An assembly is provided for an aircraft propulsion system. This assembly includes a target-type thrust reverser and a tubular trailing edge body. The target-type thrust reverser includes a plurality of thrust reverser doors. Each of the thrust reverser doors is configured to pivot between a stowed position to a deployed position. The tubular trailing edge body is configured to at least partially form a gas path nozzle for the aircraft propulsion system. The tubular trailing edge body is configured to be displaced when the thrust reverser doors pivot from the stowed position to the deployed position.

An apparatus is provided for an aircraft propulsion system. This apparatus includes a thrust reverser cascade extending longitudinally between a cascade forward end and a cascade aft end. The thrust reverser cascade extends laterally between a cascade first side and a cascade second side. The thrust reverser cascade extends radially between a cascade inner face and a cascade outer face. The thrust reverser cascade includes a plurality of vanes arranged in a longitudinally extending array. The vanes include a first vane and a second vane. A leading edge of the first vane is disposed on the cascade inner face. A leading edge of the second vane is recessed radially into the thrust reverser cascade from the cascade inner face.

A cascade assembly of a nacelle for a turbofan engine includes a one-piece cascade fixed to a translating sleeve constructed and arranged to move between forward and aft positions along a centerline. A hook device of the cascade assembly includes a first catch fixed to a stationary structure and a second catch fixed to the one-piece cascade. The first catch is adapted to mate with the second catch for translating load when the cascade assembly is in a deployed state and the translating sleeve is in the aft position.

A thrust reverser for a gas turbine engine may comprise a frame, a first reverser door pivotally mounted to the frame at a first pivot point, a second reverser door pivotally mounted to the frame at a second pivot point, a first nacelle defining a first trailing edge of the gas turbine engine coupled between the frame and the first reverser door, and a second nacelle defining a second trailing edge of the gas turbine engine coupled between the frame and the second reverser door. The first nacelle and the second nacelle translate in an aft and radial outward direction relative to the gas turbine engine in response to the thrust reverser moving to a deployed position.

A thrust reverser system for jet aircraft comprising an exhaust tailpipe mounted to the turbine engine aft turbine flange and two clamshell doors, actuators and a locking system to prevent inadvertent deployment of the clamshell doors in-flight. Two improved design clamshell doors configurations, either one or a combination of both, mounted on either side of the top and bottom of the exhaust tailpipe, fitted with two patented design actuators mounted one on each side of the external sides of the tailpipe between the clamshell doors and the tailpipe, possibly in a depression in the tailpipe called blister, assuming them to be hydraulic actuators for discussion purposes. The actuators drive the clamshell doors using improved floating linkages loosely pivoted to the exterior of the exhaust tailpipe. The actuators are connected to the doors through mechanical linkages, to deploy the doors aft of the tailpipe exhaust area during deceleration after landing, diverting the exhaust gases forward to slow down the aircraft, and the actuators also drive two movable fairings during thrust reverser operation to enclose the reversed exhaust flow forward to prevent its impingement on the skin of the aircraft and provide a ram inlet area with the sides of the clamshell doors allowing ram air from the surrounding free stream to be scooped through the gap between the movable fairing and clamshell doors thereby provide cooling of the door surface in contact with the exhaust gases and mix with the engine exhaust gases in reverse thrust mode thereby augmenting reverse thrust mass flow and energy. The exhaust tailpipe can have a circular or any geometric exhaust section or in other configuration can be fitted in with a flow mixer with the surrounding ambient air to reduce shear noise resulting from the high velocity exhaust gases for noise attenuation. The flow mixer can also be perforated to allow for suction of ambient air by the lower static pressure engine exhaust gases to reduce shear noise and increase mixing and thrust. Two fixed fairings, above and below the tailpipe at the exit section can have perforations and also perforations on the movable fairings to educt surrounding air also to reduce shear noise between surrounding air and the engine exhaust flow during forward thrust based on SAE Aerospace Information Report AIR-1191 and method of calculation. Other configurations for the trailing edges of the fixed and movable fairings can have wavy contour lines to increase the contact area between the engine exhaust gases and the surrounding air to reduce shear noise as well. Fixed circular shape or rolling bodies, depicted as wheels for discussion purpose, but they can be o

A nacelle for an aircraft turbofan includes a rear section including a thrust reversal device having an upper door and a lower door, the upper and lower doors being mobile in rotation between a stowed position in which they are aerodynamically continuous with the rest of the nacelle and a deployed position in which the upper and lower doors are able to redirect forward the core and bypass flows produced by the jet engine, each door being moved from one position to the other by at least one dedicated actuator. The opening angle (X) of the upper door in the deployed position is smaller than the opening angle (Y) of the lower door.

A nacelle is provided for an aircraft propulsion system. This nacelle includes a stationary support, a fanlet, a thrust reverser sleeve and an interface assembly providing an interface between the stationary support, the fanlet and the thrust reverser sleeve where the fanlet and the thrust reverser sleeve are respectively in stowed positions. The stationary support extends circumferentially about an axial centerline. The fanlet includes an inlet structure and a fan cowl. The fanlet is configured to translate axially along the centerline. The thrust reverser sleeve is configured to translate axially along the centerline. The interface assembly includes a pair of interlocking components, wherein a first of the interlocking components is mounted to the fanlet at the aft end of the fanlet.

A thrust reverser system for a gas turbine engine includes a transcowl movable between a stowed position, a deployed position and a partially deployed position between the stowed position and the deployed position by at least one actuator. The system includes a temperature sensor and at least one resistance sensor. The thrust reverser system includes a controller, having a processor, that: outputs one or more control signals to move the transcowl to the partially deployed position; determines whether a temperature associated with the transcowl exceeds a temperature threshold; outputs one or more control signals to move the transcowl from the partially deployed position to the stowed position; determines whether the transcowl has encountered resistance; and based on the determination, outputs one or more control signals to stop a movement of the transcowl and outputs the one or more control signals to move the transcowl to the partially deployed position.

A thrust reverser system for a gas turbine engine includes at least one hinge coupled to the thrust reverser system so as to be adjacent to at least one opening defined in the thrust reverser system. The thrust reverser system includes at least one body coupled to the at least one hinge. The at least one body has a first body end and an opposing second body end. The body pivotally coupled to the hinge such that a portion of the body is positionable within the at least one opening and the body includes at least one counterweight at the first body end or the second body end. The body is positioned within the at least one opening based on an operating condition of the gas turbine engine.

A thrust reverser system for a turbine engine includes a support structure, a transcowl, a door, a lock, and a first elastic element. The transcowl is mounted on the support structure and is translatable between a stowed position, a deployed position, and an over-stow position. The door is pivotally coupled to the support structure and is rotatable between at least a first position, a second position, and a third position. The lock is movable between a locked position, to prevent transcowl translation toward the deployed position, and an unlocked position, to allow transcowl translation toward the deployed position. The lock is only able to move to the unlocked position when the transcowl is in the over-stow position. The first elastic element is disposed within the stowed position aperture and, when engaging both the support structure and the transcowl, supplies a force to the transcowl.