Abstract: The turbojet comprises, linking two of its parts (1, 2) as a main nacelle portion and a rear nacelle portion, a device (4) which moves them relative to one another, for example in order to open a reverse gas thrust slot (3). The device (4) comprises a sleeve (5) and two rods (6, 7) which are coaxial connected together by two screw links (8, 9) and two locking means (10, 11) which may be engaged independently, such that the deployment of one of the rods (6) results in the opening of the slot (3) and the movement of the other rod (7), controlled by the same device (12), only occurs under specific turbojet maintenance circumstances.
Type:
Application
Filed:
December 20, 2018
Publication date:
June 27, 2019
Applicant:
SAFRAN AIRCAFT ENGINES
Inventors:
Emmanuel Pierre Dimitri PATSOURIS, Quentin Matthias Emmanuel Granaud, Antoine Elie Hellegouarch, Martial Alexandre Monseu, Clementine Charlotte Marie Mouton