Abstract: A thrust reverser door for an aircraft propulsion unit, including a seal positioned at an upstream edge of the door. This seal includes a part that projects with respect to the upstream edge of the door and a rigid core to stiffen the projecting part. This configuration serves to reduce aerodynamic disturbances.

Abstract: An aircraft turbomachine comprising a fan conduit with a wall, a flow of air passing through the turbomachine via the fan conduit. An air passage comprising an air opening is arranged in the wall, the air passage configured to receive a portion of the flow of the air through the fan conduit. A deflector is fixed to the wall upstream of the air opening, the deflector comprising at least one cross-section extending in the fan conduit to capture the flow of air. The at least one cross-section is porous. The deflector protects the air passage structure and is easy to produce and to fix to the wall of the fan conduit when it is screwed or riveted directly thereto. The deflector, as a result of its location in the fan conduit, is easy to access and thus allows rapid maintenance operations without having to disassemble the air passage.

Abstract: A nacelle has a fixed cowl and a mobile cowl, which is movable along a translation path between closed and open positions, a window delimited by the fixed cowl and the mobile cowl and open between an airflow and exterior of the nacelle, a reverser flap rotatably mounted to move between closed and open positions, and a drive mechanism configured to control passage of the reverser flap between the closed and open positions as the mobile cowl moves between the closed and open positions. From the closed positions, the drive mechanism assures a translation of the mobile cowl and a rotation of the reverser flap toward their respective open positions. From the open positions, the drive mechanism assures a rotation of the reverser flap and a translation of the mobile cowl toward the closed position. In some embodiments, the nacelle further includes an additional, or second, flap.

Abstract: An aircraft includes a first outer surface exposed to a hot air flow flowing in a flow direction and a device for generating a film of cold air in contact with a region to be protected of the first outer surface. The device includes a cold air outlet arranged upstream of the region to be protected as seen in the flow direction, and an inlet arranged at a second outer surface of the aircraft in contact with cold air. The inlet is arranged such that a pressure gradient exists between the inlet and the outlet so as to generate a natural flow of cold air from the inlet to the outlet as well as means to cause said inlet to communicate with said outlet.

Abstract: A turbomachine for an aircraft comprising a fan duct delimited by a wall and through which an air stream flows from upstream to downstream, and an air passage arranged in the wall comprising an air inlet opening flush with the wall, the air passage being designed to draw part of the air flow of the fan duct through the air inlet opening. To control the amount of air entering the air passage, a flap is rotatably mounted on the wall of the fan duct, about an axis of rotation disposed downstream of the air inlet opening, between an open position, in which the flap partially closes the air inlet opening and leaves free the fan duct downstream of the air inlet opening, and a closed position, in which the flap leaves open the air inlet opening and partially closes the fan duct downstream of the air inlet opening.

Abstract: An aircraft turbomachine comprising a fan conduit with a wall, a flow of air passing through the turbomachine via the fan conduit. An air passage comprising an air opening is arranged in the wall, the air passage configured to receive a portion of the flow of the air through the fan conduit. A deflector is fixed to the wall upstream of the air opening, the deflector comprising at least one cross-section extending in the fan conduit to capture the flow of air. The at least one cross-section is porous. The deflector protects the air passage structure and is easy to produce and to fix to the wall of the fan conduit when it is screwed or riveted directly thereto. The deflector, as a result of its location in the fan conduit, is easy to access and thus allows rapid maintenance operations without having to disassemble the air passage.

Abstract: An aircraft includes a first outer surface exposed to a hot air flow flowing in a flow direction and a device for generating a film of cold air in contact with a region to be protected of the first outer surface. The device includes a cold air outlet arranged upstream of the region to be protected as seen in the flow direction, and an inlet arranged at a second outer surface of the aircraft in contact with cold air. The inlet is arranged such that a pressure gradient exists between the inlet and the outlet so as to generate a natural flow of cold air from the inlet to the outlet as well as means to cause said inlet to communicate with said outlet.