Abstract: A plurality of circumferentially displaced hollow members are positioned between an outer bypass duct and the center body of the core engine. Each of the hollow members is open at the radially outward end thereof for receiving relatively cool gas from the bypass duct. Each hollow member is formed with an opening in the side thereof extending substantially the full length of the hollow member near the trailing edge thereof for discharging bypass gas from the bypass duct in a direction facilitating thorough mixing of the bypass gas and core gases. A pivoted vane is provided in this opening of each of the hollow members and these vanes are controlled to vary the airflow through the aforementioned openings. Radially extending spraybars or fuel rods are provided within each hollow member adjacent opposite sides thereof so as to be cooled by the bypass air flowing through the hollow member.

Abstract: A gas turbine engine actuation system for simultaneously controlling the flow areas defined by two generally coannular ducts, each duct terminating in a nozzle of the variable flap variety. A bell crank pivotable about an axis on the outer (secondary) nozzle is link-connected to the inner (primary) nozzle and also to a translatable actuation ring. The geometry of the flaps, link and bell crank is such that when the secondary nozzle is positioned by the ring and bell crank, the movement thereof is transferred to the primary nozzle to modulate the throat areas defined thereby. Where the secondary (supersonic) nozzle is of the divergent variety extending downstream of the primary nozzle so as to provide a common expansion surface and exit area, a link connection between one of the secondary nozzle flaps and the actuation ring causes simultaneous exit area and throat area modulation in a predetermined relationship.

Abstract: A propulsion nozzle having a substantially axial nozzle shroud and an articulated plug mounted in spacial relation therewith to form a motive fluid flow path having a throat therebetween. The plug is articulative to permit the throat of the nozzle to be disposed, as required, in a position at the downstream end of the shroud or at a position upstream of the downstream end without translating either the shroud or the plug.