A thrust reverser system for jet aircraft comprising an exhaust tailpipe mounted to the turbine engine aft turbine flange, clamshell doors, actuators and locking systems to prevent inadvertent deployment of the clamshell doors. Improved design clamshell doors shrouding the tailpipe fitted with two patented design actuators, enclosed between the doors and the tailpipe. The actuators throw the doors behind the tailpipe exhaust exit area using improved linkages attached to the tailpipe and the doors, to reverse the exhaust gases forward. The tailpipe can be of circular or any geometric shape. Reverse Exhaust gases are enclosed between the doors and two movable fairings. Several sound attenuation configurations provisions for the tailpipe, the fixed and movable fairings. Three independent locking systems provisions to prevent inadvertent deployment of the doors.

An active locking system of a movable element for a thrust reverser of an aircraft nacelle includes an active locking device of the movable element, movable between a locking position and an unlocking position, an actuator of the locking device controlled by a command for actuating the locking device, a blocking device for blocking the locking device in the unlocked position, movable between a blocking position and an unblocking position, and a device for displacing the blocking device. The actuation command controls the closure of the movable element, and the device for displacing the blocking device displaces the blocking device in the unblocking position when the movable element is at a predetermined position.

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 thrust reverser of a turbofan pod is provided that includes movable cowlings that retract relative to stationary front structure to reveal stationary or movable thrust reverser cascades, as well as a secondary variable nozzle section connected to the movable cowlings by guiding means enabling movement controlled by actuators engaged with the front structure to apply an axial thrust. The actuators are directly connected to the secondary nozzle, and in that the thrust reverser comprises latches connected to the movable cowlings, having two positions providing, alternately, latching onto the front structure or latching onto the control of the secondary nozzle.

Systems and methods are provided for an aircraft propulsor thrust reverser with a fastening system. The fastening system may include a male spool and a female spool configured to be threaded into the male spool. The male spool and the female spool may be coupled to a honeycomb structure and may evenly distribute force to the honeycomb structure to prevent plastic deformation of a honeycomb core of the honeycomb structure.

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 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.

A thrust reverser includes: a thrust-reversing element movable between a stowed position and a deployed position; at least one hydraulic actuator operably coupled to move the thrust-reversing element between the stowed and deployed positions; at least one hydraulic primary lock configured to transition, in response to a first activation pressure, between an engaged state, where movement of the thrust-reversing element is inhibited, and a released state, where movement of the thrust-reversing element is uninhibited; and a directional control unit fluidly coupled to the hydraulic actuator and the hydraulic primary lock, the directional control unit configured to transition from a first stage to a second stage in response to a second activation pressure that is greater than the first activation pressure, and where a transition from the first stage to the second stage by the directional control unit causes the hydraulic actuator to move the thrust-reversing element to the deployed position.

An engine system has a gas generator, a bi-fi wall surrounding at least a portion of the gas generator, a casing surrounding a fan, and the casing having first and second thrust reverser doors which in a deployed position abut each other and the bi-fi wall.

A nacelle comprising a fixed structure with a fixed cowling and a cowling movable in translation between closed and open positions, to open an opening between a duct and the exterior. A blocking door is rotatably movable on the movable cowling between a stowed position and a deployed position. A deployment system comprises an arm with a first end articulated on the blocking door and a second end that bears a stop, a slider fixed to the arm, a linear guide system is fixed on the fixed structure and guides the slide, and a cam. The stop is configured to lie against the cam when the movable cowling reaches an intermediate position from the closed position and to be guided by the cam to drive the rotation of the arm about the slider when the movable cowling moves from the intermediate position to an open position.