FIELD: aircraft gondola.
SUBSTANCE: thrust reverser (10) is proposed for the nacelle (1) of a turbojet engine, containing means (13; 13'; 13'') for deflecting at least part of the air flow (F) in the turbojet engine and at least one hood (14), configured to move forward relative to the outer fixed structure (11) of the thrust reverser, wherein the thrust reverser has at least one articulated rotary flap (15), said movable hood (14) is configured to alternately move from the closing position, in which it ensures aerodynamic continuity of the nacelle (1) with the flap (15) and closes the deflecting means (13; 13'; 13''), and the flap (15) is in the retracted position, into the opening position, in which it opens the passage in the gondola (1) and opens the deflecting means (13; 13'; 13''), and the flap (15) covers part of the annular channel (7) of the gondola (1), while it contains a cable-pulley system (20-25; 20'-25'; 20''-25'') for actuating the sash (15).
EFFECT: invention provides a reverser without a connecting rod in the annular channel for turbojet engines with a high bypass ratio.
15 cl, 18 dwg
