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1.发明授权Systems and methods for providing AC power from multiple turbine engine spools 有权用于从多个涡轮发动机线轴提供交流电力的系统和方法公开(公告)号：US08039983B2
公开(公告)日：2011-10-18
申请号：US12326633
申请日：2008-12-02
申请人： Richard A. Cote , Farhad Nozari
发明人： Richard A. Cote , Farhad Nozari
IPC分类号： F01D15/10
CPC分类号： H02P9/04 , F02C7/275 , F05D2220/7642 , H02P2101/30
摘要： Systems and methods for providing AC power from multiple turbine engine spools are disclosed. A system in a particular embodiment includes a turbofan engine having a compressor, a first turbine and a first shaft connected between the compressor and the first turbine, and a fan, a second turbine and a second shaft connected between the fan and the second turbine. The system can further include a state power bus and a first energy converter coupled between the first shaft and the power bus, with the first energy converter including a starter/generator, and being positioned to convert a first variable frequency energy transmitted by the first shaft to a first generally constant frequency energy. A second energy converter can be coupled between the second shaft and the power bus, with the second energy converter including a generator and being positioned to convert a second variable frequency energy transmitted by the second shaft to a second generally constant frequency energy, with the second generally constant frequency energy in phase with and at generally the same frequency as the first generally constant frequency energy. A controller can be operatively coupled to the starter/generator and the generator, e.g., to control the functions of these devices.
摘要翻译： 公开了用于从多个涡轮发动机线轴提供交流电力的系统和方法。 具体实施方式的系统包括涡轮风扇发动机，其具有压缩机，第一涡轮机和连接在压缩机和第一涡轮机之间的第一轴，以及连接在风扇和第二涡轮机之间的风扇，第二涡轮机和第二轴。 该系统还可以包括状态电源总线和耦合在第一轴和电源总线之间的第一能量转换器，其中第一能量转换器包括起动器/发电机，并且被定位成将由第一轴和第二轴传递的第一可变频率能量 到第一个普遍恒定的频率能量。 第二能量转换器可以耦合在第二轴和电力总线之间，其中第二能量转换器包括发电机并被定位成将由第二轴传递的第二可变频率能量转换成第二大体上恒定的频率能量，其中第二能量转换器 通常为与第一大体上恒定的频率能量相同频率的频率恒定频率能量和与其频率相同的频率。 控制器可以可操作地耦合到起动器/发电机和发电机，例如以控制这些装置的功能。
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2.发明申请SYSTEMS AND METHODS FOR PROVIDING AC POWER FROM MULTIPLE TURBINE ENGINE SPOOLS 有权用于从多个涡轮发动机提供交流电力的系统和方法公开(公告)号：US20120091716A1
公开(公告)日：2012-04-19
申请号：US13275160
申请日：2011-10-17
申请人： Richard A. Cote , Farhad Nozari
发明人： Richard A. Cote , Farhad Nozari
CPC分类号： H02P9/04 , F02C7/275 , F05D2220/7642 , H02P2101/30
摘要： Systems and methods for providing AC power from multiple turbine engine spools are disclosed. An aircraft system in a particular embodiment includes an engine having a first shaft connected and a second shaft. The aircraft system can further include a bus system and a first energy converter including a starter/generator, coupled between the first shaft and the bus system to convert a first variable frequency energy transmitted by the first shaft to a first generally constant frequency energy. A second energy converter can be coupled between the second shaft and the bus system, with the second energy converter including a generator to convert a second variable frequency energy transmitted by the second shaft to a second generally constant frequency energy.
摘要翻译： 公开了用于从多个涡轮发动机线轴提供交流电力的系统和方法。 在特定实施例中的飞机系统包括具有连接第一轴和第二轴的发动机。 飞行器系统还可以包括总线系统和包括启动器/发电机的第一能量转换器，其耦合在第一轴和总线系统之间，以将由第一轴传输的第一可变频率能量转换成第一大体上恒定的频率能量。 第二能量转换器可以耦合在第二轴和总线系统之间，其中第二能量转换器包括发电机，以将由第二轴传输的第二可变频率能量转换成第二大体上恒定的频率能量。
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3.发明申请Systems and Methods for Providing AC Power from Multiple Turbine Engine Spools 有权从多台涡轮发动机调速器提供交流电力的系统和方法公开(公告)号：US20100133813A1
公开(公告)日：2010-06-03
申请号：US12326633
申请日：2008-12-02
申请人： Richard A. Cote , Farhad Nozari
发明人： Richard A. Cote , Farhad Nozari
CPC分类号： H02P9/04 , F02C7/275 , F05D2220/7642 , H02P2101/30
摘要： Systems and methods for providing AC power from multiple turbine engine spools are disclosed. A system in a particular embodiment includes a turbofan engine having a compressor, a first turbine and a first shaft connected between the compressor and the first turbine, and a fan, a second turbine and a second shaft connected between the fan and the second turbine. The system can further include a state power bus and a first energy converter coupled between the first shaft and the power bus, with the first energy converter including a starter/generator, and being positioned to convert a first variable frequency energy transmitted by the first shaft to a first generally constant frequency energy. A second energy converter can be coupled between the second shaft and the power bus, with the second energy converter including a generator and being positioned to convert a second variable frequency energy transmitted by the second shaft to a second generally constant frequency energy, with the second generally constant frequency energy in phase with and at generally the same frequency as the first generally constant frequency energy. A controller can be operatively coupled to the starter/generator and the generator, e.g., to control the functions of these devices.
摘要翻译： 公开了用于从多个涡轮发动机线轴提供交流电力的系统和方法。 具体实施方式的系统包括涡轮风扇发动机，其具有压缩机，第一涡轮机和连接在压缩机和第一涡轮机之间的第一轴，以及连接在风扇和第二涡轮机之间的风扇，第二涡轮机和第二轴。 该系统还可以包括状态电源总线和耦合在第一轴和电源总线之间的第一能量转换器，其中第一能量转换器包括起动器/发电机，并且被定位成将由第一轴和第二轴传递的第一可变频率能量 到第一个普遍恒定的频率能量。 第二能量转换器可以耦合在第二轴和电力总线之间，其中第二能量转换器包括发电机并被定位成将由第二轴传递的第二可变频率能量转换成第二大体上恒定的频率能量，其中第二能量转换器 通常为与第一大体上恒定的频率能量相同频率的频率恒定频率能量和与其频率相同的频率。 控制器可以可操作地耦合到起动器/发电机和发电机，例如以控制这些装置的功能。
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4.发明授权Systems and methods for providing AC power from multiple turbine engine spools 有权用于从多个涡轮发动机线轴提供交流电力的系统和方法公开(公告)号：US08304927B2
公开(公告)日：2012-11-06
申请号：US13275160
申请日：2011-10-17
申请人： Richard A. Cote , Farhad Nozari
发明人： Richard A. Cote , Farhad Nozari
IPC分类号： H02K7/18
CPC分类号： H02P9/04 , F02C7/275 , F05D2220/7642 , H02P2101/30
摘要： Systems and methods for providing AC power from multiple turbine engine spools are disclosed. An aircraft system in a particular embodiment includes an engine having a first shaft connected and a second shaft. The aircraft system can further include a bus system and a first energy converter including a starter/generator, coupled between the first shaft and the bus system to convert a first variable frequency energy transmitted by the first shaft to a first generally constant frequency energy. A second energy converter can be coupled between the second shaft and the bus system, with the second energy converter including a generator to convert a second variable frequency energy transmitted by the second shaft to a second generally constant frequency energy.
摘要翻译： 公开了用于从多个涡轮发动机线轴提供交流电力的系统和方法。 在特定实施例中的飞机系统包括具有连接第一轴和第二轴的发动机。 飞行器系统还可以包括总线系统和包括启动器/发电机的第一能量转换器，其耦合在第一轴和总线系统之间，以将由第一轴传输的第一可变频率能量转换成第一大体上恒定的频率能量。 第二能量转换器可以耦合在第二轴和总线系统之间，其中第二能量转换器包括发电机，以将由第二轴传输的第二可变频率能量转换成第二大体上恒定的频率能量。
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5.发明授权公开(公告)号：US08163256B2
公开(公告)日：2012-04-24
申请号：US12509845
申请日：2009-07-27
IPC分类号： B01L3/02
CPC分类号： B01L3/0279 , B01L3/0217
摘要： An air displacement pipette has a tubular pipette tip with an upper section surrounding a locking chamber, and a body section leading from the upper section and tapering downwardly to a reduced diameter end. A tubular mounting shaft on the pipette has a distal end configured and dimensioned for axial insertion into the locking chamber of the pipette tip. Coacting surfaces on the distal end of the mounting shaft and the upper section of the pipette tip establish an axially interengaged relationship between the pipette tip and the mounting shaft in response to insertion of the distal end of the mounting shaft into the locking chamber. A sleeve is axially shiftable on the mounting shaft between a retracted position accommodating the establishment of the axially interengaged relationship, and an advanced position disrupting the axially interengaged relationship to thereby accommodate axial ejection of the pipette tip from the mounting shaft.
摘要翻译： 空气移液移液管具有管状移液管末端，其具有围绕锁定室的上部，以及从上部引出并向下逐渐缩小至缩小直径端的主体部分。 移液管上的管状安装轴具有远端，其构造和尺寸设计成用于轴向插入移液管尖端的锁定室。 响应于将安装轴的远端插入到锁定室中，移液管尖端和安装轴之间的联合表面在安装轴的远端和移液管尖端的上部部分之间形成轴向相互接合的关系。 套筒可以在安装轴上轴向移动，在缩回位置容纳轴向相互关联的关系的建立之间，并且前进位置破坏了轴向相互接合的关系，从而适应移液管尖端从安装轴的轴向喷射。
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公开(公告)号：US20120327378A1
公开(公告)日：2012-12-27
申请号：US13169984
申请日：2011-06-27
CPC分类号： G03B21/145 , B64D47/02 , G03B29/00 , G09F19/18 , G09F21/06 , G09F21/08 , G09F21/10 , G09G3/025 , G09G2380/12
摘要： A method and apparatus comprising a projector system and a structure connected to the projector system. The projector system is configured to project an image on an exterior surface of an aircraft. The structure is configured to be connected to the aircraft and has a shape configured to reduce an undesired airflow caused by the projector system when the aircraft is in flight.
摘要翻译： 一种包括投影仪系统和连接到投影仪系统的结构的方法和装置。 投影仪系统被配置为在飞行器的外表面上投影图像。 该结构被配置为连接到飞行器，并且具有被配置为在飞行器飞行时减少由投影仪系统引起的不希望的气流的形状。
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公开(公告)号：US08245973B2
公开(公告)日：2012-08-21
申请号：US11944246
申请日：2007-11-21
申请人： Richard A. Cote , Ty A. Larsen
发明人： Richard A. Cote , Ty A. Larsen
IPC分类号： B64C1/14
CPC分类号： B64D47/06
摘要： A method for improving the conspicuity of aircraft is described that includes determining onto which exposed portions of an aircraft surface a retro-reflective material is to be placed, and attaching the retro-reflective material to the exposed portions such that an observer of the retro-reflective material is provided with an indication of a size, location, and orientation of the aircraft.
摘要翻译： 描述了一种用于改善飞行器显着性的方法，其包括确定飞行器表面的哪个暴露部分将被放置在回射材料上，以及将反射材料附接到暴露部分， 反射材料具有飞行器的尺寸，位置和取向的指示。
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8.发明授权公开(公告)号：US07641859B2
公开(公告)日：2010-01-05
申请号：US10991673
申请日：2004-11-18
IPC分类号： B01L3/02
CPC分类号： B01L3/0279 , B01L3/0217
摘要： An air displacement pipette has a tubular pipette tip with an upper section surrounding a locking chamber, and a body section leading from the upper section and tapering downwardly to a reduced diameter end. A tubular mounting shaft on the pipette has a distal end configured and dimensioned for axial insertion into the locking chamber of the pipette tip. Coacting surfaces on the distal end of the mounting shaft and the upper section of the pipette tip establish an axially interengaged relationship between the pipette tip and the mounting shaft in response to insertion of the distal end of the mounting shaft into the locking chamber. A sleeve is axially shiftable on the mounting shaft between a retracted position accommodating the establishment of the axially interengaged relationship, and an advanced position disrupting the axially interengaged relationship to thereby accommodate axial ejection of the pipette tip from the mounting shaft.
摘要翻译： 空气移液移液管具有管状移液管末端，其具有围绕锁定室的上部，以及从上部引出并向下逐渐缩小至缩小直径端的主体部分。 移液管上的管状安装轴具有远端，其构造和尺寸设计成用于轴向插入移液管尖端的锁定室。 响应于将安装轴的远端插入到锁定室中，移液管尖端和安装轴之间的联合表面在安装轴的远端和移液管尖端的上部部分之间形成轴向相互接合的关系。 套筒可以在安装轴上轴向移动，在缩回位置容纳轴向相互关联的关系的建立之间，并且前进位置破坏了轴向相互接合的关系，从而适应移液管尖端从安装轴的轴向喷射。
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9.发明申请ELECTRICAL SYSTEMS ARCHITECTURE FOR AN AIRCRAFT, AND RELATED OPERATING METHODS 有权用于飞机的电气系统结构及相关操作方法公开(公告)号：US20090127855A1
公开(公告)日：2009-05-21
申请号：US11944199
申请日：2007-11-21
申请人： Mark S. Shander , Richard A. Cote , Michael L. Drake , Howard Carter, III , John T. Peters , Casey Y.K. Ng , Michael S. Hoag , John T. Paterson
发明人： Mark S. Shander , Richard A. Cote , Michael L. Drake , Howard Carter, III , John T. Peters , Casey Y.K. Ng , Michael S. Hoag , John T. Paterson
CPC分类号： H02J4/00 , B64D2221/00 , Y02T50/54
摘要： An electrical architecture for an aircraft is provided. The electrical architecture is particularly suitable for relatively small, compact, and lightweight aircraft. In one embodiment, the electrical architecture includes an electrical generator component coupled to the aircraft engine, and an air compression system coupled to the electrical generator component. The electrical generator component is configured to receive mechanical power from the engine and to generate a constant frequency AC electrical power from the engine mechanical power, and the air compression system is configured to receive the constant frequency AC power as an input and, in response thereto, produce a pressurized air output having variable characteristics (for example, a variable flow rate or a variable air pressure).
摘要翻译： 提供飞机的电气结构。 电气结构特别适用于相对较小，紧凑且重量轻的飞机。 在一个实施例中，电气结构包括耦合到飞行器发动机的发电机部件和耦合到发电机部件的空气压缩系统。 发电机部件被配置为从发动机接收机械动力并且从发动机机械动力产生恒定频率的交流电力，并且空气压缩系统被配置为接收作为输入的恒定频率AC电力，并且响应于此 产生具有可变特性（例如，可变流量或可变空气压力）的加压空气输出。
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公开(公告)号：US20090127386A1
公开(公告)日：2009-05-21
申请号：US11944246
申请日：2007-11-21
申请人： Richard A. Cote , Ty A. Larsen
发明人： Richard A. Cote , Ty A. Larsen
CPC分类号： B64D47/06
摘要： A method for improving the conspicuity of aircraft is described that includes determining onto which exposed portions of an aircraft surface a retro-reflective material is to be placed, and attaching the retro-reflective material to the exposed portions such that an observer of the retro-reflective material is provided with an indication of a size, location, and orientation of the aircraft.
摘要翻译： 描述了一种用于改善飞行器显着性的方法，其包括确定飞行器表面的哪个暴露部分将被放置在回射材料上，以及将反射材料附接到暴露部分， 反射材料具有飞行器的尺寸，位置和取向的指示。
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