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1. 发明申请

US20180180119A1 DAMPED ANTI-ROTATIONAL SYSTEMS 审中-公开
公开(公告)号：US20180180119A1
公开(公告)日：2018-06-28
申请号：US15901518
申请日：2018-02-21
申请人： United Technologies Corporation
发明人： Christopher T. Anglin , Yuk-Kwan Brian Yuen , Russell B. Witlicki
IPC分类号： F16D65/02 , F02C7/00 , F02C7/36
CPC分类号： F16D65/02 , F02C7/00 , F02C7/36 , F05D2260/90 , F05D2260/96 , F16D2300/22
摘要： A damped anti-rotational system is provided comprising a pawl carrier having an axis of rotation, a pawl pivotably mounted to the pawl carrier on a pivot joint, the pawl having a contact portion and a counterweight portion, a stop pin axially disposed in the pawl carrier and configured to contact the contact portion of the pawl in response to radially inward movement of the pawl, wherein the stop pin is mounted to the pawl carrier at a forward portion of the stop pin and an aft portion of the stop pin, wherein a forward O ring is disposed on the forward portion of the stop pin and an aft O ring is disposed on the aft portion of the stop pin.

2. 发明授权

US09933027B2 Damped anti-rotational systems 有权
公开(公告)号：US09933027B2
公开(公告)日：2018-04-03
申请号：US15601663
申请日：2017-05-22
申请人： United Technologies Corporation
发明人： Christopher T. Anglin , Yuk-Kwan Brian Yuen , Russell B. Witlicki
IPC分类号： F16D65/02 , F02C7/00 , F02C7/36
CPC分类号： F16D65/02 , F02C7/00 , F02C7/36 , F05D2260/90 , F05D2260/96 , F16D2300/22
摘要： A damped anti-rotational system is provided comprising a pawl carrier having an axis of rotation, a pawl pivotably mounted to the pawl carrier on a pivot joint, the pawl having a contact portion and a counterweight portion, a stop pin axially disposed in the pawl carrier and configured to contact the contact portion of the pawl in response to radially inward movement of the pawl, wherein the stop pin is mounted to the pawl carrier at a forward portion of the stop pin and an aft portion of the stop pin, wherein a forward O ring is disposed on the forward portion of the stop pin and an aft O ring is disposed on the aft portion of the stop pin.

3. 发明授权

US09863367B2 Fan nozzle drive systems that lock thrust reversers 有权
公开(公告)号：US09863367B2
公开(公告)日：2018-01-09
申请号：US14070393
申请日：2013-11-01
申请人： THE BOEING COMPANY
发明人： Michael J. Burghdoff , Jerry Edward Farstad
IPC分类号： F02K1/72 , F02K1/76 , F02K1/12 , F02K1/62
CPC分类号： F02K1/766 , F02K1/1207 , F02K1/625 , F02K1/72 , F02K1/763 , F05D2220/36 , F05D2260/30 , F05D2260/53 , F05D2260/90 , F05D2270/051
摘要： Systems and methods are provided that lock thrust reversers and also drive fan nozzles of an aircraft. One system includes a coupling configured to selectively engage and disengage. While engaged, the coupling is configured to rotate to drive a Variable Area Fan Nozzle (VAFN), at least a portion of which is on a translating portion of a thrust reverser of an aircraft. Furthermore, while engaged the coupling is configured to prevent displacement of the translating portion.

4. 发明授权

US09145830B2 Turbomachine geared architecture support assembly 有权
标题翻译：涡轮机齿轮架构支架
公开(公告)号：US09145830B2
公开(公告)日：2015-09-29
申请号：US13487661
申请日：2012-06-04
申请人： Jason Husband , James B. Coffin
发明人： Jason Husband , James B. Coffin
IPC分类号： F02C7/36 , F02C3/107 , F02K3/06 , F04D25/02
CPC分类号： F02C3/107 , F02C7/36 , F02K3/06 , F04D25/028 , F05D2260/40311 , F05D2260/90 , Y10T29/49826
摘要： An example turbomachine geared architecture support assembly includes a compliant member configured to hold a geared architecture within a turbomachine. The compliant member has a compliant section that permits rotation of the geared architecture relative to a fixed portion of the turbomachine. A stop limits rotation of the geared architecture relative to the fixed portion of the turbomachine.
摘要翻译：涡轮机械齿轮架构支撑组件的示例包括配置成在涡轮机内保持齿轮架构的顺应部件。柔性构件具有允许齿轮架构相对于涡轮机的固定部分旋转的柔性部分。停止限制齿轮架构相对于涡轮机的固定部分的旋转。

5. 发明授权

US08979506B2 Reverse rotation prevention device 有权
标题翻译：反转防止装置
公开(公告)号：US08979506B2
公开(公告)日：2015-03-17
申请号：US11333570
申请日：2006-01-17
申请人： Omar M. Kabir , Edward S. Czechowski
发明人： Omar M. Kabir , Edward S. Czechowski
IPC分类号： F04B49/00 , F04D25/16 , F04D27/00 , F16D41/12 , F16D41/18 , B60T1/00 , F16D63/00 , F16D27/00 , F16D121/18 , F16D127/00
CPC分类号： F04D25/163 , B60T1/005 , F04D27/008 , F04D27/0292 , F05D2260/90 , F16D27/00 , F16D41/12 , F16D41/18 , F16D63/006 , F16D2121/18 , F16D2127/004
摘要： Apparatus and methods to prevent the rotation of a shaft in one direction using a device comprising a collar disposed around the shaft, a locking arm with an unlocked position and a locked position, and an actuator capable of moving the locking-arm between the unlocked and locked position. When the locking arm is in the unlocked position, the collar and shaft are allowed to rotate in a first direction. However, when the locking arm is in the locked position, the collar and shaft are prevented from rotating in a second direction. This device can also be used to prevent the reverse rotation of a rotating compressor.
摘要翻译：使用包括设置在轴周围的轴环的装置，具有解锁位置的锁定臂和锁定位置来防止轴在一个方向上旋转的装置和方法，以及能够将锁定臂移动在解锁和锁定位置。当锁定臂处于解锁位置时，允许轴环和轴沿第一方向旋转。然而，当锁定臂处于锁定位置时，防止轴环和轴沿第二方向旋转。该装置也可用于防止旋转压缩机的反向旋转。

6. 发明申请

US20130097998A1 THRUST REVERSER FOR AN AIRCRAFT HAVING SEMI-RECESSED TURBOFAN ENGINES 有权
标题翻译：具有半密闭涡轮发动机的飞机的扭矩反转器
公开(公告)号：US20130097998A1
公开(公告)日：2013-04-25
申请号：US13520917
申请日：2010-12-27
申请人： Jacques Herve Marche
发明人： Jacques Herve Marche
IPC分类号： F02K1/70
CPC分类号： F02K1/70 , F02K1/62 , F05D2240/12 , F05D2260/90 , Y02T50/672
摘要： A jet propulsion unit of an aircraft, which comprises a turbofan engine (3) faired by a nacelle (1), further comprising a thrust reverser device in two parts: one part and including a means for flowing back the air (15) towards the outside of the propulsive unit, in a first angular sector of the nacelle; one part including internal backflow means which can be removed and controlled, suitable for channeling the secondary air flow, circulating in a secondary duct between the propulsive unit and the nacelle, in a second angular sector of the nacelle such as to offset the latter angularly in the secondary duct towards some external thrust reverser means. The internal backflow means comprise at least two mobile surfaces (22, 23), with each one rotatably hinged between an inoperative position in which a mobile surface is continuous with the internal surface of the nacelle, and a thrust reversal position, in which the said mobile surfaces (22, 23) locally interrupt the longitudinal secondary air flow, and channel it gradually toward some of the air backflow means.
摘要翻译：一种飞机的喷气式推进单元，包括由机舱（1）流下的涡轮风扇发动机（3），还包括两部分的推力反向装置：一部分，并且包括用于将空气（15）向后流动的装置在推进单元外部，在机舱的第一角度部分; 一个部分包括可以被移除和控制的内部回流装置，适合于在机舱的第二角度部分中引导在推进单元和机舱之间的次级管道中循环的二次空气流，以便将后者角度地偏置次级管道朝向一些外部推力反向器装置。内部回流装置包括至少两个可移动表面（22,23），每个移动表面（22,23）可旋转地铰接在不可操作的位置，其中移动表面与机舱的内表面连续，并且推力反转位置，其中所述移动表面（22,23）局部地中断纵向二次空气流动，并逐渐向其中的一些空气回流装置引导。

7. 发明申请

US20090015011A1 DEVICE FOR PRODUCING ELECTRICAL POWER IN A TWO-SPOOL GAS TURBINE ENGINE 有权
标题翻译：在两台气体涡轮发动机中生产电力的装置
公开(公告)号：US20090015011A1
公开(公告)日：2009-01-15
申请号：US12109929
申请日：2008-04-25
申请人： Antoine Olivier Francois Colin , Arnaud Lebrun , Gilles Barjon
发明人： Antoine Olivier Francois Colin , Arnaud Lebrun , Gilles Barjon
IPC分类号： F02C6/00
CPC分类号： F02C7/32 , F01D15/10 , F05D2260/85 , F05D2260/90 , H02K7/14 , H02K7/1823 , H02K16/005
摘要： The invention relates to a device for producing electrical power in a multi-spool gas turbine engine comprising at least one first rotary spool (69), for example a low-pressure spool, and a second rotary spool (24), for example a high-pressure spool, and driving an electrical machine (10). The device is one wherein, with the electrical machine (10) being of the twin-rotor type with a first rotor (13) and a second rotor (14), the first rotor (13) is mechanically connected to the first rotary spool (69) and the second rotor is mechanically connected to the second rotary spool (24).
摘要翻译：本发明涉及一种用于在多线轴燃气涡轮发动机中产生电力的装置，其包括至少一个第一旋转阀芯（69），例如低压阀芯和第二旋转阀芯（24），例如高压力阀芯，以及驱动电机（10）。该装置是其中，电机（10）是具有第一转子（13）和第二转子（14）的双转子类型，第一转子（13）机械地连接到第一旋转线轴（ 69），并且第二转子机械地连接到第二旋转滑阀（24）。

8. 发明申请

US20060005544A1 Synchronizing stationary clutch for compression braking with a two spool gas turbine engine 失效
标题翻译：与两个卷烟机涡轮发动机同步用于压缩制动的固定离合器
公开(公告)号：US20060005544A1
公开(公告)日：2006-01-12
申请号：US10889672
申请日：2004-07-12
申请人： Christopher Herlihy
发明人： Christopher Herlihy
IPC分类号： F02C3/107
CPC分类号： F16D48/06 , F01D15/02 , F01D15/12 , F02C3/107 , F02C7/36 , F05D2260/4023 , F05D2260/40311 , F05D2260/85 , F05D2260/90 , F05D2260/901 , F05D2260/902 , F16D2500/106 , F16D2500/1087 , F16D2500/50227 , F16D2500/504 , Y10S74/05
摘要： A synchronizing stationary clutch system for compression braking in a two spool gas turbine engine is provided by the present invention. The synchronizing stationary clutch system allows the two shafts of a two spool gas turbine engine to be reliably coupled at any given speed of either shaft. This coupling ability is useful to a gas turbine engine functioning in a land vehicle for the purpose of slowing the forward momentum of a rolling vehicle. The clutch system may also allow the use of auxiliary power from an electrical motor to start the engine.
摘要翻译：本发明提供了一种用于两个卷筒燃气涡轮发动机中的压缩制动的同步静止离合器系统。同步静止离合器系统允许两个卷轴燃气涡轮发动机的两个轴以任一轴的任何给定速度可靠地联接。这种耦合能力对于在陆地车辆中起作用以减缓滚动车辆的向前动量的目的的燃气涡轮发动机是有用的。离合器系统还可以允许使用来自电动机的辅助动力来起动发动机。

9. 发明申请

US20180297567A1 METHOD AND SYSTEM FOR CONTROLLING THE BRAKING OF AN AIRCRAFT EQUIPPED WITH A THRUST-REVERSAL SYSTEM 审中-公开
公开(公告)号：US20180297567A1
公开(公告)日：2018-10-18
申请号：US16010868
申请日：2018-06-18
申请人： Safran Nacelles , Safran Landing Systems
发明人： Patrick GONIDEC , Hakim MAALIOUNE , François TAILLARD , Denis JONTEF , Marie-Laure DE-CRESCENZO , Jean-François HAMMANN
IPC分类号： B60T8/17 , B64C25/42 , F02K1/76 , B60T8/171 , B60T8/1761
CPC分类号： B60T8/1703 , B60T8/171 , B60T8/17616 , B64C25/42 , F02K1/76 , F05D2220/323 , F05D2260/90 , F05D2260/901 , F05D2260/902 , Y02T50/671
摘要： The present disclosure relates to a method of controlling the braking of an aircraft equipped with a landing gear bearing braked wheels, the aircraft being propelled by jet engines and equipped with a thrust reversal system, the method involving the steps of estimating the grip/adhesion of the braked wheels and activating the thrust-reversal system or modulating the reverse-thrust generated by the thrust-reversal system if this system is already activated, based on the estimated grip/adhesion.

10. 发明授权

US09982558B2 Steam turbine 有权
公开(公告)号：US09982558B2
公开(公告)日：2018-05-29
申请号：US14777982
申请日：2013-03-22
申请人： MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
发明人： Makoto Katagake
IPC分类号： F01D17/18 , F01D17/14 , F01D21/00 , F01D17/24 , F01D21/14
CPC分类号： F01D17/18 , F01D17/145 , F01D17/24 , F01D21/006 , F01D21/14 , F05D2220/31 , F05D2260/90 , F05D2270/09
摘要： A steam turbine includes a turbine body; a steam flow passage; a regulating valve which regulates opening and closing of the steam flow passage with a linear motion; a switching drive mechanism which drives the regulating valve; an electronic governor which controls at least the switching drive mechanism; and a controller unit. The switching drive mechanism has an electric motor which rotates when supplied with power, a conversion mechanism which converts a rotary motion of the electric motor into a linear motion of the regulating valve, and a brake which brakes the rotary motion of the electric motor. At least one of the controller unit and the electronic governor performs control such that the brake is actuated and the position of the regulating valve is maintained when at least one of the electric motor and the controller unit breaks down.

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