A fan section of an aeronautical propulsion system includes a fan rotor including seventeen blades to twenty blades and having a solidity strictly less than 1.0. The solidity is equal to a ratio between a chord at the blade tip and an inter-blade pitch at the blade tip. The fan section has a hub-tip ratio greater than or equal to 0.22 and less than or equal to 0.32, a pressure ratio greater than or equal to 1.05 and less than or equal to 1.5, and a peripheral speed at the blade tip greater than or equal to 260 m/s and less than or equal to 400 m/s. The pressure ratio and the peripheral speed are measured at cruising speed.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    AERONAUTICAL PROPULSION SYSTEM COMPRISING AN OPTIMIZED FAN SECTION



    Erscheinungsdatum :

    31.07.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



    Aeronautical propulsion system

    SIMON HART / MUKESH PATEL / CHRIS BURNS | Europäisches Patentamt | 2025

    Freier Zugriff

    AERONAUTICAL PROPULSION SYSTEM

    HART SIMON / PATEL MUKESH / BURNS CHRIS | Europäisches Patentamt | 2025

    Freier Zugriff

    AERONAUTICAL PROPULSION SYSTEM

    LAWNICZEK BAPTISTE DORIAN / ESCURE DIDIER RENÉ ANDRÉ / MOUTON CLÉMENTINE CHARLOTTE MARIE | Europäisches Patentamt | 2024

    Freier Zugriff

    AERONAUTICAL PROPULSION SYSTEM

    HART SIMON / PATEL MUKESH / BURNS CHRIS | Europäisches Patentamt | 2025

    Freier Zugriff