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公开(公告)号：US5197694A
公开(公告)日：1993-03-30
申请号：US516015
申请日：1990-04-27
申请人： Dudley O. Nash , Donald F. Keck
发明人： Dudley O. Nash , Donald F. Keck
CPC分类号： B64D33/04 , B64C25/423
摘要： A thrust reverser assembly is disclosed for a wing mounted gas turbine engine exhaust nozzle having an outlet for discharging exhaust gases over a surface of the wing. The assembly in accordance with a preferred embodiment includes a deflector having forward and aft ends, and first and second sides joined together by a base. The deflector is positionable in a stowed position around the exhaust nozzle so that the aft end is aligned generally with the nozzle outlet for allowing substantially unobstructed discharge of exhaust gases therefrom, and in a deployed position for changing direction of exhaust gases for thrust reversal. A pair of bellcranks are positioned adjacent to respective ones of the deflector sides and actuators are povided for rotating the bellcranks for moving the deflector between the stowed and deployed positions. A pair of elongate tracks having rollers slidably positioned therein and being pivotally connected to the deflector are also provided for controlling the angular orienation of the deflector so that the deflector aft end is disposed against the wing surface and the base extends outwardly from the wing surface for deflecting exhaust gases upwardly and out the deflector forward end when the deflector is in the deployed position.
摘要翻译： 公开了一种用于机翼安装的燃气涡轮发动机排气喷嘴的推力反向器组件，其具有用于在机翼的表面上排放废气的出口。 根据优选实施例的组件包括具有前端和后端的偏转器，以及由底座连接在一起的第一和第二侧。 偏转器可定位在排气喷嘴周围的收纳位置，使得后端大体上与喷嘴出口对齐，用于允许基本上不受阻碍地从其排出废气，并且在用于改变排气反转方向的展开位置中用于推力反转。 一对曲拐与相应的偏转器侧相邻定位，致动器用于旋转曲拐，用于在收起位置和展开位置之间移动偏转器。 还提供一对具有可滑动地定位在其中并且可枢转地连接到偏转器的辊的细长轨道，用于控制偏转器的角度偏移，使得偏转器后端靠近机翼表面设置，并且基座从机翼表面向外延伸，以便 当偏转器处于展开位置时，将排气向上偏转并偏离偏转器前端。
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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
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.
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3.发明授权
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
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。
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4.发明授权
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
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。
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公开(公告)号：US4926633A
公开(公告)日：1990-05-22
申请号：US372416
申请日：1989-06-27
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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公开(公告)号：US4772033A
公开(公告)日：1988-09-20
申请号：US536606
申请日：1983-09-28
申请人： Dudley O. Nash
发明人： Dudley O. Nash
IPC分类号： F02K1/80 , F16L27/053 , F16J15/16
CPC分类号： F16L27/053 , F02K1/805
摘要： A flexural joint for connecting opposing ends of first and second annular ducts. The joint includes a lip which extends outwardly from the first duct and a flange member which extends outwardly from the second duct. The flange member contains a recess which is adapted to engage the lip.
摘要翻译： 用于连接第一和第二环形管道的相对端部的弯曲接头。 接头包括从第一管道向外延伸的唇缘和从第二管道向外延伸的凸缘构件。 凸缘构件包括适于接合唇缘的凹部。
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7.发明授权Apparatus and method for controlling fan duct flow in a gas turbine engine 失效用于控制燃气涡轮发动机中的风扇管道流量的装置和方法
公开(公告)号：US4285194A
公开(公告)日：1981-08-25
申请号：US32329
申请日：1979-04-23
申请人： Dudley O. Nash
发明人： Dudley O. Nash
CPC分类号： F02K3/075 , F02K1/822 , Y02T50/671 , Y02T50/675
摘要： A fan duct flow control method and apparatus is provided for controlling fan bypass airflow at an inlet into an exhaust duct cooling annulus of a variable cycle gas turbine engine. The flow control employs a translating ring as a valve-like device that interacts with an annular lip on an inlet into the exhaust duct cooling annulus. The translating ring is positioned to restrict airflow into the liner during appropriate periods in engine operation. This flow control is uniquely constructed to be conveniently operated by a variable cycle engine actuation system that injects fan bypass air into an engine exhaust duct. The method and apparatus in one form is also used to block fan duct flow and reduce forward thrust during aircraft taxi operations.
摘要翻译： 提供了一种风扇流量控制方法和装置，用于控制在可变循环燃气涡轮发动机的排气管道冷却环路的入口处的风扇旁路气流。 流量控制使用平移环作为阀状装置，其与入口中的环形唇缘相互作用到排气管冷却环中。 平移环的定位是在发动机运转的适当期间限制气流进入衬管。 这种流量控制被独特地构造，以便通过将风扇旁路空气注入到发动机排气管中的可变循环发动机致动系统方便地操作。 一种形式的方法和装置也用于阻挡风扇管道流动并减少飞机出租车操作期间的向前推力。
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公开(公告)号：US4000610A
公开(公告)日：1977-01-04
申请号：US572340
申请日：1975-04-28
CPC分类号： F02K1/006 , F02K1/1215
摘要： A flight maneuverable gas turbine exhaust nozzle is provided with cooperating variable internal converging-diverging flaps to provide area control. A flap downstream of the converging-diverging flap provides flight maneuver vectoring as well as external exhaust expansion control. A vertical take-off and landing capability is provided by deployment of a rotating bonnet-type deflector which diverts the exhaust stream downward around one side of the exhaust nozzle. The nozzle throat rotates with the deflector to produce efficient turning of the exhaust stream.
摘要翻译： 飞行机动式燃气轮机排气喷嘴设有配合可变的内部会聚发散翼片，以提供区域控制。 在会聚发散翼下游的翼片提供飞行机动矢量以及外部排气扩展控制。 通过部署旋转阀盖型偏转器来提供垂直起降能力，其将排气流向下排放到排气喷嘴的一侧。 喷嘴喉部与偏转器一起旋转以产生排气流的有效转动。
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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
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。
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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
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.
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