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.


    Access

    Download


    Export, share and cite



    Title :

    SIMULTANEOUS DUAL ENGINE BLEED THERMAL MANAGEMENT SYSTEM


    Additional title:

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


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

    Publication date :

    2023-04-12


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



    Simultaneous dual engine bleed thermal management system

    RETERSDORF ALAN / HO TONY | European Patent Office | 2020

    Free access

    SIMULTANEOUS DUAL ENGINE BLEED THERMAL MANAGEMENT SYSTEM

    RETERSDORF ALAN / HO TONY | European Patent Office | 2020

    Free access

    ENGINE BLEED SYSTEM WITH MULTI-TAP BLEED ARRAY

    SCHWARZ FREDERICK M | European Patent Office | 2017

    Free access

    ENGINE BLEED SYSTEM WITH MULTI-TAP BLEED ARRAY

    SCHWARZ FREDERICK M | European Patent Office | 2023

    Free access

    Engine bleed system with multi-tap bleed array

    SCHWARZ FREDERICK M | European Patent Office | 2020

    Free access