A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable about a central axis. The LP pressure spool has an LP compressor and an LP turbine. The HP spool has an HP turbine and an HP compressor. An accessory gear box (AGB) is drivingly connected to the HP spool. The LP compressor is disposed axially between the HP compressor and the AGB. A gear train drivingly couples the LP compressor to the LP turbine. The gear train is integrated to the AGB.


    Access

    Download


    Export, share and cite



    Title :

    Gas turbine engine shaft architecture and associated method of disassembly


    Contributors:

    Publication date :

    2019-08-27


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke / F16H Getriebe , GEARING



    GAS TURBINE ENGINE SHAFT ARCHITECTURE AND ASSOCIATED METHOD OF DISASSEMBLY

    LEFEBVRE GUY / PIETROBON JOHN | European Patent Office | 2018

    Free access


    GAS TURBINE ENGINE DISASSEMBLY/ASSEMBLY METHODS

    PORCO CARLO S / HENRIKSEN GEOFFREY / WEDEMIRE JASON et al. | European Patent Office | 2023

    Free access

    MULTI-SHAFT GAS TURBINE ENGINE

    SIDELKOVSKIY DMITRIY B | European Patent Office | 2017

    Free access

    Multi-shaft gas turbine engine

    SIDELKOVSKIY DMITRIY B | European Patent Office | 2020

    Free access