A propulsion system (20) includes a fan (100), a gear (112), a turbine (116) configured to drive the gear (112) to, in turn, drive the fan (100). The turbine (116) has an exit point (117), and a diameter (Dt) is defined at the exit point (117). A nacelle (102) surrounds a core engine housing (111). The fan (100) is configured to deliver air into a bypass duct defined between the nacelle (102) and the core engine housing (111). A core engine exhaust nozzle (122;222) is provided downstream of the exit point (117). A downstream most point (128; 228) of the core engine exhaust nozzle (122; 222) is defined at a distance from the exit point (117). A ratio of the distance to the diameter (Dt) is greater than or equal to about 0.90.


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    Titel :

    ELONGATED GEARED TURBOFAN WITH HIGH BYPASS RATIO


    Weitere Titelangaben:

    LÄNGLICHER GETRIEBETURBOLÜFTER MIT HOHEM NEBENSTROMVERHÄLTNIS
    RÉACTEUR À DOUBLE FLUX À ENGRENAGES ALLONGÉ PRÉSENTANT RAPPORT DE DÉRIVATION ÉLEVÉ


    Beteiligte:

    Erscheinungsdatum :

    13.07.2022


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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