A nacelle for a jet engine having a selectively operated reverse thruster which redirects air flow to a cascade during a reverse thrust operation, the nacelle including a fancowl panel configured as a stationary partial cover for a jet engine; and a translating cowl panel configured to move transversely during a reverse thrust operation so as to expose a cascade for emitting reverse thrust airflow. In exemplary embodiments, a moveable automatic translating panel, or a rotatable hinge panel, or an extension portion of the fancowl is used to preserve clearance with an aircraft wing in a nacelle clearance area.

A thrust reverser door includes a backskin including an interior surface and an exterior loft surface. The thrust reverser door further includes a cover plate including a cover plate body having a first side and a second side opposite the first side. The thrust reverser door further includes a grid structure mounted to the second side of the cover plate body and the interior surface of the backskin.

A thrust reverser door includes a backskin including an interior surface and an exterior loft surface. The thrust reverser door further includes a cover plate including a cover plate body having a first side and a second side opposite the first side. The thrust reverser door further includes a grid structure mounted to the second side of the cover plate body and the interior surface of the backskin.

A blocker door assembly for use in a gas turbine includes a panel, a core integrally formed with the panel, and a plurality of mounting structures extending from at least one of the panel and the core. The plurality of mounting structures are integrally formed with the core and the panel such that the panel, the core, and the mounting structures are co-molded from a thermoplastic material.

A blocker door assembly for use in a gas turbine includes a panel, a core integrally formed with the panel, and a plurality of mounting structures extending from at least one of the panel and the core. The plurality of mounting structures are integrally formed with the core and the panel such that the panel, the core, and the mounting structures are co-molded from a thermoplastic material.

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.

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.

A thrust reverser includes a frame having a longitudinal axis, a first reverser door pivotally mounted to the frame, a second reverser door pivotally mounted to the first reverser door, a crank pivotally mounted to the frame, a first link connecting the crank to the first reverser door, and a second link connecting the crank to the second reverser door. In various embodiments, both the first reverser door and the second reverser door are driven by a single actuator.

A thrust reverser includes a frame having a longitudinal axis, a first reverser door pivotally mounted to the frame, a second reverser door pivotally mounted to the first reverser door, a crank pivotally mounted to the frame, a first link connecting the crank to the first reverser door, and a second link connecting the crank to the second reverser door. In various embodiments, both the first reverser door and the second reverser door are driven by a single actuator.

An engine including a motor and a nacelle and a duct between the nacelle and the motor. The nacelle includes a fixed structure, a mobile assembly that is mobile between an advanced position and a retracted position to define a window between the duct and the outside, and a plurality of blades that are mobile in rotation between a stowed position and a deployed position, each one extending on either side of its axis of rotation with a first arm and a second arm. In the stowed position, the first arm is outside the duct and the second arm is inside the nacelle, and where, in the deployed position, the first arm is across the duct and the second arm projects out of the nacelle. With such blades, the flow of air is optimally directed towards the front without it being necessary to provide cascades.