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公开(公告)号：US20180058770A1
公开(公告)日：2018-03-01
申请号：US15694540
申请日：2017-09-01
发明人： Kyle Adriany , Elyce Bayat , Ryan Pedersen , Anthony Tran
CPC分类号： F28F1/02 , F02C7/12 , F02K9/64 , F05D2230/30 , F28D1/06 , F28D7/0025 , F28D7/0041 , F28D7/005 , F28D2021/0021 , F28D2021/004 , F28D2021/0087 , F28F1/022 , F28F1/025 , F28F1/04 , F28F2009/0285
摘要： In some embodiments, a structural heat exchanger is presented that utilizes liquid fuel as a coolant as it travels through the perimeter of a region (e.g., a chamber) of an engine. The shapes of the coolant channels of the heat exchanger may be configured to change pitch angles as it travels to the top of the region, to account for areas of the region that may demand higher cooling properties. In some embodiments, the fuel diverter that allows initial passage of the fuel through the coolant channels may be configured to drive passage of the fluid up through the coolant channels with uniform pressure, even as the volume of fluid decreases the farther the fluid travels from the initial entry point. In some embodiments, this may be implemented as a fuel diverter shaped in an annulus with a gradually decreasing radial cross-section.
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公开(公告)号：US09879563B2
公开(公告)日：2018-01-30
申请号：US13794976
申请日：2013-03-12
CPC分类号： F01D25/20 , F01D25/18 , F01M5/002 , F02C7/06 , F02C7/14 , F02K9/64 , F05D2260/213 , F05D2260/40311 , Y02T50/676
摘要： A lubricant supply system for a gas turbine engine has a lubricant lube pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear for an associated gas turbine engine. A method and apparatus are disclosed.
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公开(公告)号：US09771897B2
公开(公告)日：2017-09-26
申请号：US14350980
申请日：2012-10-08
申请人： SNECMA
摘要： A reaction propulsion device in which a first feed circuit for feeding a main thruster with a first propellant includes a branch connection downstream from a pump of a first turbopump, which branch connection passes through a first regenerative heat exchanger and a turbine of a first turbopump, and in which a second feed circuit for feeding the main thruster with a second propellant includes, downstream from a pump of a second turbopump, a branch-off passing through a second regenerative heat exchanger and a turbine of the second turbopump. At least one secondary thruster is connected downstream from the turbines of the first and second turbopumps.
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公开(公告)号：US20170122258A1
公开(公告)日：2017-05-04
申请号：US15301922
申请日：2015-04-09
申请人： AVIO S.P.A.
发明人： Paolo BELLOMI , Daniele LIUZZI , Mikhail RUDNYKH
CPC分类号： F02K9/64 , F02K9/972 , F05D2230/53 , F23M5/08 , F23M2900/05003 , F23R3/005 , F23R2900/03045 , F28D7/106 , F28F1/124 , F28F1/40 , F28F13/003 , F28F13/12 , F28F2215/10 , F28F2250/02
摘要： A combustor for a liquid propellent motor has an elongated hollow tubular casing having an inner wall delimiting a combustion chamber for the liquid propellent and an outlet nozzle for the combustion products, and an outer wall, both being coaxial to an axis of the casing; the inner and outer walls being spaced apart from each other in radial direction and delimiting at least one guiding conduit of a cooling fluid therebetween; a plurality of bar-shaped elements extending into the guiding conduit, which form a grid for perturbing the cooling fluid, stiffening the casing and increasing the heat exchange surface; the grid being part of a body made in one piece and of a single material along with the inner and outer walls.
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5.发明授权Aircraft/spacecraft fluid cooling system and aircraft/spacecraft fluid cooling method 有权飞机/航天器流体冷却系统和飞机/航天器流体冷却方式公开(公告)号：US09476654B2
公开(公告)日：2016-10-25
申请号：US14007147
申请日：2012-03-21
IPC分类号： F28F1/00 , F02K9/60 , F28D7/10 , F02K9/46 , B64G1/40 , F02K9/34 , F02K9/40 , F02K9/48 , F02K9/64 , F02K9/97 , F02C1/08 , F02C7/16 , F02C7/18 , F02C7/224
CPC分类号： F28F1/00 , B64G1/402 , F02C1/08 , F02C7/16 , F02C7/18 , F02C7/185 , F02C7/224 , F02K9/34 , F02K9/40 , F02K9/46 , F02K9/48 , F02K9/60 , F02K9/64 , F02K9/972 , F05D2260/20 , F28D7/106 , F28F2265/26
摘要： An aircraft/spacecraft fluid cooling system and an aircraft/spacecraft fluid cooling method in which a fluid in a pipe installed in aircraft or spacecraft can be cooled efficiently so that the amount of fluid required for cooling the fluid can be reduced. A fluid cooling system includes a feed line that feeds a fluid from a storage tank to a pump, and a cooling section that expands a propellant having traveled through the pump, feeds the propellant to the outer periphery of the feed line so as to cool the propellant in the feed line, and discharges the expanded propellant outside.
摘要翻译： 飞机/航天器流体冷却系统和飞机/航天器流体冷却方法，其中可以有效地冷却安装在飞行器或航天器中的管道中的流体，从而可以减少冷却流体所需的流体量。 流体冷却系统包括将流体从储罐供给到泵的供给管线和使已经通过泵行进的推进剂膨胀的冷却部分，将推进剂供给到进料管线的外周边，以冷却 推进剂在进料管线中，并将膨胀的推进剂排出外部。
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公开(公告)号：US20150337763A1
公开(公告)日：2015-11-26
申请号：US14760190
申请日：2014-01-10
申请人： SNECMA
发明人： Didier VUILLAMY , Gérard ROZ
IPC分类号： F02K9/46
CPC分类号： F02K9/60 , F02K9/40 , F02K9/46 , F02K9/605 , F02K9/64 , F02K9/972 , F05D2260/20 , F05D2260/205
摘要： The invention relates to the aerospace field, and in particular to the field of vehicles propelled by rocket engines. In particular, the invention relates to a feed circuit (6) for feeding a rocket engine (2) at least with a first liquid propellant, the feed circuit including at least one first heat exchanger (18) suitable for being connected to a cooling circuit (17) for cooling at least one heat source in order to cool said heat source by transferring heat to the first propellant, and, in addition, downstream from said first heat exchanger, a branch passing through a second heat exchanger.
摘要翻译： 本发明涉及航空航天领域，特别涉及由火箭发动机推进的车辆领域。 特别地，本发明涉及用于至少用第一液体推进剂进给火箭发动机（2）的进料回路（6），所述进料回路包括至少一个第一热交换器（18），该第一热交换器适于连接到冷却回路 （17），用于冷却至少一个热源，以便通过将热量传递到第一推进剂来冷却所述热源，并且另外在所述第一热交换器的下游，通过第二热交换器的分支。
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公开(公告)号：US08950172B2
公开(公告)日：2015-02-10
申请号：US13003371
申请日：2009-07-10
摘要： The jet (40) has an air-fuel combustion chamber (42) and a plurality of rocket engines (11) arranged upstream from the combustion chamber (42), each rocket engine having its own combustion chamber with the wall thereof being cooled by lateral injection of fuel through said wall.
摘要翻译： 喷射器（40）具有空气燃料燃烧室（42）和布置在燃烧室（42）上游的多个火箭发动机（11），每个火箭发动机具有其自身的燃烧室，其壁的侧壁被冷却 通过所述墙壁喷射燃料。
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8.发明申请AIRCRAFT/SPACECRAFT FLUID COOLING SYSTEM AND AIRCRAFT/SPACECRAFT FLUID COOLING METHOD 有权飞机/空间流体冷却系统和飞机/空间流体冷却方法公开(公告)号：US20140020872A1
公开(公告)日：2014-01-23
申请号：US14007147
申请日：2012-03-21
IPC分类号： F28F1/00
CPC分类号： F28F1/00 , B64G1/402 , F02C1/08 , F02C7/16 , F02C7/18 , F02C7/185 , F02C7/224 , F02K9/34 , F02K9/40 , F02K9/46 , F02K9/48 , F02K9/60 , F02K9/64 , F02K9/972 , F05D2260/20 , F28D7/106 , F28F2265/26
摘要： An aircraft/spacecraft fluid cooling system and an aircraft/spacecraft fluid cooling method in which a fluid in a pipe installed in aircraft or spacecraft can be cooled efficiently so that the amount of fluid required for cooling the fluid can be reduced. A fluid cooling system includes a feed line that feeds a fluid from a storage tank to a pump, and a cooling section that expands a propellant having traveled through the pump, feeds the propellant to the outer periphery of the feed line so as to cool the propellant in the feed line, and discharges the expanded propellant outside.
摘要翻译： 飞机/航天器流体冷却系统和飞机/航天器流体冷却方法，其中可以有效地冷却安装在飞行器或航天器中的管道中的流体，从而可以减少冷却流体所需的流体量。 流体冷却系统包括将流体从储罐供给到泵的供给管线和使已经通过泵行进的推进剂膨胀的冷却部分，将推进剂供给到进料管线的外周边，以冷却 推进剂在进料管线中，并将膨胀的推进剂排出外部。
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公开(公告)号：US20130125527A1
公开(公告)日：2013-05-23
申请号：US13300775
申请日：2011-11-21
申请人： Jim A. Clark , Craig W. Irwin , Reed A. Kakuska
发明人： Jim A. Clark , Craig W. Irwin , Reed A. Kakuska
IPC分类号： F02K9/97
CPC分类号： F02K9/566 , F02K9/64 , F02K9/972 , F15D1/025 , F16L55/027 , G05D7/0186
摘要： A rocket engine fluid-flow system includes a pump fluidly interconnecting a fluid source to a combustion chamber. A nozzle is in fluid communication with the combustion chamber and includes coolant tubes fluidly arranged between the pump and the combustion chamber. An orifice has a throat and is fluidly arranged between the pump and the coolant tubes. The orifice has entrance and exit ramps arranged on either side of the throat. The exit ramp has an exit ramp surface with a divergent angle that is less than a right angle. The entrance ramp provides a smooth approach to the orifice throat. In one example, the exit ramp includes an exit ramp surface having a divergent angle of 20-60°. The exit ramp radius is less than twice the throat radius in one example.
摘要翻译： 火箭发动机流体流动系统包括将流体源流体地连接到燃烧室的泵。 喷嘴与燃烧室流体连通，并且包括流体地布置在泵和燃烧室之间的冷却剂管。 孔具有喉部并且流体地布置在泵和冷却剂管之间。 孔口具有设置在喉部两侧的入口和出口斜面。 出口斜坡具有出口斜面，其具有小于直角的发散角。 入口斜坡提供了孔口喉咙平滑的方法。 在一个示例中，出口斜坡包括具有20-60°的发散角的出口斜面。 在一个示例中，出口斜坡半径小于喉部半径的两倍。
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公开(公告)号：US08341933B2
公开(公告)日：2013-01-01
申请号：US12846728
申请日：2010-07-29
IPC分类号： B63H11/00
CPC分类号： F02K9/64
摘要： A method of cooling a rocket engine that includes removal of a gaseous propellant from a tank containing liquid propellant, thereby cooling the propellant in the tank, cooling a rocket engine with a coolant, thereby heating the coolant, and transferring heat from the heated coolant into the propellant in the tank, thereby heating the propellant in the tank and maintaining the pressure in the tank. In certain embodiments, the coolant is injected into the rocket engine after transferring heat from the rocket engine to the propellant in the tank.
摘要翻译： 一种冷却火箭发动机的方法，包括从包含液体推进剂的罐中取出气体推进剂，从而冷却罐中的推进剂，用冷却剂冷却火箭发动机，从而加热冷却剂，并将热量从加热的冷却剂传递到 坦克中的推进剂，从而加热罐中的推进剂并维持罐中的压力。 在某些实施例中，在将热量从火箭发动机传递到罐中的推进剂之后，将冷却剂注入到火箭发动机中。
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