H01M 8/04225 (2016.02); H01M 8/04231 (2013.01); H01M 8/04302 (2016.02); H01M 8/04701 (2013.01); B64D 27/026 (2024.01); H01M 2250/20 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A method for operating a propulsion system for an aircraft, the propulsion system comprising a gas turbine engine and a fuel cell assembly, the fuel cell assembly comprising a fuel cell stack having a fuel cell defining an outlet positioned to remove output products from the fuel cell during operation, the method comprising:
executing a startup sequence for the fuel cell assembly, wherein executing the startup sequence for the fuel cell assembly comprises initiating the startup sequence for the fuel cell assembly;
executing a startup sequence for the gas turbine engine, wherein executing the startup sequence for the gas turbine engine comprises initiating the startup sequence for the gas turbine engine subsequent to initiating the startup sequence for the fuel cell assembly; and
operating the fuel cell assembly to provide output products to a combustion section of the gas turbine engine.