A variable-section nozzle for an aircraft nacelle includes a deformable portion of which is movable between a narrow section position and a wide section position. In particular, the variable-section nozzle includes piezoelectric actuators and a controller to control the piezoelectric actuators in order to displace the deformable portion between the narrow and wide section positions. The piezoelectric actuators can be disposed on at least one faces of the deformable portion or be disposed end-to-end to form actuating rods.

A variable area nozzle assembly for a gas turbine engine includes a nozzle disposed about a nozzle centerline and a fixed ring radially surrounding the nozzle. The nozzle includes a radially outer surface and a radially inner surface. The radially inner surface defines an outlet cross-sectional area of the nozzle. The nozzle is movable relative to the nozzle centerline between a first position of the radially inner surface defining a maximum area of the outlet cross-sectional area and a second position of the radially inner surface defining a minimum area of the outlet cross-sectional area. With the nozzle in the first position, the radially outer surface contacts the fixed ring. With the nozzle in the second position, the radially outer surface is spaced from the fixed ring.

An articulating exhaust nozzle thrust reverser includes an outer articulating panel comprising an outer skin and an outer thrust reverser door and an inner articulating panel comprising a forward inner skin, an aft inner skin, and an inner thrust reverser door. The outer articulating panel is configured to pivot to vary a nozzle exit area. The forward inner skin is configured to pivot to vary a nozzle throat area. The outer thrust reverser door is pivotally coupled to the outer skin. The inner thrust reverser door is pivotally coupled to the aft inner skin. The outer articulating panel and the inner articulating panel may be individually operated to independently vary the exhaust nozzle throat area and/or the exhaust nozzle exit area.

An articulating exhaust nozzle thrust reverser includes an outer articulating panel comprising an outer skin and an outer thrust reverser door and an inner articulating panel comprising a forward inner skin, an aft inner skin, and an inner thrust reverser door. The outer articulating panel is configured to pivot to vary a nozzle exit area. The forward inner skin is configured to pivot to vary a nozzle throat area. The outer thrust reverser door is pivotally coupled to the outer skin. The inner thrust reverser door is pivotally coupled to the aft inner skin. The outer articulating panel and the inner articulating panel may be individually operated to independently vary the exhaust nozzle throat area and/or the exhaust nozzle exit area.

An articulating exhaust nozzle thrust reverser includes an outer articulating panel comprising an outer skin and an outer thrust reverser door and an inner articulating panel comprising a forward inner skin, an aft inner skin, and an inner thrust reverser door. The outer articulating panel is configured to pivot to vary a nozzle exit area. The forward inner skin is configured to pivot to vary a nozzle throat area. The outer thrust reverser door is pivotally coupled to the outer skin. The inner thrust reverser door is pivotally coupled to the aft inner skin. The outer articulating panel and the inner articulating panel may be individually operated to independently vary the exhaust nozzle throat area and/or the exhaust nozzle exit area.

A variable area exhaust mixer is provided for a gas turbine engine. The variable area exhaust mixer includes an outer wall with a multiple of doors. Each of the multiple of doors is operable to control a passage entrance into at least one of a multiple of circumferentially arrayed vanes with a respective strut flow passage which essentially alters its bypass ratio during flight to match requirements.

A variable area exhaust mixer is provided for a gas turbine engine. The variable area exhaust mixer includes an outer wall with a multiple of doors. Each of the multiple of doors is operable to control a passage entrance into at least one of a multiple of circumferentially arrayed vanes with a respective strut flow passage which essentially alters its bypass ratio during flight to match requirements.

An articulating exhaust nozzle thrust reverser includes an outer articulating panel comprising an outer skin and an outer thrust reverser door and an inner articulating panel comprising a forward inner skin, an aft inner skin, and an inner thrust reverser door. The outer articulating panel is configured to pivot to vary a nozzle exit area. The forward inner skin is configured to pivot to vary a nozzle throat area. The outer thrust reverser door is pivotally coupled to the outer skin. The inner thrust reverser door is pivotally coupled to the aft inner skin. The outer articulating panel and the inner articulating panel may be individually operated to independently vary the exhaust nozzle throat area and/or the exhaust nozzle exit area.

A thrust reverser includes an outer articulating panel and an inner articulating panel. The outer articulating panel includes an outer thrust reverser door pivotally coupled to the outer articulating panel. The outer thrust reverser door is movable between an outer door stowed position and an outer door deployed position with respect to the outer articulating panel. The inner articulating panel includes an inner thrust reverser door pivotally coupled to the inner articulating panel. The inner thrust reverser door is movable between an inner door stowed position and an inner door deployed position with respect to the inner articulating panel. The inner thrust reverser door and the outer thrust reverser door are configured to redirect exhaust gasses to generate reverse thrust to an aircraft when the thrust reverser doors are in the deployed positions.