An environmental control system of an aircraft includes at least one heat exchanger (70) and a compression device (60) arranged in fluid communication with the at least one heat exchanger. The compression device includes a plurality of components including a first component (62) and a second component (64) coupled by a shaft (68). A first bleed port (38) is arranged in fluid communication with the first component and a second bleed port (40), distinct from the first bleed port, is arranged in fluid communication with the second component.


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    Titel :

    SIMULTANEOUS DUAL ENGINE BLEED THERMAL MANAGEMENT SYSTEM


    Weitere Titelangaben:

    SIMULTANES DUAL-BLEED SYSTEM FÜR EIN WÄRMEMANAGEMENTSYSTEM
    SYSTÈME DE GESTION THERMIQUE AVEC DEUX CIRCUITS DE PRÉLÈVEMENT D'AIR MOTEUR SIMULTANÉS


    Beteiligte:
    RETERSDORF ALAN (Autor:in) / HO TONY (Autor:in)

    Erscheinungsdatum :

    2023-04-12


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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