A system includes a first flow path fluidly connecting a first supply to an inerting apparatus. A second flow path connects a second supply to a turbine of a compressor device. A first valve, located within the first flow path, is configured to be open in a first state and closed in a second state. The first valve is configured to allow a supply of air from the first supply to an inerting apparatus directly. A second valve, located within the second flow path, is configured to be closed in the first state and open in the second state. The second valve is configured to allow a supply of air from the second supply to drive the turbine of the compressor device. When in the second state, the compressor device is operated to compress air from the first supply prior to the air being supplied to the inerting apparatus.


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    Title :

    FUEL TANK INERTING APPARATUS FOR AIRCRAFT


    Additional title:

    KRAFTSTOFFTANKINERTISIERUNGSVORRICHTUNG FÜR EIN FLUGZEUG
    APPAREIL D'INERTAGE DE RÉSERVOIR DE CARBURANT POUR AÉRONEF


    Contributors:

    Publication date :

    2019-06-05


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B60T Bremsanlagen für Fahrzeuge oder Teile davon , VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF



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