Patent ID: 11959439
Assignee: SAFRAN NACELLES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 11:
12. A thrust reverser for a turbojet engine nacelle comprising:
a diverter configured to divert at least a portion of an air flow from the turbojet engine nacelle; and
at least one cowl movable in translation relative to an outer fixed structure of the thrust reverser,
wherein the thrust reverser comprises at least one rotatably hinged flap, the at least one cowl being capable of moving alternately
from a closure position in which it provides aerodynamic continuity of the nacelle with the at least one rotatably hinged flap and covers the diverter, the at least one rotatably hinged flap being in a retracted position,
to an opening position in which it opens a passage in the nacelle and uncovers the diverter, the at least one rotatably hinged flap obstructs a portion of an annular channel of the nacelle when in the opening position, and wherein the thrust reverser comprises a cable-pulley system for driving the at least one rotatably hinged flap, the cable-pulley system comprising at least one cable associated with at least one pulley to connect the at least one rotatably hinged flap to the thrust reverser,
wherein the diverter is fixed relative to the outer fixed structure, and
wherein the at least one cable of the cable-pulley system is secured, at a first end, to the diverter and the at least one cable is secured, at a second end, to the at least one cowl.