An aircraft turbojet engine comprising a fan configured to provide a reverse thrust and a nacelle comprising an air intake, the air intake comprising at least one circulation duct in the annular cavity opening, on the one hand, at the air intake lip and, on the other hand, at the inner wall and/or the outer wall so as to promote a reverse thrust phase, the air intake comprising at least one cover member mounted to move between a covered position, in which the cover member closes the circulation duct at the air intake lip and an uncovered position, in which the cover member opens the circulation duct at the air intake lip.
TURBORÉACTEUR COMPRENANT UNE NACELLE AVEC UNE ENTRÉE D'AIR POUR FAVORISER UNE PHASE D'INVERSION DE POUSSÉE
TURBOREACTOR COMPRISING A NACELLE WITH AN AIR INTAKE FOR IMPROVING A REVERSE THRUST PHASE
TURBOFANTRIEBWERK UMFASSEND EINER GONDEL MIT EINEM LUFTEINLASS UM EINE SCHUBUMKEHRPHASE ZU BESSERN
20.09.2023
Patent
Elektronische Ressource
Französisch
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