Aircraft engine nozzle
AssigneeThe Boeing Company
InventorDean Leon Parham
Life of this patent
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Abstract
An apparatus and method comprising a fan nozzle sleeve, a plurality of slider mechanisms, and a fan nozzle actuator system. A flow of gases generated by an engine moves through and exits the engine at an aft end of the fan nozzle sleeve. The plurality of slider mechanisms is configured to connect the fan nozzle sleeve to a translating sleeve for a thrust reverser for the engine. The fan nozzle actuator system is configured to activate the plurality of slider mechanisms to move the fan nozzle sleeve in an aft direction to change a direction of the flow of gases exiting the engine at the aft end of the fan nozzle sleeve.
Claims12
An apparatus comprising:
- a fan nozzle sleeve, wherein a flow of gases generated by an engine moves through the engine and exits the engine at an aft end of the fan nozzle sleeve;
- a plurality of slider mechanisms configured to connect the fan nozzle sleeve to a translating sleeve for a thrust reverser for the engine;
- and
- a fan nozzle actuator system configured to activate the plurality of slider mechanisms to move the fan nozzle sleeve in an aft direction and rotate the fan nozzle sleeve to change a direction of the flow of gases exiting the fan nozzle sleeve, and wherein moving the fan nozzle sleeve in the aft direction moves the fan nozzle sleeve axially along a longitudinal axis through a center of the engine and radially away from the longitudinal axis through the center of the engine.
Dependencies are inferred from the claim text.