A system and method for an improved thrust reverser is provided. The provided thrust reverser employs hidden linkage assemblies to decrease drag in the engine exhaust flow and increase turbine engine performance. The hidden linkage assemblies are placed in a space between the blocker door and the transcowl, thereby not affecting the engine exhaust flow.

A system and method for an improved thrust reverser is provided. The provided thrust reverser employs hidden linkage assemblies to decrease drag in the engine exhaust flow and increase turbine engine performance. The hidden linkage assemblies are placed in a space between the blocker door and the transcowl, thereby not affecting the engine exhaust flow.

A thrust reverser may comprise a frame, a first reverser door being movable relative to the frame, and a second reverser door being movable relative to the frame and rotationally movable relative to the first reverser door via a first pivot point, the first pivot point being movable relative to the frame via a first link rotationally mounted to the frame via a second pivot point.

A thrust reverser may comprise a frame, a first reverser door being movable relative to the frame, and a second reverser door being movable relative to the frame and rotationally movable relative to the first reverser door via a first pivot point, the first pivot point being movable relative to the frame via a first link rotationally mounted to the frame via a second pivot point.

A thrust reverser system for a gas turbine engine includes a transcowl movable between a stowed position, a deployed position and a partially deployed position between the stowed position and the deployed position by at least one actuator. The system includes a temperature sensor and at least one resistance sensor. The thrust reverser system includes a controller, having a processor, that: outputs one or more control signals to move the transcowl to the partially deployed position; determines whether a temperature associated with the transcowl exceeds a temperature threshold; outputs one or more control signals to move the transcowl from the partially deployed position to the stowed position; determines whether the transcowl has encountered resistance; and based on the determination, outputs one or more control signals to stop a movement of the transcowl and outputs the one or more control signals to move the transcowl to the partially deployed position.

An active locking system of a movable element for a thrust reverser of an aircraft nacelle includes an active locking device of the movable element, movable between a locking position and an unlocking position, an actuator of the locking device controlled by a command for actuating the locking device, a blocking device for blocking the locking device in the unlocked position, movable between a blocking position and an unblocking position, and a device for displacing the blocking device. The actuation command controls the closure of the movable element, and the device for displacing the blocking device displaces the blocking device in the unblocking position when the movable element is at a predetermined position.

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 for a gas turbine engine may comprise a frame, a first reverser door pivotally mounted to the frame at a first pivot point, a second reverser door pivotally mounted to the frame at a second pivot point, a first nacelle defining a first trailing edge of the gas turbine engine coupled between the frame and the first reverser door, and a second nacelle defining a second trailing edge of the gas turbine engine coupled between the frame and the second reverser door. The first nacelle and the second nacelle translate in an aft and radial outward direction relative to the gas turbine engine in response to the thrust reverser moving to a deployed position.

A thrust reverser for a gas turbine engine may comprise a frame, a first reverser door pivotally mounted to the frame at a first pivot point, a second reverser door pivotally mounted to the frame at a second pivot point, a first nacelle defining a first trailing edge of the gas turbine engine coupled between the frame and the first reverser door, and a second nacelle defining a second trailing edge of the gas turbine engine coupled between the frame and the second reverser door. The first nacelle and the second nacelle translate in an aft and radial outward direction relative to the gas turbine engine in response to the thrust reverser moving to a deployed position.

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.