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.


    Access

    Download


    Export, share and cite



    Title :

    AERONAUTICAL PROPULSION SYSTEM COMPRISING AN OPTIMIZED FAN SECTION



    Publication date :

    2025-07-31


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    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

    HART SIMON / PATEL MUKESH / BURNS CHRIS | European Patent Office | 2025

    Free access

    AERONAUTICAL PROPULSION SYSTEM

    LAWNICZEK BAPTISTE DORIAN / ESCURE DIDIER RENÉ ANDRÉ / MOUTON CLÉMENTINE CHARLOTTE MARIE | European Patent Office | 2024

    Free access

    AERONAUTICAL PROPULSION SYSTEM

    HART SIMON / PATEL MUKESH / BURNS CHRIS | European Patent Office | 2025

    Free access

    Aeronautical propulsion system

    SIMON HART / MUKESH PATEL / CHRIS BURNS | European Patent Office | 2025

    Free access