Patent ID: 6289670
Filing Date: 2001-09-18
Classification: F02K,F05D

Abstract:
An exhaust nozzle of a turbojet engine mounted on a supersonic aircraft, the exhaust nozzle comprising:an external cowling formed by an inner annular wall (7) and an outer aerodynamic fairing (9), the inner annular wall (7) bounding an exhaust duct through which a gas flow passes during engine operation;a set of hot flaps (14) mounted in a pivotable manner on a downstream end (15) of the inner annular wall (7);a set of cold flaps (16) mounted in a pivotable manner on a downstream end (17) of the outer aerodynamic fairing (9);a thrust reverser (30) including two eyelids (31, 32) which are mounted in a pivotable manner on opposite sides of an axial plane of symmetry and downstream of the inner annular wall (7), the eyelids (31, 32) being movable between a forward-thrust position in which the eyelids (31, 32) are situated in an extension of the cold flaps (16) and a thrust-reversal position in which the eyelids (31, 32) project into the exhaust duct to deflect the gas flow;a first control mechanism (21) arranged to drive the hot and cold flaps (14, 16);a second control mechanism (35, 36) arranged to drive the eyelids (31, 32) between the forward-thrust and thrust reversal positions; anda third control mechanism (50) arranged to drive the eyelids (31, 32) in a direction perpendicular to the axial plane of symmetry, whereby the eyelids (31, 32) are driven away from the axial plane of symmetry in a takeoff mode.