Patent ID: 6327846
Filing Date: 2001-12-11
Classification: F02K

Abstract:
A wide-vectoring, axisymmetric exhaust nozzle for a turbojet engine, comprising a ring of converging flaps (21) supported on a vectoring structure (12) which is mounted on the downstream end of an exhaust housing (2) having an axis X in such a way as to be tiltable about a stationary center O located on the axis X, and a device configured to tilt the vectoring structure (12) and regulate the exhaust cross-section (A8) of the converging flaps;said vectoring structure (12) mounted on the downstream end of the exhaust housing (2) by means of an intermediate ring (9) pivotable, relative to the exhaust housing (2), about a first axis (7) passing through the center O, and pivotable, relative to the vectoring structure (12), about a second axis (10) perpendicular to the first axis (7) and also passing through the center O;said intermediate ring (9) connected by two mutually diametrically opposite first pivoting links (11a, 11b) to the vectoring structure (12) and further connected to the exhaust housing (2) by two mutually diametrically opposite second pivoting links (8a, 8b) having axes of rotation that are perpendicular to axes of rotation of the first pivoting links (11a, 11b), said intermediate ring (9) resting on two support arms (6a, 6b) situated outside the downstream end of the exhaust housing (2) to which they are rigidly joined; andsaid tilting device for the vectoring structure (12) being connected by linkrods to the converging flaps (21).