Thrust vectorable exhaust nozzle

Details Thrust vectorable exhaust nozzle Thrust vectorable exhaust nozzle

F - Mech Eng,Light,Heat,Weapons

02

K

60/105

F02K 1/00 (2006.01) F02K 1/12 (2006.01)

Patent

CA 1054384

THRUST VECTORABLE EXHAUST NOZZLE Abstract A gas turbine engine flight maneuverable nozzle for installation within an aircraft wing or the like is provided with pivotably connected conver- gent and divergent flaps partially defining an exhaust stream flow path. A third flap, pivotably connected to the divergent flap, partially defines the wing control surface contour. In the cruise and flight maneuver modes, an actua- tion system provides synchronous movement of the convergent and divergent flaps to control, in a predetermined relationship, the areas of the exhaust stream flow path throat and exit. A vectoring actuator, carried by the main actuator, overrides the main actuator in the flight maneuvering mode and causes the divergent flap to pivot downward, thus deflecting the exhaust stream. Simultaneously, the control surface contour defining flap is reposi- tioned to increase the control surface camber thereby increasing lift. Flow separation from the wing control surface is prevented by the effect of super- circulation due to the exhaust stream. Flap actuator forces are reduced by providing the convergent flap with a pressure-balancing feature. Therein one surface of the flap is exposed to pressurized air from the compressor portion of the engine to create a moment about the flap pivot axis which is counter to the moment created by the pressure of the exhaust stream upon the flap exhaust stream flow path defining surface.

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