An engine system has a gas generator, a bi-fi wall surrounding at least a portion of the gas generator, a casing surrounding a fan, and the casing having first and second thrust reverser doors which in a deployed position abut each other and the bi-fi wall.

A thrust reverser for a gas turbine engine includes a frame, a first reverser door pivotally mounted to the frame, and a second reverser door pivotally mounted to the first reverser door.

A thrust reverser for a gas turbine engine includes a frame, a first reverser door pivotally mounted to the frame, and a second reverser door pivotally mounted to the first reverser door.

A nacelle comprising a fixed structure with a fixed cowling and a cowling movable in translation between closed and open positions, to open an opening between a duct and the exterior. A blocking door is rotatably movable on the movable cowling between a stowed position and a deployed position. A deployment system comprises an arm with a first end articulated on the blocking door and a second end that bears a stop, a slider fixed to the arm, a linear guide system is fixed on the fixed structure and guides the slide, and a cam. The stop is configured to lie against the cam when the movable cowling reaches an intermediate position from the closed position and to be guided by the cam to drive the rotation of the arm about the slider when the movable cowling moves from the intermediate position to an open position.

A thrust reverser may include a frame, a track disposed on the frame, a carrier operatively coupled to the track, and a first reverser door operatively coupled to the carrier. The first reverser door is movable relative to the frame, wherein the first reverser door is configured to move to a first position in response to the carrier moving with respect to the track in a first direction, and move to a second position in response to the carrier moving with respect to the track in a second direction.

A thrust reverser for an aircraft propulsion unit. The thrust reverser includes three gates that can be deployed downstream of an outlet section of the propulsion unit. The device increases the possibilities for installation of the reverser, in particular when a tail assembly extends in line with the propulsion unit.

Aspects of the disclosure regard an exhaust nozzle of a gas turbine engine which includes an outer nozzle wall, a flow channel, a centerbody arranged in the flow channel, at least two struts connecting the centerbody to the nozzle wall, a thrust reverser unit, and a plurality of actuators, wherein each actuator is associated with a strut for displacing the strut in the axial direction. The struts are connected to a structure of the outer nozzle wall that forms part of the thrust reverser unit. For allowing axial relative movement between the struts and the outer nozzle wall, each strut includes a sliding element extending radially from the radial outer end of the strut, wherein the sliding element is arranged in a receiving slot that extends in the axial direction in the nozzle wall. It is provided that the sliding element comprises an interaction structure that interacts with one of the actuators for effecting relative axial movement between the strut and the nozzle wall.

A thrust reverser for an aircraft includes a jetpipe and a thrust reverser door. The thrust reverser door has an aft end, a forward end, and an interior surface facing radially inward. The interior surface defines a continuous profile with a downstream nozzle portion directly adjacent to the aft end, a concave portion directly adjacent to the downstream nozzle portion, and a convex portion directly adjacent to the forward end and adjacent to the concave portion.

A closing system that includes a closing actuator for doors of a thrust reverser, two sliding members, and a detection device. The closing actuator includes two first connecting rods. Each first connecting rod is configured to be connected to a first lateral edge of each door. The closing actuator is arranged to move each door at least towards the direct jet position. Each sliding member carries a second connecting rod configured to be connected to a second lateral edge of each door. The second connecting rods are arranged to be driven by the doors when the closing actuator moves the doors towards the direct jet position so as to displace the two sliding members. The detection device detects a defect of one of the first and second connecting rods. The detection device is configured to detect the relative position of the two sliding members in the direct jet position.

A closing system that includes a closing actuator for doors of a thrust reverser, two sliding members, and a detection device. The closing actuator includes two first connecting rods. Each first connecting rod is configured to be connected to a first lateral edge of each door. The closing actuator is arranged to move each door at least towards the direct jet position. Each sliding member carries a second connecting rod configured to be connected to a second lateral edge of each door. The second connecting rods are arranged to be driven by the doors when the closing actuator moves the doors towards the direct jet position so as to displace the two sliding members. The detection device detects a defect of one of the first and second connecting rods. The detection device is configured to detect the relative position of the two sliding members in the direct jet position.