An aircraft propulsion assembly, including a turbine engine comprising at least one gas generator configured to generate a main flow, which is supplied by a central jet to at least one power turbine, the central jet being surrounded by an outer fairing, and the power turbine driving, on the periphery thereof, at least one fan rotor. The aircraft propulsion assembly comprises first movable means which are arranged so as to divert at least some of the main flow from the central jet to the outside of the outer fairing and preferably upstream of the turbine engine so as to generate thrust reversal. An aircraft which uses the propulsion assembly, particularly on the rear tip of the fuselage of the aircraft.

A thrust reverser for a nacelle may comprise a composite track beam and a composite lug. The composite lug may be inserted through a through-hole in the composite track beam. Continuous fibers in the composite lug may provide strength in the in-plane direction.

Aspects of the disclosure are directed to a thrust reverser of an aircraft, comprising: a wall having a first surface that partially forms a flow channel associated with an air flow, a blocker door having a second surface that partially forms the flow channel, and a dielectric elastomeric device that is configured to selectively expand and contract within a cavity formed between the wall and the blocker door where the cavity is substantially radially adjacent to the flow channel when the thrust reverser is in a stowed state.

Aspects of the disclosure are directed to a thrust reverser of an aircraft, comprising: a wall having a first surface that partially forms a flow channel associated with an air flow, a blocker door having a second surface that partially forms the flow channel, and a dielectric elastomeric device that is configured to selectively expand and contract within a cavity formed between the wall and the blocker door where the cavity is substantially radially adjacent to the flow channel when the thrust reverser is in a stowed state.

A thrust reverser system deployable from a core cowl is provided. The thrust reverser system may comprise one or more doors that are configured to overlap to reduce leakage and increate reverse thrust while deployed. The doors may be configured to vanes that are configured to split and/or direct airflow.

A thrust reverser system deployable from a core cowl is provided. The thrust reverser system may comprise one or more doors that are configured to overlap to reduce leakage and increate reverse thrust while deployed. The doors may be configured to vanes that are configured to split and/or direct airflow.

An aircraft thrust reverser actuation system includes a plurality of actuator assemblies that are each configured, upon receipt of a drive torque, to move to a position. The rotary hydraulic motor is coupled to each of the actuator assemblies and is configured, upon receipt of hydraulic fluid, to rotate and supply the drive torque to each of the actuator assemblies. The control valve is in fluid communication with the rotary hydraulic motor and is configured, upon receipt of electrical current, to move to a valve position based on the magnitude of the received electrical current, to thereby control the direction and flow of hydraulic fluid to the hydraulic motor. The valve control is configured, upon receipt of thrust reverser commands, to supply the electrical current to the control valve and selectively vary the magnitude of the electrical current based on the positions of the actuator assemblies.

An aircraft thrust reverser actuation system includes a plurality of actuator assemblies that are each configured, upon receipt of a drive torque, to move to a position. The rotary hydraulic motor is coupled to each of the actuator assemblies and is configured, upon receipt of hydraulic fluid, to rotate and supply the drive torque to each of the actuator assemblies. The control valve is in fluid communication with the rotary hydraulic motor and is configured, upon receipt of electrical current, to move to a valve position based on the magnitude of the received electrical current, to thereby control the direction and flow of hydraulic fluid to the hydraulic motor. The valve control is configured, upon receipt of thrust reverser commands, to supply the electrical current to the control valve and selectively vary the magnitude of the electrical current based on the positions of the actuator assemblies.

An aircraft dual-flow turbine engine assembly includes: an internal shroud for externally delimiting a primary flow path of the turbine engine gases; an external shroud for internally delimiting a secondary flow path of the turbine engine gas; and at least one air discharge duct extending between the internal shroud and the external shroud, the air discharge duct opening into the secondary flow path through an outlet orifice equipped with discharge fins. At least some of the discharge fins are movably mounted so as to be able to be incidence-control between a propulsion position, and a reverse thrust position.

An aircraft dual-flow turbine engine assembly includes: an internal shroud for externally delimiting a primary flow path of the turbine engine gases; an external shroud for internally delimiting a secondary flow path of the turbine engine gas; and at least one air discharge duct extending between the internal shroud and the external shroud, the air discharge duct opening into the secondary flow path through an outlet orifice equipped with discharge fins. At least some of the discharge fins are movably mounted so as to be able to be incidence-control between a propulsion position, and a reverse thrust position.