A compound engine assembly 10 with an engine core 12 including at least one internal combustion engine 12', a turbine section 18, and a compressor 14 having an outlet in fluid communication with an inlet of the engine core 12. A casing 21 is connected to the turbine section 18, compressor 14 and engine core 12. A mount cage 104 is connected to mounts 105 attached to the casing 21 between the compressor 14 and a hot zone including the turbine section 18 and exhaust pipe(s) 30. The mount cage 104 may include a plurality of struts 106 all extending from the mounts away from the turbine section and engine core. The struts are separated from the hot zone by at least one firewall. The casing 21 may be a gearbox module casing 21 through which a turbine shaft 19 is engaged with an engine shaft 16. The mount cage 104 may be completely contained within an axial space with the turbine section 18 and exhaust pipe(s) 30 being located outside of the axial space.


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    Titel :

    COMPOUND ENGINE ASSEMBLY WITH MOUNT CAGE


    Weitere Titelangaben:

    TURBOCOMPOUND TRIEBWERK UND MONTAGEANORDNUNG
    MOTEUR TURBOCOMPOUND AVEC ENSEMBLE DE SUPPORT


    Beteiligte:
    ZOLOTOV ANDREY (Autor:in) / LAMARRE SYLVAIN (Autor:in) / FONTAINE MIKE (Autor:in) / JULIEN ANDRE (Autor:in) / GAUL MICHAEL (Autor:in) / THOMASSIN JEAN (Autor:in) / MITROVIC LAZAR (Autor:in) / MEDVEDEV ILYA (Autor:in) / USIKOV SERGEY (Autor:in)

    Erscheinungsdatum :

    2020-09-02


    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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