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.


    Access

    Download


    Export, share and cite



    Title :

    SPLIT COMPRESSOR SYSTEM ON MULTI-SPOOL ENGINE


    Additional title:

    SYSTEME DE COMPRESSEUR BIBLOC SUR MOTEUR MULTICORPS


    Contributors:

    Publication date :

    2020-03-12


    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



    Cooled-Spool Piston Compressor

    Online Contents | 1994


    Cooled-Spool Piston Compressor

    Morris, Brian G. | NTRS | 1994


    Multi-spool gas turbine engine architecture

    LEFEBVRE GUY | European Patent Office | 2020

    Free access

    Multi-spool gas turbine engine architecture

    LEFEBVRE GUY | European Patent Office | 2021

    Free access

    SPLIT COMPRESSOR GAS TURBINE ENGINE

    VALOIS PATRICK / TURCOTTE HERVE / PLANTE GHISLAIN | European Patent Office | 2022

    Free access