Locking actuators for thrust reverser actuation systems, engines and aircraft including the same, and associated methods. A locking actuator includes an actuator housing, an extension element, and a lock assembly. The extension element is configured to translate along an actuator axis to transition between a retracted state and an extended state. The lock assembly transitions between a locked state and an unlocked state independent of transitioning the extension element between the retracted and extended states. In examples, a thrust reverser actuation system includes an actuator assembly with the locking actuator and a hydraulic control assembly. In examples, an engine includes a thrust generator, a nacelle, a transcowl, and the thrust reverser actuation system. In examples, a method of operating a thrust reverser actuation system includes transitioning a lock assembly from a locked state to an unlocked state and transitioning an extension element from a retracted state to an extended state.

A thrust reverser for an aircraft propulsion assembly, this reverser including a mobile annular external structure, a single actuator for controlling the position of this mobile external structure and a device for guiding the mobile external structure when changing its position. The actuator and the guiding device are housed in a fairing of a pylon of the propulsion assembly to a wing or fuselage of the aircraft.

An interspatial blocker for a thrust reverser system of a turbofan engine, and a thrust reverser system and a turbofan engine incorporating the same. The interspatial blocker includes a first and second flap that rotate from a stored position to a blocking position, and a leading-edge structure rotatably coupling the first flap to the second flap. The leading-edge structure is set up to be installed in a fan nacelle of a turbofan engine in a substantially radial orientation such that the first flap rotates in a first direction about a first axis extending in a substantially radial direction from the stored position to the blocking position, and such that the second flap rotates in a second direction about a second axis extending in the substantially radial direction from the stored position to the blocking position, with the first direction being opposite to the second direction.

An interspatial blocker for a thrust reverser system of a turbofan engine, and a thrust reverser system and a turbofan engine incorporating the same. The interspatial blocker includes a first and second flap that rotate from a stored position to a blocking position, and a leading-edge structure rotatably coupling the first flap to the second flap. The leading-edge structure is set up to be installed in a fan nacelle of a turbofan engine in a substantially radial orientation such that the first flap rotates in a first direction about a first axis extending in a substantially radial direction from the stored position to the blocking position, and such that the second flap rotates in a second direction about a second axis extending in the substantially radial direction from the stored position to the blocking position, with the first direction being opposite to the second direction.

Systems and methods are provided for an aircraft propulsor with a fan cowl with one or more tangential restraints. The tangential restraints may be configured to enter respective tangential receiving portions of a fixed portion of the aircraft propulsor. The fan cowl may receive a load that may include a bending load. The tangential restraints may be configured to convert the bending load to membrane tension and thus decrease deflection of the fan cowl. The fan cowl may be a translating sleeve used for a reverse thrust.

Systems and methods are provided for an aircraft propulsor with a fan cowl with one or more tangential restraints. The tangential restraints may be configured to enter respective tangential receiving portions of a fixed portion of the aircraft propulsor. The fan cowl may receive a load that may include a bending load. The tangential restraints may be configured to convert the bending load to membrane tension and thus decrease deflection of the fan cowl. The fan cowl may be a translating sleeve used for a reverse thrust.

A turbofan with a nacelle having a slider that is movable between an advanced position and a retracted position to open a window between a duct and the outside, blades, each one being able to move in rotation between a stowed position and a deployed position, and a maneuvering system that moves each blade, a transmission arrangement that rotates the blades one after the other, a drive system that converts the translational movement of the slider into a rotational movement of a first blade and that has a ball screw system, an epicyclic gear train, and an assembly of arms and levers.

A turbofan with a nacelle having a slider that is movable between an advanced position and a retracted position to open a window between a duct and the outside, blades, each one being able to move in rotation between a stowed position and a deployed position, and a maneuvering system that moves each blade, a transmission arrangement that rotates the blades one after the other, a drive system that converts the translational movement of the slider into a rotational movement of a first blade and that has a ball screw system, an epicyclic gear train, and an assembly of arms and levers.

A cascade for a thrust reversal device intended to be mounted on a turbomachine of an aircraft, the cascade including first partitions extending in a first direction, second fixed partitions extending in a second direction orthogonal to the first direction, and a frame inside which the first and second partitions extend, the frame including at least two fixed walls extending according to the first direction, and at least one part of each first partition extending between two second partitions. At least one first partition is mobile according to the second direction between a first position wherein the first partition is distant, in the second direction, from the fixed walls to form a plurality of resonating cavities with the first partitions and/or the fixed walls, and a second position wherein the one first partition is in contact with a fixed wall or another first partition.

A cascade for a thrust reversal device intended to be mounted on a turbomachine of an aircraft, the cascade including first partitions extending in a first direction, second fixed partitions extending in a second direction orthogonal to the first direction, and a frame inside which the first and second partitions extend, the frame including at least two fixed walls extending according to the first direction, and at least one part of each first partition extending between two second partitions. At least one first partition is mobile according to the second direction between a first position wherein the first partition is distant, in the second direction, from the fixed walls to form a plurality of resonating cavities with the first partitions and/or the fixed walls, and a second position wherein the one first partition is in contact with a fixed wall or another first partition.