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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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公开(公告)号：US07568382B2
公开(公告)日：2009-08-04
申请号：US11809329
申请日：2007-05-31
IPC分类号： G01M15/00
CPC分类号： G01L5/133
摘要： An engine test system includes a base constructed and arranged to reside at a fixed location. The system further includes an engine support member constructed and arranged to concurrently support an engine and move relative to the base. The system further includes a linear transducer having (i) a first portion supported by the base, (ii) a second portion supported by the engine support member, and (iii) a circuit adjacent the first and second portions. The circuit is constructed and arranged to provide a linear transducer signal identifying an amount of linear compression and/or tension between the engine support member and the base along a predefined direction. When the linear transducer resides at a break in station, such an embodiment provides a simple, low cost mechanism which is capable of providing a horsepower measurement for every engine passing through the break in station.
摘要翻译： 引擎测试系统包括构造和布置成驻留在固定位置的基座。 该系统还包括构造和布置成同时支撑发动机并相对于基座移动的发动机支撑构件。 该系统还包括线性换能器，其具有（i）由基座支撑的第一部分，（ii）由发动机支撑构件支撑的第二部分，以及（iii）与第一和第二部分相邻的电路。 电路被构造和布置成提供线性换能器信号，其沿着预定方向识别发动机支撑构件和基座之间的线性压缩和/或张力的量。 当线性换能器驻留在车站中断时，这种实施例提供了一种简单的低成本机构，其能够为通过车站中断的每个发动机提供马力测量。
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公开(公告)号：US20090112440A1
公开(公告)日：2009-04-30
申请号：US11928293
申请日：2007-10-30
IPC分类号： F02D41/00
CPC分类号： F02D41/182 , F02D41/3809 , F02D2200/0402 , F02D2200/0406 , F02D2200/0414 , G01F1/88
摘要： A piston aircraft engine assembly includes a piston aircraft engine, a fuel source, and a control system adapted to deliver fuel from the fuel source to the piston aircraft engine. The control system includes a mass airflow sensing apparatus adapted provide a pressure signal, an electronic engine controller coupled to the mass airflow sensing apparatus, and a set of fuel injectors. The electronic engine controller is adapted to (i) receive the pressure signal from the mass airflow sensing apparatus and (ii) generate a set of fuel injector signals based on the pressure signal received from the mass airflow sensing apparatus. The set of fuel injectors is adapted to meter the fuel in response to the set of fuel injector signals generated by the electronic engine controller.
摘要翻译： 活塞式飞机发动机组件包括活塞飞机发动机，燃料源和适于将燃料从燃料源输送到活塞飞机发动机的控制系统。 控制系统包括适于提供压力信号的质量气流感测装置，耦合到质量气流感测装置的电子发动机控制器和一组燃料喷射器。 电子发动机控制器适于（i）从质量气流感测装置接收压力信号，以及（ii）基于从质量气流感测装置接收的压力信号产生一组燃料喷射器信号。 该组燃料喷射器适于响应于由电子发动机控制器产生的一组燃料喷射器信号来计量燃料。
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5.发明申请Sensing rotation of an engine component relative to an engine body using a starter ring 有权使用起动环感测发动机部件相对于发动机主体的旋转公开(公告)号：US20080148833A1
公开(公告)日：2008-06-26
申请号：US11590533
申请日：2006-10-31
申请人： Ken Kremer , Forrest Lysinger , Jason Rogers
发明人： Ken Kremer , Forrest Lysinger , Jason Rogers
IPC分类号： G01L3/26
CPC分类号： F02N15/00 , F02D41/009 , F02N11/00 , F02N15/006 , F02P7/0677 , G01P3/481 , G01P3/487
摘要： In one embodiment, a sensing apparatus senses rotation of an engine component (e.g., a crank shaft) relative to an engine body. The sensing apparatus includes a sensor, and a bracket configured to position the sensor in a fixed location relative to the engine body. The starter ring has (i) a support portion configured to rotate in tandem with the engine component, (ii) a starter interface mounted to the support portion, the starter interface being configured to receive drive from a starter motor during operation of the starter motor, and (iii) a trigger portion mounted to the support portion. The trigger portion is configured to provide a series of indicators during rotation of the engine component. The series of indicators (e.g., a series of magnetic field perturbations during rotation of the engine component) is readable by the sensor thus enabling identification of component positioning and speed.
摘要翻译： 在一个实施例中，感测装置相对于发动机主体感测发动机部件（例如，曲轴）的旋转。 感测装置包括传感器和配置成将传感器相对于发动机主体定位在固定位置的支架。 起动环具有（i）配置成与发动机部件串联旋转的支撑部分，（ii）安装到支撑部分的起动器接口，起动器接口构造成在起动电动机的运行期间从起动电动机接收驱动 ，和（iii）安装到支撑部分的触发器部分。 触发器部分构造成在发动机部件旋转期间提供一系列指示器。 指示器系列（例如，发动机部件旋转期间的一系列磁场扰动）可由传感器读取，从而能够识别部件定位和速度。
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公开(公告)号：US20030234002A1
公开(公告)日：2003-12-25
申请号：US10355273
申请日：2003-01-31
发明人： Donald J. Rivera
IPC分类号： F02M001/00
CPC分类号： F02M19/035 , F02M17/04 , F02M19/12
摘要： The present invention provides a fuel control apparatus with a modular fuel pressure modifying mechanism (i.e., a fuel metering section) and modular fuel regulator mechanism (i.e.. r fuel regulator section) that can each be calibrated independently of each other, and independent from the modular air passage mechanism (i.e., an airflow section). The air passage mechanism has an air intake end and an air outlet end and is constructed and arranged to accommodate airflow therethrough. the air passage mechanism having a first surface portion formed on an outer surface thereon. The modular fuel pressure modifying mechanism is constructed and arranged to receive fuel from a supply and deliver a portion of the hid at a pressure that is different from the pressure of the fuel supply, the modular fuel pressure modifying mechanism being removably mountable to the first surface portion of the air passage mechanism. The modular fuel pressure modifying mechanism is constructed and arranged to he calibrated prior to being mounted to the air passage mechanism. The fuel regulator mechanism is constructed and arranged to communicate with the airflow in the air passage mechanism and the modular fuel pressure modifying mechanism to regulate an amount of fuel delivered to the engine. The modular fuel pressure modifying mechanism and the modular fuel regulator mechanism are removably mountable to the modular air passage mechanism independently from each other.
摘要翻译： 本发明提供了一种燃料控制装置，其具有模块化燃料压力调节机构（即，燃料计量部分）和模块化燃料调节器机构（即，燃料调节器部分），其可以彼此独立地校准，并且独立于 模块化空气通道机构（即气流部分）。 空气通道机构具有进气端和空气出口端，并且构造和布置成适应气流通过。 空气通道机构具有形成在其上的外表面上的第一表面部分。 模块化燃料压力调节机构被构造和布置成从供应源接收燃料并以不同于燃料供应的压力的压力输送一部分隐藏物，模块化燃料压力调节机构可拆卸地安装到第一表面 空气通道机构的一部分。 模块化燃料压力调节机构被构造和布置成在安装到空气通道机构之前进行校准。 燃料调节机构被构造和布置成与空气通道机构中的气流和模块化燃料压力调节机构相通以调节输送到发动机的燃料量。 模块化燃料压力调节机构和模块化燃料调节机构可独立于可拆卸地安装到模块化空气通道机构。
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7.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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公开(公告)号：US20090259350A1
公开(公告)日：2009-10-15
申请号：US12100244
申请日：2008-04-09
IPC分类号： B64D31/00
CPC分类号： F02C9/00 , B64F5/60 , F05D2260/80 , F05D2270/708
摘要： One embodiment is directed to a method for testing an aircraft prior to flight. The method includes receiving a user signal from a pre-flight test input source, the user signal indicating that a pilot of the aircraft has directed engine control circuitry, which is arranged to electronically control operation of a set of piston engines of the aircraft during flight, to begin testing the aircraft in an automated manner. The method includes, in response to the user signal, conducting a pre-flight test of the aircraft from the engine control circuitry. The method includes, upon completion of the pre-flight test, outputting a result of the pre-flight test from the engine control circuitry.
摘要翻译： 一个实施例涉及在飞行之前测试飞行器的方法。 该方法包括从飞行前测试输入源接收用户信号，该用户信号指示飞行器的飞行员指示发动机控制电路，该引擎控制电路被布置成在飞行期间以电子方式控制飞行器的一组活塞发动机的操作 ，以自动方式开始测试飞机。 该方法包括响应于用户信号，从发动机控制电路进行飞机的飞行前试验。 该方法包括在完成飞行前测试之后，从发动机控制电路输出飞行前测试的结果。
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9.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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公开(公告)号：US07284524B2
公开(公告)日：2007-10-23
申请号：US11065346
申请日：2005-02-25
申请人： Scott Matas , Tim Mooney , Mike Sitar
发明人： Scott Matas , Tim Mooney , Mike Sitar
IPC分类号： F02B23/08
CPC分类号： F02B23/08 , F02B2023/085 , F02F1/06 , F02F1/30 , Y02T10/125 , Y02T10/146
摘要： Cylinder head assemblies including a cylinder head and a piston are disclosed. The cylinder head includes: a recessed valve region including a first and second bulbous portion connected by a waist, the first bulbous portion accommodating an intake valve and the second bulbous portion accommodating an exhaust valve; an intake port passageway having a gradually contoured flowpath between an intake port and the intake valve in the valve region; and an exhaust port passageway having a gradually contoured flowpath between an exhaust port and the exhaust valve in the valve region. The piston includes a recessed region that substantially conforms to the recessed valve region of the cylinder head. Related overhaul kits and methods of making improved cylinder head assemblies are further disclosed.
摘要翻译： 公开了包括气缸盖和活塞的气缸盖组件。 气缸盖包括：凹陷阀区域，包括由腰部连接的第一和第二球形部分，第一球形部分容纳进气阀，第二球形部分容纳排气阀; 进气口通道，其在阀区域中的进气口和进气门之间具有逐渐变形的流路; 以及排气口通道，其在阀区域中的排气口和排气阀之间具有逐渐变形的流路。 活塞包括基本上符合气缸盖的凹陷阀区域的凹陷区域。 进一步公开了相关的检修套件和制造改进的气缸盖组件的方法。
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