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121. 发明授权

US09180964B2 Autorotative enhancement system 有权
标题翻译：自动增强系统
公开(公告)号：US09180964B2
公开(公告)日：2015-11-10
申请号：US13834215
申请日：2013-03-15
申请人： Bell Helicopter Textron Inc.
发明人： Dudley E. Smith , Cory M. Hitte , Bryan Marshall , Carlos Alexander Fenny
IPC分类号： B64C27/12 , B64C27/00 , B64D27/24
CPC分类号： B64C27/006 , B64C27/12 , B64D27/24 , B64D2027/026 , Y10T29/49117
摘要： An autorotative enhancement system comprises a transmission having a driveshaft configured to couple to an engine. A mast is configured to couple to multiple rotor blades. An autorotative assist unit is configured to the transmission and is configured to store energy during normal operation and drive the rotor blades through the transmission to provide supplemental autorotative assistance upon loss of engine power.
摘要翻译：自动增强系统包括具有被配置为耦合到发动机的驱动轴的变速器。桅杆配置成连接到多个转子叶片。自动辅助单元被构造成用于变速器，并且被配置为在正常操作期间存储能量并且通过变速器驱动转子叶片，以在发动机动力损失时提供补充的自动辅助。

122. 发明申请

US20150274306A1 HYBRID DRIVE FOR GAS TURBINE ENGINE 审中-公开
标题翻译：混合动力用于气体涡轮发动机
公开(公告)号：US20150274306A1
公开(公告)日：2015-10-01
申请号：US14620259
申请日：2015-02-12
申请人： United Technologies Corporation
发明人： William G. Sheridan
IPC分类号： B64D27/10 , B64D27/24 , F02C7/36 , F02C6/20 , F02C6/00
CPC分类号： B64D27/24 , B64D35/02 , B64D35/04 , B64D2027/026 , F01D15/12 , F02C7/36 , F02K3/077 , F05D2220/323 , F05D2220/36 , F05D2240/40 , F05D2250/312 , F05D2260/4023 , F05D2260/4031 , Y02T50/62 , Y10S903/903
摘要： A gas turbine engine has a fan drive turbine for selectively driving a fan rotor. A drive shaft between the fan drive turbine and the fan rotor includes a clutch, and an electric motor. The electric motor is positioned such that it is not downstream of a flow path relative to the fan drive turbine. A method of operating a gas turbine engine is also disclosed.
摘要翻译：燃气涡轮发动机具有用于选择性地驱动风扇转子的风扇驱动涡轮机。风扇驱动涡轮机和风扇转子之间的驱动轴包括离合器和电动机。电动机被定位成使得其不相对于风扇驱动涡轮机的流动路径的下游。还公开了一种操作燃气涡轮发动机的方法。

123. 发明申请

US20150260095A1 Engines and integral engine/ generators 审中-公开
标题翻译：发动机和整体发动机/发电机
公开(公告)号：US20150260095A1
公开(公告)日：2015-09-17
申请号：US13136279
申请日：2011-07-25
申请人： Mitja Victor Hinderks
发明人： Mitja Victor Hinderks
IPC分类号： F02B77/13 , B64D27/04 , F02N11/04 , F02B59/00 , F02M25/07 , B63H21/14 , B64D27/24
CPC分类号： F02B77/13 , B63B1/28 , B63H5/125 , B63H21/14 , B63H21/20 , B63H2021/205 , B64D27/04 , B64D27/24 , B64D2027/026 , F01L1/0532 , F01L1/06 , F01L1/12 , F01L1/146 , F01L1/185 , F01L1/20 , F01L1/28 , F01L1/36 , F01L1/46 , F01L3/02 , F01L3/22 , F01L2001/0537 , F01L2101/00 , F01L2101/02 , F01L2105/00 , F02B59/00 , F02M26/00 , F02N11/04 , Y02T70/5209 , Y02T70/5218 , Y02T70/5236 , Y02T70/5281 , Y02T90/46 , Y10S903/905
摘要： Fluid working reciprocating devices are described, including internal combustion engines, compressors and pumps, and how such devices may transfer power to electric generators or turbines. Devices can be within casings which may be “snapped into” larger machinery, such as vehicles, aircraft or marine craft. A number of arrangements for pistons and cylinders of unconventional configuration are described, mostly intended for use in IC engines operating without cooling. Included are toroidal combustion or working chambers, some with fluid flow through the core of the toroid, a single piston reciprocating between a pair of working chambers, tensile valve actuation, tensile links between piston and crankshaft, energy absorbing piston—crank links, crankshafts supported on gas bearings, cylinders rotating in housings, injectors having components which reciprocate or rotate during fuel delivery. In some embodiments pistons may rotate while reciprocating. High temperature exhaust emissions systems are described, including those containing filamentary material.
摘要翻译：描述了流体工作往复运动装置，包括内燃机，压缩机和泵，以及这些装置如何将功率传递给发电机或涡轮机。设备可以在可能被“卡入”较大机械的机壳内，例如车辆，飞机或海工。描述了用于非常规配置的活塞和气缸的多种布置，主要用于在没有冷却的情况下运行的IC发动机中。包括环形燃烧或工作室，一些流体流过环形铁芯，单个活塞在一对工作室之间往复运动，拉伸阀致动，活塞和曲轴之间的拉伸连接，能量吸收活塞 - 曲柄连杆，支撑的曲轴在气体轴承，在壳体中旋转的气缸，具有在燃料输送期间往复运动或旋转的部件的喷射器。在一些实施例中，活塞可以在往复运动的同时旋转。描述了高温废气排放系统，包括含有丝状材料的废气排放系统。

124. 发明授权

US09079661B2 Ultra-rapid air vehicle and related method for aerial locomotion 有权
标题翻译：超快速飞行器及相关方法进行航空运动
公开(公告)号：US09079661B2
公开(公告)日：2015-07-14
申请号：US13516878
申请日：2010-12-20
申请人： Marco Prampolini , Yohann Coraboeuf
发明人： Marco Prampolini , Yohann Coraboeuf
IPC分类号： B64C30/00 , B64D27/20 , B64C3/10 , B64C5/08 , B64C5/10 , B64C23/06 , B64G1/14 , B64D27/02
CPC分类号： B64C30/00 , B64C3/10 , B64C5/08 , B64C5/10 , B64C23/076 , B64D27/023 , B64D27/20 , B64D27/26 , B64D2027/026 , B64G1/14 , Y02T50/12 , Y02T50/164 , Y02T50/44 , Y02T90/44
摘要： The invention concerns an ultra-rapid air vehicle together with a method of aerial locomotion by means of an ultra-rapid air vehicle, where the air vehicle is propelled by a system of motors formed of turbojets (TB1, TB2), ramjets (ST1, ST2) and a rocket motor which can be made streamlined to reduce the drag of the base during the cruise phase, and where the vehicle has a gothic delta wing (A) fitted with moving fins (a1, a2) at both outer ends of the trailing edge of the delta wing (A).
摘要翻译：本发明涉及一种超快速空中飞行器以及超快速空中飞行器的空中移动方法，其中，空中交通工具由涡轮喷气发动机（TB1，TB2），冲击器（ST1， ST2）和火箭发动机，其可以被制成流线型以减少在巡航阶段期间底座的阻力，并且其中车辆具有装配有活动翅片（a1，a2）的哥特式三角翼（A），其在两个外端处三角翼的后缘（A）。

125. 发明授权

US09073626B2 Actuating blades of an unducted fan 有权
标题翻译：未引风扇的驱动叶片
公开(公告)号：US09073626B2
公开(公告)日：2015-07-07
申请号：US13641738
申请日：2011-04-20
申请人： Eric De Wergifosse
发明人： Eric De Wergifosse
IPC分类号： B64C11/44 , F04D29/36 , B64C11/06 , F04D25/06 , B64D27/02
CPC分类号： B64C11/44 , B64C11/06 , B64D2027/026 , F04D25/0613 , F04D29/362 , Y02T50/66
摘要： An actuator device for actuating a swivel-mounted member carried by a rotor of a propulsion engine including: at least one electricity source; an electric actuator for swiveling the swivel-mounted member; a power supply circuit connecting the electricity source to the actuator; and an inertial device connected to the power supply circuit, the inertial device configured to convert electrical energy coming from the power supply circuit into mechanical energy, to store the mechanical energy, and to convert the mechanical energy into electrical energy for the power supply circuit.
摘要翻译：一种用于致动由推进发动机的转子承载的旋转安装构件的致动器装置，包括：至少一个电源; 用于使旋转安装构件旋转的电致动器; 将电源连接到致动器的电源电路; 以及连接到所述电源电路的惯性装置，所述惯性装置被配置为将来自所述电源电路的电能转换成机械能，以存储所述机械能，以及将所述机械能转换为所述电源电路的电能。

126. 发明授权

US09068574B2 Assembly having a control device with racks for controlling the angular position of pivotally-mounted blades in a turbine engine 有权
标题翻译：具有控制装置的组件具有用于控制涡轮发动机中枢转安装的叶片的角位置的齿条
公开(公告)号：US09068574B2
公开(公告)日：2015-06-30
申请号：US13578765
申请日：2011-02-07
申请人： Eric Jacques Boston , Michel Andre Bouru , Laurent Jablonski , Philippe Gerard Edmond Joly
发明人： Eric Jacques Boston , Michel Andre Bouru , Laurent Jablonski , Philippe Gerard Edmond Joly
IPC分类号： F04D29/36 , F03D7/02 , B63H3/00 , B64C11/32 , B64C11/48 , B64D27/02
CPC分类号： F04D29/362 , B63H3/002 , B64C11/32 , B64C11/48 , B64D2027/026 , F03D7/0224 , F04D29/36 , F05D2260/74
摘要： An assembly in a turbine engine for controlling plural toothed pivotally-mounted blades arranged in azimuth around the axis of the turbine engine and including an actuator ring controlling a position of the blades. Racks mounted on the ring present corresponding sets of teeth meshing with the set of teeth of a respective one of the blades to place it in a selected angular position, and they are held in the radial direction by radial positioning mechanism fastened to the blade. Each rack is mounted on the ring by plural guides spaced apart circumferentially around the ring, that connect together movements of the rack and of the ring in the circumferential direction, and that are configured to slide relative to the ring, for each guide in its own radial direction, and relative to the rack in a direction of movement that is substantially radial and specific to the rack.
摘要翻译：涡轮发动机中的组件，其用于控制围绕涡轮发动机的轴线方位布置的多个带齿的可枢转地安装的叶片，并且包括控制叶片位置的致动器环。安装在环上的机架呈现出与相应一个叶片的齿组啮合的相应组齿，以将其置于选定的角度位置，并且通过紧固到叶片的径向定位机构将其保持在径向方向。每个机架通过围绕环周向间隔开的多个引导件安装在环上，所述引导件在圆周方向上将齿条和环的运动连接在一起，并且被配置为相对于环滑动，对于每个引导件在其自身中径向方向，并且相对于齿条在基本上径向并且特定于齿条的运动方向上。

127. 发明授权

US09045223B2 Method of assisting a pilot of a single-engined rotary wing aircraft during a stage of flight in autorotation 有权
标题翻译：在自转过程中在飞行阶段协助单引擎旋翼飞机的飞行员的方法
公开(公告)号：US09045223B2
公开(公告)日：2015-06-02
申请号：US13969666
申请日：2013-08-19
申请人： AIRBUS HELICOPTERS
发明人： Matthieu Connaulte , Christian Mercier , Damien Mariotto
IPC分类号： B64C19/00 , B64C27/00 , B64C27/14 , B64D27/24 , B64D31/00 , B64D35/02 , B64D35/08 , G06F17/00 , B64D27/02
CPC分类号： B64C27/006 , B64C27/14 , B64D27/24 , B64D31/00 , B64D35/02 , B64D35/08 , B64D2027/026 , Y02T50/44 , Y02T50/64
摘要： A method of assisting a pilot of a single-engined rotary wing aircraft (1) during a stage of flight in autorotation, said aircraft (1) including a hybrid power plant having an engine (13), an electric machine (12), and a main gearbox (11). Said aircraft (1) also includes electrical energy storage means (14) and a main rotor (2) mechanically connected to said hybrid power plant (5). According to said method, while in flight, the operation of said engine (13) is monitored in order to detect a failure thereof, in particular by monitoring for a drop of power on said main rotor (2), and then in the event of a failure of said engine (13) being detected, said electric machine (12) is controlled to deliver auxiliary power We to said main rotor (2), thereby enabling the pilot of said aircraft (1) to be assisted in maneuvering said aircraft (1) during said stage of flight in autorotation following said failure.
摘要翻译：一种在自动驾驶的飞行阶段期间辅助单引擎旋转翼飞机（1）的飞行员的方法，所述飞机（1）包括具有发动机（13），电机（12）的混合动力设备，以及主变速箱（11）。所述飞机（1）还包括机电连接到所述混合动力装置（5）的电能存储装置（14）和主转子（2）。根据所述方法，在飞行中，在监视所述发动机（13）的操作以便检测其故障，特别是通过监视所述主转子（2）上的动力下降，然后在检测到所述发动机（13）的故障，所述电机（12）被控制以将辅助动力输送到所述主转子（2），从而使得所述飞机（1）的飞行员能够辅助操纵所述飞行器 1）在所述故障发生后的所述飞行阶段。

128. 发明授权

US09008942B2 Method of managing an engine failure on a multi-engined aircraft having a hybrid power plant 有权
标题翻译：在具有混合动力装置的多发发动机上管理发动机故障的方法
公开(公告)号：US09008942B2
公开(公告)日：2015-04-14
申请号：US14060802
申请日：2013-10-23
申请人： Airbus Helicopters
发明人： Nadine Dyrla , Matthieu Connaulte , Joris Cezard
IPC分类号： G06F19/00 , B64C19/00 , B64C27/14 , B64D27/24 , B64D31/00 , B64D35/02 , B64D35/08 , B64D27/02
CPC分类号： B64D31/00 , B64C27/14 , B64D27/24 , B64D35/02 , B64D35/08 , B64D2027/026 , Y02T50/44 , Y02T50/64
摘要： A method of managing an engine failure on a rotary wing aircraft (1) having a hybrid power plant (5) with at least two fuel-burning engines (13, 13′), at least one electric machine (12), and a main gearbox (11). Said aircraft (1) also has electrical energy storage means (14) and a main rotor (2) mechanically connected to said hybrid power plant (5). In said method, during each flight, the operation of said engines (13, 13′) is monitored in order to detect a failure of any one of them, and then once a failure of one of said engines (13, 13′) has been detected, said electric machine (12) is controlled, if necessary, to deliver auxiliary power We in order to avoid a deficit appearing in the total power WT of said hybrid power plant (5), thereby enabling the pilot of said aircraft (1) to fly said aircraft (1) safely without degrading said hybrid power plant (5).
摘要翻译：一种在具有至少两个燃料燃烧发动机（13,13'）的混合动力装置（5），至少一个电动机（12）和主机变速箱（11）。所述飞机（1）还具有机电连接到所述混合动力装置（5）的电能存储装置（14）和主转子（2）。在所述方法中，在每次飞行期间，监视所述发动机（13,13'）的操作以便检测其中任何一个的故障，然后一旦所述发动机（13,13'）中的一个发生故障如果需要，则控制所述电机（12）输送辅助动力，以避免出现在所述混合动力装置（5）的总功率WT内的缺陷，从而使所述飞机（1 ）安全地飞行所述飞机（1）而不降低所述混合动力装置（5）。

129. 发明授权

US08967964B2 Boundary layer energiser 有权
标题翻译：边界层激励器
公开(公告)号：US08967964B2
公开(公告)日：2015-03-03
申请号：US12883553
申请日：2010-09-16
申请人： Christopher T. J. Sheaf , Zahid M. Hussain
发明人： Christopher T. J. Sheaf , Zahid M. Hussain
IPC分类号： F01D5/18 , F02K3/04 , B64C11/48 , B64C21/04 , B64C21/08 , B64D29/04 , F02K1/34 , F01D5/14 , B64D27/02 , B64D33/02
CPC分类号： F02K3/04 , B64C11/48 , B64C21/04 , B64C21/08 , B64C2230/04 , B64C2230/06 , B64D29/04 , B64D2027/026 , B64D2033/0226 , F01D5/145 , F02K1/34 , F05D2240/121 , F05D2240/122 , F05D2240/127 , F05D2240/14 , F05D2240/303 , F05D2240/304 , F05D2250/131 , F05D2250/132 , F05D2260/96 , F05D2270/17 , Y02T50/166 , Y02T50/66 , Y02T50/671 , Y02T50/673 , Y10S415/914
摘要： A boundary layer energizer (20) for energizing a boundary layer flow over a surface (22), the boundary layer energizer (20) comprising a plurality of passages (24), each passage terminating in a respective hole (26) provided on the surface (22), the holes being arranged in a cluster (23) on the surface, wherein the plurality of passages are angled with respect to one another at the surface such that, when in use, a vortex (24) is formed by a fluid flowing through the plurality of passages.
摘要翻译：边界层激发器（20），用于激励边界层流过表面（22），所述边界层增能器（20）包括多个通道（24），每个通道终止于设置在所述表面上的相应孔（26）中（22），所述孔布置在所述表面上的簇（23）中，其中所述多个通道在所述表面处相对于彼此成角度，使得当在使用中时，流体（24）由流体流过多个通道。

130. 发明申请

US20150028594A1 REVERSIBLE ELECTRICAL MACHINE FOR AN AIRCRAFT 有权
标题翻译：用于飞机的可逆电机
公开(公告)号：US20150028594A1
公开(公告)日：2015-01-29
申请号：US13945326
申请日：2013-07-18
申请人： Eurocopter
发明人： Damien Mariotto
IPC分类号： H02K7/18 , B64D27/24 , B64D35/02 , H02K7/108 , H02K16/00
CPC分类号： H02K7/1823 , B60L11/12 , B60L2200/10 , B60L2220/42 , B64C27/14 , B64D27/24 , B64D35/02 , B64D2027/026 , H02K7/006 , H02K7/108 , H02K16/00 , H02K16/02 , Y02E20/16 , Y02T10/641 , Y02T10/646 , Y02T10/7077 , Y02T50/64
摘要： A reversible electrical machine (1) comprising: a first electrical device (10) having a first stator (11) and a first rotor (12); a second electrical device (20) including a second rotor (22) and a second stator (21) together with an outlet shaft (50) and first disengageable coupling means (30) enabling said first and second rotors (12, 22) to be associated and dissociated in rotation. Said reversible electrical machine (1) also includes second disengageable coupling means (40) that are disengageable under a predetermined force and that mechanically connect said second rotor (22) to said outlet shaft (50). Said first electrical device (10) is a motor for transmitting high mechanical power to said outlet shaft (50), while said second electrical device (20) is a motor-generator for operating in motor mode to transmit additional mechanical power to said outlet shaft (50), and in generator mode for receiving mechanical power from said outlet shaft (50).
摘要翻译：一种可逆电机（1），包括：具有第一定子（11）和第一转子（12）的第一电气装置（10）包括第二转子（22）和第二定子（21）以及出口轴（50）和第一可脱离联接装置（30）的第二电气装置（20），使得所述第一和第二转子（12,22）能够是相关联和旋转分离。所述可逆电机（1）还包括可在预定力下分离并且将所述第二转子（22）机械地连接到所述出口轴（50）的第二可脱离联接装置（40）。所述第一电气设备（10）是用于将高机械功率传输到所述出口轴（50）的电动机，而所述第二电气设备（20）是用于以电动机模式操作的电动发电机，以将额外的机械动力传递到所述出口轴（50），以及用于从所述出口轴（50）接收机械动力的发电机模式。

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