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.

公开(公告)号：US20050279081A1

公开(公告)日：2005-12-22

申请号：US11155511

申请日：2005-06-20

申请人： Alain Lardellier

发明人： Alain Lardellier

IPC分类号： B64C7/02 ,  B64D29/00 ,  B64D33/04 ,  F02K1/56 ,  F02K1/64 ,  F02K1/70 ,  F02K3/06 ,  F03H99/00 ,  F02K3/04

CPC分类号： F02K1/64 ,  B64C7/02 ,  B64D33/04 ,  F02K1/563 ,  F02K1/70 ,  F02K3/06 ,  F03H99/00 ,  F05D2260/90 ,  F05D2260/901

摘要： The braking method for an aircraft propelled by at least one ducted fan jet engine, the latter comprising a fan, a jet engine core in which the primary flow circulates, a secondary flow exhaust nozzle, encased in a nacelle, comprises the step, in low-power operation, of unloading at least part of the secondary flow so as to reduce the residual thrust of the jet engine without producing any thrust. With the method of the invention, aircraft braking can be achieved without any thrust reverser device using the braking force generated by the drag of the jet engine or engines completed by reduction of residual thrust by unloading the secondary flow.

摘要翻译： 用于由至少一个管道式风扇喷气发动机推进的飞行器的制动方法，后者包括风扇，主流循环的喷气发动机芯，包封在机舱中的二次排气喷嘴，包括该步骤，低于 卸载二次流的至少一部分，以减少喷气发动机的剩余推力而不产生任何推力。 利用本发明的方法，可以实现飞机制动，而没有任何推力反向器装置使用由喷射发动机或发动机的拖动产生的制动力，其通过卸载二次流而减少残余推力而完成。

公开(公告)号：US09127623B2

公开(公告)日：2015-09-08

申请号：US14271626

申请日：2014-05-07

申请人： AIRCELLE

发明人： Vincent Peyron

IPC分类号： F02K1/76 ,  F02K1/72 ,  F02K1/56 ,  F02K1/54 ,  F02K1/32 ,  F02K1/70

CPC分类号： F02K1/763 ,  F02K1/32 ,  F02K1/54 ,  F02K1/56 ,  F02K1/70 ,  F02K1/72 ,  F05D2260/901 ,  F05D2270/66 ,  Y02T50/671

摘要： A thrust reverser device for a turbojet engine nacelle includes a cowl mounted translating between a closing position and an opening position in which the cowl opens a passage in the nacelle and uncovers deflecting cascades. The cowl is associated with a blocking flap pivotally mounted on the cowl between a retracted position and a pivoted blocking position in which the blocking flap closes partially an air flow path of the nacelle. The blocking flap is equipped with a driving mechanism including an assembly forming a lever pivotally mounted on the cowl and articulated at each of ends of the lever, by means of driving links, respectively on the blocking flap and on a fixed structure of the thrust reverser device. In particular, the assembly and the driving links are articulated in an articulation plane substantially perpendicular to the blocking flap and substantially radial to the thrust reverser device.

摘要翻译： 用于涡轮喷气发动机机舱的推力反向装置包括在关闭位置和打开位置之间平移的整流罩，其中整流罩在机舱中打开通道并且露出偏转级联。 整流罩与在缩回位置和枢转阻断位置之间枢转地安装在整流罩上的阻挡盖相关联，其中阻挡片部分地封闭机舱的空气流动路径。 挡板装有一个驱动机构，该驱动机构包括一个组件，该组件形成一个可枢转地安装在整流罩上的杠杆，并分别通过驱动连杆分别在挡板上和推力反向器的固定结构上铰接在杠杆的每个端部 设备。 特别地，组件和驱动连杆在基本上垂直于阻挡挡板的关节平面中铰接并且基本上径向铰接到推力反向器装置。

公开(公告)号：US20140360158A1

公开(公告)日：2014-12-11

申请号：US14328967

申请日：2014-07-11

申请人： AIRCELLE

发明人： Patrick Gonidec ,  Laurent Albert Blin ,  Xavier Bouteiller ,  LoÏc Chapelain

IPC分类号： F02K1/32

CPC分类号： F02K1/32 ,  F02K1/70 ,  F05D2260/901 ,  Y02T50/672

摘要： A thrust reverser for aircraft turbojet engine nacelle includes at least one upstream door and a downstream door. The upstream and downstream doors move in concert between a direct jet position and a reverse jet position. In the direct jet position, two doors are closed, and in the reverse jet position the two doors are open and able to deflect a part of a cold air flow circulating inside the nacelle. The thrust reverser further includes a curved downstream edge of the upstream door to make adapted a part of cold air flow circulating between an upper camber of the upstream door and a lower camber of the downstream door.

摘要翻译： 用于飞行器涡轮喷气发动机机舱的推力反向器包括至少一个上游门和下游门。 上游和下游门在直接喷射位置和反向喷射位置之间协调运动。 在直接喷射位置，两个门关闭，并且在反向喷射位置，两个门是敞开的，并且能够使在机舱内循环的一部分冷气流偏转。 推力反向器还包括上游门的弯曲的下游边缘，以使适应的一部分冷气流在上游门的上弯道和下游门的下弧面之间循环。

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。

公开(公告)号：US20240167432A1

公开(公告)日：2024-05-23

申请号：US18314322

申请日：2023-05-09

申请人： Woodward, inc.

发明人： Joseph Thomas Kopecek ,  William Muster

IPC分类号： F02K1/76 ,  F02K1/72

CPC分类号： F02K1/763 ,  F02K1/72 ,  F05D2260/4031 ,  F05D2260/406 ,  F05D2260/602 ,  F05D2260/605 ,  F05D2260/901

摘要： The subject matter of this specification can be embodied in, among other things, an actuator apparatus includes an output member configured to actuate between a first positional configuration and a second positional configuration, a source fluid reservoir, a fluid velocity resistor configured to provide a predetermined resistance to fluid flow, a fluid velocity fuse configured to flow fluid flows having a first predetermined range of fluid velocities and to block fluid flows having second predetermined range of fluid velocities, and a fluid actuator assembly configured to urge fluid flow from the source fluid reservoir through the fluid velocity resistor and the fluid velocity fuse based on actuation of the output member.

公开(公告)号：US20150176528A1

公开(公告)日：2015-06-25

申请号：US14271626

申请日：2014-05-07

申请人： AIRCELLE

发明人： Vincent PEYRON

IPC分类号： F02K1/76 ,  F02K1/72

CPC分类号： F02K1/763 ,  F02K1/32 ,  F02K1/54 ,  F02K1/56 ,  F02K1/70 ,  F02K1/72 ,  F05D2260/901 ,  F05D2270/66 ,  Y02T50/671

摘要： A thrust reverser device for a turbojet engine nacelle includes a cowl mounted translating between a closing position and an opening position in which the cowl opens a passage in the nacelle and uncovers deflecting cascades. The cowl is associated with a blocking flap pivotally mounted on the cowl between a retracted position and a pivoted blocking position in which the blocking flap closes partially an air flow path of the nacelle. The blocking flap is equipped with a driving mechanism including an assembly forming a lever pivotally mounted on the cowl and articulated at each of ends of the lever, by means of driving links, respectively on the blocking flap and on a fixed structure of the thrust reverser device. In particular, the assembly and the driving links are articulated in an articulation plane substantially perpendicular to the blocking flap and substantially radial to the thrust reverser device.

摘要翻译： 用于涡轮喷气发动机机舱的推力反向装置包括在关闭位置和打开位置之间平移的整流罩，其中整流罩在机舱中打开通道并且露出偏转级联。 整流罩与在缩回位置和枢转阻断位置之间枢转地安装在整流罩上的阻挡盖相关联，其中阻挡片部分地封闭机舱的空气流动路径。 挡板装有一个驱动机构，该驱动机构包括一个组件，该组件形成一个可枢转地安装在整流罩上的杠杆，并分别通过驱动连杆分别在挡板上和推力反向器的固定结构上铰接在杠杆的每个端部 设备。 特别地，组件和驱动连杆在基本上垂直于阻挡挡板的关节平面中铰接并且基本上径向铰接到推力反向器装置。

公开(公告)号：US20150137725A1

公开(公告)日：2015-05-21

申请号：US14578110

申请日：2014-12-19

申请人： AIRCELLE

发明人： Hakim MAALIOUNE ,  Alain NOURRISSON

IPC分类号： F02K1/76 ,  H02P7/06

CPC分类号： F02K1/763 ,  B64D33/04 ,  B64D41/00 ,  B64D2221/00 ,  F02K1/76 ,  F05D2260/901 ,  F05D2270/62 ,  H02P7/06 ,  Y02T50/44 ,  Y02T50/671

摘要： A thrust reverser device for an aircraft includes at least two thrust reversers, and each of them includes a movable cowl movably actuated by an actuator driven by an electric motor. The electric motor is powered by a single power-conversion module including at least one autotransformer which is supplied with an alternating electric voltage and connected to at least one rectifier stage converting the alternating electric voltage into a direct voltage. The rectifier stage is connected to a current balancing stage and a current smoothing stage, supplying with the direct voltage the electric motor of the electric actuator of the movable cowl.

摘要翻译： 用于飞行器的推力反向装置包括至少两个推力反向器，并且它们中的每一个包括由由电动机驱动的致动器可移动地致动的可动外罩。 电动机由单个功率转换模块供电，所述单个功率转换模块包括至少一个自耦变压器，该自耦变压器被提供有交流电压并且连接到将交流电压转换为直流电压的至少一个整流器级。 整流器级连接到电流平衡级和电流平滑级，向可动罩的电致动器的电动机提供直流电压。

公开(公告)号：US11686273B2

公开(公告)日：2023-06-27

申请号：US17068273

申请日：2020-10-12

申请人： Woodward, Inc.

发明人： Joseph Thomas Kopecek ,  William Muster

IPC分类号： F02K1/76 ,  F02K1/72

CPC分类号： F02K1/763 ,  F02K1/72 ,  F05D2260/406 ,  F05D2260/4031 ,  F05D2260/602 ,  F05D2260/605 ,  F05D2260/901

摘要： The subject matter of this specification can be embodied in, among other things, an actuator apparatus includes an output member configured to actuate between a first positional configuration and a second positional configuration, a source fluid reservoir, a fluid velocity resistor configured to provide a predetermined resistance to fluid flow, a fluid velocity fuse configured to flow fluid flows having a first predetermined range of fluid velocities and to block fluid flows having second predetermined range of fluid velocities, and a fluid actuator assembly configured to urge fluid flow from the source fluid reservoir through the fluid velocity resistor and the fluid velocity fuse based on actuation of the output member.

公开(公告)号：US09587584B2

公开(公告)日：2017-03-07

申请号：US14578110

申请日：2014-12-19

申请人： AIRCELLE

发明人： Hakim Maalioune ,  Alain Nourrisson

IPC分类号： H02P7/06 ,  F02K1/76 ,  B64D41/00 ,  B64D33/04

CPC分类号： F02K1/763 ,  B64D33/04 ,  B64D41/00 ,  B64D2221/00 ,  F02K1/76 ,  F05D2260/901 ,  F05D2270/62 ,  H02P7/06 ,  Y02T50/44 ,  Y02T50/671

摘要： A thrust reverser device for an aircraft includes at least two thrust reversers, and each of them includes a movable cowl movably actuated by an actuator driven by an electric motor. The electric motor is powered by a single power-conversion module including at least one autotransformer which is supplied with an alternating electric voltage and connected to at least one rectifier stage converting the alternating electric voltage into a direct voltage. The rectifier stage is connected to a current balancing stage and a current smoothing stage, supplying with the direct voltage the electric motor of the electric actuator of the movable cowl.

摘要翻译： 用于飞行器的推力反向装置包括至少两个推力反向器，并且它们中的每一个包括由由电动机驱动的致动器可移动地致动的可动外罩。 电动机由单个功率转换模块供电，所述单个功率转换模块包括至少一个自耦变压器，该自耦变压器被提供有交流电压并且连接到将交流电压转换为直流电压的至少一个整流器级。 整流器级连接到电流平衡级和电流平滑级，向可动罩的电致动器的电动机提供直流电压。