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公开(公告)号：US06415599B1
公开(公告)日：2002-07-09
申请号：US09853277
申请日：2001-05-11
IPC分类号： F02K100
CPC分类号： F02K1/002 , Y02T50/671
摘要： An aircraft gas turbine axisymmetric vectoring nozzle has an interface ring centered about a nozzle, a vectoring ring disposed radially inwardly of and apart from the interface ring, and a bearing radially disposed between the vectoring ring and the interface ring. The bearing may be a sliding bearing having a sliding interface between the vectoring ring and the interface ring and the sliding interface is spherical. The bearing may be constructed of sliding bearing segments having sliding interfaces between the vectoring ring and the interface ring and the sliding interfaces are spherical. Each of the bearing segments includes an outer sliding element attached to the interface ring, an inner sliding element attached to the vectoring ring, and spherically curved outer and inner sliding surfaces on the outer and inner sliding elements respectively wherein the spherically curved outer and inner sliding surfaces define the sliding interfaces between the vectoring ring and the interface ring. At least one of the outer sliding elements is circumferentially disposed and trapped between circumferentially spaced apart rails disposed on a corresponding one of the inner sliding elements. A plurality of interface ring support guides are disposed radially inwardly of and in sliding support relationship with the interface ring and located axially forward of the vectoring ring.
摘要翻译： 飞机燃气轮机轴对称矢量喷嘴具有以喷嘴为中心的界面环，设置在接口环径向内侧和远离接口环的向心环，以及径向设置在矢量环与界面环之间的轴承。 轴承可以是在向量环和界面环之间具有滑动界面的滑动轴承，并且滑动界面是球形的。 轴承可以由在向量环和界面环之间具有滑动界面并且滑动界面是球形的滑动轴承段构成。 每个轴承段包括附接到接口环的外部滑动元件，附接到向量环的内部滑动元件，以及外部和内部滑动元件上的球形弯曲的外部和内部滑动表面，其中，球形弯曲的外部和内部滑动 表面定义了向量环和接口环之间的滑动接口。 外部滑动元件中的至少一个周向地设置并且被捕获在设置在对应的一个内部滑动元件上的周向间隔开的轨道之间。 多个界面环支撑引导件设置在与界面环的径向内侧并与其成滑动支撑的关系中并且位于向心环的轴向前方。
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2.发明授权
公开(公告)号：US6142416A
公开(公告)日：2000-11-07
申请号：US818051
申请日：1997-03-14
CPC分类号： F02K1/15 , F02K1/008 , F02K1/12 , Y02T50/677
摘要： A nozzle failsafe nozzle actuating system for an aircraft gas turbine engine variable exhaust nozzle having a plurality of pivotal flaps circumferentially disposed about a nozzle centerline and bounding an exhaust gas flowpath in the nozzle is provided with a number of primary actuators which are operably connected to nozzle flaps for pivoting and setting an attitude of the flaps relative to the centerline and wherein each of the primary actuators is extendable between a fully extended position and a fully retracted position, and a failsafe nozzle actuating actuator for setting the attitude of each of the flaps to a failsafe attitude during a failsafe mode of the nozzle actuating system wherein the failsafe attitude is such that each of the primary actuators is at a partially retracted position between the fully extended and the fully retracted positions. A particular embodiment provides actuator assembly wherein a failsafe piston rod of the failsafe actuator is disposed concentrically about a primary rod of the primary actuator and a stop element is provided for the failsafe rod to engage the primary rod when the primary rod is being retracted and the failsafe rod is extended.
摘要翻译： 一种用于飞机燃气涡轮发动机可变排气喷嘴的喷嘴故障保护喷嘴致动系统，其具有围绕喷嘴中心线周向设置并围绕喷嘴中的排气流动路径的多个枢转翼片设置有多个主致动器，其可操作地连接到喷嘴 用于枢转和设定翼片相对于中心线的姿态的翼片，并且其中每个主致动器在完全延伸位置和完全缩回位置之间可延伸;以及故障保护喷嘴致动致动器，用于将每个翼片的姿态设置为 在喷嘴致动系统的故障安全模式期间的故障安全姿态，其中故障保护姿态使得每个主致动器处于完全伸出位置和完全缩回位置之间的部分缩回位置。 特定实施例提供致动器组件，其中故障保护致动器的故障安全活塞杆围绕主致动器的主杆同心地设置，并且提供止动元件用于故障安全杆在主杆正在缩回时与主杆接合， 故障安全杆伸长。
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公开(公告)号：US5484105A
公开(公告)日：1996-01-16
申请号：US274523
申请日：1994-07-13
CPC分类号： F02K1/1223 , B64D33/04 , F02K1/1292 , F02K1/805 , F02K1/82 , F05D2250/324 , Y02T50/671
摘要： A nozzle cooling system having apparatus to overexpand the exhaust flow in a divergent section of an aircraft gas turbine engine nozzle, relative to the air in the engine nozzle's bay and a valve to allow ambient air from the bay to flow over divergent flaps and seals of the divergent section, and rapidly cool the divergent section of the nozzle for IR suppression. An area ratio control apparatus may be used to change a ratio of the nozzle exit area to the nozzle throat area to an overexpanded level that reduces static pressures along at least a longitudinally extending portion of the surfaces to below the ambient pressure of air outside the nozzle to draw the ambient air into the exhaust gas flowpath, and a valve apparatus to controllably flow the ambient air into the exhaust gas flowpath when the static pressures are below the ambient pressure. Further embodiments of the present invention provide alternative area ratio control apparatus, such as a variable exit area control apparatus to vary the exit area or a variable throat area control apparatus to vary the throat area, or both. Valve apparatus with a gap apparatus to controllably open gaps between the circumferentially adjacent divergent flaps and seals are provided such as spring loaded divergent seal retainers and flapper valves sealingly disposed over corresponding cooling apertures through the divergent seals.
摘要翻译： 一种喷嘴冷却系统，其具有相对于发动机喷嘴的间隙中的空气而过度扩张飞机燃气涡轮发动机喷嘴的发散部分中的排气流的装置，以及允许来自舱室的环境空气流过发散管喷嘴的间隙的发散翼和密封件 发散部分，并快速冷却喷嘴的发散部分进行IR抑制。 面积比率控制装置可以用于将喷嘴出口面积与喷嘴喉部区域的比率改变为过度喷射水平，其将表面的至少纵向延伸部分的静压力降低到喷嘴外部的空气的环境压力以下 以将环境空气吸入废气流路，以及阀装置，当静压力低于环境压力时，可控制地将环境空气流入废气流径。 本发明的另外的实施例提供了可替换的面积比例控制装置，例如改变出口区域的可变出口区域控制装置或改变喉部区域的可变喉区域控制装置，或两者。 具有间隙装置的阀装置可控制地打开周向相邻的发散片和密封件之间的间隙，例如通过发散密封件密封地设置在相应的冷却孔上的弹簧加载的发散密封保持器和挡板阀。
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公开(公告)号：US5820024A
公开(公告)日：1998-10-13
申请号：US500310
申请日：1995-07-06
CPC分类号： F02K1/15 , F02K1/12 , Y02T50/671
摘要： A hollow actuating ring and apparatus for actuating and/or vectoring the flaps of an aircraft gas turbine engine nozzle by transferring actuation loads from a small number of actuators to a greater number of pivotal divergent flap members of the nozzle. The actuating ring has a generally hollow annular structure including axially spaced apart coaxial forward and aft walls, struts axially extending between and structurally joining together the forward and aft walls, and a ring stiffening for decreasing the effective ring bending and torsional length of at least one of the forward and aft walls between the struts. Stiffening structure is provided for spreading out loads transferred from the struts to one of the forward and aft walls using structural braces extending diagonally between the struts and one of the forward and aft walls.
摘要翻译： 一种中空的致动环和装置，用于通过将致动载荷从少量致动器传递到喷嘴的更多数量的枢转扩张翼片构件来致动和/或矢量化飞行器燃气涡轮发动机喷嘴的翼片。 致动环具有大致中空的环形结构，其包括轴向间隔开的同轴的前后壁，在其之间轴向延伸并在结构上将前后壁连接在一起的支柱，以及用于减小至少一个的有效环弯曲和扭转长度的环加强 的支柱之间的前后壁。 提供了加强结构，用于将从支柱传递到其中一个前后壁的载荷，使用在支柱和前壁和后壁中的一个之间对角地延伸的结构支架。
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公开(公告)号：US5174502A
公开(公告)日：1992-12-29
申请号：US698045
申请日：1991-05-10
CPC分类号： F02K1/1292 , F02K1/002 , F02K1/008 , F05D2250/31 , F05D2250/34 , Y02T50/671
摘要： The present invention provides support for a vectoring ring used to pivot flaps in a gas turbine engine thrust vectoring nozzle. The ring support transfers at least a portion of the side loads acting generated by a gas turbine engine thrust vectoring nozzle to a relatively stationary portion of the engine. The support includes apparatus that provides for allowing two degree of freedom (2 DOF) pivoting or gimballing motion and axial translation of the vectoring ring.
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6.发明授权Axisymmetric vectoring nozzle actuating system having multiple power control circuits 失效具有多个功率控制电路的轴对称矢量喷嘴致动系统
公开(公告)号：US5740988A
公开(公告)日：1998-04-21
申请号：US422731
申请日：1995-04-13
CPC分类号： F02K1/008 , F02K1/15 , Y02T50/671
摘要： A failsafe nozzle actuating system for an aircraft gas turbine engine axisymmetric vectoring exhaust nozzle has a vectoring ring operably linked to a plurality of pivotal flaps which are circumferentially disposed about a nozzle centerline and bounding an exhaust gas flowpath in the nozzle. The failsafe nozzle actuating system has at least two independently operable first and second vectoring actuating systems including first and second groups of actuators operably connected to the vectoring ring and first and second failsafe control means to control power to the first and second groups of actuators, respectively. The first group of vectoring actuators is interdigitated with the second group of second vectoring actuators around the nozzle. Either of the two groups of actuators are operable to actuate the nozzle when the other group is failsafed.
摘要翻译： 用于飞机燃气涡轮发动机轴对称矢量排气喷嘴的故障保护喷嘴致动系统具有可操作地连接到多个枢转翼片的矢量环，所述枢转翼围绕喷嘴中心线周向设置并且限制喷嘴中的废气流动路径。 故障安全喷嘴致动系统具有至少两个可独立操作的第一和第二向量化致动系统，其包括可操作地连接到向导环的第一组和第二组致动器，以及分别对第一和第二组致动器控制动力的第一和第二故障保护控制装置 。 第一组矢量执行器与喷嘴周围的第二组第二矢量执行器相互交错。 两组致动器中的任何一个可操作以在另一组故障通过时致动喷嘴。
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