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1. 发明申请

US20190218998A1 ENGINE ASSEMBLY WITH COMBINED ENGINE AND COOLING EXHAUST 审中-公开
公开(公告)号：US20190218998A1
公开(公告)日：2019-07-18
申请号：US16359152
申请日：2019-03-20
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Andre JULIEN , Jean THOMASSIN , Maxime COURTOIS , Bruno VILLENEUVE , Richard ULLYOTT , Serge DUSSAULT , Luc DIONNE , Serge LAFORTUNE , Anthony JONES , Behzad HAGSHENAS , David H. MENHEERE
IPC分类号： F02K1/38 , B64D41/00 , F02K1/82 , F01C1/22 , F01C21/18 , F01N3/05 , F01P5/02 , F01P11/10 , F02B53/02 , F02B63/04 , F02B63/06 , F02B67/04 , F02C5/00 , F02K5/00 , F02C7/18 , F02C7/14
CPC分类号： F02K1/386 , B64D41/00 , B64D2041/002 , F01C1/22 , F01C21/18 , F01N3/05 , F01P5/02 , F01P11/10 , F02B53/02 , F02B63/04 , F02B63/06 , F02B67/04 , F02B2053/005 , F02C5/00 , F02C7/14 , F02C7/18 , F02K1/82 , F02K5/00 , F05D2220/50 , F05D2260/213 , F05D2300/173 , F05D2300/43 , F05D2300/603 , Y02T10/17 , Y02T50/53 , Y02T50/672 , Y02T50/676
摘要： An engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system in fluid communication with a heat exchanger, an exhaust duct in fluid communication with air passages of the heat exchanger, a fan in fluid communication with the exhaust duct for driving a cooling air flow through the air passages of the heat exchanger and into the exhaust duct, and an intermediate duct in fluid communication with an exhaust of the engine and having an outlet positioned within the exhaust duct downstream of the fan and upstream of the outlet of the exhaust duct. The outlet of the intermediate duct is spaced inwardly from a peripheral wall of the exhaust duct. The engine assembly may be configured as an auxiliary power unit. A method of discharging air and exhaust gases in an auxiliary power unit having an internal combustion engine is also discussed.

2. 发明授权

US10006363B2 System and method for aviation electric power production 有权
公开(公告)号：US10006363B2
公开(公告)日：2018-06-26
申请号：US14655747
申请日：2013-11-26
申请人： General Electric Company
发明人： Adon Delgado, Jr. , Todd James Buchholz , Christopher Dale Mathias
IPC分类号： F02C6/00 , F02C3/22 , F02C6/08 , F02C7/00 , B64D37/30 , B64D41/00
CPC分类号： F02C3/22 , B64D37/30 , B64D41/00 , B64D2221/00 , F02C6/08 , F02C7/00 , Y02T50/44 , Y02T50/53 , Y02T90/44
摘要： An electrical power system for an aircraft including a turbine engine coupled to the aircraft and providing propulsive thrust and emitting heat during operation to define a high temperature source, a cryogenic fuel system located within the aircraft and providing fuel for the turbine and emitting heat at a lower temperature than the heat from the turbine engine to define a low temperature source and an electrical power generator located on the aircraft and having a thermodynamic generator using the temperature difference to generate electrical power and a method for producing electric power.

3. 发明申请

US20170323496A1 INTEGRATED WIRELESS DATA SYSTEM FOR AVIONICS PERFORMANCE INDICATION 审中-公开
公开(公告)号：US20170323496A1
公开(公告)日：2017-11-09
申请号：US15586990
申请日：2017-05-04
申请人： TECAT PERFORMANCE SYSTEMS, LLC
发明人： DOUGLAS M. BAKER
IPC分类号： G07C5/08 , G01L1/26 , G01L5/16 , B64C11/30
CPC分类号： G07C5/0825 , B64C11/00 , B64C11/30 , B64D45/00 , B64D2045/0085 , B64F5/60 , G01L1/26 , G01L5/16 , G07C5/0841 , Y02T50/53
摘要： An integrated wireless data system and method for avionic performance indication for measuring, monitoring and displaying in-use, real-world engine-out characteristics on a propeller driven aircraft for the purposes of health monitoring, performance optimization, and regulatory compliance is provided. Engine-out characteristics may be measured either at the propeller extension hub mounted between the engine and propeller, on the crankshaft flange, or on the propeller itself, and include, but are not limited to, the engine output torque, thrust, vibration, bending loads and temperature. Data may be transmitted wirelessly to a base unit located inside the cockpit and user selected parameters are updated on a display in real-time. The system may also store all collected data, for later download and analysis. The system may also have a software interface that can be used to download, view and analyze all recorded data, as well as to configure the system settings and alerts.

4. 发明授权

US09771165B2 Compound engine assembly with direct drive of generator 有权
公开(公告)号：US09771165B2
公开(公告)日：2017-09-26
申请号：US14750207
申请日：2015-06-25
申请人： Pratt & Whitney Canada Corp.
发明人： Richard Ullyott , Anthony Jones , Andre Julien , Jean Thomassin
IPC分类号： F01D15/10 , F02C6/00 , H02K7/18 , H02P9/04 , B64D41/00 , F01C1/22 , F02C3/10 , F01C11/00 , B64D13/06
CPC分类号： B64D41/00 , B64D2013/0611 , F01C1/22 , F01C11/008 , F02C3/10 , H02K7/1815 , H02K7/1823 , Y02T50/44 , Y02T50/53
摘要： A compound engine assembly for use as an aircraft auxiliary power unit, having an engine core including internal combustion engine(s) in driving engagement with an engine shaft, a generator having a generator shaft directly engaged to the engine shaft such as to be rotatable at a same speed, a compressor having an outlet in communication with the engine core inlet, and a turbine section having an inlet in communication with the engine core outlet and configured to compound power with the engine core. The turbine section may include a first stage turbine having an inlet in communication with the engine core outlet, and a second stage turbine having an inlet in communication with the first stage turbine outlet. A method of providing electrical power to an aircraft is also discussed.

5. 发明申请

US20170057650A1 Energy Cell Regenerative System For Electrically Powered Aircraft 有权
标题翻译：电动飞机能量电池再生系统
公开(公告)号：US20170057650A1
公开(公告)日：2017-03-02
申请号：US14679653
申请日：2015-04-06
申请人： Dale Martin Walter-Robinson
发明人： Dale Martin Walter-Robinson
IPC分类号： B64D27/24 , H02K7/18 , H02P4/00
CPC分类号： B64D27/24 , B64D41/00 , B64D41/007 , B64D2027/026 , H02J7/0068 , H02J7/32 , H02J7/345 , H02K7/1823 , H02K53/00 , H02P4/00 , Y02T50/53 , Y02T50/54 , Y02T50/64 , Y10S74/09
摘要： A system for providing regenerative power for an aircraft to sustain flight includes multiple energy cells disposed within the aircraft, the energy cells being configured to supply power to a propulsion motor and electronics of the aircraft, a fan generator harnessing propeller blast created by an aircraft propeller and converting kinetic energy of the propeller blast into electrical energy, a charger receiving the electrical energy generated by the fan generator and using the electrical energy to recharge one or more of the energy cells, and a power transfer switch selectively connecting one of the energy cells to the propulsion motor and electronics of the aircraft, such that the energy cells are rotated one at a time to power the propulsion motor and electronics. During recharging, the one or more of the energy cells are disconnected by the power transfer switch.
摘要翻译：用于为飞行器提供再生能量以维持飞行的系统包括设置在飞行器内的多个能量单元，所述能量单元被配置为向飞行器的推进马达和电子设备供电，利用由飞行器螺旋桨产生的风扇发电机并且将螺旋桨鼓风的动能转换成电能;充电器，其接收由风扇发生器产生的电能并使用电能对一个或多个能量单元进行再充电;以及功率转换开关，其选择性地将能量单元到飞行器的推进电机和电子设备，使得能量单元一次一个旋转以为推进电机和电子设备供电。在再充电期间，一个或多个能量单元由电力转换开关断开。

6. 发明授权

US09573697B2 Energy recovery of an aircraft 有权
标题翻译：能量回收的飞机
公开(公告)号：US09573697B2
公开(公告)日：2017-02-21
申请号：US14562244
申请日：2014-12-05
申请人： THE BOEING COMPANY
发明人： Alfredo Criado , Grzegorz M. Kawiecki
IPC分类号： B64D41/00 , B64C23/06 , F03D1/06 , F03D9/00
CPC分类号： B64D41/007 , B64C23/065 , B64D41/00 , F03D1/06 , F03D9/10 , F03D9/25 , F03D9/32 , F03D13/20 , Y02E10/721 , Y02T50/164 , Y02T50/53
摘要： An apparatus for energy recovery of an aircraft, an aircraft comprising the apparatus and a method of energy recovery are disclosed. The apparatus comprises a turbine having a body and rotor blades. The turbine is adapted to be mounted to the exterior of an aircraft, such that the body receives an air stream flowing at the exterior of the aircraft. The rotor blades are selectively movable between a stowed position and a deployed position, wherein at the deployed position the rotor blades are rotated by the air stream so as to generate electricity. The blades may be deployed during descent of the aircraft to recover energy normally irretrievably dissipated as the aircraft descends and slows. The blades are stowed when not in use, such as during take-off and cruise.
摘要翻译：公开了一种用于飞机能量回收的装置，包括该装置的飞机和能量回收方法。该装置包括具有主体和转子叶片的涡轮机。涡轮适于安装在飞行器的外部，使得主体接收在飞行器外部流动的空气流。转子叶片可选择性地在收起位置和展开位置之间移动，其中在展开位置，转子叶片由空气流旋转以产生电力。在飞机下降期间，叶片可以部署，以恢复正常不可逆转地消耗的能量，随着飞机下降和减速。刀片在不使用时存放，例如在起飞和巡航期间。

7. 发明申请

US20160376023A1 COMPOUND ENGINE ASSEMBLY WITH DIRECT DRIVE OF GENERATOR 有权
标题翻译：具有直接驱动发电机的复合发动机总成
公开(公告)号：US20160376023A1
公开(公告)日：2016-12-29
申请号：US14750207
申请日：2015-06-25
申请人： Pratt & Whitney Canada Corp.
发明人： Richard ULLYOTT , Anthony JONES , Andre JULIEN , Jean THOMASSIN
IPC分类号： B64D41/00 , H02K7/18 , F02C3/10
CPC分类号： B64D41/00 , B64D2013/0611 , F01C1/22 , F01C11/008 , F02C3/10 , H02K7/1815 , H02K7/1823 , Y02T50/44 , Y02T50/53
摘要： A compound engine assembly for use as an aircraft auxiliary power unit, having an engine core including internal combustion engine(s) in driving engagement with an engine shaft, a generator having a generator shaft directly engaged to the engine shaft such as to be rotatable at a same speed, a compressor having an outlet in communication with the engine core inlet, and a turbine section having an inlet in communication with the engine core outlet and configured to compound power with the engine core. The turbine section may include a first stage turbine having an inlet in communication with the engine core outlet, and a second stage turbine having an inlet in communication with the first stage turbine outlet. A method of providing electrical power to an aircraft is also discussed.
摘要翻译：一种用作飞机辅助动力单元的复合发动机组件，其具有包括与发动机轴驱动接合的内燃机的发动机芯，具有直接接合到发动机轴的发电机轴，该发电机轴可以在相同的速度，具有与发动机芯入口连通的出口的压缩机，以及涡轮部分，其具有与发动机芯出口连通的入口并且被配置成与发动机芯体相互补给动力。涡轮机部分可以包括具有与发动机芯出口连通的入口的第一级涡轮机和具有与第一级涡轮机出口连通的入口的第二级涡轮机。还讨论了向航空器提供电力的方法。

8. 发明申请

US20160280368A1 LAYER MATERIAL FOR ARRANGING ON A ROTOR BLADE TIP OF A HELICOPTER, HELICOPTER LIGHT SYSTEM, AND HELICOPTER COMPRISING THE SAME 审中-公开
标题翻译：用于安装直升机，直升机灯系统和包括其的直升机的转子叶片的层材料
公开(公告)号：US20160280368A1
公开(公告)日：2016-09-29
申请号：US15080703
申请日：2016-03-25
申请人： Goodrich Lighting Systems GmbH
发明人： Christian Schoen , Andre Hessling-Von Heimendahl
IPC分类号： B64C27/46 , B64D47/06 , B64D47/04 , F21V9/16 , F21V7/22
CPC分类号： B64C27/463 , B64D47/04 , B64D47/06 , F21V7/22 , F21V9/30 , Y02T50/53
摘要： In an embodiment, a layer material configured to be arranged on a rotor blade tip of a helicopter comprises at least one light emitting or reflecting section that emits or reflects light after being exposed to a remote light source. The light source can be arranged on the body of the helicopter.
摘要翻译：在一个实施例中，构造成布置在直升机的转子叶片尖端上的层材料包括在暴露于远程光源之后发射或反射光的至少一个发光或反射部分。光源可以安排在直升机的身上。

9. 发明申请

US20150247770A1 LANDING LOAD MONITOR FOR CARRIER-BASED AIRCRAFT 审中-公开
标题翻译：用于基于航空器的航空器的着陆负载监视器
公开(公告)号：US20150247770A1
公开(公告)日：2015-09-03
申请号：US13847192
申请日：2013-03-19
申请人： C. Kirk Nance
发明人： C. Kirk Nance
IPC分类号： G01L5/16 , G01L5/00 , G01P15/00 , B64C25/68 , B64D45/00
CPC分类号： G01L5/16 , B64C25/68 , B64D45/00 , B64D2045/008 , G01L5/0052 , Y02T50/53
摘要： A landing load monitor is used for aircraft during a carrier-type landing event having an arresting cable. The aircraft is provided with a tail-hook assembly that includes a tail-hook and a mounting assembly. The tail-hook is coupled to the aircraft by way of the mounting assembly. A sensor measures the load applied by the tail-hook to the aircraft. A processor is connected to the sensor. The tail-hook loads during a landing event over elapsed time are stored in memory for subsequent retrieval and analysis. The sensor may be located on the tail-hook itself or in the mounting assembly. The aircraft is also provided with inboard and outboard accelerometers on each wing. In addition, the landing gear has pressure sensors to monitor the internal pressure of the landing gear struts. These additional sensors are used during the landing event to monitor the loads on the aircraft. They are also used to identify asymmetrical landings.
摘要翻译：在具有拦阻电缆的承载型着陆事件中，着陆负载监视器用于飞机。飞机设有尾钩组件，其包括尾钩和安装组件。尾钩通过安装组件联接到飞行器。传感器测量由尾钩施加到飞机的负载。处理器连接到传感器。在着陆事件超过经过时间的尾钩负载被存储在存储器中用于随后的检索和分析。传感器可以位于尾钩本身或安装组件中。飞机还在每个机翼上都配有内置和外侧加速度计。此外，起落架具有用于监测起落架支柱的内部压力的压力传感器。在着陆事件期间使用这些附加传感器来监视飞机上的负载。它们也用于识别不对称着陆。

10. 发明授权

US09045234B2 Method for airborne kinetic energy conversion 有权
标题翻译：空中动能转换方法
公开(公告)号：US09045234B2
公开(公告)日：2015-06-02
申请号：US13856892
申请日：2013-04-04
申请人： SUNLIGHT PHOTONICS INC.
发明人： Sergey V. Frolov , Michael Cyrus , Allan J. Bruce
IPC分类号： F03D9/00 , B64B1/06 , B64D33/00 , B64D41/00 , B64D47/00
CPC分类号： B64D33/00 , B64C39/024 , B64C2201/042 , B64C2201/066 , B64C2201/141 , B64D27/24 , B64D41/00 , B64D41/007 , B64D47/00 , B64D2041/002 , F03D9/007 , F03D9/11 , F03D9/25 , F03D9/30 , G05D1/0005 , G05D1/101 , H02S10/12 , Y02T50/53 , Y02T50/64
摘要： Methods and apparatus to harvest renewable energy are provided herein. In some embodiments, a method to harvest renewable energy includes providing an aircraft suitable for untethered flight in an open airspace and an airborne kinetic energy conversion system attached to the airframe, the airborne kinetic energy conversion system comprising a turbine, a generator connected to the turbine, and electrical storage means connected to the generator; flying the aircraft; gaining excess kinetic energy; and converting excess kinetic energy into electricity using the kinetic energy conversion system.
摘要翻译：本文提供了收获可再生能源的方法和设备。在一些实施例中，一种收获可再生能源的方法包括提供适用于开放空域中的无螺旋飞行的飞行器以及连接到机身的机载动能转换系统，该机载动能转换系统包括涡轮机，连接到涡轮机的发电机和连接到发电机的电存储装置; 飞机飞行获得过量的动能; 并使用动能转换系统将过量的动能转化为电能。

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