Patent ID: 9677502
Date: 2017-06-13
CPC Classifications: B64D,F02K,F05D

Claim:
1. A thrust reverser for a nacelle of a turbojet engine, comprising: at least one outer cowl movable in translation from a closed position toward an open position, said at least one outer cowl made of two half-cowls hinged on hinges; a first actuator for translationally actuating a downstream frame; a second actuator for rotatably actuating each of the two half-cowls; a lock for locking and unlocking the two half-cowls together; cascade vanes supported at an upstream end thereof by an upstream frame and at a downstream end thereof by the downstream frame, the cascade vanes being enclosed in an envelope formed by a fan casing and a fan cowl; and a connection between the downstream frame and said at least one outer cowl, wherein the connection keeps said at least one outer cowl and the downstream frame secured together when actuating the first actuator and wherein, after unlocking the two half-cowls, the connection detaches said at least one outer cowl from the downstream frame when actuating the second actuator so as to provide access to an inside of the nacelle in one single manual unlocking operation.