A gas turbine engine has an engine core including a low pressure compressor, a high pressure compressor, a high pressure turbine and a low pressure turbine coaxially mounted about an engine axis and fluidly connected in series by a core gaspath. The low pressure turbine is drivingly connected to the low pressure compressor via an external shaft disposed radially outwardly of the core gaspath.


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    Titel :

    GAS TURBINE ENGINE ARCHITECTURE WITH SPLIT COMPRESSOR SYSTEM


    Beteiligte:
    PLANTE GHISLAIN (Autor:in) / VALOIS PATRICK (Autor:in) / DUBREUIL JEAN (Autor:in) / BLAIS DANIEL (Autor:in)

    Erscheinungsdatum :

    02.08.2018


    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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