To reduce the overall mass of an engine assembly for aircraft, this assembly comprises a part of the fuselage of an aircraft, a turbomachine comprising an unfaired propeller, together with an annular row of unfaired after-guide vanes located aft of the propeller and rotationally fixed in relation to a longitudinal axis of the turbomachine, and a mounting pylon. At least part of the leading edge of the pylon is incorporated within the annular row between two after-guide vanes.
ENSEMBLE MOTEUR POUR AERONEF COMPRENANT UN BORD D'ATTAQUE DE MAT INTEGRE A UNE RANGEE ANNULAIRE D'AUBES DIRECTRICES DE SORTIE NON CARENEES
2018-04-13
Patent
Electronic Resource
French
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
PROCEDE DE DETERMINATION DU CALAGE ANGULAIRE D'UNE RANGEE ANNULAIRE D'AUBES DE STATOR
European Patent Office | 2021
|Système de détermination du calage angulaire d’une rangée annulaire d’aubes de stator
European Patent Office | 2022
|SYSTEME DE SORTIE D'AIR POUR UN BORD D'ATTAQUE D'AERONEF
European Patent Office | 2015
|PROCEDE DE DETERMINATION DU CALAGE ANGULAIRE D'UNE RANGEE ANNULAIRE D'AUBES DE STATOR
European Patent Office | 2024
|European Patent Office | 2019
|