A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable of one another about an engine axis. The LP spool comprises an LP turbine, an LP compressor and an LP shaft. The HP pressure spool comprises an HP turbine, an HP compressor and an HP shaft. The LP turbine is in fluid flow communication with the HP turbine and disposed downstream therefrom. The HP compressor is in fluid flow communication with the LP compressor and disposed downstream therefrom. The LP shaft has an upstream shaft portion extending upstream of the LP turbine to a location upstream of the LP compressor to provide a first power take-off at an upstream end of the engine and a downstream shaft portion extending downstream of the LP turbine to provide a second power take-off at a downstream end of the engine, thereby allowing mounting of a reduction gear box at either end of the engine.


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    Titel :

    Turbine shaft power take-off


    Beteiligte:
    LEFEBVRE GUY (Autor:in)

    Erscheinungsdatum :

    2019-10-29


    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 / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F02K JET-PROPULSION PLANTS , Strahltriebwerke / F16H Getriebe , GEARING



    TURBINE SHAFT POWER TAKE-OFF

    LEFEBVRE GUY | Europäisches Patentamt | 2018

    Freier Zugriff

    POWER TAKE OFF SHAFT

    LEE MUN KI / KIM BYUNG KI / KO JAE DEOK et al. | Europäisches Patentamt | 2018

    Freier Zugriff

    Split-Shaft Power Take-Offs

    Moyer, L. J. | SAE Technical Papers | 1969