A variable area nozzle assembly includes a fixed structure surrounding an exhaust duct extending along a nozzle axis. The fixed structure defines an exhaust duct outlet of the exhaust duct. The fixed structure includes a first side beam and a second side beam. Each of the first side beam and the second side beam extend in a direction axially aft from the exhaust duct outlet. Each of an upper thrust reverser door and a lower thrust reverser door are pivotably mounted to the first side beam and the second side beam at a first axial position. An upper panel and a lower panel are pivotably mounted to the upper thrust reverser door and the lower thrust reverser door, respectively, at a second axial position located axially forward of the first axial position. The upper panel and the lower panel define a nozzle outlet cross-sectional area therebetween.

A variable area nozzle assembly for a gas turbine engine includes a fixed structure surrounding an exhaust duct extending along a nozzle centerline. The fixed structure further includes a first lateral side and a second lateral side opposite the first lateral side. The variable area nozzle assembly further includes a nozzle. The nozzle includes a nozzle outlet including a nozzle outlet cross-sectional area. The variable area nozzle assembly further includes a thrust reverser system including a first thrust reverser door and a second thrust reverser door. The first thrust reverser door is pivotably mounted to the fixed structure at the first lateral side. The second thrust reverser door is pivotably mounted to the fixed structure at the second lateral side. The first thrust reverser door and the second thrust reverser door define a portion of the nozzle outlet of the nozzle.

A variable area nozzle assembly includes a fixed structure surrounding an exhaust duct extending along a nozzle axis. The fixed structure defines an exhaust duct outlet of the exhaust duct. The fixed structure includes a first side beam and a second side beam. Each of the first side beam and the second side beam extend in a direction axially aft from the exhaust duct outlet. Each of an upper thrust reverser door and a lower thrust reverser door are pivotably mounted to the first side beam and the second side beam at a first axial position. An upper panel and a lower panel are pivotably mounted to the upper thrust reverser door and the lower thrust reverser door, respectively, at a second axial position located axially forward of the first axial position. The upper panel and the lower panel define a nozzle outlet cross-sectional area therebetween.

A two-dimensional variable area plug (2D VAP) nozzle assembly for a high-speed flight vehicle. In one embodiment, a 2D VAP nozzle assembly comprises a nozzle including a plurality of sidewalls; a plug body within the nozzle, the plug body abutting at least two of the plurality of sidewalls; a first convergent flap hingedly connected to at least one of the plurality of sidewalls; and a second convergent flap hingedly connected to at least one of the plurality of sidewalls. In one embodiment, the nozzle assembly includes only a first convergent flap and a second convergent flap, without diverging flaps. The 2D VAP nozzle assembly has a simplified design with reduced sidewall length, which results in reduced manufacturing and maintenance costs.

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.

An apparatus is provided for an aircraft propulsion system. This apparatus includes an exhaust nozzle. The exhaust nozzle includes a flowpath, a passage, an outer door, an inner door and an actuator configured to move the outer door and the inner door between an open arrangement and a closed arrangement. The flowpath extends axially along a centerline through the exhaust nozzle. The passage extends laterally into the exhaust nozzle to the flowpath when the outer door and the inner door are in the open arrangement. The outer door is configured to pivot inwards towards the centerline when the outer door moves from the closed arrangement to the open arrangement. The inner door is configured to pivot outwards away from the centerline when the inner door moves from the closed arrangement to the open arrangement.

An apparatus is provided for an aircraft propulsion system. This apparatus includes an exhaust nozzle. The exhaust nozzle includes a flowpath, a passage, an outer door, an inner door and an actuator configured to move the outer door and the inner door between an open arrangement and a closed arrangement. The flowpath extends axially along a centerline through the exhaust nozzle. The passage extends laterally into the exhaust nozzle to the flowpath when the outer door and the inner door are in the open arrangement. The outer door is configured to pivot inwards towards the centerline when the outer door moves from the closed arrangement to the open arrangement. The inner door is configured to pivot outwards away from the centerline when the inner door moves from the closed arrangement to the open arrangement.

A nozzle for a gas turbine engine. An array of convergent petals hingedly coupled to a nozzle exit of fixed diameter. An array of divergent petals, each divergent petal hingedly coupled to one of the array of convergent petals. A cam surface associated with the array of convergent petals. A pivot point coupled to the array of divergent petals by a first linkage and to a fixed point by a second linkage. A cam follower coupled to the second linkage by a third linkage, the cam follower arranged to abut and travel in contact with the cam surface. An actuator coupled to the cam follower and arranged to translate the cam follower along the cam surface to move the convergent and divergent petals.

A flap for a variable area exhaust nozzle of a gas turbine engine, having a support structure and a gas shield having a plurality of gas shield segments connected to the support structure and adjacently arranged along a longitudinal direction of the flap corresponding to flow through the nozzle. Each of the gas shield segments has a flowpath section arranged to cooperate with a corresponding flowpath section of an adjacent gas shield segment to define a flowpath surface of the gas shield to bound flow through the nozzle. The gas shield segments are configured to permit the respective flowpath section to move longitudinally relative the support structure in response to thermal expansion of the gas shield.

An exhaust system or nozzle for use in a gas turbine engine is disclosed herein. The exhaust system is adapted to adjust various streams of pressurized air produced by the gas turbine engine to control operation of the gas turbine.