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1.发明申请公开(公告)号：US20090031992A1
公开(公告)日：2009-02-05
申请号：US12104646
申请日：2008-04-17
CPC分类号： F02M69/465 , F02M55/02 , F02M55/025 , F02M61/14 , F02M2200/26 , F02M2200/306 , Y10T29/49231
摘要： A fuel injector mounting assembly is configured to limit or constrain movement of a fuel injector relative to a corresponding cylinder assembly. For example, the fuel injector mounting assembly includes a base that is secured to a cylinder assembly's housing and a fuel conduit. The fuel conduit includes a first fuel conduit portion which operates in conjunction with a cylinder assembly's fuel manifold to capture a fuel injector between the fuel injector mounting assembly and the cylinder assembly's fuel manifold. The fuel conduit also includes a second fuel conduit portion which is secured to a compliant fuel line. With such a configuration of the fuel injector mounting assembly, both ends of the fuel injector are secured to the cylinder assembly to minimize any relative motion in the fuel injector's seals relative to either the cylinder assembly's fuel manifold or to the compliant fuel line.
摘要翻译： 燃料喷射器安装组件被配置为限制或限制燃料喷射器相对于相应的气缸组件的运动。 例如，燃料喷射器安装组件包括固定到气缸组件的壳体和燃料导管的基座。 燃料管道包括第一燃料管道部分，其与气缸组件的燃料歧管结合操作以在燃料喷射器安装组件和气缸组件的燃料歧管之间捕获燃料喷射器。 燃料管道还包括固定到柔性燃料管线的第二燃料管道部分。 通过燃料喷射器安装组件的这种构造，燃料喷射器的两端固定到气缸组件，以使燃料喷射器的密封件相对于气缸组件的燃料歧管或柔性燃料管线的任何相对运动最小化。
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2.发明授权Fuel injector mounting assembly for an aircraft engine fuel delivery system 有权用于飞机发动机燃料输送系统的燃油喷射器安装组件公开(公告)号：US07802560B2
公开(公告)日：2010-09-28
申请号：US12104646
申请日：2008-04-17
CPC分类号： F02M69/465 , F02M55/02 , F02M55/025 , F02M61/14 , F02M2200/26 , F02M2200/306 , Y10T29/49231
摘要： A fuel injector mounting assembly is configured to limit or constrain movement of a fuel injector relative to a corresponding cylinder assembly. For example, the fuel injector mounting assembly includes a base that is secured to a cylinder assembly's housing and a fuel conduit. The fuel conduit includes a first fuel conduit portion which operates in conjunction with a cylinder assembly's fuel manifold to capture a fuel injector between the fuel injector mounting assembly and the cylinder assembly's fuel manifold. The fuel conduit also includes a second fuel conduit portion which is secured to a compliant fuel line. With such a configuration of the fuel injector mounting assembly, both ends of the fuel injector are secured to the cylinder assembly to minimize any relative motion in the fuel injector's seals relative to either the cylinder assembly's fuel manifold or to the compliant fuel line.
摘要翻译： 燃料喷射器安装组件被配置为限制或限制燃料喷射器相对于相应的气缸组件的运动。 例如，燃料喷射器安装组件包括固定到气缸组件的壳体和燃料导管的基座。 燃料管道包括第一燃料管道部分，其与气缸组件的燃料歧管结合操作以在燃料喷射器安装组件和气缸组件的燃料歧管之间捕获燃料喷射器。 燃料管道还包括固定到柔性燃料管线的第二燃料管道部分。 通过燃料喷射器安装组件的这种构造，燃料喷射器的两端固定到气缸组件，以使燃料喷射器的密封件相对于气缸组件的燃料歧管或柔性燃料管线的任何相对运动最小化。
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公开(公告)号：US07828509B2
公开(公告)日：2010-11-09
申请号：US11708414
申请日：2007-02-20
IPC分类号： F04D29/10
CPC分类号： F04C15/0038 , F02M37/045 , F04C14/26
摘要： A fuel pump includes a bearing element disposed in proximity to an impeller. The bearing element is configured to form a fuel seal with the impeller and to drain fuel leaked from the pump chamber back into the pump chamber. The bearing element minimizes leakage of fuel from the pump chamber into an engine coupled to the impeller. The fuel pump also includes redundant lip seals configured to provide redundant sealing relative to a shaft of the impeller within the fuel pump in order to minimize engine oil from entering the pump chamber and to minimize fuel from entering the engine. Integration of both the bearing element and the redundant lip seals as part of the fuel pump results in the fuel pump having a relatively compact size.
摘要翻译： 燃料泵包括设置在叶轮附近的轴承元件。 轴承元件构造成与叶轮形成燃料密封，并将从泵室泄漏的燃料排放回泵室。 轴承元件使燃料从泵室泄漏到与叶轮连接的发动机中最小化。 燃料泵还包括冗余唇形密封件，其配置成相对于燃料泵内的叶轮的轴提供冗余的密封，以便最小化发动机油进入泵室并使燃料进入发动机最小化。 作为燃料泵的一部分，轴承元件和冗余唇形密封件的集成导致燃料泵具有相对紧凑的尺寸。
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公开(公告)号：US20080199302A1
公开(公告)日：2008-08-21
申请号：US11708414
申请日：2007-02-20
IPC分类号： F04D1/04
CPC分类号： F04C15/0038 , F02M37/045 , F04C14/26
摘要： A fuel pump includes a bearing element disposed in proximity to an impeller. The bearing element is configured to form a fuel seal with the impeller and to drain fuel leaked from the pump chamber back into the pump chamber. The bearing element minimizes leakage of fuel from the pump chamber into an engine coupled to the impeller. The fuel pump also includes redundant lip seals configured to provide redundant sealing relative to a shaft of the impeller within the fuel pump in order to minimize engine oil from entering the pump chamber and to minimize fuel from entering the engine. Integration of both the bearing element and the redundant lip seals as part of the fuel pump results in the fuel pump having a relatively compact size.
摘要翻译： 燃料泵包括设置在叶轮附近的轴承元件。 轴承元件构造成与叶轮形成燃料密封，并将从泵室泄漏的燃料排放回泵室。 轴承元件使燃料从泵室泄漏到与叶轮连接的发动机中最小化。 燃料泵还包括冗余唇形密封件，其配置成相对于燃料泵内的叶轮的轴提供冗余的密封，以便最小化发动机油进入泵室并使燃料进入发动机最小化。 作为燃料泵的一部分，轴承元件和冗余唇形密封件的集成导致燃料泵具有相对紧凑的尺寸。
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公开(公告)号：US07875989B2
公开(公告)日：2011-01-25
申请号：US11899053
申请日：2007-09-04
CPC分类号： H02J1/10 , H02J9/066 , Y10T307/344
摘要： An aircraft engine power distribution system for an aircraft engine controller, such as a FADEC, is provided where the power source is independent from the conventional airframe power system, without the need for a back-up battery. The aircraft engine power distribution system includes a magnetic generator operated by an aircraft engine. The aircraft engine power distribution system also includes a power distributor that rectifies the generator output and provides the rectified power to the engine controller as its primary source of power. In this configuration, as long as the aircraft engine is able to operate the magnetic generator, the engine controller receives power. Accordingly, the engine controller operates regardless of the operational status of the airframe power system.
摘要翻译： 提供用于飞机发动机控制器（例如FADEC）的飞机发动机配电系统，其中电源独立于常规的机身电力系统，而不需要备用电池。 飞机发动机配电系统包括由飞机发动机操作的磁力发电机。 飞机发动机配电系统还包括一个功率分配器，其对发电机输出进行整流，并将整流后的功率提供给发动机控制器作为其主要电源。 在这种配置中，只要飞机发动机能够操作磁力发电机，发动机控制器就会接收电力。 因此，无论机身电力系统的运行状态如何，发动机控制器都运行。
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6.发明申请公开(公告)号：US20100043750A1
公开(公告)日：2010-02-25
申请号：US11948424
申请日：2007-11-30
CPC分类号： F02P7/0675 , F02D41/009 , F02D41/0097
摘要： A crankshaft detection system includes a pickup element mounted to an end of a crankshaft and disposed within a rear portion of the aircraft engine's crankcase. The crankshaft detection system also includes pickup element sensor secured to a mounting location formed in the rear portion of the aircraft engine's crankcase and disposed in proximity to the pickup element. As the crankshaft rotates the pickup element relative to the pickup element sensor, the pickup element causes the pickup element sensor to generate a signal indicative of the angular velocity and rotational position of the crankshaft. In order to optimize engine performance, in response to the signal, the controller controls a spark event associated with each the cylinder assembly of the engine such that ignition of the fuel and air mixture occurs within each cylinder assembly at a time prior to each piston of each cylinder assembly reaching a top dead center position.
摘要翻译： 曲轴检测系统包括安装在曲轴端部并设置在飞机发动机曲轴箱的后部内的拾取元件。 曲轴检测系统还包括固定到形成在飞机发动机的曲轴箱的后部并且设置在拾取元件附近的安装位置的拾取元件传感器。 当曲轴相对于拾取元件传感器旋转拾取元件时，拾取元件使得拾取元件传感器产生指示曲轴的角速度和旋转位置的信号。 为了优化发动机性能，响应于信号，控制器控制与发动机的每个气缸组件相关联的火花事件，使得在每个气缸组件内的燃料和空气混合物的点燃在每个活塞的每个活塞之前的时间发生 每个气缸组件达到上止点位置。
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7.发明授权公开(公告)号：US08015962B2
公开(公告)日：2011-09-13
申请号：US11948424
申请日：2007-11-30
IPC分类号： F02P7/067
CPC分类号： F02P7/0675 , F02D41/009 , F02D41/0097
摘要： A crankshaft detection system includes a pickup element mounted to an end of a crankshaft and disposed within a rear portion of the aircraft engine's crankcase. The crankshaft detection system also includes pickup element sensor secured to a mounting location formed in the rear portion of the aircraft engine's crankcase and disposed in proximity to the pickup element. As the crankshaft rotates the pickup element relative to the pickup element sensor, the pickup element causes the pickup element sensor to generate a signal indicative of the angular velocity and rotational position of the crankshaft. In order to optimize engine performance, in response to the signal, the controller controls a spark event associated with each the cylinder assembly of the engine such that ignition of the fuel and air mixture occurs within each cylinder assembly at a time prior to each piston of each cylinder assembly reaching a top dead center position.
摘要翻译： 曲轴检测系统包括安装在曲轴端部并设置在飞机发动机曲轴箱的后部内的拾取元件。 曲轴检测系统还包括固定到形成在飞机发动机的曲轴箱的后部并且设置在拾取元件附近的安装位置的拾取元件传感器。 当曲轴相对于拾取元件传感器旋转拾取元件时，拾取元件使得拾取元件传感器产生指示曲轴的角速度和旋转位置的信号。 为了优化发动机性能，响应于信号，控制器控制与发动机的每个气缸组件相关联的火花事件，使得在每个气缸组件内的燃料和空气混合物的点燃在每个活塞的每个活塞之前的时间发生 每个气缸组件达到上止点位置。
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公开(公告)号：US20090058183A1
公开(公告)日：2009-03-05
申请号：US11899053
申请日：2007-09-04
IPC分类号： H02J3/38
CPC分类号： H02J1/10 , H02J9/066 , Y10T307/344
摘要： An aircraft engine power distribution system for an aircraft engine controller, such as a FADEC, is provided where the power source is independent from the conventional airframe power system, without the need for a back-up battery. The aircraft engine power distribution system includes a magnetic generator operated by an aircraft engine. The aircraft engine power distribution system also includes a power distributor that rectifies the generator output and provides the rectified power to the engine controller as its primary source of power. In this configuration, as long as the aircraft engine is able to operate the magnetic generator, the engine controller receives power. Accordingly, the engine controller operates regardless of the operational status of the airframe power system.
摘要翻译： 提供用于飞机发动机控制器（例如FADEC）的飞机发动机配电系统，其中电源独立于常规的机身电力系统，而不需要备用电池。 飞机发动机配电系统包括由飞机发动机操作的磁力发电机。 飞机发动机配电系统还包括一个功率分配器，其对发电机输出进行整流，并将整流后的功率提供给发动机控制器作为其主要电源。 在这种配置中，只要飞机发动机能够操作磁力发电机，发动机控制器就会接收电力。 因此，无论机身电力系统的运行状态如何，发动机控制器都运行。
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