Abstract: A translating sleeve structure for a cascade type thrust reverser system for controlling fan air for a turbofan aircraft gas turbine jet engine, such translating sleeve having a plurality of circumferentially arranged spaced blocker doors, each of which is hingedly connected to a door receptacle bonded into a single layer honeycomb panel inner wall of the sleeve at a longitudinal position which is aft of bleed ports positioned in the core cowl of the engine for periodically expelling gases from the engine at elevated temperatures and pressures. Positioning such blocker doors aft of the bleed ports precludes injury to the blocker doors or to their hinged connections to the core cowl and permits smaller uniformly sized doors to be used.

Abstract: A novel pivoting door thrust reverser which provides a nozzle for the exhaust of a bypass engine that ensures a smooth continuous flow path for the exhaust without leakage around the pivoted upper and lower reverser doors. The upper reverser door is provided with a pair of biased cooperating crescent shaped kicker members that are biased outwardly in a controlled movement when the doors are deployed to deflect the upper portion of the reversed exhaust efflux forwardly in a predetermined direction to avoid interference with the control surfaces of the aircraft. The lower reverser door is provided with pivoted splitter plates that are biased outwardly when the door is deployed to abut and form a unitary splitter element that divides the lower exhaust efflux into two portions that are directed forwardly and away from the inlet of the engine to preclude foreign object damage to the engine.

Abstract: A structure to provide a variable nozzle for the fan air flow of a turbofan aircraft gas turbine engine with the nozzle being defined by the exit throat area defined by the aft edge of a trailing edge portion of the fan cowl and the core engine housing. A trailing edge cowl portion is slidably positioned in a rearwardly opening annular cavity in the aft end of the fan cowl for reciprocal axial translation between a deployed position to provide an enlarged exit throat area to provide enhanced performance of the aircraft engine during take off and climb to a cruising altitude and a stowed position to provide an optimum exit throat area for cruise condition of the engine. The trailing edge portion is sealably secured within the core cowl cavity to preclude any air leakage from the fan air stream of the fan duct around the trailing edge portion.

Abstract: A pivot door type aircraft turbine engine thrust reverser which includes a pair of pivoting panels on the inner side of the door. The panels are positioned alongside the door actuation mechanism. The panels form a flush surface along the fan duct flow path when stowed during normal engine operation in flight. When the door is deployed in thrust reversing mode, one end of the door moves to at least partially block airflow through the duct and divert it out along the door through an opening uncovered by door deployment. During door deployment, a linkage moves the panels toward the outer surface of the door, exposing a door deflector plate to the airflow. Air flows along the door, then along the panel, out through the opening, then impacts the deflector plate which deflects the airflow in the reverse direction.

Abstract: A cascade assembly for directing the gases externally of a jet aircraft engine in a forwardly direction when the engine is in a gas reversing mode. The cascade assembly comprises a plurality of cascade panel sections positioned in a side by side relationship over an opening in the engine nacelle. The panel sections have a plurality of spaced apart curvilinear vanes angled from the centerline of the engine. Longitudinal beams are positioned over the longitudinal edges and adjacent ends of at least one cascade panel section to secure it in place. The beam is "T" configured in the cross-section with feet or pads on each end to overlay the longitudinal outer edge and adjacent end surfaces of the cascade panel section or sections which it is securing in place. The pads or feet on the beam ends include apertures therethrough for securing the beams to aircraft structure. Both the cascade panel sections and beams are constructed of molded plastic or cured composite materials.