Spirit Aerosystems, Inc.

Spirit Areosystems, Inc.

Michael Patrick Urban

John Michael Welch

Henry Arnold Schaefer

Matthew Tymes

Thomas Scott

An aircraft nacelle comprising an outer cowl having an inner wall and an outer wall surrounding the inner wall. The inner wall may have an inner opening formed therethrough and the outer wall may have an outer opening formed therethrough at an aft end of the nacelle. The nacelle may further comprise a translating panel configured to cover the inner and outer openings in a stowed position and to translate aft to a deployed position. The translating panel may be fixed to cascade guide vane panels which rest between the inner and outer wall in the stowed position and are exposed to airflow via the inner and outer openings when translated aft to the deployed position, thereby increasing a nozzle area of the nacelle. Guide vanes of the cascade guide vane panels are angled slightly aftward to direct the nacelle's airflow outward and aftward.

Cascade-style variable area fan duct nozzle

A method and aerodynamic device for modifying at least one vane of a cascade thrust reverser. One or more of the aerodynamic devices may be formed and attached to forward-facing surfaces of vanes of the thrust reverser. The aerodynamic device may include a first side shaped to rest flush against at least a portion of the forward-facing surface of the vane, a second side opposite of the first side, a ledge portion protruding from the first side and configured to rest flush against a blunt leading edge of the vane, a rounded first end portion extending from the ledge portion to the second side of the aerodynamic device, and a second end opposite of the first end portion at which the first side and the second side converge. The aerodynamic device changes the size and contour of airflow channels between the vanes, increase the efficiency of the thrust reverser.

Aerodynamic device for thrust reverser cascades

Latch beams and hinge beams of an aircraft thrust reverser and a method for manufacturing the beams. The latch and hinge beams may comprise a plurality of hollow composite tubes joined with a plurality of machined metal fittings in alternating succession. The metal fittings may comprise at least one of hinge fittings and latching fittings. The latch and hinge beams may further comprise slider tracks configured to slidably attach to a translating sleeve of the thrust reverser. The hinge beams may each be rotatably attached to an engine strut or pylon of the aircraft, and the latch beams may each be mechanically latched with each other. Each of the latch and hinge beams may also be fixedly attached to an inner engine cowling of the thrust reverser.

Hybrid beam for a thrust reverser unit

A hybrid torque box comprising a plurality of composite tubes and metal fittings attached together in alternating succession and configured to attach a thrust reverser to an engine fan case of an aircraft. The hybrid torque box may be substantially hollow and may comprise two V-blades for attaching the torque box to the engine fan case. The hybrid torque box may also be attached to or integral with a bull nose fairing configured for attachment with a cascade of the thrust reverser. Furthermore, the hybrid torque box may comprise and/or attach to a cowl interface flange configured for interfacing with an outer cowl of the thrust reverser.

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Wichita, KS, United States of America

Michael Patrick Urban