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81. 发明授权

EP2516262B1 OPTIMIZATION OF DOWNSTREAM OPEN FAN PROPELLER POSITION 有权
标题翻译：下游开式风扇螺旋桨位置的优化
公开(公告)号：EP2516262B1
公开(公告)日：2018-03-14
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.

82. 发明公开

EP2562082A3 An aircraft propulsion system and a method of controlling the same 无效转让
标题翻译：飞机推进系统及其控制方法
公开(公告)号：EP2562082A3
公开(公告)日：2017-11-22
申请号：EP12180220.1
申请日：2012-08-13
申请人： Rolls-Royce plc
发明人： Neuteboom, Martin
IPC分类号： B64C11/48 , B64D29/04 , B64C11/00 , F01D9/04 , B64D27/00
CPC分类号： B64C11/00 , B64C11/48 , B64D29/04 , B64D2027/005 , F01D9/041 , Y02T50/66
摘要： An aircraft propulsion system (100) has a propulsive rotor assembly (20, 80) rotatable about an axis of rotation (24) and comprising a plurality of blades (22, 82) and a rotationally fixed vane assembly (60) located adjacent to the propulsive rotor assembly and arranged circumferentially around the axis of rotation. As airflow enters the propulsive rotor assembly, a portion of the airflow passes over the vane assembly which is configured to direct the airflow away from the rotor blades so as to reduce the relative velocity of the redirected airflow over the rotor blades. This results in a reduced tendency of the airflow through the propulsive rotor assembly to become choked.
摘要翻译：一种飞行器推进系统（100）具有可围绕旋转轴线（24）旋转并且包括多个叶片（22,82）和旋转固定叶片组件（60）的推进转子组件（20,80），所述旋转固定叶片组件（60）推进的转子组件并围绕旋转轴线周向布置。随着气流进入推进式转子组件，一部分气流经过叶片组件，该叶片组件被配置为引导气流离开转子叶片，从而降低转子叶片上重新引导的气流的相对速度。这导致通过推进式转子组件的气流倾向于减小。

83. 发明授权

EP2163474B1 Blade pitch control 有权转让
标题翻译：叶片桨距控制
公开(公告)号：EP2163474B1
公开(公告)日：2017-11-22
申请号：EP09251853.9
申请日：2009-07-23
申请人： Rolls-Royce plc
发明人： David Michael Gainford , Jonathan Edmund Holt , Stephen Granville Garner
IPC分类号： B64C11/30 , B64C11/48 , F01D7/00
CPC分类号： F01D7/00 , B64C11/306 , B64C11/44 , B64C11/48 , B64D2027/005 , Y02T50/66
摘要： A method of controlling blade pitch angle, comprising the steps of: comparing demanded (54,56) and measured (58,74) blade pitch angle and calculating any difference (62,74) therebetween, in a primary electrical control system (50), where there is a difference (62), applying torque (66) to a blade pitch regulator (68) to reduce the magnitude of the difference (62) to zero, and in a secondary electrical control system (52), where the difference (76) is greater than a pre-determined threshold (86), applying torque (80) to a blade pitch regulator (82) to reduce the magnitude of the difference (76) to the threshold (86). Also an electrical system of blade pitch angle control for a set of blades (23,24) comprising: primary (50) and secondary (52) electrical control systems, means for comparing (60,72) demanded (54,56) and measured (58,74) blade pitch angle and calculating any difference (62,76) therebetween, a look-up function (64,78) having the difference (62,76) as its input and outputting a required torque (66,80), and a torque regulator (68,82) to apply the required torque (66,80) to the set of blades (23,24).

84. 发明公开

EP2189646A3 Variable pitch rotor arrangement in a gas turbine engine 有权转让
标题翻译：燃气轮机发动机中的变桨距转子装置
公开(公告)号：EP2189646A3
公开(公告)日：2017-11-15
申请号：EP09252354.7
申请日：2009-10-02
申请人： Rolls-Royce plc
发明人： Wilson, Robert Edward , Holt, Jonathan Edmund , Morgan, Anthony
IPC分类号： F02K3/02 , F01D7/00 , B64C11/38 , B64C11/40 , B64C11/48 , B64D27/02
CPC分类号： F02K3/025 , B64C11/385 , B64C11/40 , B64C11/48 , B64D2027/026 , F05D2260/76
摘要： A engine such as a gas turbine engine has a bladed rotor 24 having variable pitch blades 8. In normal operation, the pitch angle of the blades 8 is controlled by a primary pitch control system. A back-up system is provided for controlling the blades 8, for example to displace them to a feathered condition, in the event of failure of the primary pitch control system. The back-up system comprises a pump 32 mounted on the rotor 24, and driven by relative rotation between the rotor 24 and a contra-rotating rotor 23. In response to a failure signal on a conduit 48, the pump delivers hydraulic fluid under pressure to a secondary actuator 30, which acts on the blade 8.
摘要翻译：诸如燃气涡轮发动机的发动机具有带有可变桨距叶片8的叶片转子24.在正常操作中，叶片8的桨距角由主桨距控制系统控制。在主变桨控制系统发生故障的情况下，提供备用系统来控制叶片8，例如将它们移位到羽毛状态。该备用系统包括安装在转子24上并由转子24和反转转子23之间的相对旋转驱动的泵32.响应于导管48上的故障信号，泵将压力下的液压流体到作用在叶片8上的次级致动器30。

85. 发明公开

EP3233627A1 TURBOMACHINE À HÉLICE MULTI-DIAMÈTRES 有权
标题翻译： TURBOMACHINEÀHÉLICEMULTI-DIAMÈTRES
公开(公告)号：EP3233627A1
公开(公告)日：2017-10-25
申请号：EP15830811.4
申请日：2015-12-17
申请人： Safran Aircraft Engines
发明人： VION, Laurence, Francine , GRUBER, Mathieu, Simon, Paul
IPC分类号： B64C11/18 , B64C11/48
CPC分类号： B64C11/48 , B64C11/18 , B64C11/306 , F01D7/00 , Y02T50/66
摘要： The invention relates to a turbomachine (1) comprising at least two unducted propellers (10, 11), one of which is an upstream propeller (10) and one a downstream propeller (11), the upstream propeller (10) comprising a plurality of blades (2), at least one first blade of which has a different length from that of a second blade.
摘要翻译：本发明涉及包括至少两个无螺旋桨（10,11）的涡轮机（1），其中一个是上游螺旋桨（10），另一个是下游螺旋桨（11），上游螺旋桨（10）包括多个刀片（2），其至少一个第一刀片具有与第二刀片不同的长度。

86. 发明公开

EP3222519A1 AIRPLANE 有权
标题翻译：飞机
公开(公告)号：EP3222519A1
公开(公告)日：2017-09-27
申请号：EP16164278.0
申请日：2016-04-07
申请人： Robby Moto Engineering S.r.l.
发明人： Papetti, Roberto , Ciacchi, Piercarlo , Calati, Eugenio
IPC分类号： B64C11/48 , B64D33/10 , B64D35/06 , B64D35/08 , B64D27/02
CPC分类号： B64C11/48 , B64D33/10 , B64D35/06 , B64D35/08 , B64D2027/026
摘要： The airplane (1) comprises at least a fuselage (2) and at least a pair of wings (3) associated with the fuselage (2) to form an aircraft body (2, 3) associated with an engine assembly (4) suitable for providing mechanical energy for takeoff and maintaining the aircraft body (2, 3) in flight, wherein the engine assembly (4) is associated with a propulsion system (5) having at least a propeller (8, 9) suitable for converting the mechanical energy into propulsion thrust, and which comprises:
- at least a first piston engine (6) associated with the propulsion system (5) and configured for take-off and maintaining the aircraft body (2, 3) in flight at low altitude;
- at least a second piston engine (7) associated with the propulsion system (5) and configured to maintain the aircraft body (2,3) in flight at high altitude.
摘要翻译：所述飞机（1）包括至少一个机身（2）和与所述机身（2）相关联的至少一对机翼（3），以形成与发动机组件（4）相关的飞机本体（2,3），所述飞机本体适合于提供用于起飞和保持飞行中的飞行器主体（2,3）的机械能，其中发动机组件（4）与推进系统（5）相关联，推进系统（5）具有适于将机械能所述至少一个第一活塞发动机（6）与所述推进系统（5）相关联并且被配置用于在低海拔处起飞和保持所述飞机主体（2,3）在飞行中; - 至少一个第二活塞发动机（7），该第二活塞发动机与推进系统（5）相关联并且被配置为在高海拔处维持飞行器主体（2,3）飞行。

87. 发明公开

EP2483556A4 ELECTRICAL POWER GENERATION APPARATUS FOR CONTRA- ROTATING OPEN-ROTOR AIRCRAFT PROPULSION SYSTEM 审中-实审
标题翻译：发电装置用于与对面开式转子一种平面驱动系统
公开(公告)号：EP2483556A4
公开(公告)日：2016-09-14
申请号：EP10820931
申请日：2010-09-02
申请人： ROLLS ROYCE NAM TECH INC
发明人： BLACKWELDER MARK J , ALT JOHN TIMOTHY , GAGNE STEVEN , VETTERS DANIEL KENT
IPC分类号： F03D9/00 , B64C11/48 , B64D15/12 , B64D27/00 , B64D27/02 , F02K3/072 , H02K7/18
CPC分类号： H02K7/1823 , B64C11/48 , B64D15/12 , B64D2027/005 , B64D2027/026 , F02K3/072 , F05D2220/768 , Y02T50/66 , Y02T50/671
摘要： An electrical power generation apparatus is embedded in a contra-rotating propulsion system that includes overlapping first and second shafts operatively connected for counter-rotation about a common axis. The electrical power generation apparatus includes a winding mounted to one of the shafts and a field array mounted to the other of the shafts adjacent to the winding. Relative rotation of the winding and the field array induces electrical current in the winding.

88. 发明授权

EP2436596B1 Pitch change apparatus for counter-rotating propellers 有权
标题翻译：反转螺旋桨的变桨装置
公开(公告)号：EP2436596B1
公开(公告)日：2016-07-13
申请号：EP11183355.4
申请日：2011-09-29
申请人： General Electric Company
发明人： Glynn, Christopher Charles , Zatorski, Darek Tomasz , Yeager, Donald Scott , Dinsmore, Nicholas Rowe , Menard, Jeffrey Raymond , Miller, Brandon Wayne
IPC分类号： B64C11/38 , B64C11/48 , B64D27/02
CPC分类号： B64C11/38 , B64C11/48 , B64D2027/005 , B64D2027/026 , Y02T50/66

89. 发明公开

EP2888165A4 VARIABLE GEOMETRY LIFT FAN MECHANISM 审中-公开
标题翻译： HUBGEBLÄSEMECHANISMUS可变几何形状
公开(公告)号：EP2888165A4
公开(公告)日：2016-04-13
申请号：EP13830270
申请日：2013-08-23
申请人： ZEE AERO INC
发明人： LONG GEOFFREY A , LYASOFF RODIN
IPC分类号： B64C29/00 , B64C11/28 , B64C11/48 , B64C27/02 , B64C27/50
CPC分类号： F04D19/02 , B64C11/00 , B64C11/16 , B64C11/28 , B64C11/48 , B64C27/022 , B64C27/20 , B64C27/50

90. 发明公开

EP2557033A3 Modular counter rotating propeller system 有权转让
标题翻译：模块化反向旋转的螺旋桨系统
公开(公告)号：EP2557033A3
公开(公告)日：2015-11-11
申请号：EP12179560.3
申请日：2012-08-07
申请人： Hamilton Sundstrand Corporation
发明人： Perkinson, Robert H.
IPC分类号： B64C11/48 , B64C11/30
CPC分类号： B64C11/48 , B64C11/306 , B64D2027/005 , Y02T50/66
摘要： A self-contained counter rotating turbo prop system (14) is driven by a gas turbine engine (10) through a reduction gearbox (12). A gear train housed separate from the reduction gearbox (12) provides the counter-rotation of a first and second pluralities of propeller blades (18,20). The entire counter-rotating propeller system (14) is disposed within cowlings (16A,16B) and is separate from the gas turbine engine (10) and reduction gearbox (12). The counter rotating propeller system (14) includes a collective blade angle actuation system (55) that provides for adjustment of blade angle of both the first and second plurality of propeller blades (18,20) with a single actuator.

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