Abstract: A nacelle has a fixed cowl and a mobile cowl, which is movable along a translation path between closing and opening 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 closing/closed positions, the drive mechanism assures a translation of the mobile cowl and a rotation of the reverser flap toward their respective opening/open positions. From the open/opening positions, the drive mechanism assures a rotation of the reverser flap and a translation of the mobile cowl toward their respective closed/closing position. In some embodiments, the nacelle further includes an additional, or second, flap.

Abstract: A nacelle has a fixed cowl and a mobile cowl, which is movable along a translation path between closing and opening 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 closing/closed positions, the drive mechanism assures a translation of the mobile cowl and a rotation of the reverser flap toward their respective opening/open positions. From the open/opening positions, the drive mechanism assures a rotation of the reverser flap and a translation of the mobile cowl toward their respective closed/closing position. In some embodiments, the nacelle further includes an additional, or second, flap.

Abstract: A nacelle for a ducted fan turbojet engine comprising an engine. The nacelle comprises a fixed cowl, an upstream wall bounding off, with the engine, a working section for a secondary flow, a movable cowl with an interior wall and an exterior wall, and movable in translation between a closing position where the exterior wall adjoins the fixed cowl and the interior wall prolongs the upstream wall, and an opening position where the exterior wall is distant from the fixed cowl so as to open a window and the interior wall is distant from the upstream wall, an inverter flap between the interior wall and the exterior wall mounted to be free in rotation about an axis of rotation situated on the interior wall and a drive mechanism for moving the movable cowl.

Abstract: A seal is interposed between two surfaces of an aircraft propulsion assembly. The seal includes at least two layers each comprising a plurality of strands made of a heat-resistant material, the strands of a first layer being oriented in a first orientation and the strands of a second layer being oriented in a second orientation different than the first orientation.

Abstract: An aircraft nacelle includes a cowling, an engine housed in an internal volume of the cowling, and at least one thrust reverser, an air passage duct being formed between an internal wall of the cowling and an external wall of the engine. The cowling includes a fixed cowling part and a moving cowling part that is translationally movable between a plurality of positions, at least one of the positions varying an air flow through the duct. The moving cowling part includes the at least one thrust reverser so that translational movement of the moving cowling part also allows the moving cowling part to switch from a position in which the at least one thrust reverser is retracted into a reverse-thrust position in which a bypass flow is deflected to generate a reverse thrust.

Abstract: The invention relates to an engine assembly for aircraft in which the coupling device comprises a fore aerodynamic structure having a cradle equipped with an aerodynamic cowling, the cradle being hinge mounted on the air intake of the engine, and the fan cowls being mounted to move on the cradle so as to be able to occupy an open position as well as a closed position in which they are supported by the air intake and by a thrust reverser. According to the invention, when the cowls are in open position, the cradle adopts a first configuration in which its aft end rests on a span of the engine mounting structure, and when the cowls are in closed position, the cradle, borne by said cowls, adopts a second configuration in which it is lacking any direct mechanical link with the other elements of the engine mounting structure.

Abstract: An aircraft nacelle in which a power plant with an outside surface is arranged, whereby the nacelle has an inside wall that with the outside surface of the power plant delimits a secondary annular pipe, at least one moving part so as to create at least one lateral opening, and a thrust reversal device that has at least one moving physical obstacle that can occupy a first retracted state in which it does not deflect the stream that circulates in the secondary pipe and another deployed state in which it at least partially deflects the stream that circulates in the secondary annular pipe toward the at least one side opening, characterized in that it includes a ring that is arranged in the secondary pipe, distant from the inside wall of the nacelle and the outside surface of the power plant that supports the at least one moving physical obstacle.

Abstract: The invention relates to an engine assembly for aircraft in which the coupling device comprises a fore aerodynamic structure having a cradle equipped with an aerodynamic cowling, the cradle being hinge mounted on the air intake of the engine, and the fan cowls being mounted to move on the cradle so as to be able to occupy an open position as well as a closed position in which they are supported by the air intake and by a thrust reverser. According to the invention, when the cowls are in open position, the cradle adopts a first configuration in which its aft end rests on a span of the engine mounting structure, and when the cowls are in closed position, the cradle, borne by said cowls, adopts a second configuration in which it is lacking any direct mechanical link with the other elements of the engine mounting structure.

Abstract: Aircraft nacelle including a cowling and an engine, the cowling including a fixed portion and a mobile portion able to slide in order to define a radial opening with the mobile portion, a thrust reverser system including a plurality of flaps intended to be deployed in order to seal at least partially an annular channel surrounding the engine, the mobile portion of the cowling including an annular housing extending longitudinally in order to receive the flaps in rest position. Each flap is linked to the fixed portion by a pivot joint and is linked to the mobile portion by a sliding-pivot joint, in such a way that a sliding of the mobile portion in separating from the fixed portion provokes a rotation of each flap around the axis of rotation of the joint with the fixed portion.

Abstract: The invention relates to an aircraft nacelle comprising a cowling, an engine housed in an internal volume of the cowling and at least one thrust reverser, an air passage duct (7) being formed between the internal wall of the said cowling and an external wall of the said engine (12). According to the invention, the said cowling comprises a fixed cowling part (2) and a moving cowling part (3) capable of translational movement between a plurality of positions, at least one of the said positions varying the air flow through the said duct (7), the said moving cowling part (3) comprising the said at least one thrust reverser so that translational movement of the said moving cowling (3) also allows the said moving cowling (3) to switch from a position in which the said at least one thrust reverser is retracted into a reverse-thrust position in which the bypass flow is deflected to generate a reverse thrust.

Abstract: An aircraft nacelle in which a power plant with an outside surface (46) is arranged, whereby the nacelle has an inside wall (44) that with the outside surface (46) of the power plant delimits a secondary annular pipe, at least one moving part (52) so as to create at least one lateral opening (54), and a thrust reversal device that has at least one moving physical obstacle (56, 58) that can occupy a first retracted state in which it does not deflect the stream that circulates in the secondary pipe and another deployed state in which it at least partially deflects the stream that circulates in the secondary annular pipe toward the at least one side opening (54), characterized in that it includes a ring (50) that is arranged in the secondary pipe, distant from the inside wall (44) of the nacelle and the outside surface (46) of the power plant that supports the at least one moving physical obstacle (56, 58).

Abstract: Aircraft nacelle comprising a cowling and an engine, the cowling comprising a fixed portion and a mobile portion able to slide in order to define a radial opening with the mobile portion, a thrust reverser system comprising a plurality of flaps intended to be deployed in order to seal at least partially an annular channel surrounding the engine, the mobile portion of the cowling comprising an annular housing extending longitudinally in order to receive the flaps in rest position. Each flap is linked to the fixed portion by a pivot joint and is linked to the mobile portion by a sliding-pivot joint, in such a way that a sliding of the mobile portion in separating from the fixed portion provokes a rotation of each flap around the axis of rotation of the joint with the fixed portion.