A turbofan having a fixed structure, a fan, a fan casing surrounding the fan, an outer cowl disposed around the fan casing and mounted so as to be articulated on the fixed structure, and a deployment system that moves the outer cowl from a closed position to an open position. The deployment system has a guide rail fastened around the fan casing, a slider that is able to move along the guide rail and has a shoe. An activation system of the deployment system moves the slider and the shoe alternately in one direction or the other along the guide rail. One end of an arm of the deployment system is mounted to be articulated on the shoe and another end is mounted to be articulated on the outer cowl. Such a motorized deployment system makes it possible to save space and mass in the turbofan.


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    Title :

    TURBORÉACTEUR DOUBLE FLUX D'UN AÉRONEF COMPORTANT UN CAPOT ARTICULÉ EN ROTATION ET UN SYSTÈME DE DÉPLOIEMENT DUDIT CAPOT


    Additional title:

    DUAL-FLOW TURBOJET ENGINE OF AN AIRCRAFT COMPRISING A ROTATING HINGED COVER AND A SYSTEM FOR DEPLOYING SAID COVER
    ZWEISTROM-TURBOLUFTSTRAHLTRIEBWERK EINES LUFTFAHRZEUGS MIT SICH DREHENDER GELENKABDECKUNG UND ENTFALTUNGSSYSTEM FÜR DIESE ABDECKUNG


    Contributors:

    Publication date :

    2023-09-20


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    French


    Classification :

    IPC:    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 / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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