A propulsion system (20) for an aircraft includes an open propulsor rotor (34) and a turbine engine (30) configured to drive rotation of the open propulsor rotor (34) about an axis (22). The turbine engine (30) includes a core flowpath (84), a bypass flowpath (86), a fan section (75) and an engine core (90). The engine core (90) includes a compressor section (76), a combustor section (77) and a turbine section (78). The core flowpath (84) extends through the compressor section (76), the combustor section (77) and the turbine section (78) from an inlet (124) into the core flowpath (84) to an exhaust (128) from the core flowpath (84). The inlet (124) is next to and downstream of the fan section (75). The bypass flowpath (86) extends outside of and along the engine core (90) from an inlet (126) into the bypass flowpath (86) to an exhaust (130) from the bypass flowpath (86). The inlet (126) is next to and downstream of the fan section (75). The engine core (90) is arranged axially between the fan section (75) and the open propulsor rotor (34).


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    Titel :

    OPEN ROTOR AIRCRAFT PROPULSION SYSTEM WITH BYPASS FLOWPATH


    Weitere Titelangaben:

    ANTRIEBSSYSTEM FÜR EIN FLUGZEUG MIT OPEN ROTOR UND BYPASSKANAL
    SYSTÈME DE PROPULSION D'AÉRONEF À ROTOR OUVERT ET À DOUBLE FLUX


    Beteiligte:

    Erscheinungsdatum :

    06.08.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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