There is provided an air pressurisation system for an aircraft. The air pressurisation system comprises a blower compressor configured to be mechanically coupled to a spool of a gas turbine engine and configured to receive a first inlet flow of air from a bypass duct of the gas turbine engine; a delivery line configured to convey air compressed by the blower compressor to a cabin pressurisation system of the aircraft; a core bleed line configured to selectively provide a second inlet flow of gases from a compressor of the gas turbine engine 10 to the delivery line in an augmented air supply mode of the air pressurisation system; and an air/oil separator arranged in the core bleed line for removing contaminating oil and oil mist from the second inlet flow of gases before the second inlet flow of gases is provided to the delivery line.


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    Title :

    AIR PRESSURISATION SYSTEM


    Contributors:

    Publication date :

    2025-07-10


    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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