An aircraft turbojet engine extending along an X axis and comprising a blower configured to provide a reverse thrust and a nacelle comprising an air intake which comprises at least one deflection member movably mounted between a deployed position in which the deflection member projects from the inner wall or from the lip of the air intake in a radially inward direction of deployment facing the X axis or in a longitudinal direction of deployment with respect to the X axis, in order to allow a release of the reverse air flow from the inner wall to support the reverse thrust phase, and a retracted position in which the air intake has an aerodynamic profile so as to guide the internal air flow along the inner wall in order to support the thrust phase.
TURBOREACTEUR COMPRENANT UNE NACELLE AVEC UNE ENTRÉE D'AIR POUR FAVORISER UNE PHASE D'INVERSION DE POUSSEE
TURBOREACTOR COMPRISING A NACELLE WITH AN AIR INTAKE FOR IMPROVING A REVERSE THRUST
TURBOFANTRIEBWERK UMFASSEND EINER GONDEL MIT EINEM LUFTEINLASS UM EINE SCHUBUMKEHRPHASE ZU BESSERN
2023-01-25
Patent
Electronic Resource
French
European Patent Office | 2020
|European Patent Office | 2020
|European Patent Office | 2023
|European Patent Office | 2020
|European Patent Office | 2021
|