According to one embodiment of this disclosure an integrated fuel cell and environmental control system (30) includes a turbo-compressor (32). The turbo-compressor includes a rotatable shaft (40, a compressor (34) rotatable with the shaft (40) to generate a flow of compressed air, a motor (36) connected to the shaft (40), and a turbine (38) connected to the shaft (40). The system further includes a fuel cell (10A, 10B) connected to the compressor by a first compressed air supply line that supplies a first portion of the flow of compressed air to the fuel cell. The fuel cell (10A, 10B) is connected to the turbine (38) by a fuel cell exhaust line that supplies a flow of fuel cell exhaust to the turbine (38) and causes the turbine (38) to rotate. The system further includes an environmental control system (56) connected to the compressor by a second compressed air supply line that supplies a second portion of the flow of compressed air to the environmental control system (56).


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    Titel :

    INTEGRATED FUEL CELL AIRCRAFT PRESSURIZATION AND COOLING SYSTEM


    Weitere Titelangaben:

    FLUGZEUGDRUCKAUSGLEICHS- UND KÜHLSYSTEM MIT INTEGRIERTER BRENNSTOFFZELLE
    SYSTÈME DE REFROIDISSEMENT ET DE PRESSURISATION À PILE À COMBUSTIBLE INTÉGRÉ POUR AÉRONEF


    Beteiligte:

    Erscheinungsdatum :

    2021-10-13


    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 / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS



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