초록 ▼

A variable geometry exhaust nozzle for a turbojet engine is disclosed having an array of outer flaps and an array of inner flaps radially spaced apart and extending about a central axis of the exhaust duct structure. The array of outer flaps comprises a plurality of outer flaps each having an upstre

A variable geometry exhaust nozzle for a turbojet engine is disclosed having an array of outer flaps and an array of inner flaps radially spaced apart and extending about a central axis of the exhaust duct structure. The array of outer flaps comprises a plurality of outer flaps each having an upstream end pivotally attached to the engine duct structure. The array of inner flaps comprises a plurality of upstream inner flaps, each having an upstream edge pivotally attached to the engine duct structure and a plurality of downstream inner flaps each having an upstream edge portion pivotally attached to a downstream edge portion of a corresponding upstream inner flap. A control annulus is movably attached to the engine structure so as to be movable axially along the central axis and is connected to an actuator which moves the control annulus between upstream and downstream limit positions along the central axis. The control annulus is connected to the upstream and downstream inner flaps such that the axial components of the forces exerted by the control annulus on the connections to the upstream and downstream inner flaps extend in opposite directions. The control annulus is also connected to the outer flap such that the axial component of the force exerted by the control annulus on the outer flap during flap movement extends in the same direction as does the axial component of the force exerted by the control annulus on the upstream inner flap connection. Since the axial components of the forces are in opposite directions, the actuator need only exert a minimal force on the control annulus to vary the positions of the flaps.

대표청구항 ▼

A variable geometry exhaust nozzle for a turbojet engine having a structure bounding an exhaust duct extending about a central axis through which gases pass in an upstream to downstream direction and comprising: a) a first array of outer flaps extending about the central axis and comprising a plural

A variable geometry exhaust nozzle for a turbojet engine having a structure bounding an exhaust duct extending about a central axis through which gases pass in an upstream to downstream direction and comprising: a) a first array of outer flaps extending about the central axis and comprising a plurality of outer flaps each having an upstream end portion pivotally attached to the engine structure; b) a second array of inner flaps extending about the central axis and located radially inwardly of the outer flaps, the second array comprising: i) a plurality of upstream inner flaps, each having an upstream edge portion pivotally attached to the engine structure and having a downstream edge portion; and, ii) a plurality of downstream flaps, each having an upstream edge portion pivotally attached to the downstream edge portion of an upstream inner flap; c) a control annulus movably attached to the engine structure so as to be movable along the central axis; d) actuating means connected to the engine structure and to the control annulus so as to move the control annulus between upstream and downstream limit positions; and, e) connecting means comprising first connector means connecting at least one upstream inner flap to the control annulus and second connector means connecting at least one downstream inner flap to the control annulus such that axial movement of the control annulus changes the geometry of the exhaust nozzle whereby the axial component of the force exerted by the control annulus on the first connection means extends in an opposite direction to the axial component of the force exerted by the control annulus on the second connector means.