A nacelle for an aircraft bypass turbomachine, including: an annular envelope extending about a longitudinal axis, a thrust reverser including: an annular movable cowl situated downstream of the annular envelope and able to slide with respect to the annular envelope along the longitudinal axis between a closed position and an open position in which the cowl and the nacelle casing define an opening between one another, at least one first thrust reverser cascade, an actuating mechanism designed to allow a partial or total thrust-cancelling configuration of the thrust reverser, in which configuration the movable cowl is moved into its open position while maintaining the or each first cascade in its retracted position, the opening being occupied by at least one second thrust-attenuating cascade of the thrust reverser, in such a way that the secondary flow passing through the opening exits to the outside of the nacelle with a speed oriented so as to generate a substantially zero or positive thrust along the longitudinal axis.


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    Title :

    NACELLE POUR TURBOMACHINE À DOUBLE FLUX D'AÉRONEF, COMPRENANT UN INVERSEUR DE POUSSÉE


    Additional title:

    NACELLE FOR AN AIRCRAFT BYPASS TURBOMACHINE, COMPRISING A THRUST REVERSER
    GONDEL FÜR EINE BYPASS-TURBOMASCHINE EINES FLUGZEUGS MIT EINER SCHUBUMKEHRVORRICHTUNG



    Publication date :

    2022-12-07


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    French


    Classification :

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



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