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1. 发明授权

EP2368795B1 Propeller arrangement 有权转让
标题翻译： Propelleranordnung
公开(公告)号：EP2368795B1
公开(公告)日：2017-04-05
申请号：EP11154441.7
申请日：2011-02-15
申请人： Rolls-Royce plc
发明人： Lavrenko, Alexander
IPC分类号： B64C11/00 , B64C11/48
CPC分类号： B64C11/003 , B64C11/48 , B64D2027/026

2. 发明公开

EP1687200A2 METHODS AND SYSTEMS FOR STARTING PROPELLER-DRIVEN DEVICES 审中-公开
标题翻译：方法和系统启动螺旋桨驱动的装置
公开(公告)号：EP1687200A2
公开(公告)日：2006-08-09
申请号：EP04810203.2
申请日：2004-11-01
申请人： The Insitu Group, Inc.
发明人： SLIWA, Steven, M. , VON FLOTOW, Andreas, H. , DENNIS, Brian, D.
IPC分类号： B63H1/00
CPC分类号： B64C11/003 , A63H27/02 , B64C11/04 , B64C11/14 , B64C11/28 , B64C39/024 , B64C2201/044 , B64C2201/082 , B64C2201/102 , B64C2201/165 , B64C2201/182 , B64C2201/201 , B64C2201/206 , B64D41/007 , F02K5/023 , F05D2260/85 , Y02T50/44 , Y02T50/672
摘要： Methods and systems for starting propeller driven aircraft and other devices are disclosed. A system in accordance with one embodiment of the invention includes a removable fixture that is coupled to the propeller and has at least one portion exposed to a flowstream to rotate the propeller during engine start-up. The fixture is configured to separate from the propeller after the engine begins to turn over (e.g., after the engine starts and/or rotates above a threshold rate). Accordingly, the system can include a releasable link between the fixture and the propeller.

3. 发明公开

EP0866765A1 ROTOR SYSTEM HAVING ALTERNATING LENGTH ROTOR BLADES FOR REDUCING BLADE-VORTEX INTERACTION (BVI) NOISE 失效
标题翻译：与不同的纸张长度转子系统，以降低噪音水平VONBLATTWIRBELN
公开(公告)号：EP0866765A1
公开(公告)日：1998-09-30
申请号：EP96942814.0
申请日：1996-11-27
申请人： Sikorsky Aircraft Corporation
发明人： VISINTAINER, Joseph, A. , MOFFITT, Robert, C.
IPC分类号： B64C11 , B64C27 , B64C29
CPC分类号： B64C11/003 , B64C29/0033
摘要： A rotor system (4) having odd and even blade assemblies (Ob, Eb) mounting to and rotating with a rotor hub assembly (6) wherein the odd blade assemblies (Ob) define a radial length RO, and the even blade assemblies (Eb) define a radial length RE and wherein the radial length RE is between about 70 % to about 95 % of the radial length RO. Other embodiments of the invention are directed to a Variable Diameter Rotor system (4) which may be configured for operating in various operating modes for optimizing aerodynamic and acoustic performance. The Variable Diameter Rotor system (4) includes odd and even blade assemblies (Ob, Eb) having inboard and outboard blade sections (10, 12) wherein the outboard blade sections (12) telescopically mount to the inboard blade sections (10). A positioning means (70) is provided for positioning the outboard blade sections (12) with respect to the inboard blade sections (10) such that the radial length RE of the even blade assemblies (Eb) is equal to the radial length RO of the add blade assemblies (Ob) in a first operating mode, and such that the radial length RE is between about 70 % to about 95 % of the length RO in a second operating mode.

4. 发明公开

EP0651713A4 VARIABLE DIAMETER ROTOR DRIVE SYSTEM. 失效
标题翻译：具有可变直径的转子的驱动系统。
公开(公告)号：EP0651713A4
公开(公告)日：1997-02-26
申请号：EP93919838
申请日：1993-07-27
申请人： UNITED TECHNOLOGIES CORP
发明人： FRADENBURGH EVAN A , MILLER GORDON GLENN
IPC分类号： B64C11/00 , B64C27/46 , B64C27/54
CPC分类号： B64C27/46 , B64C11/003 , B64C27/54
摘要： A drive system for varying the diameter of a variable diameter rotor has a gear assembly associated with a single coaxial shaft (13) lower end which includes a gear set for increasing the speed of rotation of the central shaft (13) relative to the rotor drive shaft (2) to change the diameter of the variable diameter blades. A pair of brakes are used, one (37) to slow the coaxial shaft relative to the drive shaft and another (25) to lock the rotor shaft (2) and coaxial shaft (13) together for corotation during constant diameter flight conditions. Utilizing a lower gear assembly reduces hub complexity and allows the variable diameter rotor drive system to be adapted to gimballed rotors which require shaft flexibility. Since only a single shaft extends through the rotor drive shaft, hub complexity is reduced.

5. 发明公开

EP2492192A3 Disc rotor retraction system 有权
标题翻译：碟片回收系统
公开(公告)号：EP2492192A3
公开(公告)日：2017-08-30
申请号：EP12157385.1
申请日：2012-02-28
申请人： The Boeing Company
发明人： Podgurski, Daniel Michael
IPC分类号： B64C27/32 , B64C27/30 , B64C11/00 , B64C27/46
CPC分类号： B64C27/32 , B64C11/003 , B64C27/00 , B64C27/30 , B64C27/46 , B64C27/467 , B64C27/473
摘要： A disc rotor blade retraction system includes a main blade spar (22) incorporating a hydraulic cylinder (54) and having a screw thread (34). A ball screw (24) is concentrically carried within the main blade spar and is operably connected to a ball nut (60) which has an outboard end connected to an intermediate spar (26) with a hydraulic piston (62) received for reciprocation in the hydraulic cylinder. A first geared actuator (20) engages the ball screw and a second geared actuator (30) engages the main blade spar screw thread. A hydraulic fluid accumulator (74) providing pressurized hydraulic fluid is connected to an outboard end of the hydraulic cylinder and a controller actuates the first and second geared actuators.
摘要翻译：盘式转子叶片收缩系统包括结合液压缸（54）并具有螺纹（34）的主叶片翼梁（22）。滚珠丝杠（24）同心地承载在主叶片翼梁内并且可操作地连接到滚珠螺母（60），该滚珠螺母具有连接到中间翼梁（26）的外侧端部，液压活塞（62）接收用于在液压缸。第一齿轮致动器（20）接合滚珠丝杠，并且第二齿轮致动器（30）接合主叶片翼梁螺纹。提供加压液压流体的液压流体蓄能器（74）连接到液压缸的外侧端，并且控制器致动第一和第二齿轮致动器。

6. 发明授权

EP2596247B1 TURBOMOTEUR A DEUX HELICES CONTRAROTATIVES NON CARENEES 有权转让
标题翻译：有两个相对的，COAT地段螺旋桨涡扇-ENGINE（CROR）
公开(公告)号：EP2596247B1
公开(公告)日：2015-09-02
申请号：EP11741673.5
申请日：2011-07-13
申请人： Snecma
发明人： VUILLEMIN, Alexandre, Alfred, Gaston
IPC分类号： F04D19/02 , F04D29/32 , F04D29/66 , B64C11/00 , B64C11/48 , F02K3/072
CPC分类号： F04D19/024 , B64C11/003 , B64C11/06 , B64C11/306 , B64C11/48 , B64D2027/026 , F02K3/072 , F04D29/324 , F04D29/362 , F04D29/666 , Y02T50/66

7. 发明公开

EP2368795A3 Propeller arrangement 有权转让
标题翻译：螺旋桨组件
公开(公告)号：EP2368795A3
公开(公告)日：2014-04-02
申请号：EP11154441.7
申请日：2011-02-15
申请人： Rolls-Royce plc
发明人： Lavrenko, Alexander
IPC分类号： B64C11/00 , B64C11/48
CPC分类号： B64C11/003 , B64C11/48 , B64D2027/026
摘要： A propeller arrangement has a first propeller assembly providing a row of first propellers, and a second propeller assembly, rearward of the first propeller assembly, providing a row of second propellers. The first and second propellers are radially extendable and retractable. The propeller arrangement further has a control system for controlling the extension and retraction of the first and second propellers. The control system is arranged such that when the propellers of one of the first and second propeller assemblies extend, the propellers of the other of the first and second assemblies retract.

8. 发明授权

EP2492192B1 Disc rotor retraction system 有权
公开(公告)号：EP2492192B1
公开(公告)日：2018-11-14
申请号：EP12157385.1
申请日：2012-02-28
申请人： The Boeing Company
发明人： Podgurski, Daniel Michael
IPC分类号： B64C27/32 , B64C27/30 , B64C11/00 , B64C27/46
CPC分类号： B64C27/32 , B64C11/003 , B64C27/00 , B64C27/30 , B64C27/46 , B64C27/467 , B64C27/473
摘要： A disc rotor blade retraction system includes a main blade spar (22) incorporating a hydraulic cylinder (54) and having a screw thread (34). A ball screw (24) is concentrically carried within the main blade spar and is operably connected to a ball nut (60) which has an outboard end connected to an intermediate spar (26) with a hydraulic piston (62) received for reciprocation in the hydraulic cylinder. A first geared actuator (20) engages the ball screw and a second geared actuator (30) engages the main blade spar screw thread. A hydraulic fluid accumulator (74) providing pressurized hydraulic fluid is connected to an outboard end of the hydraulic cylinder and a controller actuates the first and second geared actuators.

9. 发明公开

EP2596247A1 TURBOMOTEUR A DOUBLE HELICE NON CARENEE 有权转让
标题翻译：有两个相对的，COAT地段螺旋桨涡扇-ENGINE（CROR）
公开(公告)号：EP2596247A1
公开(公告)日：2013-05-29
申请号：EP11741673.5
申请日：2011-07-13
申请人： Snecma
发明人： VUILLEMIN, Alexandre, Alfred, Gaston
IPC分类号： F04D19/02 , F04D29/32 , F04D29/66 , B64C11/00 , B64C11/48 , F02K3/072
CPC分类号： F04D19/024 , B64C11/003 , B64C11/06 , B64C11/306 , B64C11/48 , B64D2027/026 , F02K3/072 , F04D29/324 , F04D29/362 , F04D29/666 , Y02T50/66
摘要： The present invention relates to a turbine engine including two outer coaxial counter-rotating unducted propellers, i.e. an upstream propeller and a downstream propeller, respectively. Said engine is characterized in that the blades of the downstream propeller (124) are retractable in the lengthwise direction thereof so as to reduce the diameter of the propeller. Said reduction in the diameter of the downstream propeller makes it possible to reduce the noise caused by the vortices generated by the upstream propeller.

10. 发明公开

EP2516262A1 OPTIMIZATION OF DOWNSTREAM OPEN FAN PROPELLER POSITION 有权
标题翻译：一个优化的下游的开放螺旋桨式风扇的位置
公开(公告)号：EP2516262A1
公开(公告)日：2012-10-31
申请号：EP10782158.9
申请日：2010-11-18
申请人： The Boeing Company
发明人： MOORE, Matthew D. , BOREN, Kelly L. , LANGTRY, Robin B.
IPC分类号： B64C11/00 , B64C11/48
CPC分类号： B64C11/003 , B64C11/48 , B64D2027/026
摘要： A method and apparatus for controlling a propeller of a contra-rotation open fan (CROF) engine of an aircraft. A diameter of the propeller is set to be at a first diameter during at least a portion of a first flight condition of the aircraft. The diameter of the propeller is set to be at a second diameter, different from the first diameter, during at least a portion of a second flight condition of the aircraft.

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