A fuel tank inerting system of an aircraft includes a first air flow provided from a first source having a first temperature and a second air flow including cabin outflow air having a second temperature. The first temperature is greater than the second temperature. A fuel tank inerting heat exchanger is arranged in fluid communication with both the first air flow and the second air flow. At least one air separating module is configured to separate an inert gas from the first air flow output from the fuel tank inerting heat exchanger.


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    Title :

    FUEL TANK INERTING SYSTEM USING CABIN OUTFLOW AIR


    Contributors:
    HO TONY (author) / BRUNO LOUIS J (author) / COUTIN AIDEN (author)

    Publication date :

    2021-06-24


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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