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1. 发明公开

EP3374837A1 MULTIFUNCTIONAL AERODYNAMIC, PROPULSION, AND THERMAL CONTROL SYSTEM 审中-公开
公开(公告)号：EP3374837A1
公开(公告)日：2018-09-19
申请号：EP16745907.2
申请日：2016-06-30
申请人： Raytheon Company
发明人： LYONS, Paul, M. , DANFORTH, Jeremy, C. , VOLLIN, Jeff, L. , SUMMERS, Matt, H.
IPC分类号： G05D23/01 , F25B9/02 , F25B19/00
CPC分类号： F42B15/34 , B64D27/00 , B64G1/40 , F25B9/02 , F25B19/005
摘要： An open-loop thermal control system and method for components that generate heat includes a reservoir for containing a pressurized working fluid, a first heat exchanger in thermal communication with the working fluid, a Joule-Thomson expansion valve in fluid communication with the reservoir, and a second heat exchanger in fluid communication with the valve. The first heat exchanger is configured to transfer heat from the components to the fluid in the reservoir. The valve is configured to expand the working fluid into a two-phase fluid having a primary use of cooling. The second heat exchanger is configured to receive heat from the components and receive the two-phase fluid. The second heat exchanger provides a single-phase working fluid for at least one secondary use before the working fluid is expelled from the thermal control system.

2. 发明公开

EP2163730A3 Method and system for controlling propeller overspeed 有权
标题翻译：用于控制螺旋桨超速的方法和系统
公开(公告)号：EP2163730A3
公开(公告)日：2018-01-03
申请号：EP09251852.1
申请日：2009-07-27
申请人： Rolls-Royce plc
发明人： Gainford, David Michael , Holt, Jonathan Edmund
IPC分类号： F01D21/02 , F02C9/00 , B64C11/30
CPC分类号： F01D21/02 , B64C11/306 , B64C11/48 , B64D27/00 , B64D35/06 , B64D2027/005 , B64D2027/026 , F02C9/00 , F05D2270/021 , Y02T50/44 , Y02T50/66 , Y02T50/671
摘要： An engine having at least one stage of propeller rotor blades, and a load, the at least one stage being associated with electrical generation means to generate electricity for the load. The load is switchable into a high load state in the event of an overspeed signal from the rotor blades. Also a method of controlling rotor overspeed of an engine, characterised by the steps of:
i. detecting an overspeed signal from the at least one stage, and
ii. switching the load into a high load state to apply torque to the at least one stage to counteract the overspeed.
摘要翻译：一种具有至少一级螺旋桨转子叶片的发动机以及一个负载，所述至少一个级与用于为负载发电的发电装置相关联。在来自转子叶片的超速信号的情况下，负载可切换到高负载状态。还是一种控制发动机转子超速的方法，其特征在于以下步骤：i。检测来自所述至少一个级的超速信号，以及ii。将负载切换到高负载状态以将扭矩施加到至少一个级以抵消超速。

3. 发明公开

EP3210659A1 DRONE MUNI D'UN BLOC BATTERIE À FONCTION RIGIDIFICATRICE 审中-公开
标题翻译：无人机具有电池组与加强功能
公开(公告)号：EP3210659A1
公开(公告)日：2017-08-30
申请号：EP17156320.8
申请日：2017-02-15
申请人： Parrot Drones
发明人： SANLAVILLE, Thierry , DUCLOUX, Maxime , MORRA, Flavien
IPC分类号： A63H27/00 , B64C39/02
CPC分类号： B64D27/00 , B64C27/08 , B64C39/024 , B64C2201/024 , B64C2201/027 , B64C2201/042 , B64C2201/108 , B64C2201/165 , B64D47/08
摘要： L'invention concerne un drone à voilure tournante (10) comprenant un corps de drone (22) et des bras de liaison (24, 26, 28, 30) comprenant à leur extrémité un bloc propulseur (32). Il comprend un bloc batterie (34) rigide comprenant au moins un moyen de fixation et un profil de guidage (48). Le corps de drone (22) comprend une plateforme (36) ayant au moins un rail de guidage (38) apte à coopérer avec le profil de guidage (48) du bloc batterie (34) et au moins un moyen de fixation complémentaire du moyen de fixation du bloc batterie de sorte que le bloc batterie rigidifie le corps de drone.
摘要翻译：本发明涉及包括无人驾驶飞机主体（22）和连接臂（24,26,28,30）的旋翼飞行器（10），连接臂（24,26,28,30）在其端部包括推进剂单元（32）。它包括刚性电池组（34），其包括至少一个固定装置和引导轮廓（48）。无人机主体（22）包括具有至少一个能够与电池组（34）的导向轮廓（48）配合的导轨（38）的平台（36），以及至少一个与该装置固定电池组，使电池组加强无人机主体。

4. 发明公开

EP2452876A3 Aircraft propulsion system and system for taxiing an aircraft 有权
标题翻译：飞机推进系统和系统用于飞行器的辊
公开(公告)号：EP2452876A3
公开(公告)日：2014-07-23
申请号：EP11250898.1
申请日：2011-11-16
申请人： Rolls-Royce Corporation
发明人： Burns, Donald , Rajashekara, Kaushik
IPC分类号： B64D27/00 , B64D33/00 , B64D35/00 , F02C7/32 , F02C7/36
CPC分类号： B64D27/00 , B64D33/00 , B64D35/00 , B64D2205/00 , F02C7/32 , F02C7/36 , Y02T50/44 , Y02T50/823
摘要： The present invention relates to a system for taxiing an aircraft without starting one or more main aircraft propulsion engines. In one embodiment, a low pressure spool of a gas turbine engine is driven by a mechanical coupling with an auxiliary power unit, and by an electrical machine.

5. 发明公开

EP2685065A2 A gas turbine engine 有权转让
标题翻译： Gasturbinenmotor
公开(公告)号：EP2685065A2
公开(公告)日：2014-01-15
申请号：EP13171359.6
申请日：2013-06-11
申请人： Rolls-Royce plc
发明人： Stretton, Richard , Howarth, Nicholas
IPC分类号： F02C3/067
CPC分类号： B64C11/001 , B64D27/00 , B64D2027/005 , F02C3/067 , F02C7/04 , F02C7/05 , F02K3/025 , F02K3/04 , F05D2220/323 , F05D2220/325 , F05D2240/302 , F05D2250/324 , F05D2250/51 , Y02T50/66 , Y02T50/671 , Y02T50/673
摘要： A gas turbine engine (10) having an axial flow direction (X) therethrough in use. The gas turbine engine (10) comprises one or more rotor stages each comprising at least one rotor blade (120) having a root portion (122). The gas turbine engine (10) comprises a shroud (126) located upstream of one or more of the rotor stages relative to the axial flow direction (X). The shroud (126) defines a through passageway (128) extending between an inlet (130) and an outlet (132) which comprises a diffuser region (138). The diffuser region (138) is configured to reduce the axial velocity of air exiting the outlet (132) relative to air entering the diffuser portion (138) in use, wherein the outlet (132) is located such that air exiting the outlet (132) is directed substantially to the root portion (122) only of the rotor blades (120).
摘要翻译：一种在使用中具有轴流动方向（X）的燃气轮机（10）。燃气涡轮发动机（10）包括一个或多个转子级，每个转子级包括至少一个具有根部（122）的转子叶片（120）。燃气涡轮发动机（10）包括相对于轴向流动方向（X）定位在一个或多个转子级的上游的护罩（126）。护罩（126）限定了在入口（130）和包括扩散器区域（138）的出口（132）之间延伸的通道（128）。扩散器区域（138）构造成在使用时相对于进入扩散器部分（138）的空气减少离开出口（132）的空气的轴向速度，其中出口（132）定位成使得离开出口（132）的空气）基本上指向转子叶片（120）的根部（122）。

6. 发明公开

EP2452876A2 Aircraft propulsion system and system for taxiing an aircraft 有权
标题翻译： Flugzeug，Antriebssystem und System zum Rollen eines Flugzeugs
公开(公告)号：EP2452876A2
公开(公告)日：2012-05-16
申请号：EP11250898.1
申请日：2011-11-16
申请人： Rolls-Royce Corporation
发明人： Burns, Donald , Rajashekara, Kaushik
IPC分类号： B64D27/00 , B64D33/00 , B64D35/00
CPC分类号： B64D27/00 , B64D33/00 , B64D35/00 , B64D2205/00 , F02C7/32 , F02C7/36 , Y02T50/44 , Y02T50/823
摘要： The present invention relates to a system for taxiing an aircraft without starting one or more main aircraft propulsion engines. In one embodiment, a low pressure spool of a gas turbine engine is driven by a mechanical coupling with an auxiliary power unit, and by an electrical machine.
摘要翻译：本发明涉及一种在不启动一个或多个主飞行器推进发动机的情况下滑行飞机的系统。在一个实施例中，燃气涡轮发动机的低压阀芯由与辅助动力单元的机械联接以及电机驱动。

7. 发明授权

EP0714363B1 MULTI-PURPOSE AIRCRAFT 失效
标题翻译：多用途飞机
公开(公告)号：EP0714363B1
公开(公告)日：1998-01-07
申请号：EP95900354.2
申请日：1994-08-24
申请人： Gevers, David E.
发明人： Gevers, David E.
IPC分类号： B64C25/52 , B64C3/54 , B64C35/00 , B64C1/00 , B64D25/08
CPC分类号： B64D35/04 , B64C1/00 , B64C3/38 , B64C3/54 , B64C3/56 , B64C25/52 , B64C25/54 , B64C25/66 , B64C35/00 , B64C35/002 , B64C35/008 , B64C2001/0045 , B64D27/00 , B64D27/08 , B64D29/04 , Y02T50/12 , Y02T50/14 , Y02T50/44
摘要： Several innovative systems for an aircraft, and aircraft incorporating them, are disclosed. Features include inboard-mounted engine(s) (24,25) with a belt drive system (84,99) for turning wing-situated propellers (8,9); compound landing gear integrating ski (29,114), pontoon and wheel (18,19,21) subcomponents; pivotal mounting armatures (6,7) for landing gear and/or propellers which provide a plurality of possible landing gear and/or propeller configurations; and a compound wing structure (14,15) featuring extendable wing panels (4,5) that permit the wing span of the aircraft to be nearly doubled while in flight. Aircraft incorporating such features will enjoy several safety advantages over conventional multi-engine aircraft and will be capable of modifications during flight which permit landings on any of snow, hard surfaces (runways) and water.

8. 发明公开

EP0296643A2 Fire resistant seal 失效
标题翻译： Feuerfeste Dichtung。
公开(公告)号：EP0296643A2
公开(公告)日：1988-12-28
申请号：EP88200810.5
申请日：1988-04-26
申请人： THE BOEING COMPANY
发明人： Chee, Wan T. , Aspinall, Eric L.
IPC分类号： B64D27/00
CPC分类号： B64D27/00
摘要： A fire resistant seal formed of an inner layer (20) of elastomer material that is compressible and flexible, a middle layer (22) of ceramic fiber that is fire resistant, and an outer layer (24) of elastic fabric. In the preferred embodiment, the ceramic fiber middle layer (22) totally encloses the elastomer inner layer (20), and the wear resistant outer layer (24) totally encloses the middle layer (22) and the inner layer (20). In this particular application, the fire resistant seal (10) has a toroidal-shaped compressible portion (12) and an integrally formed flange portion (14).
摘要翻译：由可压缩和柔性的弹性体材料的内层（20）形成的耐火密封件，耐火的陶瓷纤维的中间层（22）和弹性织物的外层（24）。在优选实施例中，陶瓷纤维中间层（22）完全包围弹性体内层（20），耐磨外层（24）完全包围中间层（22）和内层（20）。在该特定应用中，耐火密封件10具有环形可压缩部分12和整体形成的凸缘部分14。

9. 发明授权

EP2789831B1 Rigid raft for a gas turbine engine 有权转让
公开(公告)号：EP2789831B1
公开(公告)日：2018-08-08
申请号：EP14162568.1
申请日：2014-03-31
申请人： Rolls-Royce plc
发明人： Amarasinghe, Ashan , Willmot, Michael
IPC分类号： F01D25/28 , F02C7/32 , B60R16/02
CPC分类号： F02C7/00 , B64D27/00 , F01D25/28 , F02C7/32 , F02C9/00 , F05D2300/43 , F05D2300/603 , H02G3/00 , H02G3/04 , Y02T50/672
摘要： A rigid raft is provided for a gas turbine engine. The raft has an electrical system and/or a fluid system embedded in the material of the raft. The raft further has one or more first mounts for mounting the raft to the gas turbine engine, and one or more second mounts for mounting a gas turbine engine component to the raft. The raft further has one or more tethers which extend between respective first and second mounts and are embedded in the material of the raft.

10. 发明公开

EP2971873A1 FIRE SEAL END CAP AND ASSOCIATED MULTI-MEMBER ASSEMBLY AND METHOD 有权
标题翻译： FEUERSCHUTZENDKAPPE，多个相关元件及其制造方法
公开(公告)号：EP2971873A1
公开(公告)日：2016-01-20
申请号：EP14706404.2
申请日：2014-02-05
申请人： The Boeing Company
发明人： LIVINGSTON, Scott M. , MAULDIN, Jack W. , LOTTER, Robert P. , PHILIPP, Paul B. , ALSHOBBER, Khalid S. , HARRIS, John N.
IPC分类号： F16J15/06 , B64D45/00 , B64C1/10 , B64C1/16 , B64D27/00 , F16J15/02
CPC分类号： A62C3/08 , A62C2/06 , A62C99/009 , B64C1/10 , B64C1/16 , B64D27/00 , B64D45/00 , B64D2045/009 , F02K1/78 , F16J15/027 , F16J15/065 , F16L55/10 , F16L55/1026
摘要： A multi-member assembly including a first structural member, a second structural member opposed from the first structural member, a crossover seal positioned between the first and second structural members, wherein the crossover seal defines a bore, and an end cap including a cap portion and a plug portion protruding from the cap portion, wherein the plug portion is at least partially received in the bore such that the cap portion bridges the first and second structural members.

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