An aft cascade ring includes a first ring portion having a first arc shape and defining a first portion first lug. The aft cascade ring further includes a second ring portion having a second arc shape and defining a second portion first lug, the second ring portion being coupled to the first ring portion such that the first portion first lug and the second portion first lug are aligned.

A thrust reverser cascade of an aircraft engine comprises a frame and a vane overmolded onto the frame. The frame and the vane each comprise reinforcement fibers in a thermoplastic matrix. A method is disclosed for manufacturing the thrust reverser cascade or another part comprising an aerodynamic surface configured to interact with a flow of fluid. The method comprises providing a first portion of the part and overmolding a second portion of the part onto the first portion where the second portion includes the aerodynamic surface.

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.

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 turbojet engine comprising an engine, a nacelle comprising a fan case, an intermediate case having a part forming a hub and an outer shroud radially spaced away from the hub by a secondary, or bypass, flow path and fixed to the hub via arms, in which the outer shroud is situated to the rear and in the continuity of the fan case, a fixed structure fixed to the outer shroud, a mobile assembly mounted with the ability to effect translational movement on the fixed structure, and a ramp fixed to the outer shroud and configured to direct the secondary or bypass flow to exit the outer shroud. Such a turbojet engine makes it possible to simplify assembly and among other things, makes it possible to fix the ramp directly to the outer shroud.

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.

An improved thrust reverser for an aircraft propulsion assembly includes redirection of the air flow for performing the thrust reversal by one or more closure membranes, i.e. by thin and flexible structures deployed across the propulsion assembly. The improved thrust reverser includes at least one closure membrane arranged to deflect at least one portion of the air flow in the direction of the evacuation structure when the thrust reverser is in the reverse jet position and an intermediate structure movable in rotation relative to the fixed structure.

A thrust reverser includes two thrust reverser elements movable between a retracted position in which the thrust reverser is inactive and a deployed position in which the thrust reverser is active, a cylinder for deploying the thrust reverser elements, and a single-acting cylinder for retracting the thrust reverser elements.

A propulsion unit includes a gas turbine engine arranged along an axis and an exhaust system coupled to the gas turbine engine. The gas turbine engine includes an engine core configured to discharge a core flow and a fan configured to be driven by the engine core to discharge a bypass flow. The exhaust system receives the mixed bypass and core flows from the gas turbine engine.

An assembly is provided for an aircraft propulsion system. This assembly includes a fixed structure, a translating structure, a blocker door and a folding linkage. The translating structure is configured to move between a stowed position and a deployed position. The blocker door is pivotally attached to the translating structure at a first pivot joint. The folding linkage links the blocker door to the fixed structure. The folding linkage includes a member pivotally attached to the blocker door at a second pivot joint that is radially outboard of a skin of the blocker door when the translating structure is in the stowed position. The second pivot joint is radially outboard of the first pivot joint when the translating structure is in the stowed position.