An aircraft engine exhaust nozzle system having thrust vectoring capability for use in flight path management, for in-flight thrust reversal or modulation, or for thrust reversal during landing; and which includes a variable area nozzle for improved propulsion efficiency. The preferred embodiment utilizes an exhaust passageway having a rectangular nozzle exit area for minimum base area, boattail, and interference drag. An aerodynamically shaped plug is centrally located in the path of the exhaust gases. The portion of the plug extending aft of the nozzle exit plane is used as a thrust vector control means and comprises a pair of oppositely facing surfaces which can be displaced for changing the flow pattern of the exhaust gases, thereby generating a thrust vector for use as a primary flight control in rotating the aircraft about one of its major axes. The oppositely facing surfaces can also be positioned for forward thrust modulation or for full reversal of the thrust vector. A portion of the plug extending forward of the exit plane provides for variable throat area control by displacement of plug surface panels to obtain a desired nozzle throat area and, independently, a passageway shape and exit area for improved propulsion efficiency.
A two dimensional vectoring nozzle assembly has an expandable plug therein including a first pair of panels and a second pair of downstream panels extending between spaced, parallel side walls and wherein a pivoted connection between the first pair of inlet panels and the second pair of downstream panels is located at the nozzle throat and is associated with a mechanism to cause the pivoted connection therebetween to move substantially in a vertical plane at the throat of the nozzle between open and closed positions therein and wherein an exhaust port in the nozzle is selectively opened by a movable door operated between open and closed positions by the mechanism and operative when the expandable nozzle is in its closed position to open the door to concurrently restrict flow through the throat region of the nozzle while opening the exhaust port whereby exhaust flow through the nozzle is directed by the blocking action of the expandable plug from a point upstream thereof through the exhaust opening in the nozzle thereby to produce a thrust vector on the nozzle assembly arranged generally perpendicularly to the flow of gas through the exhaust nozzle during restricted gas flow through the outlet thereof.
This invention relates to a cooling air management system for a movable centerbody having articulating panels located in the two-dimensional exhaust nozzle of a jet engine so that movement of the centerbody and articulating its panels can provide thrust vectoring, variable geometry internal nozzle expansion or other flight control functions. Cooling air supplied from a fan discharge and/or ram air is fed internally of the centerbody to enhance its operation in a hostile environment while assuring sufficient pressure to effectuate cooling throughout the flight envelope of the aircraft, which during different regimes requires different cooling loads.
This invention relates to a seal adapted to prevent leakage at the interface of a movable plug with articulated panels and the side wall of a two-dimensional nozzle for a gas turbine engine. The seal prevents the high pressure cooling air internal of the plug from escaping to the lower pressure exhaust gases and comprises judiciously located dam-like members installed in the vent slots in the side wall fabricated from Finwall.RTM. material which material achieves indirect heat exchange relation and film cooling.
This invention relates to sealing means for a movable centerbody having collapsible panels located in the two-dimensional exhaust nozzle of a jet engine so that movement of the centerbody and collapsing its walls serves to provide thrust vectoring, variable geometry and internal nozzle expansion. Cooling air supplied internally of said centerbody is utilized to pressurize the seal to assure that the jet exhaust does not ingress into the centerbody cavity or cooling air does not indiscriminately egress therefrom.
An exhaust nozzle of a gas turbine engine effective for reducing the emission of infrared radiation and providing an extensive maneuvering capability. The nozzle preferably is of the two-dimensional type and includes an exhaust cowl with a generally rectangular cross-sectional exhaust opening and a plug within the downstream end of the cowl. The plug, which is preferably wedge-shaped, is pivotable about a transverse axis running through the aft portion of the plug by an appropriate means, for example, a cam or a screw jack mechanism. The nozzle can also include blocker doors and louvers for providing thrust reversal.
