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91. 发明申请

US20120079804A1 COWL ASSEMBLY 审中-公开
标题翻译： COWL装配
公开(公告)号：US20120079804A1
公开(公告)日：2012-04-05
申请号：US13247466
申请日：2011-09-28
申请人： Alan Roy Stuart , Kenneth Stephan Scheffel
发明人： Alan Roy Stuart , Kenneth Stephan Scheffel
IPC分类号： F02K3/02
CPC分类号： F02K1/72 , F02K1/76 , F02K3/06
摘要： An assembly for a turbofan engine includes a first cowl member comprising an aft portion and a translatable cowl member comprising a forward portion configured to be received within the aft portion. The translatable cowl member is configured to be moveable with respect to the first cowl member between a first operational position wherein the forward portion is received within the aft portion of the first cowl member, and a second operational position wherein a smaller portion of the forward portion is received within the aft portion than in the first operational position. The translatable cowl member is configured to cooperate with a core cowl of the turbofan engine to define a portion of a fan duct having an exit nozzle, and the translatable cowl member is configured to define a flow control location near the exit nozzle that is associated with a controlling fan duct area.
摘要翻译：用于涡轮风扇发动机的组件包括第一整流罩构件，其包括后部部分和可平移的整流罩构件，其包括构造成容纳在后部中的前部。可平移整流罩构件被构造成可在第一操作位置和第二操作位置之间相对于第一整流罩构件在第一操作位置和第二操作位置之间移动，其中前部部分被容纳在第一整流罩构件的后部中，在后部中被接收在第一操作位置。所述可平移整流罩构件被构造成与所述涡轮风扇发动机的核心罩一起配合以限定具有出口喷嘴的风扇管道的一部分，并且所述可平移整流罩构件构造成限定出口喷嘴附近的流动控制位置，所述流动控制位置与控制风扇管道面积。

92. 发明申请

US20090065634A1 Control system for the nacelle of a turboreactor 有权
标题翻译：涡轮反应器机舱的控制系统
公开(公告)号：US20090065634A1
公开(公告)日：2009-03-12
申请号：US11919353
申请日：2006-06-12
申请人： Thierry Marin Martinod
发明人： Thierry Marin Martinod
IPC分类号： B64D27/16
CPC分类号： F02K1/76 , B64D29/08 , F05D2240/14 , F05D2270/52 , F05D2270/62 , Y02T50/671
摘要： The invention relates to an electrical control system for the nacelle of a turboreactor, comprising a plurality of electromechanical manoeuvring elements for a plurality of actuating devices embodied as auxiliary parts of the turboreactor. The invention is characterized in that the control system comprises an electronic control box comprising a plurality of control inlets to be connected to control elements, and a plurality of outlets connected to electromechanical manoeuvring of the auxiliary actuating devices. The control box can translate each instruction received into an operating sequence for at least one corresponding electromechanical manoeuvring element. The invention also relates to a nacelle and an aircraft provided with one such control system.
摘要翻译：本发明涉及一种用于涡轮反应器的机舱的电气控制系统，其包括用于多个作为涡轮反应器的辅助部件的致动装置的机电操纵元件。本发明的特征在于，该控制系统包括一个电子控制箱，该电子控制箱包括多个要连接到控制元件的控制进口，以及连接到辅助致动装置的机电操纵的多个出口。控制箱可以将接收的每条指令转换成至少一个对应的机电操纵元件的操作顺序。本发明还涉及一种具有一个这样的控制系统的机舱和飞机。

93. 发明授权

US07104500B1 Thrust reverser with sliding pivot joints 失效
标题翻译：具有滑动枢轴接头的推力反向器
公开(公告)号：US07104500B1
公开(公告)日：2006-09-12
申请号：US11037744
申请日：2005-01-18
申请人： Craig M. Smith
发明人： Craig M. Smith
IPC分类号： B64C25/68
CPC分类号： B64D33/04 , F02K1/60 , F02K1/76
摘要： A target type thrust reverser is provided for reversing the thrust of jet engines, particularly on aircraft. The thrust reverser preferably has a plurality of doors that occupy a stowed position about the nozzle of the jet engine until deployed. In the stowed position, the doors are out of the exhaust stream of the jet engine. The doors are mounted to pivot joints on the rear portions of the doors. To deploy the thrust reverser, actuators connected to the pivot joints cause the pivot joints to translate linearly aft, and link rods attached to the forward portions of the doors cause the doors to pivot about the sliding pivot joints. In this manner, the distance between the doors and the engine exhaust nozzle is minimized during deployment, which enables significant weight savings due to reduced loads and fewer parts. A novel lock is also provided for simultaneously locking the thrust reverser doors and the actuators.
摘要翻译：提供了一种目标型推力反向器，用于扭转喷气发动机的推力，特别是在飞机上。推力反向器优选地具有多个门，其围绕喷气发动机的喷嘴占据收起位置直到展开。在收起位置时，门从喷气发动机的排气流中排出。门安装在门的后部的枢轴接头上。为了部署推力反向器，连接到枢转接头的致动器使枢转接头线性地平移，并且连接到门的前部的连接杆使得门围绕滑动枢转接头枢转。以这种方式，在展开期间门和发动机排气喷嘴之间的距离最小化，这由于减少的负载和较少的部件而能够显着减轻重量。还提供了一种新颖的锁，用于同时锁定推力反向器门和致动器。

94. 发明申请

US20060101805A1 Floating flexible firewall seal 有权
标题翻译：浮动柔性防火墙密封
公开(公告)号：US20060101805A1
公开(公告)日：2006-05-18
申请号：US10987491
申请日：2004-11-12
申请人： Robert Greco
发明人： Robert Greco
IPC分类号： F02K1/54
CPC分类号： F02K1/76 , F02K1/54 , F02K1/805
摘要： A seal assembly is provided for sealing an interface between a shaft and a bore formed in a firewall, where the shaft has an annular foot extending radially outward therefrom and a flowpath extending therethrough in fluid communication with the bore. The assembly includes a flexible annular seal, a ring, and a plurality of retainers.
摘要翻译：提供密封组件用于密封轴和形成在防火墙中的孔之间的界面，其中所述轴具有从其径向向外延伸的环形脚和与所述孔流体连通的从其延伸的流路。组件包括柔性环形密封件，环形件和多个保持件。

95. 发明授权

US06926234B2 Electromechanical turbojet thrust reverser with continuous position control 有权
标题翻译：具有连续位置控制的机电涡轮喷气推力反向器
公开(公告)号：US06926234B2
公开(公告)日：2005-08-09
申请号：US10678104
申请日：2003-10-06
申请人： Baptiste Colotte , Alexandre Courpied , Marc Croixmarie , Patrick Joland , Gilles Le Gouellec , Marion Michau
发明人： Baptiste Colotte , Alexandre Courpied , Marc Croixmarie , Patrick Joland , Gilles Le Gouellec , Marion Michau
IPC分类号： B64D33/00 , F02K1/54 , F02K1/76 , F02K1/70
CPC分类号： F02K1/76 , F02K1/763 , F05D2270/54 , F05D2270/62 , Y02T50/671
摘要： A turbojet thrust reverser includes two doors each controlled by a respective electronic control unit, at least one sensor per door measuring at least one item of position data concerning the door, at least one sensor of each door being connected to the electronic control unit controlling that door, the electronic control units being connected to each other in order to exchange the position data, a FADEC having two channels each connected to both electronic control units in order to receive from each of the electronic control units data concerning the positions of each of the doors and data concerning the operating state of each of the electronic control units, the channels being connected to each other in order to exchange the door position data and the electronic control unit state data so that the airplane pilot is continuously informed about the positions of the doors and the states of the electronic units, even in the event of a breakdown in one of the electronic units and in one of the FADEC channels.
摘要翻译：涡轮喷气推进反向器包括两个门，每个门由相应的电子控制单元控制，每门至少一个传感器测量关于门的至少一个位置数据，每个门的至少一个传感器连接到电子控制单元，门，电子控制单元彼此连接以便交换位置数据; FADEC具有两个通道，每个通道都连接到两个电子控制单元，以便从每个电子控制单元接收关于每个电子控制单元的位置的数据门和关于每个电子控制单元的操作状态的数据，通道彼此连接，以便更换门位置数据和电子控制单元状态数据，使得飞行器飞行员不断地被通知关于门和电子单元的状态，即使在一个电子单元故障的情况下也是如此的FADEC渠道。

96. 发明授权

US06845945B1 Thrust reverser with sliding pivot joints 失效
标题翻译：具有滑动枢轴接头的推力反向器
公开(公告)号：US06845945B1
公开(公告)日：2005-01-25
申请号：US09909561
申请日：2001-07-20
申请人： Craig M. Smith
发明人： Craig M. Smith
IPC分类号： B64D33/04 , F02K1/60 , F02K1/76 , B64C25/68
CPC分类号： B64D33/04 , F02K1/60 , F02K1/76
摘要： A target type thrust reverser is provided for reversing the thrust of jet engines, particularly on aircraft. The thrust reverser preferably has a plurality of doors that occupy a stowed position about the nozzle of the jet engine until deployed. In the stowed position, the doors are out of the exhaust stream of the jet engine. The doors are mounted to pivot joints on the rear portions of the doors. To deploy the thrust reverser, actuators connected to the pivot joints cause the pivot joints to translate linearly aft, and link rods attached to the forward portions of the doors cause the doors to pivot about the sliding pivot joints. In this manner, the distance between the doors and the engine exhaust nozzle is minimized during deployment, which enables significant weight savings due to reduced loads and fewer parts. A novel lock is also provided for simultaneously locking the thrust reverser doors and the actuators.
摘要翻译：提供了一种目标型推力反向器，用于扭转喷气发动机的推力，特别是在飞机上。推力反向器优选地具有多个门，其围绕喷气发动机的喷嘴占据收起位置直到展开。在收起位置时，门从喷气发动机的排气流中排出。门安装在门的后部的枢轴接头上。为了部署推力反向器，连接到枢转接头的致动器使枢转接头线性地平移，并且连接到门的前部的连接杆使得门围绕滑动枢转接头枢转。以这种方式，在展开期间门和发动机排气喷嘴之间的距离最小化，这由于减少的负载和较少的部件而能够显着减轻重量。还提供了一种新颖的锁，用于同时锁定推力反向器门和致动器。

97. 发明授权

US06810656B2 Thrust reverser system power drive unit with dual sequential torque decoupler and method 失效
标题翻译：推力逆变器系统动力驱动单元采用双顺序扭矩分离器和方法
公开(公告)号：US06810656B2
公开(公告)日：2004-11-02
申请号：US10317885
申请日：2002-12-12
申请人： Robert D. Kortum , Andrew T. Johnson
发明人： Robert D. Kortum , Andrew T. Johnson
IPC分类号： F02K154
CPC分类号： F02K1/76 , F02K1/763
摘要： A thrust reverser system that includes one or more power drive units operable to supply a drive force. The power drive unit includes a motor and at least two output sections, each operably coupled to transmit the drive force to the thrust reverser movable components. Each of the output sections is operable to decouple the motor from associated thrust reverser movable components upon a torque magnitude being reached in the output section. A deadband coupler is provided to couple the first and second output sections together a time period after the torque magnitude is reached in one of the output sections.
摘要翻译：推力反向器系统，其包括可操作以提供驱动力的一个或多个动力驱动单元。动力驱动单元包括马达和至少两个输出部分，每个输出部分可操作地联接以将驱动力传递到推力反向器可移动部件。每个输出部分可操作以在输出部分中达到转矩幅度时将马达与相关联的推力反向器可移动部件分离。提供死区耦合器以在输出部分之一达到转矩幅度之后的时间周期将第一和第二输出部分耦合在一起。

98. 发明申请

US20040112040A1 Thrust reverser system power drive unit with dual sequential torque decoupler and method 失效
公开(公告)号：US20040112040A1
公开(公告)日：2004-06-17
申请号：US10317885
申请日：2002-12-12
发明人： Robert D. Kortum , Andrew T. Johnson
IPC分类号： F02K001/54
CPC分类号： F02K1/76 , F02K1/763
摘要： A thrust reverser system that includes one or more power drive units operable to supply a drive force. The power drive unit includes a motor and at least two output sections, each operably coupled to transmit the drive force to the thrust reverser movable components. Each of the output sections is operable to decouple the motor from associated thrust reverser movable components upon a torque magnitude being reached in the output section. A deadband coupler is provided to couple the first and second output sections together a time period after the torque magnitude is reached in one of the output sections.

99. 发明申请

US20030159429A1 Gearless electric thrust reverser actuators and actuation system incorporating same 有权
标题翻译：无齿轮电动推力反向器执行器和并入其的致动系统
公开(公告)号：US20030159429A1
公开(公告)日：2003-08-28
申请号：US10083854
申请日：2002-02-27
发明人： Todd A. Langston , Andrew T. Johnson , Terry J. Ahrendt
IPC分类号： F02K001/54
CPC分类号： F02K1/76 , F02K1/763 , Y02T50/671
摘要： A gearless electric thrust reverser actuator includes an electric motor that is coupled to a jack screw without any intervening gears. The actuator may additionally include all of the actuation and sensing components in a single actuation package. Thus, the actuator is relatively lightweight and compact.
摘要翻译：无齿轮电动推力反向器致动器包括电动马达，其连接到千斤顶螺钉，而没有任何中间齿轮。致动器可另外包括单个致动包中的所有致动和感测部件。因此，致动器相对较轻且紧凑。

100. 发明授权

US06546716B2 Jet engine nozzle with variable thrust vectoring and exhaust area 失效
公开(公告)号：US06546716B2
公开(公告)日：2003-04-15
申请号：US09842178
申请日：2001-04-26
申请人： Jean-Pierre Lair
发明人： Jean-Pierre Lair
IPC分类号： F02K110
CPC分类号： B64C15/02 , F02K1/002 , F02K1/006 , F02K1/04 , F02K1/11 , F02K1/15 , F02K1/54 , F02K1/60 , F02K1/70 , F02K1/76 , F02K1/805 , F05D2240/55 , Y02T50/672
摘要： A variable area exhaust nozzle with a variable thrust vector angle for a turbo-fan engine and mounted on the aft portion of the nacelle which wraps said engine. The nozzle may include a fixed structure having at least two lateral arms separating two radial cutouts. The cutouts are positioned one above the other, one being located above the engine axis, the other one below the engine axis. At least two shells close the fixed structure cutouts and are pivotally mounted on the fixed structure to form a portion of the exhaust nozzle of the engine. A sealing means ensures fluid tightness between the shells and the fixed structure for any angular position of said shells. Actuator means are provided for pivoting the shells either to a symmetrical configuration for changing of the value of the exhaust area of the nozzle or to an unsymmetrical configuration for changing the angle of the thrust vector of the exhaust nozzle. In operation, the value of the exhaust area and the thrust vector angle of the exhaust nozzle are varied during flight to optimize performance of the aircraft.

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