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公开(公告)号：US11982234B1
公开(公告)日：2024-05-14
申请号：US18168173
申请日：2023-02-13
发明人： Kashif Mohammed , Benjamin Renaud
CPC分类号： F02C7/224 , F02C7/14 , F02C7/16 , F16K17/40 , F28F27/02 , F05D2220/323 , F05D2240/35 , F05D2260/213
摘要： A heat exchanger, has: a heat exchanger core having an inlet, an outlet, at least one first conduit connecting the inlet to the outlet, and at least one second conduit in heat exchange relationship with the at least one first conduit; a bypass conduit connecting the inlet to the outlet while bypassing the at least one first conduit; and a valve in communication with the bypass conduit and having: a valve member movable between a closed position in which fluid communication through the valve and via the bypass conduit is blocked and an open position in which fluid communication through the bypass conduit and through the valve is permitted, the valve member defining an auxiliary passage, and a thermal fuse overlapping the auxiliary passage and blocking fluid communication through the valve member via the auxiliary passage, the thermal fuse having a melting temperature above a predetermined temperature of the fluid.
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公开(公告)号：US10072796B2
公开(公告)日：2018-09-11
申请号：US15209215
申请日：2016-07-13
CPC分类号： F16N29/02 , B63H3/08 , B64C11/00 , B64C11/303 , B64C11/40 , F16N2210/08 , F16N2230/00 , F16N2250/04 , F16N2250/08 , F16N2270/20 , G01F15/003
摘要： There is described herein methods and system for correcting steady state errors in propeller speed by calculating a leakage flow rate as a function of engine and propeller parameters.
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公开(公告)号：US11230979B2
公开(公告)日：2022-01-25
申请号：US16296988
申请日：2019-03-08
发明人： David Waddleton , Benjamin Renaud , Sebastien Bergeron , Etienne Plamondon , Jean-Gabriel Gauvreau
摘要： A liquid fuel system for an aircraft engine includes a first fuel supply conduit hydraulically connected to a fuel source, a second fuel supply conduit hydraulically connected to the engine, a fuel return conduit hydraulically connected to the second fuel supply conduit, and a fuel pump. The fuel pump has a main inlet hydraulically connected to the first fuel supply conduit, an outlet hydraulically connected to the second fuel supply conduit, and an intermediate inlet hydraulically connected to the fuel return conduit. The intermediate inlet is located between the main inlet and the outlet and in use has a pressure between the main inlet pressure and the outlet pressure. A method of supplying a liquid fuel to an aircraft engine is also described.
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公开(公告)号：US11459958B2
公开(公告)日：2022-10-04
申请号：US16361819
申请日：2019-03-22
发明人： David Waddleton , Benjamin Renaud , Sebastien Bergeron , Etienne Plamondon , Jean-Gabriel Gauvreau
摘要： A rotodynamic pump for pumping a fluid includes an impeller, a housing surrounding the impeller, and a pressure regulating mechanism. The pressure regulating mechanism is configured to adjust the clearance between the impeller and the impeller housing to regulate pressure of the fluid downstream of the impeller. A method of regulating the delivery pressure is also disclosed.
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公开(公告)号：US11280342B2
公开(公告)日：2022-03-22
申请号：US16376320
申请日：2019-04-05
发明人： David Waddleton , Benjamin Renaud , Sebastien Bergeron , Etienne Plamondon , Jean-Gabriel Gauvreau
摘要： A method of controlling a delivery pressure of an aircraft engine fuel system includes operating a rotodynamic fuel pump hydraulically connected to the fuel system to pump a fluid from an inlet of the rotodynamic pump and out of an outlet of the rotodynamic pump for delivery to the fuel system. The method further includes varying an angular relationship between the inlet and the outlet of the pump to control the delivery pressure. An aircraft engine fuel system and a rotodynamic pump are also described.
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公开(公告)号：US11092126B2
公开(公告)日：2021-08-17
申请号：US16558847
申请日：2019-09-03
摘要： A method of operating an aircraft engine of an aircraft, the aircraft engine having a common-rail fuel injection system for injecting fuel into a combustion chamber of the aircraft engine, including: pressurizing fuel for circulation through the common-rail injection system; circulating a portion of the pressurized fuel through a motive flow inlet of an ejector pump; and entraining a flow through the ejector pump with the portion of the pressurized fuel circulating through the motive flow inlet.
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公开(公告)号：US10830391B2
公开(公告)日：2020-11-10
申请号：US16100768
申请日：2018-08-10
摘要： There is described herein methods and system for correcting steady state errors in propeller speed by calculating a leakage flow rate as a function of engine and propeller parameters.
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公开(公告)号：US10738749B1
公开(公告)日：2020-08-11
申请号：US16294160
申请日：2019-03-06
摘要： There is disclosed a method of de-icing a component of an engine assembly having a common-rail fuel injection system, including: pressurizing fuel to circulate the fuel through the common-rail injection system; drawing a portion of the fuel upstream of common-rail injectors of the common-rail injection system and directing a remainder of the fuel toward the common-rail injectors; and transferring heat from the drawn portion of the fuel to the component.
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