A turboprop or turboshaft engine comprises a first spool including a first compressor drivingly connected to a first turbine, the first turbine further drivingly connected to a load. The engine comprising a second spool including a second compressor drivingly connected to a second turbine, the second compressor fluidly connected to the first compressor to receive compressed air therefrom. The engine further comprises a third spool including a third compressor drivingly connected to a third turbine, the third compressor fluidly connected to the second compressor to receive compressed air therefrom.


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    Titel :

    SPLIT COMPRESSOR SYSTEM ON MULTI-SPOOL ENGINE


    Weitere Titelangaben:

    SYSTEME DE COMPRESSEUR BIBLOC SUR MOTEUR MULTICORPS


    Beteiligte:

    Erscheinungsdatum :

    2020-03-12


    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 / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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