Abstract: A two-dimensional thrust vectoring nozzle (10) includes aftward divergent flaps (26, 28) positioned by a linkage assembly (38). The assembly (38) includes a linear track (42) pivotable about a transverse axis (44) for positioning a scissors linkage pivot (52) to selectively vary the divergence angle and vertical thrust vector of the nozzle (10).

Abstract: First and second flaps (10, 12) are joined at a hinge joint formed by a hollow hinge pin (22) passing through alternating lug extensions (18, 20) of the first and second flaps (10, 12). A plurality of flow openings (24) in the hollow hinge pin (22) are provided for establishing fluid communication between the interior of the first flap (10) and the interior of the second flap (12).

Abstract: A cooled liner assembly for a nozzle has a plurality of longitudinally aligned support hinges secured to a support plate. A thin plate liner of arcuate shape is hinged to the support hinges with cooling air supplied between the liner and support plate. The liner is lightweight resisting the differential pressure of 25 psi in membrane hoop stresses, with components experiencing bending moments remote from the hot gas inside the nozzle.

Abstract: A convergent/divergent gas turbine engine exhaust nozzle having reverse thrust capability includes a door which blocks a reverse flow outlet port when the nozzle convergent flap is in any forward thrust operating mode. The door is coupled to the convergent nozzle flap such that it opens as the convergent nozzle flap moves to a reverse thrust position and the flap directs the exhaust gases through the reverser outlet.

Abstract: A two-dimensional variable area convergent/divergent exhaust nozzle having the capability for wide throat area variation includes upper and lower spaced apart flap means. The upper flap means comprises an upstream converging flap having its rear edge hinged to the forward edge of a downstream diverging flap, wherein the nozzle is movable between maximum and minimum throat area positions by actuation means which includes guide means, such as cam tracks, for guiding the forward edge of the upstream flap to move downstream while simultaneously constraining both the upper flap means hinge joint and the rear edge of the diverging flap to move both downstream and closer to the engine axis. This type of motion permits large changes in throat area with minimal increase in the slope of the diverging flap permitting use of a shorter diverging flap. Preferably the forward and rearward edge of the converging flap move along circular arcs having the same center in order to minimize moments on the flap.

Abstract: A seal plate rests along the edge of a moveable flap surface and extends outwardly therefrom into contact with a stationary wall to seal the gap between the flap edge and the wall. The seal plate is hinged for rotation to one end of a pivotable support link which is hinged at its other end to the flap. The gas pressure load on the seal plate presses it against the flap surface and also tends to rotate the support link to press the outward edge of the seal plate against the stationary wall.

Abstract: A three dimensional converging/diverging nozzle assembly includes upstream converging nozzle flaps pivotally connected to an inner unison ring, diverging nozzle flaps pivotally connected to the downstream ends of the converging flaps, and external connectors pivotally connected at their downstream ends to the downstream ends of the diverging flaps and at their upstream ends to an outer unison ring. The outer unison ring is interconnected to the inner unison ring such that axial translation of either unison ring results in axial translation of the other unison ring, but at a different rate of speed. In one embodiment the unison rings are interconnected by a cam track and linkage arrangement.

Abstract: The upstream ends of the flaps of a variable area nozzle are pivotally connected to an axially translatable unison ring. Apparatus is associated with the flaps to cause the flaps to rotate as the unison ring is translated to vary the area of the nozzle. The unison ring includes a balance surface fixed relative thereto which is subject to a net pressure load in the downstream direction thereby reducing the force which an actuator must exert to move the unison ring or to hold the unison ring in fixed position. Preferably the balance surface is an annular surface which extends radially inwardly and has a radially inner edge to which the upstream ends of the flaps are pivotally attached.

Abstract: A gas turbine engine exhaust nozzle assembly having vertical thrust capability comprises a two-dimensional converging/diverging nozzle and a veer flap for forward thrust operation and a rotatable hood type deflector for vertical thrust operation, wherein the forward edge of the veer flap is attached to the downstream edge of the deflector hood. During forward thrust operation, the hood and rear edge of the divergent flap portion of the converging/diverging nozzle are moved synchronously to maintain the rear edge of the divergent flap portion and the front edge of the veer flap adjacent each other such that the veer flap is aligned with and acts as an extension of the divergent flap portion of the converging/diverging nozzle. Preferably, means are provided to independently trim the orientation of the veer flap to maximize thrust. A movable ventral flap defines the nozzle throat between itself and the deflector hood when the hood is deployed for vertical thrust.

Abstract: A flow diverter located in a cylindrical duct has two opposite side sections of the duct formed of semi-circular cross-section movable between an open position for flow through said cylindrical duct and a closed position where the side sections cooperate to block flow through said duct, said side sections have the same width and both have ends of semi-circular shape; said semi-circular shape having a diameter equal to the width of the section. Pivots extend outwardly from each end of each section and are mounted for pivotal movement in a mounting structure fixed externally of said duct. Said opposite side sections have a cooling liner which has an overlapping sealing arrangement.

Abstract: An exhaust nozzle has main flaps with seals therebetween. Each flap and seal is constructed having inner and outer members which cooperate to form a liner for cooling air therethrough which extends substantially around the entire circumference of the liner. This arrangement provides a construction for cooling airflow which is compatible with nozzle diameter change. While the seal basically floats, it is maintained in place longitudinally and circumferentially so that leakage does not occur between the flaps. The coolant flows through the flaps and seals of the convergent section of the nozzle and is directed over the divergent section of the nozzle.

Abstract: A high strength, lightweight exhaust nozzle flap assembly (22) includes a first flap (26) with integral sidewall disks (34, 35) for imparting moments (72, 73) to a cantilevered flap (26) for reducing the mid span deflection of the flap (26) due to internal nozzle static gas pressure. A second flap (42) is also provided with thrust bearings (80, 81) for establishing a combined structure with further resistance to deflection.