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1.发明公开公开(公告)号：US20240263745A1
公开(公告)日：2024-08-08
申请号：US18641463
申请日：2024-04-22
CPC分类号： F17C7/02 , B64D37/005 , B64D37/30 , F17C2201/0109 , F17C2221/012 , F17C2223/0161 , F17C2227/0135 , F17C2227/0304 , F17C2227/0374 , F17C2250/043 , F17C2250/0439 , F17C2250/0626 , F17C2250/0636 , F17C2265/066 , F17C2270/0189
摘要： A fuel supply system (1) for a hydrogen-powered aircraft includes: a fuel tank (2) that stores liquefied hydrogen; a pump (5) that discharges the liquefied hydrogen from the fuel tank (2) to supply the liquefied hydrogen to a propulsion device (102); a pressure increasing mechanism (3) that increases a tank internal pressure being a pressure in an inner part of the fuel tank (2); a flow rate controller (71) that controls a flow rate of the liquefied hydrogen to be supplied from the fuel tank (2) to the propulsion device (102); and a pressure controller (73) that controls, on the basis of information which is about the flow rate of the liquefied hydrogen and is input from the flow rate controller (71), the pressure increasing mechanism (3) to adjust the tank internal pressure.
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公开(公告)号：US12006058B2
公开(公告)日：2024-06-11
申请号：US16850361
申请日：2020-04-16
申请人： BOMBARDIER INC.
发明人： Vincenzo Furgiuele
CPC分类号： B64D37/28 , B64D37/00 , B64D37/005 , B64D37/02 , B64D37/32
摘要： A method of and a system for operating a fuel pump management system of an aircraft. The method comprises receiving, from a fuel gauge, an electronic reading of a level of fuel fluid contained in a fuel tank; and analysing the electronic reading of the level of the fuel fluid, the analysing comprising upon determining that the level of fuel fluid is equal or below a predetermined fuel level threshold, causing a fuel pump in communication with the fuel tank to be shut down.
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公开(公告)号：US11811200B2
公开(公告)日：2023-11-07
申请号：US16367745
申请日：2019-03-28
发明人： Timothy Sanderson , Stuart Quayle
IPC分类号： H02G1/08 , H02G3/22 , H02G1/06 , B64F5/40 , B64F5/10 , B60P7/14 , F16L41/12 , F16L47/16 , F16L47/20 , B64D37/00 , B64C1/10 , B25B27/16 , B25B27/14
CPC分类号： H02G1/085 , B25B27/14 , B25B27/16 , B60P7/14 , B64C1/10 , B64D37/005 , B64F5/10 , B64F5/40 , F16L41/12 , F16L47/16 , F16L47/20 , H02G1/06 , H02G3/22
摘要： An apparatus and method for installing an aircraft bulkhead connector with a bulkhead is disclosed where access to only one side of the bulkhead is required. The disclosure is also applicable to installation of bulkhead connectors in aircraft fuel tanks. An aircraft bulkhead connector and installation tool is also disclosed. The bulkhead connector includes a female end portion and the installation tool includes a male end portion. The male end portion of the installation tool is removably engaged with the female end portion of the bulkhead connector, such that the installation tool protrudes beyond the female end portion of the bulkhead connector. The installation tool may be inserted through an aperture in a bulkhead and used to both position and hold the bulkhead connector during the installation process.
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公开(公告)号：US11685544B2
公开(公告)日：2023-06-27
申请号：US16197879
申请日：2018-11-21
CPC分类号： B64D37/005 , F16L39/04
摘要： An expandable fuel line section for an aircraft, a fuel line for an aircraft, and a method for fabricating an expandable fuel line section for an aircraft are provided. In one non-limiting example, the expandable fuel line section includes a first inner tube section subassembly. A second inner tube section subassembly is in fluid communication with the first inner tube section subassembly. An outer tube subassembly has an outer tube wall surrounding an outer tube channel. The first and second inner tube section subassemblies are slidingly disposed in the outer tube channel to move between retracted positions and extended positions.
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5.发明申请公开(公告)号：US20180354644A1
公开(公告)日：2018-12-13
申请号：US15935339
申请日：2018-03-26
CPC分类号： B64D37/34 , B01D53/864 , B01D53/8668 , B01D2257/102 , B01D2257/702 , B01D2259/4575 , B64D37/005 , B64D37/32
摘要： A catalytic inerting system (CIS) architecture includes a fuel tank including a fuel tank inlet and a fuel tank outlet, the fuel tank defining a space for containing a liquid fuel and an ullage space above the liquid fuel containing an ullage gas. A catalytic reactor is in fluid communication with the fuel tank, the catalytic reactor having a catalytic inlet and a catalytic outlet, wherein the catalytic reactor receives an ullage gas flow from the fuel tank outlet and performs a catalytic reaction on the ullage gas to produce a more inert flow from the catalytic outlet to the fuel tank inlet. A bypass line provides a flow pathway between the fuel tank inlet and the fuel tank outlet, thereby bypassing the fuel tank, and a flow control mechanism controls relative flows of the inert flow from the catalytic outlet to the fuel tank inlet versus through the bypass line.
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公开(公告)号：US10082444B2
公开(公告)日：2018-09-25
申请号：US15033007
申请日：2014-10-27
IPC分类号： F02C7/22 , G01M15/00 , B64D37/00 , B64D37/14 , B64D37/32 , F02C7/232 , F16K37/00 , B64D37/02 , G01L19/00
CPC分类号： G01M15/00 , B64D37/00 , B64D37/005 , B64D37/02 , B64D37/14 , B64D37/32 , F02C7/232 , F05D2260/80 , F16K37/00 , F16K37/005 , G01L19/0092
摘要： A method for detecting a failure in a fuel return valve of an aircraft engine fuel circuit, the fuel circuit including a fuel tank, an engine fuel system connected to the fuel tank capable of delivering a flow of fuel to the engine depending on a speed of the engine, a fuel return pipe connected between the engine fuel system and the fuel tank, a fuel return valve arranged to switch between an open and closed position, the valve being capable of blocking the fuel return pipe in the closed position, and of bringing the fuel return pipe into communication with the fuel tank in the open position, the method including measuring a pressure of the flow of fuel from the fuel tank, and if the measured pressure is lower than a predefined threshold, measuring the engine speed.
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公开(公告)号：US10071816B2
公开(公告)日：2018-09-11
申请号：US14769889
申请日：2014-03-06
申请人： BOMBARDIER INC.
CPC分类号： B64D37/32 , B64D37/005 , B64D37/02
摘要： A tank wall connector system for use with a composite tank, the connector comprises a connector having a body extending from an interior of the tank to an exterior of the tank when installed through a hole in the composite tank. The connector has a first electrical conductivity property. An interface is positioned between the connector and a wall of the composite tank when installed to the tank thereby preventing physical contact between the connector and the tank wall in the interior of the tank, the interface having a second electrical conductivity property, different from the first electrical conductivity property.
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公开(公告)号：US10053269B2
公开(公告)日：2018-08-21
申请号：US14616793
申请日：2015-02-09
申请人： The Boeing Company
发明人： Eric Yuen-Jun Chan
IPC分类号： G01N21/00 , B65D65/38 , B64D37/04 , B64D37/00 , G01L9/00 , G01F23/16 , G01K1/00 , G01N9/00 , G01N33/00 , G01K11/32 , G01N21/65
CPC分类号： B65D65/38 , B64D37/005 , B64D37/04 , G01F23/164 , G01K1/00 , G01K11/32 , G01L9/0079 , G01N9/00 , G01N21/65 , G01N33/00
摘要： A fuel sensing system utilizes a fiber optic sensor comprising a membrane made of a direct band gap semiconductor material (such as gallium arsenide) that forms an optical cavity with an optical fiber inside a hermetically sealed sensor package located at the bottom of a fuel tank. The optical fiber inside the fuel tank is not exposed to the fuel. The optical cavity formed by the bottom surface of the membrane and the surface of the distal end of the internal optical fiber is capable of behaving as a Fabry-Pérot interferometer. Multiple light sources operating at different wavelengths and multiple spectrometers can be coupled to the confronting surface of the membrane via the optical fiber inside the fuel tank, a hermetically sealed fiber optic connector that passes through the wall of the fuel tank, and a fiber optic coupler located outside the fuel tank.
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公开(公告)号：US20180215535A1
公开(公告)日：2018-08-02
申请号：US15938064
申请日：2018-03-28
申请人： THE BOEING COMPANY
CPC分类号： B65D90/34 , B64D37/005 , B64F5/45 , B64F5/60
摘要： A system for controlling an environment within a fuel tank is provided. The system includes a conduit with a plurality of vents, wherein the conduit defines a path through the fuel tank, and wherein the conduit is configured to direct a flow of air along the path and out the plurality of vents.
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10.发明授权公开(公告)号：US10036326B2
公开(公告)日：2018-07-31
申请号：US15032821
申请日：2014-10-27
申请人： SNECMA
CPC分类号： F02C7/232 , B64D37/00 , B64D37/005 , B64D37/14 , B64D37/32 , F05D2260/80
摘要： A method detects a failure in a fuel return valve of an aircraft engine fuel circuit. A fuel system is connected to a fuel tank of the circuit and includes a high-pressure pump delivering a flow rate to an actuating cylinder, a cutoff valve capable of feeding the actuating cylinder disposed in a feed pipe of the engine; a fuel return pipe; a fuel return valve arranged to switch between an open position and a closed position. The method includes starting the engine at an engine speed; increasing the engine speed until a flow rate reaches a predefined value sufficient for opening the cutoff valve; measuring the position of the actuating cylinder and an engine speed corresponding to the opening of said cutoff valve.
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