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公开(公告)号：US09038955B2
公开(公告)日：2015-05-26
申请号：US13559227
申请日：2012-07-26
申请人： Kenichi Goto
发明人： Kenichi Goto
CPC分类号： B64D37/28 , Y10T137/7303
摘要： A fuel transfer system for an aircraft includes an upper tank, a lower tank, a fuel transfer line connecting the upper tank to the lower tank, an upper fuel transfer line outlet in the lower tank, a lower fuel transfer line outlet in the lower tank, an upper float valve associated with the upper fuel transfer line outlet, and a lower float valve associated with the lower fuel transfer line outlet. The upper fuel transfer line outlet, which is in the lower tank, is in fluid communication with the upper tank. The lower fuel transfer line outlet, which is located in the lower tank, is in fluid communication with the upper tank.
摘要翻译： 一种用于飞行器的燃料传输系统，包括上部罐，下部罐，连接上部罐与下部罐的燃料传输线，下部罐中的上部燃料传输线出口，下部罐中的下部燃料传输线出口 ，与上燃料传输线出口相关联的上浮阀和与下燃料传输线出口相关联的下浮阀。 位于下部箱体中的上部燃料传输管路出口与上部箱体流体连通。 下部燃料传输线出口位于下部箱体中，与上部箱体流体连通。
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公开(公告)号：US08950186B2
公开(公告)日：2015-02-10
申请号：US13229751
申请日：2011-09-11
申请人： William H. McCabe
发明人： William H. McCabe
CPC分类号： F02C9/30 , B64D37/28 , F02C7/222 , F02C7/236 , F02C9/28 , F05D2260/80 , F05D2270/304
摘要： A system and method for supplementing fuel feed pressure and flow within an aircraft fuel system. The fuel system includes boost and override fuel pumps delivering fuel from the tanks to a fuel manifold, and a jettison fuel pump. The method includes the steps of: (a) sensing whether the aircraft engine is operating near maximum power; (b) upon sensing the condition, operating the jettison fuel pump in fluid interconnection with the override fuel pump to deliver fuel to the fuel manifold; and (c) upon sensing the cessation of the condition, deactivating the jettison fuel pump. The system includes a monitoring circuit signaling when the aircraft engine speed is greater than a predetermined threshold, and a fuel system control circuit operating a jettison fuel pump enable circuit portion in response to the signal while omitting other jettisoning operations. The jettison fuel pump consequently functions as an override fuel pump assist.
摘要翻译： 用于补充飞机燃料系统内的燃料供给压力和流量的系统和方法。 燃料系统包括增压和超控燃料泵，其将燃料从罐运送到燃料歧管以及喷射燃料泵。 该方法包括以下步骤：（a）检测飞机发动机是否在最大功率附近运行; （b）在感测到该状况时，操作喷射燃料泵与超控燃料泵的流体互连以将燃料输送到燃料歧管; 和（c）在检测到状况停止时，停用喷射燃料泵。 该系统包括当飞行器发动机转速大于预定阈值时的监视电路信号，以及燃料系统控制电路，在省略其它放弃操作的同时响应该信号操作喷射燃料泵启动电路部分。 因此，抛射燃料泵作为超控燃油泵辅助。
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公开(公告)号：US20140027575A1
公开(公告)日：2014-01-30
申请号：US13559227
申请日：2012-07-26
申请人： Kenichi Goto
发明人： Kenichi Goto
IPC分类号： B64D37/28
CPC分类号： B64D37/28 , Y10T137/7303
摘要： A fuel transfer system for an aircraft includes an upper tank, a lower tank, a fuel transfer line connecting the upper tank to the lower tank, an upper fuel transfer line outlet in the lower tank, a lower fuel transfer line outlet in the lower tank, an upper float valve associated with the upper fuel transfer line outlet, and a lower float valve associated with the lower fuel transfer line outlet. The upper fuel transfer line outlet, which is in the lower tank, is in fluid communication with the upper tank. The lower fuel transfer line outlet, which is located in the lower tank, is in fluid communication with the upper tank.
摘要翻译： 一种用于飞行器的燃料传输系统，包括上部罐，下部罐，连接上部罐与下部罐的燃料传输线，下部罐中的上部燃料传输线出口，下部罐中的下部燃料传输线出口 ，与上燃料传输线出口相关联的上浮阀和与下燃料传输线出口相关联的下浮阀。 位于下部箱体中的上部燃料传输管路出口与上部箱体流体连通。 下部燃料传输线出口位于下部箱体中，与上部箱体流体连通。
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公开(公告)号：US20240125274A1
公开(公告)日：2024-04-18
申请号：US18487229
申请日：2023-10-16
申请人： Airbus SAS , Airbus Operations SAS
发明人： Olivier RASPATI , Jonathan LANDOLT
摘要： An apparatus contains a dihydrogen tank and/or a dihydrogen circuit, and a device for regulating a concentration of dihydrogen located outside the tank and/or the circuit. The device includes at least one pair of electrical conductors including a first electrical conductor supplied with a first voltage and a second electrical conductor supplied with a second voltage which is different from the first voltage. At least one controller repeatedly commands the application of a predetermined voltage difference between the first electrical conductor and the second electrical conductor so that an electric arc of controlled power is formed in order to burn dihydrogen possibly coming from the tank and/or from the circuit. Thus, dihydrogen does not accumulate in undesired places in the apparatus.
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公开(公告)号：US20230406528A1
公开(公告)日：2023-12-21
申请号：US18152824
申请日：2023-01-11
发明人： Ikumi Kurihara , Toshiaki Fujii
摘要： An aircraft includes a cabin in which an occupant rides, and a driving source driven by using fuel supplied thereto, the aircraft further including a tank unit which is disposed between the cabin and the driving source and in which a plurality of fuel tanks for storing the fuel are stacked.
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公开(公告)号：US11332257B2
公开(公告)日：2022-05-17
申请号：US16595689
申请日：2019-10-08
申请人： BOMBARDIER INC.
发明人： Andrei Drancea , George Viscotchi
摘要： Fuel systems, apparatus and associated methods for preventing or hindering unwanted fuel transfer between fuel tanks of aircraft are described. An exemplary apparatus comprises a conduit portion disposed inside a fuel tank for receiving fuel in the first fuel tank. The conduit portion includes an orifice through a wall of the conduit. The orifice permits venting an interior of the conduit portion to an interior of the fuel tank to prevent unwanted fuel transfer due to siphoning. A deflector is disposed and configured to deflect a stream of fuel discharged from the orifice during fuel transfer.
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公开(公告)号：US20210139159A1
公开(公告)日：2021-05-13
申请号：US16678905
申请日：2019-11-08
发明人： Charles E. Reuter , Gerald P. Dyer
摘要： Apparatus and associated methods relate to simultaneously pumping and measuring density of an aircraft fuel. The aircraft fuel is pumped by a centrifugal pump having an impeller. A rotational frequency of the impeller is determined while the centrifugal pump is pumping the aircraft fuel. Flow rate of the aircraft fuel through the centrifugal pump is sensed. Pressure of the aircraft fuel is measured at two different points within or across the centrifugal pump or a differential pressure is measured between the two different points while the centrifugal pump is pumping the aircraft fuel. Density of the aircraft fuel is determined based on a head-curve relation characterizing the centrifugal pump. The head-curve relation relates the fuel density to the rotational frequency, the flow rate, and pressures at the two different points or the differential pressure between the two different points.
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公开(公告)号：US10710737B2
公开(公告)日：2020-07-14
申请号：US15363509
申请日：2016-11-29
发明人： Dylan James , Justine McCarthy , Angus Morgan , Michael Poad , Nicholas Morton , Henry Edwards , Richard Burness , Christopher Slack
摘要： An aircraft fuel tank system including a fuel tank compartment for containing liquid fuel and having a float-activated valve arranged to become positively buoyant when immersed in liquid fuel so that the float moves up to a raised position which causes the valve to close and prevent liquid fuel from flowing out of the fuel tank compartment through the valve. The float is also arranged to move down to a lowered position in response to a level of the liquid fuel in the fuel tank compartment dropping, the movement of the float to the lowered position causing the valve to open and permit liquid fuel to flow out of the fuel tank compartment through the valve. A pressure-activated valve may be used as an alternative to the float-activated valve.
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公开(公告)号：US10670442B2
公开(公告)日：2020-06-02
申请号：US15635558
申请日：2017-06-28
摘要： An airplane is provided. The airplane includes a fuel gauging and quantity estimation system with an improved estimation accuracy. The fuel gauging and quantity estimation system operates by detecting an environment of a tank comprising a liquid and selecting one or more liquid gauging algorithms based on the environment. The fuel gauging and quantity estimation system further operates by receiving sensor data characterizing the liquid of the tank and utilizing the sensor data and the one or more liquid gauging algorithms to determine a property of the liquid.
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公开(公告)号：US10309313B2
公开(公告)日：2019-06-04
申请号：US14909646
申请日：2014-07-31
摘要： A fuel circuit of an aircraft engine including a fuel tank; an engine fuel system including a low-pressure pump and a high-pressure pump, and a fuel recirculating pipeline connected to the engine fuel system; and a fuel recirculating valve arranged so as to switch between an open position and a closed position according to the pressure differential of the low-pressure pump, the valve being able to obstruct the fuel recirculating pipeline in the closed position, and to bring the fuel recirculating pipeline into communication with the fuel tank in the open position.
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