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AssigneeSafran Aircaft Engines
InventorsEmmanuel Pierre Dimitri PATSOURIS, Quentin Matthias Emmanuel Granaud, Antoine Elie Hellegouarch, Martial Alexandre Monseu, Clementine Charlotte Marie Mouton
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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.
Turbojet, characterized in that it comprises, linking a first element (1) and a second element (2) of its structure, a device (4) which comprises a first rod (7), fixed to the second element (2), a second rod (6) concentric with the first rod (7), an actuator shaft (5) which is concentric with the first rod (7) and the second rod (6) and mounted on the first element and being able to pivot on it, where links using nut and screws (8, 9) connect the second rod (6) on the one hand to the first rod (7) and on the other to the actuator shaft (5), the removable means of locking (10, 11) between the second rod (6) and the first rod (7) on the one hand, the actuator shaft (5) on the other hand, the shaft, the first rod and the second rod being coaxial with a central axis (X′) of the device and an actuator (12) fixed to the first structure element (1) and which causes pivoting of the actuator shaft (5).
Dependencies are inferred from the claim text.