A solid oxide fuel cell stack for an aircraft engine includes ring-shaped fuel cell assemblies of parallel tubular oxide fuel cells circumferentially around a central axis. A first stacking manifold for each fuel cell assembly is in contact with a first side of the individual fuel cell assembly, a second stacking manifold is in contact with a second side of the individual fuel cell assembly, and a central recess for leading an engine shaft through. Each fuel cell includes a tubular anode and tubular cathode, the fuel cell assemblies stacked in an axial direction through pairs of first and second stacking manifolds contacting each other. Each first stacking manifold includes a hydrogen inlet and is connected to first ends of the anodes of the fuel cells. Each second stacking manifold includes a hydrogen and steam outlet and is connected to second ends of the anodes of the fuel cells.


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    Titel :

    SOLID OXIDE FUEL CELL STACK FOR AN AIRCRAFT ENGINE


    Beteiligte:
    NEHTER PEDRO (Autor:in) / GEISLER HELGE (Autor:in) / AHILAN VIGNESH (Autor:in)

    Erscheinungsdatum :

    09.05.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    H01M Verfahren oder Mittel, z.B. Batterien, für die direkte Umwandlung von chemischer in elektrische Energie , PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS




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