The present disclosure relates to a gas turbine engine (10) for an aircraft comprising: an engine core (11) comprising a turbine (17), a compressor (15), and a core shaft (26, 27); and an environmental control system mounted on the engine core comprising a first air passage (41) arranged to deliver air from outside the engine core to an aircraft cabin and/or for wing anti icing, a subsidiary compressor (42) located in the first air passage (41) and arranged to compress air in the first air passage, the subsidiary compressor being powered by the core shaft (26,27), and a second air passage (43) arranged to inject air from the compressor (15) into the first air passage.


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    Title :

    ENVIRONMENTAL CONTROL SYSTEM


    Additional title:

    KLIMAANLAGE IM FLUGZEUG
    SYSTÈME DE CONTRÔLE ENVIRONNEMENTAL


    Contributors:

    Publication date :

    2023-08-30


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02K JET-PROPULSION PLANTS , Strahltriebwerke / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS



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