Patent ID: 6276126
Filing Date: 2001-08-21
Classification: F02K,Y02T

Abstract:
An axisymmetric turbojet-engine exhaust nozzle which is directable as a unit, comprising:an exhaust duct (1) through which exhaust gases flow, the exhaust duct (1) having an axis X;an outer ring of cold flaps (11);an inner ring of hot flaps which comprises a set of converging flaps (7) and a set of diverging flaps (10), the set of diverging flaps (10) being situated downstream in an extension of the set of converging flaps (7) and hinging therefrom;a spherical wall (5) situated around the axis X at a downstream end of the exhaust duct (1) and supported thereby, an upstream end (6) of each of the converging flaps (7) being arranged to rest against the spherical wall (5);a control ring (12) situated around an axis Y and enclosing the spherical wall (5), the control ring (12) being displaceable parallel to the axis X and pivotable relative to the axis X when acted on by a control mechanism (30), the cold flaps (11) hinging on the control ring (12) and on downstream ends of the diverging flaps (10);a plurality of control levers (13) hinging on the control ring (12), each of the control levers (13) having an upstream end (15) which rests against an external surface (16) of the spherical wall (5) and a downstream end (17) which connects to a downstream end (8) of the converging flaps (7); anda synchronizing system which links the control ring (12) to the upstream end (15) of each of the control levers (13), the synchronizing system being arranged to ensure self-centering of the control ring (12), the outer ring of cold flaps (11) and the inner ring of hot flaps relative to the spherical wall (5).