Aircraft engine systems include a core assembly having at least a burner section and a fuel cell configured to generate electrical power. A cryogenic fuel source is configured to supply a fuel through a fuel supply line to each of the burner section and the fuel cell for reaction to generate the electrical power. A system controller is configured to direct fuel to each of the combustor section and the fuel cell. The controller determines if an amount of fuel in the fuel supply line is in excess of that necessary for operation of the core assembly and, based on a determination that excess fuel is present, the controller is configured to direct at least a portion of the excess fuel from the fuel supply line to the fuel cell to generate the electrical power.


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    Title :

    HYBRID ELECTRIC HYDROGEN ENGINE FOR AIRCRAFT


    Contributors:

    Publication date :

    2024-01-11


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02D CONTROLLING COMBUSTION ENGINES , Steuern oder Regeln von Brennkraftmaschinen



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