A gas turbine engine includes a fan, a compressor section having at least two sequential compressors, a combustor section fluidly connected to the compressor section, and a turbine section fluidly connected to the combustor section. The turbine section includes at least a first turbine, a second turbine and a third turbine. One of the first turbine, the second turbine and the third turbine is a fan-drive turbine. An environmental control system air supply includes at least a first compressor bleed and a second compressor bleed. Each of the first compressor bleed and the second compressor bleed are positioned upstream of a highest pressure compressor of the at least two compressors.


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    Titel :

    COMPRESSOR BLEED AIR SUPPLY FOR AN AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM


    Beteiligte:

    Erscheinungsdatum :

    2016-04-28


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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