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1. 发明授权

US5176323A Reduced weight nozzle actuation mechanism 失效
标题翻译：减少重量喷嘴启动机制
公开(公告)号：US5176323A
公开(公告)日：1993-01-05
申请号：US685096
申请日：1991-04-15
申请人： Dudley O. Nash
发明人： Dudley O. Nash
IPC分类号： F02K1/08 , F02K1/12 , F02K1/15
CPC分类号： F02K1/12 , F02K1/1292 , F02K1/15 , Y02T50/671
摘要： A fluid supply and synchronizing mechanism are provided for a jet engine exhaust nozzle. The exhaust nozzle has flaps which are moved by flap mounted actuators which move with the flaps. The fluid supply includes a supply tube, a return tube and a strut for each actuator. The two tubes and strut are connected to each actuator for movement with the actuator. The strut prevents flexing of the tubes during movement. The synchronizing mechanism interconnects the flaps so that movement of any one flap is transmitted to all other flaps thereby retaining nozzle symmetry.

2. 发明授权

US4000612A Cooling system for a thrust vectoring gas turbine engine exhaust system 失效
标题翻译：推力矢量化燃气轮机发动机排气系统的冷却系统
公开(公告)号：US4000612A
公开(公告)日：1977-01-04
申请号：US599644
申请日：1975-07-28
申请人： Thomas G. Wakeman , Dudley O. Nash
发明人： Thomas G. Wakeman , Dudley O. Nash
IPC分类号： F02K1/12 , B64D33/08 , F02K1/00 , F02K1/60 , F02K1/78 , F02K1/20 , F02K11/04
CPC分类号： F02K1/006 , Y02T50/671
摘要： A thrust vectoring gas turbine engine exhaust nozzle is provided with a variable area flow path wherein cooling of the stationary flow path side walls is partially obtained by the film cooling technique. Regulating means, such as a valve, is provided to control the pressure drop of the cooling fluid across the walls as a function of nozzle flow path area, thus optimizing the coolant flow rate as a function of flow path area. Where a rotating bonnet-type deflector is employed to divert the exhaust stream downward to obtain a vertical take-off and landing capability, a system is provided to cool the deflector walls by both the impingement and convection cooling techniques. A favorable pressure gradient for the cooling fluid is obtained by exhausting the cooling fluid to ambient pressure whenever the deflector is deployed. Another valve is provided to regulate the flow of coolant to an expansion flap when the deflector is in its stowed position external to the flow path.
摘要翻译：推力矢量化燃气轮机发动机排气喷嘴设置有可变区域流动路径，其中通过膜冷却技术部分地获得固定流路侧壁的冷却。提供诸如阀门的调节装置，以便根据喷嘴流动路径面积来控制冷却流体穿过壁的压降，从而优化作为流路面积的函数的冷却剂流量。在使用旋转阀盖型偏转器将排气流向下转移以获得垂直起飞和着陆能力的情况下，提供系统以通过冲击和对流冷却技术来冷却偏转器壁。每当偏转器被展开时，通过将冷却流体排放到环境压力来获得冷却流体的有利的压力梯度。另一个阀被设置成当偏转器处于其位于流动路径外部的收起位置时调节冷却剂到膨胀瓣的流动。

3. 发明授权

US3979067A Actuating means for a thrust vectoring gas turbine engine exhaust nozzle 失效
标题翻译：用于推力矢量燃气涡轮发动机排气喷嘴的致动装置
公开(公告)号：US3979067A
公开(公告)日：1976-09-07
申请号：US572341
申请日：1975-04-28
申请人： Dudley O. Nash
发明人： Dudley O. Nash
IPC分类号： F02K1/06 , B64C15/02 , B64D33/00 , F02K1/00 , F02K1/11 , F02K1/12 , F02K1/78 , F02K1/20
CPC分类号： F02K1/006 , F02K1/1215 , Y02T50/671
摘要： A thrust vectoring gas turbine exhaust nozzle is provided with cooperating variable internal coverging-diverging flaps to provide nozzle flow path area control. A vertical take-off and landing capability is obtained by deployment of a rotating bonnet-type deflector which diverts the exhaust stream downward around one side of the exhaust nozzle. Actuating means are provided to rotate the nozzle throat simultaneously with deflector rotation to produce efficient turning of the exhaust stream in the lift mode. The actuation means also simultaneously controls the nozzle flow path area and external exhaust expansion in the cruise mode.
摘要翻译：推力矢量式燃气轮机排气喷嘴配有可配合的可变内部覆盖 - 发散翼片，以提供喷嘴流路面积控制。通过部署旋转阀盖型偏转器获得垂直起降能力，该导流器将废气流向下排放到排气喷嘴的一侧。提供致动装置以同时具有偏转器旋转来旋转喷嘴喉部，以在提升模式下有效地转动废气流。致动装置还同时控制巡航模式下的喷嘴流路面积和外部排气膨胀。

4. 发明授权

US5101624A Exhaust nozzle hinge 失效
标题翻译：排气喷嘴铰链
公开(公告)号：US5101624A
公开(公告)日：1992-04-07
申请号：US724490
申请日：1991-06-27
申请人： Dudley O. Nash , Stephen J. Szpunar
发明人： Dudley O. Nash , Stephen J. Szpunar
IPC分类号： F02K1/12 , F02K1/80
CPC分类号： F02K1/805 , F02K1/12
摘要： A hinge for pivotably connecting upstream and downstream wall sections of an exhaust nozzle of a gas turbine engine. Each wall section includes a liner spaced from the interior surface of the wall section to define respective first and second cooling air flow passages therebetween. One of the wall sections includes a curved end portion and the hinge includes a leaf seal which extends from the other wall section and biases against the curved end portion to form an air tight seal and define, at least in part, a plenum at the hinged connection of the wall sections. The plenum provides an air flow communication path between the first and second cooling air flow passages to transfer cooling air from the air flow passage of the upstream wall section to the air flow passage of the downstream wall section to thereby increase the efficiency of cooling of each of the wall sections.
摘要翻译：用于可旋转地连接燃气涡轮发动机的排气喷嘴的上游和下游壁部分的铰链。每个壁部分包括与壁部分的内表面间隔开的衬垫，以在它们之间限定相应的第一和第二冷却空气流动通道。一个壁部分包括弯曲的端部部分，并且铰链包括叶密封件，该叶片密封件从另一个壁部分延伸并且偏压在弯曲的端部部分上以形成气密密封，并且至少部分地限定铰接的连接壁部分。增压室在第一和第二冷却空气流动通道之间提供空气流动连通路径，以将冷却空气从上游壁部分的空气流动通道传递到下游壁部分的空气流动通道，从而提高每个的墙段。

5. 发明授权

US4920742A Heat shield for gas turbine engine frame 失效
标题翻译：燃气涡轮发动机架的隔热罩
公开(公告)号：US4920742A
公开(公告)日：1990-05-01
申请号：US200333
申请日：1988-05-31
申请人： Dudley O. Nash , Ronald E. Quinn
发明人： Dudley O. Nash , Ronald E. Quinn
IPC分类号： F02C7/20 , F01D25/16 , F02K1/82 , F23R3/00
CPC分类号： F02K1/82 , F01D25/162 , F23R3/002 , F23R2900/00005 , Y02T50/671
摘要： A heat shield assembly for use in a turbine engine frame includes inner and outer flowpath liners for shielding the inner and outer turbine frame members from hot exhaust gasses flowing through the turbine engine. The flowpath liners are supported on the turbine frame members with a support structure which allows the flowpath liners to freely expand and contract under thermally induced forces. In this manner thermal stresses are minimized. The flowpath liner support structure also provides uniform support for the flowpath liners and allows for the even and unobstructed flow of cooling air through the flowpath liners.

6. 发明授权

US4901527A Low turbulence flame holder mount 失效
标题翻译：低湍流火焰支架安装
公开(公告)号：US4901527A
公开(公告)日：1990-02-20
申请号：US156876
申请日：1988-02-18
申请人： Dudley O. Nash , James R. Reigel , Frederick J. Stine
发明人： Dudley O. Nash , James R. Reigel , Frederick J. Stine
IPC分类号： F23R3/20
CPC分类号： F23R3/20
摘要： A low turbulence, close-coupled mounting structure for a flame holder disposed in an afterburner section of a gas turbine engine is provided. The afterburner section has a plurality of angularly spaced, radially extending fuel injection nozzles, with a fairing surrounding each nozzle to form open ended heat shields about the nozzles. A flame holder having a first cross-sectional configuration is disposed in recessed portions formed in the fairings surrounding the nozzles. The cross-sectional configuration of the recessed portions is configured to substantially conform to a portion of the cross-section of the flame holder such that the flame holder is recessed into the fairings when mounted thereon, thus eliminating outward projections at the connection of the flame holder and fairings. The flame holders are secured in the recessed portions by pins extending through aligned apertures in the skirts of the flame holder.

7. 发明授权

US4409788A Actuation system for use on a gas turbine engine 失效
标题翻译：用于燃气涡轮发动机的致动系统
公开(公告)号：US4409788A
公开(公告)日：1983-10-18
申请号：US252687
申请日：1981-04-09
申请人： Dudley O. Nash , Thomas S. Clayton
发明人： Dudley O. Nash , Thomas S. Clayton
IPC分类号： F02K1/82 , F02K3/075
CPC分类号： F02K1/822 , F02K3/075 , Y02T50/671 , Y02T50/675
摘要： An actuation system is provided for transferring axial motion into an interior of a gas turbine engine at a number of locations around an outer casing of the engine, with one synchronous movement. An external hydraulic actuator activates the system by rotating one outer crank which, in turn, rotates a single outer yoke. The yoke is mechanically linked to a plurality of crankshafts that extend through the outer casing of the engine and transmit rotational movement into the engine interior. The crankshafts are linked inside the engine to an annular sliding member causing that member to move axially. In one embodiment of this invention, the actuation system is used to open and close a slide valve between inner and outer bypass ducts of a variable cycle aircraft engine.
摘要翻译：提供致动系统，用于通过一次同步运动将轴向运动传递到在发动机的外壳周围的多个位置处的燃气涡轮发动机的内部。外部液压执行器通过旋转一个外部曲柄来启动系统，外部曲柄又旋转单个外部轭。轭架与多个曲轴机械连接，多个曲轴延伸穿过发动机的外壳并将旋转运动传递到发动机内部。曲轴在发动机内部连接到环形滑动件上，导致该构件轴向移动。在本发明的一个实施例中，致动系统用于在可变循环飞行器发动机的内部和外部旁路管道之间打开和关闭滑阀。

8. 发明授权

US4181260A Hydraulic actuation ring 失效
标题翻译：液压驱动环
公开(公告)号：US4181260A
公开(公告)日：1980-01-01
申请号：US778476
申请日：1977-03-17
申请人： Dudley O. Nash
发明人： Dudley O. Nash
IPC分类号： F02K1/12 , F02K1/15 , B64C15/06
CPC分类号： F02K1/12 , F02K1/15 , Y02T50/671
摘要： A polygonal hydraulic actuation ring is provided for modulating the area of a variable position nozzle. The actuation ring comprises a plurality of actuators arranged end to end in the form of a polygon circumscribing a plurality of pivotable flaps, each of which is acted upon directly by one of the actuators. The actuators are synchronized by the use of gears and helical screws to expand and contract in unison, thereby changing the diameter of the polygonal actuation ring and the exhaust flow path area defined by the flaps. Rod end and head end hydraulic fluid flows are provided to all actuators simultaneously through a system of internal flow passages, and only one rod end supply line and one head end supply line are required for the entire actuation ring. Cooling is provided by an air film flowing over each hydraulic cylinder and by hydraulic fluid recirculation. The sliding joint on each polygonal side is equipped with close fitting rollers arranged to handle moment loading which would result from unbalanced air loading of the flaps, thus protecting the piston rods and seals from damage due to moment loading. The actuation ring is readily adaptable to thrust vectorable nozzles.
摘要翻译：提供多边形液压致动环用于调制可变位置喷嘴的面积。所述致动环包括多个致动器，所述多个致动器以包围多个可枢转翼片的多边形的形式端对端设置，每个翼片由致动器中的一个直接作用。致动器通过使用齿轮和螺旋螺杆来同步，以一致地膨胀和收缩，从而改变多边形致动环的直径和由翼片限定的排气流动路径区域。杆端和头端液压流体通过内部流动通道系统同时提供给所有致动器，并且整个致动环仅需要一个杆端供应管线和一个头端供应管线。通过在每个液压缸上流动的空气膜和通过液压流体再循环来提供冷却。每个多边形侧面上的滑动关节装有紧密配合的滚轮，用于处理由翼片不平衡的空气负载引起的力矩载荷，从而保护活塞杆和密封件免受由于载荷的损害。驱动环容易适应推力可动的喷嘴。

9. 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。

10. 发明授权

US4926633A Coolant pressure regulating apparatus 失效
标题翻译：冷却液压力调节装置
公开(公告)号：US4926633A
公开(公告)日：1990-05-22
申请号：US372416
申请日：1989-06-27
申请人： Dudley O. Nash , Frederick C. Herzner
发明人： Dudley O. Nash , Frederick C. Herzner
IPC分类号： F01D25/12 , F02C7/18 , F02K1/82 , F23R3/06 , F23R3/26
CPC分类号： F02K1/822 , F01D25/12 , F02C7/18 , F23R3/06 , F23R3/26 , Y02T50/671 , Y02T50/675
摘要： A coolant pressure regulating appartus having a predetermined number of coolant pressure regulating valves which rotate against a spring bias to divert coolant flow and excess pressure from the coolant air fan duct into the engine core exhaust flow. The pressure regulator valve regulates the pressure within a closed cavity suppressor to the pressure level within the core without any affect upon the upstream fan duct pressure.
摘要翻译：具有预定数量的冷却剂压力调节阀的冷却剂压力调节阀，其克服弹簧偏压旋转，以将冷却剂流和过冷压从冷却剂空气风扇导管转移到发动机芯排气流中。压力调节阀将闭合的腔体抑制器内的压力调节到芯内的压力水平，而不影响上游风机管道压力。

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