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1. 发明申请

US20180094605A1 TURBOFAN ENGINE FOR A CIVIL SUPERSONIC AIRCRAFT 审中-公开
公开(公告)号：US20180094605A1
公开(公告)日：2018-04-05
申请号：US15720935
申请日：2017-09-29
申请人： Rolls-Royce Deutschland Ltd & Co KG
发明人： Knut ROSENAU , James Robert MCLEAVY HILL
IPC分类号： F02K1/09 , F02K1/44 , F02K1/60 , F02K1/76 , F02K3/06
CPC分类号： F02K1/09 , F02K1/1223 , F02K1/44 , F02K1/60 , F02K1/763 , F02K3/06 , F05D2220/80 , F05D2260/96
摘要： A turbofan engine for a civil supersonic aircraft, including: an engine intake; a multi-stage fan that is arranged behind the engine intake; a core engine that comprises a compressor, a combustion chamber and a turbine; a primary flow channel that leads through the core engine; a secondary flow channel that leads past the core engine; an adjustable converging-diverging thrust nozzle that forms a nozzle throat area and a nozzle outlet area, wherein at least the nozzle throat area is adjustable; and a thrust reverser that is integrated in the adjustable converging-diverging thrust nozzle.

2. 发明授权

US09915226B2 Variable area fan nozzle hidden blocker door thrust reverser 有权
公开(公告)号：US09915226B2
公开(公告)日：2018-03-13
申请号：US14743649
申请日：2015-06-18
申请人： Rohr, Inc.
发明人： Timothy Gormley
IPC分类号： F02K1/72 , F02K1/09
CPC分类号： F02K1/72 , F02K1/09
摘要： A thrust reverser of an aircraft comprises a blocker door and a variable area fan nozzle (VAFN) panel configured to conceal the blocker door from a duct associated with a bypass fan flow when the VAFN panel is in a closed position.

3. 发明授权

US09745918B2 Gas turbine engine with noise attenuating variable area fan nozzle 有权
公开(公告)号：US09745918B2
公开(公告)日：2017-08-29
申请号：US14609800
申请日：2015-01-30
申请人： United Technologies Corporation
发明人： Jonathan Gilson , Dennis Cicon , Oliver V. Atassi
IPC分类号： F02K1/09 , F02K1/00 , F02K1/82
CPC分类号： F02K1/09 , F02K1/002 , F02K1/827 , F05D2260/96
摘要： A nacelle assembly for a high-bypass gas turbine engine includes a core nacelle defined about an engine centerline axis. A fan nacelle is mounted at least partially around the core nacelle to define a fan bypass flow path. A variable area fan nozzle is in communication with the fan bypass flow path. The variable area fan nozzle has a first fan nacelle section and a second fan nacelle section. The second fan nacelle section is axially movable relative to the first fan nacelle section to define an auxiliary port at a non-closed position to vary a fan nozzle exit area and adjust fan bypass airflow. The second fan nacelle section includes an acoustic system that has an acoustic impedance located on a radially outer surface.

4. 发明申请

US20170167441A1 DIELECTRIC SEAL DEVICE 审中-公开
公开(公告)号：US20170167441A1
公开(公告)日：2017-06-15
申请号：US14964363
申请日：2015-12-09
申请人： Rohr, Inc.
发明人： Joel H. Frank , Lubomir A. Ribarov
IPC分类号： F02K1/80 , F02K1/08 , F16J15/02
CPC分类号： F02K1/805 , F02K1/09 , F05D2240/55 , F16J15/022 , F16J15/061 , F16J15/068 , H01L41/193
摘要： A seal device that may be for a variable area fan nozzle (VAFN) assembly of a turbofan engine is positioned between first and second surfaces configured to move between close and distant positions. The seal device includes a first electrode engaged to the first surface and a second electrode spaced between the first and second surfaces and spaced from the first electrode. A resilient first element of the device is disposed between and engages to the first and second electrodes, and is configured to move between contracted and expanded states when the electrodes are energized. A resilient second element of the device opposes the second surface and is engaged to the second electrode. The second element is configured to move between a compressed mode when the first and second surfaces are in the close position and an extended mode when the first and second surfaces are in the distant position.

5. 发明申请

US20170138305A1 ACTUATING DEVICE FOR MOVING A MOVABLE COVER OF A THRUST REVERSER 审中-公开
公开(公告)号：US20170138305A1
公开(公告)日：2017-05-18
申请号：US15216631
申请日：2016-07-21
申请人： SAFRAN ELECTRONICS & DEFENSE
发明人： Mickael WERQUIN , David CHARRIER , Oleg GOMOLKO , Pascal OMNES
IPC分类号： F02K1/76 , F16H25/24
CPC分类号： F02K1/763 , F02K1/09 , F02K1/72 , F02K1/766 , F16H25/20 , F16H25/2454 , Y10T74/18704
摘要： An actuating device for moving a mobile cap of a thrust reverser, which includes: an actuator having a first element, such as a screw, and a second element, such as a nut, collaborating with the first element in such a way that turning the first element causes the second element to move in a translational movement. A locking piece is rotationally mobile between a locked position in which the locking piece prevents the first element from turning, and an unlocked position in which the locking piece allows the first element to turn. An unlocking piece is rotationally mobile between an active position in which the unlocking piece urges the locking piece towards the unlocked position and a passive position in which the unlocking piece allows the locking piece to return to the locked position.

6. 发明授权

US09551298B2 Variable area fan nozzle with one or more integrated blocker doors 有权
标题翻译：具有一个或多个集成阻塞门的可变区域风扇喷嘴
公开(公告)号：US09551298B2
公开(公告)日：2017-01-24
申请号：US13949998
申请日：2013-07-24
申请人： Rohr, Inc.
发明人： Alan Binks , Michael J. Layland , Norman J. James
IPC分类号： F02K1/72 , F02K1/09 , F02K1/76
CPC分类号： F02K1/72 , F02K1/09 , F02K1/763 , F02K1/766 , F05D2260/57
摘要： A nacelle assembly for a turbofan engine includes a forward nacelle portion having an aft edge and defining a bypass duct that transports bypass airflow of the turbofan engine, a translatable sleeve that is translatable aft of the forward nacelle portion, and a variable area fan nozzle (VAFN) airfoil that is movable between a stowed position, a VAFN flow position, and a thrust reverse position. Blocker doors for the thrust position are integrated into the VAFN airfoil.
摘要翻译：用于涡轮风扇发动机的机舱组件包括具有后缘并且限定输送涡轮风扇发动机的旁路气流的旁通管道的前部机舱部分，可向前的机舱部分的可平移的可平移的套筒以及可变区域的风扇喷嘴（ VAFN）翼型件，其可在收起位置，VAFN流动位置和推力倒置位置之间移动。用于推力位置的阻挡门被集成到VAFN翼型中。

7. 发明申请

US20160222917A1 NACELLE FOR AN AIRCRAFT ENGINE WITH VARIABLE SECTION NOZZLE 审中-公开
标题翻译：用于具有可变部分喷嘴的飞机发动机的NACELLE
公开(公告)号：US20160222917A1
公开(公告)日：2016-08-04
申请号：US15093805
申请日：2016-04-08
申请人： AIRCELLE
发明人： Peter SEGAT , Sarah TISSOT , Xavier BOUTEILLER
IPC分类号： F02K1/76 , B64D33/04 , F02K1/72
CPC分类号： F02K1/763 , B64D33/04 , F02K1/09 , F02K1/1261 , F02K1/72 , F02K1/766 , F05D2220/323 , F05D2240/128 , F05D2240/129
摘要： The present disclosure concerns a nacelle for an aircraft engine, which includes a thrust reverser cowling that is slidably mounted between a direct jet position, and a reversed jet position in which the cowling opens a passage in the nacelle and uncovers a deflection device, and at least one actuator for moving the cowling. The nozzle section of the cowling delimits at least one opening that is combined with a leakage door, the leakage door being movably mounted on the cowling between a closed position in which the door engages with the associated opening to counteract the flow of air through said opening, and an open escape position in which the door is retracted to allow a portion of the air flow to flow through said opening.
摘要翻译：本公开涉及一种用于飞行器发动机的机舱，其包括可滑动地安装在直接喷射位置和反向喷射位置之间的推力反向器整流罩，在该反向喷射位置中，整流罩打开机舱中的通道并露出偏转装置，并且在至少一个用于移动整流罩的致动器。整流罩的喷嘴部分限定了与泄漏门组合的至少一个开口，泄漏门可移动地安装在整流罩上，在关闭位置之间，门与相关联的开口啮合以抵消空气流过所述开口以及敞开的逃逸位置，其中门缩回以允许空气流的一部分流过所述开口。

8. 发明申请

US20160208641A9 TRANSLATING VARIABLE AREA FAN NOZZLE PROVIDING AN UPSTREAM BYPASS FLOW EXIT 有权
标题翻译：提供可变区域风扇喷嘴提供上升旁通流量出口
公开(公告)号：US20160208641A9
公开(公告)日：2016-07-21
申请号：US13770455
申请日：2013-02-19
申请人： ROHR, INC.
发明人： Daniel M. Amkraut , Michael John Layland , Norman John James
IPC分类号： F01D25/00
CPC分类号： F01D25/00 , F02K1/09 , F02K3/06 , F05D2260/606
摘要： A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating nozzle segment having a forward edge and a first end. The nozzle segment is movably disposed behind the aft edge such that an upstream bypass flow exit is defined between the aft edge and the forward edge when the nozzle segment is in a deployed position. A deflector is disposed between the aft edge and the forward edge proximate to the first end. The deflector substantially prevents bypass flow from exiting the upstream bypass flow exit in a region that is proximate to the first end.
摘要翻译：用于涡轮风扇发动机的可变区域风扇喷嘴组件包括具有后边缘的机舱和具有前边缘和第一端的平移喷嘴段。喷嘴段可移动地设置在后边缘之后，使得当喷嘴段处于展开位置时，在后边缘和前边缘之间限定上游旁路流出口。偏转器设置在靠近第一端的后边缘和前边缘之间。偏转器基本上防止在接近第一端的区域中旁路流离开上游旁路流出口。

9. 发明申请

US20160160798A1 INTEGRATED THRUST REVERSER DEVICE AND AIRCRAFT ENGINE NACELLE EQUIPPED THEREWITH 有权
标题翻译：集成式逆向装置和飞机发动机装置
公开(公告)号：US20160160798A1
公开(公告)日：2016-06-09
申请号：US15017931
申请日：2016-02-08
申请人： AIRCELLE
发明人： Philipe GUERIN , Olivier KERBLER , Jean-Paul RAMI
IPC分类号： F02K1/72
CPC分类号： F02K1/72 , F02K1/09 , F02K1/62 , F02K1/625 , F02K1/70 , F02K1/76 , F02K1/763 , F02K1/766 , F02K3/06
摘要： The present disclosure provides a thrust reverser device that is integrated in an aircraft nacelle. Blocking flaps are stored inside a mobile cowl disposed in a downstream section of the nacelle, under deflection cascade assemblies during direct-jet operation of the nacelle. Various devices are provided for executing the passage from direct-jet operation to reverse-jet operation in two stages: the mobile cowl moves in translation towards the downstream end of the nacelle; and each flap is then deployed in the main air flow path.
摘要翻译：本公开提供了集成在飞机机舱中的推力反向装置。在机舱的直接喷射操作期间，阻挡翼片存储在设置在机舱的下游部分中的可移动的整流罩内，在偏转级联组件下。提供了用于执行从直接喷射操作到反向喷射操作的两个阶段的通道的各种装置：移动整流罩朝向机舱的下游端移动; 然后将每个翼片部署在主空气流路中。

10. 发明授权

US09303590B2 Variable area fan nozzle actuation system 有权
标题翻译：可变区域风扇喷嘴致动系统
公开(公告)号：US09303590B2
公开(公告)日：2016-04-05
申请号：US13477250
申请日：2012-05-22
申请人： Randall Ray West , Joe Everet Sternberger
发明人： Randall Ray West , Joe Everet Sternberger
IPC分类号： F02K3/075 , F02K1/09 , F02K1/76
CPC分类号： F02K3/075 , F02K1/09 , F02K1/763 , F02K1/766
摘要： An aircraft nacelle having a fixed structure fixed relative to an aircraft pylon, a translating thrust reverser sleeve translatable aftward, relative to the fixed structure, and a translating variable area fan nozzle (VAFN) panel translatable aftward, relative to the translating thrust reverser sleeve. The nacelle may also include a VAFN actuator mounted on the translating thrust reverser sleeve and a VAFN drive unit attached to the fixed structure. The VAFN drive unit may be coupled to drive the VAFN actuator via first and second coupling components when the translating thrust reverser sleeve is stowed. When the translating thrust reverser sleeve is deployed, the first and second coupling components may decouple, disconnecting the VAFN drive unit from the VAFN actuator.
摘要翻译：具有相对于飞机塔架固定的固定结构的飞机机舱，相对于固定结构向后可平移的平移推力反向器套筒以及相对于平移推力反向器套筒向后平移的平移可变区域风扇喷嘴（VAFN）面板。机舱还可以包括安装在平移推力反向器套筒上的VAFN致动器和附接到固定结构的VAFN驱动单元。当平移推力反向器套筒被收起时，VAFN驱动单元可以被联接以通过第一和第二联接部件驱动VAFN致动器。当平移推力反向器套筒被部署时，第一和第二联接部件可以解耦，将VAFN驱动单元与VAFN致动器断开连接。

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