A pre-exit thrust reverser includes an upper reverser door pivotally mounted to a frame and having an upper trailing edge, a lower reverser door pivotally mounted to the frame and having a lower trailing edge and an exhaust duct fixedly mounted to the frame. The upper trailing edge is configured to extend aft of the lower trailing edge when the thrust reverser assumes a deployed state.

A propulsion system includes a bypass turbine engine and a pylon. The turbine engine includes an engine, two internal cowls, two outer cowls, a first lock for locking the internal cowls to the engine, cascades of vanes fixed to the outer cowl via hooping, wherein the outer cowls are movable in translation with respect to the engine, in which each outer cowl is able to slide parallel to a direction of translation on an internal cowl via a top guideway connection and a bottom guideway connection, and in which each outer cowl is mounted with the ability to slide parallel to the direction of translation on the pylon via an upper guideway connection. The propulsion system makes it possible during maintenance operations to move the outer cowl and the internal fixed structure towards the rear and therefore away from the front cowls to get at the engine.

An apparatus is provided for an aircraft propulsion system. This apparatus includes a thrust reverser cascade extending longitudinally between a cascade forward end and a cascade aft end. The thrust reverser cascade extends laterally between a cascade first side and a cascade second side. The thrust reverser cascade extends radially between a cascade inner face and a cascade outer face. The thrust reverser cascade includes a plurality of vanes and a wall. The vanes are arranged in a longitudinally extending array along the cascade inner face. The vanes include a first vane and a second vane. The wall is configured to block gas flow radially through the thrust reverser cascade between the first vane and the second vane.

An apparatus is provided for an aircraft propulsion system. This apparatus includes a thrust reverser cascade extending longitudinally between a cascade forward end and a cascade aft end. The thrust reverser cascade extends laterally between a cascade first side and a cascade second side. The thrust reverser cascade extends radially between a cascade inner face and a cascade outer face. The thrust reverser cascade includes a plurality of vanes and a wall. The vanes are arranged in a longitudinally extending array along the cascade inner face. The vanes include a first vane and a second vane. The wall is configured to block gas flow radially through the thrust reverser cascade between the first vane and the second vane.

A thrust reverser may include a frame, an actuation arrangement, a reverser door pivotally coupled to the frame, and a deployable fairing pivotally coupled to the frame, wherein the deployable fairing is configured to move away from a central axis of the thrust reverser to provide clearance for one of more thrust reverser pivot doors to rotate into a deployed position.

A thrust reverser may include a frame, an actuation arrangement, a reverser door pivotally coupled to the frame, and a deployable fairing pivotally coupled to the frame, wherein the deployable fairing is configured to move away from a central axis of the thrust reverser to provide clearance for one of more thrust reverser pivot doors to rotate into a deployed position.

A thrust reverser for a gas turbine engine includes a reverser door pivotally mounted to a frame, an exhaust duct translationally mounted to the frame and an actuator having an actuator rod connected to the reverser door and to the exhaust duct.

A thrust reverser for a gas turbine engine includes a reverser door pivotally mounted to a frame, an exhaust duct translationally mounted to the frame and an actuator having an actuator rod connected to the reverser door and to the exhaust duct.

A safety maintenance panel for a thrust reverser is provided. The thrust reverser may comprise one or more doors configured to actuate from a closed position to a deployed position. The safety maintenance panel may be located on the thrust reverser. The safety maintenance panel may comprise a safety pin configured to engage the door in the deployed position to at least partially limit movement of the door from the deployed position. In that respect, the safety pin may be inserted into a panel pin hole through the maintenance panel and a door pin hole through the door to lock the door into the deployed position.

A safety maintenance panel for a thrust reverser is provided. The thrust reverser may comprise one or more doors configured to actuate from a closed position to a deployed position. The safety maintenance panel may be located on the thrust reverser. The safety maintenance panel may comprise a safety pin configured to engage the door in the deployed position to at least partially limit movement of the door from the deployed position. In that respect, the safety pin may be inserted into a panel pin hole through the maintenance panel and a door pin hole through the door to lock the door into the deployed position.