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1. 发明授权

US06735936B2 Variable area nozzle for gas turbine engines driven by shape memory alloy actuators 有权
标题翻译：由形状记忆合金致动器驱动的燃气涡轮发动机的可变面积喷嘴
公开(公告)号：US06735936B2
公开(公告)日：2004-05-18
申请号：US09824419
申请日：2001-04-02
申请人： Nancy M. Rey , Robin Mihekun Miller , Thomas G. Tillman , Robert M. Rukus , John L. Kettle
发明人： Nancy M. Rey , Robin Mihekun Miller , Thomas G. Tillman , Robert M. Rukus , John L. Kettle
IPC分类号： F02K112
CPC分类号： F02K1/1207 , F03G7/065 , F05D2300/505 , Y02T50/671 , Y10T74/20
摘要： A gas turbine engine includes a variable area nozzle having a plurality of flaps. The flaps are actuated by a plurality of actuating mechanisms driven by shape memory alloy (SMA) actuators to vary fan exist nozzle area. The SMA actuator has a deformed shape in its martensitic state and a parent shape in its austenitic state. The SMA actuator is heated to transform from martensitic state to austenitic state generating a force output to actuate the flaps. The variable area nozzle also includes a plurality of return mechanisms deforming the SMA actuator when the SMA actuator is in its martensitic state.
摘要翻译：燃气涡轮发动机包括具有多个翼片的可变区域喷嘴。翼片由形状记忆合金（SMA）致动器驱动的多个致动机构致动，以改变风扇存在的喷嘴面积。 SMA致动器在其马氏体状态下具有变形的形状，并且其奥氏体状态具有母体形状。 SMA致动器被加热以从马氏体状态转变为奥氏体状态，产生力输出以致动翼片。可变区域喷嘴还包括当SMA致动器处于其马氏体状态时使SMA致动器变形的多个返回机构。

2. 发明授权

US06295805B1 Exhaust induced ejector nozzle system and method 失效
标题翻译：排气诱导喷嘴系统及方法
公开(公告)号：US06295805B1
公开(公告)日：2001-10-02
申请号：US09662263
申请日：2000-09-14
申请人： Jesse R. Lackey , Jeffrey A. Catt
发明人： Jesse R. Lackey , Jeffrey A. Catt
IPC分类号： F02K112
CPC分类号： F02K1/36 , F05D2260/601
摘要： An exhaust induced ejector nozzle (20) includes a convergent portion (30) and a divergent portion (34) disposed downstream from the convergent portion (30). The ejector nozzle (20) also includes an ejector (40) having an outlet (46) disposed within the divergent portion (34). The ejector (40) is operable to provide entrainment of a nacelle airflow (18) from a nacelle airflow area (44) into the divergent portion (34). The ejector nozzle (20) further includes a convergent ejector (60) extending between the convergent portion (30) and the nacelle airflow area (44). The convergent ejector (60) is operable to draw a portion of an exhaust airflow (42) into the nacelle airflow area (44) to increase a flow rate of the nacelle airflow (18).
摘要翻译：排气感应喷射器喷嘴（20）包括会聚部分（30）和设置在会聚部分（30）下游的发散部分（34）。喷射器喷嘴（20）还包括具有设置在发散部分（34）内的出口（46）的喷射器（40）。喷射器（40）可操作以将机舱气流（18）从机舱气流区域（44）引入到发散部分（34）中。喷射器喷嘴（20）还包括在收敛部分（30）和机舱气流区域（44）之间延伸的会聚喷射器（60）。会聚喷射器（60）可操作以将一部分排气气流（42）吸入机舱气流区域（44）中以增加机舱气流（18）的流量。

3. 发明授权

US06688099B2 Variable area thrust reverser nozzle 有权
标题翻译：可变面积推力反向器喷嘴
公开(公告)号：US06688099B2
公开(公告)日：2004-02-10
申请号：US10440842
申请日：2003-05-19
申请人： Jean-Pierre Lair
发明人： Jean-Pierre Lair
IPC分类号： F02K112
CPC分类号： F02K1/06 , B64D33/04 , F02K1/70 , F02K1/766
摘要： A turbofan exhaust nozzle includes a jet pipe having a pair of thrust reverser doors disposed on opposite sides thereof. Each door has a hinge arm joined to a swing arm, which in turn is joined to the pipe. Each door also includes a latching clip at a forward end, and a deployment clevis between the clip and hinge arm. A common actuator is connected to both doors by corresponding links joined to the clevises for driving the links aft to pivot aft the doors and swing arms. A first lock selectively locks the latching clip and a second lock selectively locks the swing arms in coordination with the first lock for permitting variable area axial movement of the doors, thrust reverser deployment thereof, and retraction to stowed positions of the doors.
摘要翻译：涡轮风扇排气喷嘴包括具有设置在其相对侧上的一对推力反向器门的喷射管。每个门具有连接到摆臂的铰链臂，该摇臂又连接到管道。每个门还包括在前端的闩锁夹和夹子和铰链臂之间的部署U形夹。共同的致动器通过连接到U形夹的相应链节连接到两个门，用于驱动后部的链节以枢转门和摆臂的后方。第一锁定器选择性地锁定闩锁夹，并且第二锁定器选择性地锁定摆臂与第一锁配合，以允许门的可变区域轴向运动，推力反向器的展开以及收回门的收起位置。

4. 发明授权

US06327846B1 Universal-joint vectoring system for a turbojet-engine exhaust nozzle 有权
标题翻译：用于涡轮喷气发动机排气喷嘴的通用联合矢量系统
公开(公告)号：US06327846B1
公开(公告)日：2001-12-11
申请号：US09551749
申请日：2000-04-18
申请人： Didier Georges Feder , Guy Jean-Louis Lapergue
发明人： Didier Georges Feder , Guy Jean-Louis Lapergue
IPC分类号： F02K112
CPC分类号： F02K1/1292 , F02K1/008
摘要： The invention relates to a wide-vectoring, axisymmetric turbojet-engine exhaust nozzle including vectoring structure (12) supporting a plurality of converging flaps (21). The vectoring structure is mounted on the downstream end of an exhaust housing (2) by means of an intermediate ring (9) which is pivotable about a first axis relative to the exhaust housing (2) and further about a second axis perpendicular to the first axis and relative to the vectoring structure (12). The converging flaps (21) hinge on the downstream end of the vectoring structure (12). A single drive ring (27) controlled by three linear actuators (28) and linked by linkrods (24) to the converging flaps (21) controls the tipping of the vectoring structure (12) and the kinematics of the flaps (21).
摘要翻译：本发明涉及一种宽矢量的轴对称涡轮喷气发动机排气喷嘴，其包括支撑多个会聚翼片（21）的矢量结构（12）。矢量结构通过中间环（9）安装在排气壳体（2）的下游端，中间环围绕第一轴线相对于排气罩（2）枢转，并且还围绕垂直于第一并且相对于向量结构（12）。会聚翼片（21）铰接在矢量化结构（12）的下游端。由三个线性致动器（28）控制并通过链接（24）连接到会聚翼片（21）的单个驱动环（27）控制向量结构（12）的倾斜和襟翼（21）的运动学。

5. 发明授权

US06301877B1 Ejector extension cooling for exhaust nozzle 失效
标题翻译：喷油嘴延长冷却排气喷嘴
公开(公告)号：US06301877B1
公开(公告)日：2001-10-16
申请号：US08556317
申请日：1995-11-13
申请人： George P. Liang , William J. Yeager , John F. Soileau
发明人： George P. Liang , William J. Yeager , John F. Soileau
IPC分类号： F02K112
CPC分类号： F02K1/822 , Y02T50/675
摘要： The cooling of the exhaust nozzle of a fan jet engine powering aircraft is enhanced by providing an extension cooling concept that includes an extension piece extending axially downstream of the nozzles variable throat that utilizes fan air to cool the forward portion of the divergent nozzle surfaces adjacent to the gas path of the engine and ram air to cool the surfaces downstream of the ejector. A variable vane varies the area of the ejector slot as a function of Aj for compensating for flow losses at off-design points of the nozzle positions during the flight envelope of the aircraft so as to avoid overtemperature of the components.
摘要翻译：通过提供延伸冷却概念增强了对飞行器供电的风扇喷气发动机的排气喷嘴的冷却，该延伸冷却概念包括在喷嘴可变喉部的轴向下游延伸的延伸件，该延伸件利用风扇空气来冷却相邻的发散喷嘴表面的前部发动机的气体路径和冲压空气以冷却喷射器下游的表面。可变叶片将喷射器槽的面积作为Aj的函数改变，以补偿在飞行器的飞行包络期间喷嘴位置的设计外的流量损失，以避免部件过热。

6. 发明授权

US06779336B2 Cooled variable geometry exhaust nozzle 有权
标题翻译：冷却可变几何排气喷嘴
公开(公告)号：US06779336B2
公开(公告)日：2004-08-24
申请号：US10190277
申请日：2002-07-05
申请人： James P. Allore , Stephen A. Paul , Charles D. Stoner
发明人： James P. Allore , Stephen A. Paul , Charles D. Stoner
IPC分类号： F02K112
CPC分类号： F02K1/1223 , F02K1/06 , F02K1/822 , Y02T50/671 , Y02T50/675
摘要： A variable geometry exhaust nozzle 10 for a turbine engine includes convergent and divergent flaps 12, 18 that circumscribe a gaspath 26 and define convergent and divergent nozzle sections 30, 32 with a throat 34 therebetween. A projection 56, which resides on the divergent flaps, extends radially inwardly from the nozzle. The nozzle also includes a coolant flowpath comprising an interior space 44 in the nozzle, an intake 58 for admitting coolant C into the interior space, and a coolant outlet 60 aft of the intake for discharging the coolant from the interior space. The intake resides forward of the throat. During operation, a coolant film flows along the radially inner surface of the nozzle. The projection encourages a portion of the coolant film to enter and flow through the the coolant flowpath to convectively cool the nozzle. The location of the intake, forward of the throat, takes advantage of the locally high gaspath pressure to ensure that an adequate quantity of the coolant enters and flows through the coolant flowpath.
摘要翻译：用于涡轮发动机的可变几何形状排气喷嘴10包括会聚和发散的折板12,18，其包围气体路径26并且限定会聚和发散的喷嘴部分30,32，其间具有喉部34。位于发散翼片上的突起56从喷嘴径向向内延伸。喷嘴还包括冷却剂流路，其包括喷嘴中的内部空间44，用于将冷却剂C进入内部空间的进气口58和用于从内部空间排出冷却剂的进气口后部的冷却剂出口60。摄入量位于喉咙前方。在操作期间，冷却剂膜沿喷嘴的径向内表面流动。该突起促使冷却剂膜的一部分进入并流过冷却剂流动路径以对流地冷却喷嘴。进气口位于喉部的前方，利用局部较高的气路压力来确保足够量的冷却剂进入并流过冷却剂流路。

7. 发明授权

US06658854B2 Methods and apparatus for retaining gas turbine engine nozzle basesheets 有权
公开(公告)号：US06658854B2
公开(公告)日：2003-12-09
申请号：US10061629
申请日：2002-02-01
申请人： Darrell Senile , Bernard J. Renggli
发明人： Darrell Senile , Bernard J. Renggli
IPC分类号： F02K112
CPC分类号： F02K1/12 , F02K1/1223 , Y10T29/49346
摘要： A method for assembling a flap and seal system for a gas turbine engine exhaust nozzle including a plurality of backbone assemblies facilitates attaching a basesheet to a backbone. The method includes attaching an attachment system including at least one strap to a basesheet, and coupling the basesheet to a backbone using the attachment system strap.

8. 发明授权

US06378294B1 System for activating an adjustable tube by means of an elastic ring for a thrust nozzle 有权
标题翻译：用于通过用于推力喷嘴的弹性环来激活可调节管的系统
公开(公告)号：US06378294B1
公开(公告)日：2002-04-30
申请号：US09647454
申请日：2000-09-28
申请人： François Abbe , Pierre Camy , Georges Habarou , Michel Thual
发明人： François Abbe , Pierre Camy , Georges Habarou , Michel Thual
IPC分类号： F02K112
CPC分类号： F02K1/002 , F02K1/1292 , Y02T50/672
摘要： A steerable nozzle for a reaction engine comprises a fixed portion (1) for connection to the engine, a plurality of steerable flaps (21) mounted on one end (11) of the fixed portion, and flap steering means (3, 4, 22, 31). The nozzle is characterized in that the flap steering means comprise a resilient ring (3) having a first circumference secured to said end (11) of the fixed portion and a second circumference connected to the flaps (21), and control means (4) for moving the second circumference of the resilient ring.
摘要翻译：用于反作用发动机的可转向喷嘴包括用于连接到发动机的固定部分（1），安装在固定部分的一端（11）上的多个可转向翼片（21）和挡板转向装置（3,4,22），31）。喷嘴的特征在于，翼片转向装置包括弹性环（3），其具有固定到固定部分的所述端部（11）的第一周边和连接到翼片（21）的第二圆周，以及控制装置（4）用于移动弹性环的第二圆周。

9. 发明授权

US06212877B1 Vectoring ring support and actuation mechanism for axisymmetric vectoring nozzle with a universal joint 失效
标题翻译：用万向节轴对称矢量喷嘴的矢量环支撑和致动机构
公开(公告)号：US06212877B1
公开(公告)日：2001-04-10
申请号：US09148926
申请日：1998-09-04
申请人： Bernard J. Renggli
发明人： Bernard J. Renggli
IPC分类号： F02K112
CPC分类号： F02K1/008 , F02K1/15 , F05D2250/33 , Y02T50/672
摘要： A vectoring ring support and actuation apparatus is provided for transferring the side loads acting on a vectoring ring and generated by a gas turbine engine thrust vectoring nozzle to a relatively stationary portion of the engine and tilting the vectoring ring to vector the thrust of the nozzle. The apparatus includes an axially pivotable first link pivotably mounted on a relatively stationary first portion of the engine, an axially pivotable second link pivotably supported by and connected to the first link, and a vectoring ring connected to an aft end of the second link. An actuator is operably mounted between a relatively stationary second portion of the engine (spaced axially apart from the stationary first portion of the engine) and the second link to axially pivot the first link with respect. Preferably a first joint links the actuator to the second link and has at least first and second rotational degrees of freedom with corresponding first and second perpendicular axes of rotation. A second joint may be used to pivotably connect the second link to the first link and has one rotational degree of freedom and a third axis of rotation co-linear with one of the first and second perpendicular axes of rotation. The first joint is preferably a ball joint having three rotational degrees of freedom.
摘要翻译：提供矢量环支撑和致动装置，用于将作用在矢量环上并由燃气涡轮发动机推力矢量化喷嘴产生的侧向载荷传递到发动机的相对静止部分并且倾斜矢量环以矢量喷嘴的推力。该装置包括可枢转地安装在发动机的相对固定的第一部分上的可轴向枢转的第一连杆，可枢转地支撑并连接到第一连杆的可轴向枢转的第二连杆，以及连接到第二连杆的后端的矢量环。致动器可操作地安装在发动机的相对固定的第二部分（与发动机的固定的第一部分轴向间隔开）和第二连杆之间以相对于第一连杆轴向枢转。优选地，第一接头将致动器连接到第二连杆并且具有至少第一和第二旋转自由度以及相应的第一和第二垂直旋转轴线。可以使用第二接头来将第二连杆可枢转地连接到第一连杆，并且具有一个旋转自由度并且第三旋转轴线与第一和第二垂直旋转轴线之一共线。第一接头优选为具有三个旋转自由度的球窝接头。

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