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1. 发明授权

US4000854A Thrust vectorable exhaust nozzle 失效
标题翻译：推力矢量排气喷嘴
公开(公告)号：US4000854A
公开(公告)日：1977-01-04
申请号：US618796
申请日：1975-10-02
申请人： Mieczyslaw Konarski , Dudley O. Nash
发明人： Mieczyslaw Konarski , Dudley O. Nash
IPC分类号： F02K1/06 , B64C15/02 , B64D33/04 , F02K1/00 , F02K1/12 , B64C9/30 , B64C9/38 , B64C15/06
CPC分类号： F02K1/1292 , F02K1/006 , F05D2260/15 , Y02T50/671
摘要： A gas turbine engine flight maneuverable nozzle for installation within an aircraft wing or the like is provided with pivotably connected convergent 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 actuation 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 repositioned 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.
摘要翻译：用于安装在飞行器机翼等内的燃气涡轮发动机飞行机动喷嘴设置有部分地限定排气流流动路径的可枢转地连接的收敛和发散的翼片。可枢转地连接到发散翼的第三挡板部分地限定翼控制表面轮廓。在巡航和飞行机动模式中，致动系统提供收敛和发散翼片的同步运动，以预定关系控制排气流路径喉部和出口的区域。由主执行机构承载的矢量执行器在飞行操纵模式下超越主致动器，并使发散片向下枢转，从而使排气流偏转。同时，控制表面轮廓限定翼片重新定位以增加控制面的外倾度，从而增加升力。通过排气流引起的超级循环的影响，防止与翼部控制面的流动分离。

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