A nacelle having a fan casing, a cowl that movable between an advanced position and a retracted position that opens an opening between a bypass duct and the outside, deflectors secured to the mobile cowl, wherein, in the advanced position, they are around the fan casing and wherein, in the retracted position, they are across the opening, and a fan ramp with a mounting base and flaps that are able to rotate on the mounting base between a stowed position and a deployed position. For each flap, the fan ramp has a return element that urges the flap) into the deployed position, and the deflectors have a stop in contact with the flap when the mobile cowl passes from the retracted position to the advanced position. Thus, in the advanced position, the flaps are folded back and their bulk is reduced.

A connecting rod for a nacelle of a turbine engine is described. The connecting rod includes a region configured to move the center of aerodynamic forces able to be exerted on the connecting rod, in the direction of an air flow intended to be generated during a thrust generated by the turbine engine.

A primary lock system for a translating cowl thrust reverser system includes a primary lock having a housing, a lock, and a manual mechanism. The lock is disposed at least partially within, and is movable relative to, the housing and is movable between a lock position and an unlock position. The manual mechanism is coupled to the lock and is configured, in response to a manual input force supplied to the manual mechanism, to: selectively move from a first position to a second position, whereby the lock is selectively moved from the lock position to the unlock position, respectively, and selectively prevent movement of the lock out of the lock position.

A translating cowl thrust reverser system with efflux management includes a support structure, a transcowl, a cowl shield, and a single cascade structure. The transcowl and cowl shield are moveable together between a first position, in which the transcowl abuts the support structure, and a second position, in which an aperture is formed between the transcowl and the support structure. The cowl shield has cowl shield turning vanes. The single cascade structure is disposed within the aperture and includes a forward wall, a curved vane, internal turning vanes, and external turning vanes. In the first position, each cowl shield turning vane is disposed between a different pair of external turning vanes. The cowl shield turning vanes, the internal turning vanes, and the external turning vanes turn the airflow so that it is directed substantially perpendicular to, and vertically outboard relative to, a plane of symmetry.

Compression mold assembly for forming a preform of a cascade includes first and second die elements and an axis of alignment. Line of removal of a formed preform is positioned perpendicular to a plane perpendicular to the axis of alignment. First die portion includes first curved surface forming interior surface of first strong back and second die portion includes first curved surface forming interior surface of a second strong back of a cell of a formed preform. Second die portion includes second curved surface forming an interior surface of a first vane on forward side of the cell of the formed preform and first die portion further includes first wall member which extends along line of removal and a second wall member which extends angularly from first wall portion forming an interior surface of a second vane positioned on an aft side of the cell.

A first cascade segment of a thrust reverser system has a first cascade segment flow area and is associated with a first lateral sector. A second cascade segment has a second cascade segment flow area and is associated with a second lateral sector. The second cascade segment flow area may be at least 1.2 times the first cascade segment flow area. The first lateral sector has a first leakage flow area and a first total flow area that is equal to a sum of at least the first cascade segment flow area and the first leakage flow area. The second lateral sector has a second leakage flow area and a second total flow area that is equal to a sum of at least the second cascade segment flow area and the second leakage flow area. The second total flow area may be within 10% of the first total flow area.

The subject matter of this specification can be embodied in, among other things, a system that includes a flexible structure, a power inverter, a first electromechanical device configured to urge movement of a first portion of the flexible structure based on power received from the power inverter, a second electromechanical device configured to urge movement of a second portion of the flexible structure based on power received from the power inverter, a feedback sensor configured to provide a feedback signal indicative of alignment between the first portion and the second portion, and a controller configured to control operation of at least one of the first electromechanical device and the second electromechanical device based on the feedback signal.

An assembly is provided for an aircraft propulsion system. This assembly includes a thrust reverser system. The thrust reverser system includes a cavity, a sleeve and a turning door. The sleeve is configured to translate along a centerline between a sleeve stowed position and a sleeve deployed position. The turning door is configured to move between a turning door stowed position and a turning door deployed position. The turning door is disposed within the cavity when the sleeve is disposed in the sleeve stowed position. The turning door projects in a radial outward direction away from the sleeve and the centerline when the sleeve is in the sleeve deployed position.

Disclosed herein is a blocker door for use in a thrust reverser portion of a nacelle. The blocker door includes a structural frame having a plurality of connected and crossing ribs. The blocker door also includes a front sheet positioned on an airflow side of and attached to the structural frame. The blocker door also includes at least one acoustic core positioned between the ribs of the structural frame and comprising a plastic material.

An assembly includes a structure with 6 o'clock and 12 o'clock beams and front and rear curved beams, in which the 12 o'clock beam is mounted to be able to rotate on a pylon of an aircraft between a closed position and a raised position, a fan cowl fixed to the structure, a thrust reverser with a rear cowl and that is able to move in translation along the 6 o'clock and 12 o'clock beams between a forward position and a backward position, cascades fixed to the thrust reverser, and a mover for moving the thrust reverser. With such an arrangement, the fan cowl and the thrust reverser are fixed to the same structure, and it is this structure that is hinged to the pylon.