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 rack for holding a portion of a thrust reverser. The rack may include a base and a supporting frame disposed perpendicularly with the base. The base and the supporting frame may include a hinge at each location where the base and the supporting frame are coupled together. The rack may also include two supporting poles parallel to the supporting frame. The two supporting poles may be designed such that the portion of the thrust reverser may be mounted onto the two supporting poles.

A rack for holding a portion of a thrust reverser. The rack may include a base and a supporting frame disposed perpendicularly with the base. The base and the supporting frame may include a hinge at each location where the base and the supporting frame are coupled together. The rack may also include two supporting poles parallel to the supporting frame. The two supporting poles may be designed such that the portion of the thrust reverser may be mounted onto the two supporting poles.

A bypass turbofan engine with a nacelle comprising a fan case and a thrust-reversal system. The fan case comprises an exterior wall, and the reversal system comprises a slider having an upstream frame, a downstream frame and a plurality of spars fixed between the upstream frame and the downstream frame, in which the slider is able to move between a forward position and a retracted position. The fan case comprises, at a rear edge of its exterior wall, a support. Each support comprises, for each spar, a shoe fixed to the exterior wall and positioned radially about the spar, and a skirt secured to the shoes and extending the rear edge, in which, in a forward position, the skirt bears around the downstream frame, and in which in a forward/retracted/intermediate position, the shoes are distant from the spars from the upstream frame.

A thrust reverser pivot door may comprise a support structure configured to pivot between a stowed position and a deployed position, and a pivot door outer skin coupled to the support structure, wherein a forward lip of the pivot door outer skin is configured to extend forward of a torque box and overlap the fan case to advantageously increase the overall size or area of the pivot door.

A thrust reverser pivot door may comprise a support structure configured to pivot between a stowed position and a deployed position, and a pivot door outer skin coupled to the support structure, wherein a forward lip of the pivot door outer skin is configured to extend forward of a torque box and overlap the fan case to advantageously increase the overall size or area of the pivot door.

A manufacturing process is provided during which a thrust reverser cascade is formed for an aircraft propulsion system. During the formation of the thrust reverser cascade, a first panel of material is stamped into a first corrugated body. A second panel of material is stamped into a second corrugated body. The first corrugated body is bonded to the second corrugated body.

A manufacturing process is provided during which a thrust reverser cascade is formed for an aircraft propulsion system. During the formation of the thrust reverser cascade, a first panel of material is stamped into a first corrugated body. A second panel of material is stamped into a second corrugated body. The first corrugated body is bonded to the second corrugated body.

An exhaust nozzle of a gas turbine engine which includes a nozzle wall, the nozzle wall including an upstream, fixed structure and a downstream, translatable structure that is translatable relative to the fixed structure, a flow channel which is limited radially outwards by the nozzle wall, a centerbody arranged in the flow channel, at least one strut connecting the centerbody to the nozzle wall, a thrust reverser unit that comprises blocking doors, a first actuation system for deployment of the blocking doors into a deployed position for thrust reversal, and a second actuation system for translating the translatable structure between a stowed, upstream position and a fully deployed, downstream position. It is provided that the at least one strut is connected to the fixed structure, that the blocking doors are connected to the translatable structure, and that the first actuation system and the second actuation system are independent actuation systems.

An exhaust nozzle of a gas turbine engine which includes a nozzle wall, the nozzle wall including an upstream, fixed structure and a downstream, translatable structure that is translatable relative to the fixed structure, a flow channel which is limited radially outwards by the nozzle wall, a centerbody arranged in the flow channel, at least one strut connecting the centerbody to the nozzle wall, a thrust reverser unit that comprises blocking doors, a first actuation system for deployment of the blocking doors into a deployed position for thrust reversal, and a second actuation system for translating the translatable structure between a stowed, upstream position and a fully deployed, downstream position. It is provided that the at least one strut is connected to the fixed structure, that the blocking doors are connected to the translatable structure, and that the first actuation system and the second actuation system are independent actuation systems.