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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    Title :

    OPEN ROTOR AIRCRAFT PROPULSION SYSTEM WITH BYPASS FLOWPATH


    Additional title:

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


    Contributors:

    Publication date :

    2025-08-06


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    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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