An environmental control system of an aircraft includes at least one heat exchanger and a compression device arranged in fluid communication with the at least one heat exchanger. The compression device includes a plurality of components including a first component and a second component coupled by a shaft. A first bleed port is arranged in fluid communication with the first component and a second bleed port, distinct from the first bleed port, is arranged in fluid communication with the second component.


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    Title :

    SIMULTANEOUS DUAL ENGINE BLEED THERMAL MANAGEMENT SYSTEM


    Contributors:
    RETERSDORF ALAN (author) / HO TONY (author)

    Publication date :

    2020-01-02


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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