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公开(公告)号：EP4286672A1
公开(公告)日：2023-12-06
申请号：EP23176570.2
申请日：2023-05-31
摘要： A cooling and fueling system (100) for a hypersonic vehicle includes a regenerative cooling circuit (110), a fuel tank (120) configured to support fuel, a water tank (130) configured to support water, and a valve (140b) disposed between the water tank and the regenerative cooling circuit. The valve is actuatable to dispense water from the water tank when the hypersonic vehicle reaches a threshold speed to enable the water to mix with the fuel to produce a combustible mixture that passes through the regenerative cooling circuit. The combustible mixture is configured to inhibit fuel coking and has a predetermined thermal property configured to cool a surface of a hot engine wall of the hypersonic vehicle as the combustible mixture passes through the regenerative cooling circuit.
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3.发明授权
公开(公告)号：EP2233727B1
公开(公告)日：2017-12-13
申请号：EP10250566.6
申请日：2010-03-25
发明人： Jarmon, David C.
IPC分类号： F02K7/10 , F01D25/08 , F02K1/82 , F02K9/64 , F02K9/97 , F02K7/16 , F02K7/14 , F02C6/18 , F01D13/00 , B64D33/02 , B64C30/00 , F02C7/224 , B64D37/34 , B64D33/08
CPC分类号： F02K7/14 , B64C30/00 , B64D33/08 , B64D37/34 , B64D2033/026 , F01D13/00 , F02C6/18 , F02C7/224 , F02K1/822 , F02K7/16 , F02K9/64 , F02K9/972 , F05D2220/80 , F05D2250/15 , F05D2260/205 , F05D2260/38 , F05D2260/52 , Y02T50/44
摘要： An apparatus includes a thermoelectric (TE) device (82), a gas flow conduit (80) proximate to one side of the thermoelectric device, a plurality of flexible tubes (84) proximate to a second side of the thermoelectric device, and a spring (86) to control contact force between the flexible tubes and the thermoelectric device. The spring comprises a coil spring at least partially circumscribing the gas flow conduit. The thermoelectric device converts a temperature differential between the flexible tubes and the gas flow conduit into electrical energy.
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4.发明公开Method for ram accelerating a projectile in a barrel and apparatus therefor 失效一种用于通过在筒及其装置冲压式喷气燃烧的手段加速弹丸方法。
公开(公告)号：EP0663582A3
公开(公告)日：1995-11-02
申请号：EP94309451.6
申请日：1994-12-16
发明人： Brandeis, Julius
CPC分类号： F41A1/00
摘要： A method for accelerating projectiles comprises introducing the projectile into an accelerator barrel, feeding a combustible gas mixture into said barrel and igniting said mixture to accelerate the projectile, and is characterized in that a fluid is stored in the projectile and is ejected therefrom into the space between the projectile and the barrel. Suitable accelerator systems are disclosed.
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公开(公告)号：EP4232700A1
公开(公告)日：2023-08-30
申请号：EP21763427.8
申请日：2021-02-10
申请人： Raytheon Company
发明人： JONES, Jaylan , MESSITT, Donald , HODGE, Brian , HARRIS, Gabe
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6.发明公开
公开(公告)号：EP4198295A1
公开(公告)日：2023-06-21
申请号：EP22020614.8
申请日：2022-12-16
发明人： WOLANSKI, Piotr , KAWALEC, Michal
摘要： The invention relates to a method of raising the temperature of any of the propellant components of a rocket engine to a higher temperature, in which the stream of a liquid cryogenic component is subjected to initial evaporation and heating by heat received from the products of detonation combustion of the fuel-rich mixture in the detonation chamber, through its walls, and then detonation chamber - in the mixing zone, this partially vaporized stream is gradually and multi-point introduced into the hot stream of rotating detonation products, obtaining a stream of evaporated and heated cryogenic component to feed the engine combustion chamber.
According to the invention, a propellant mixture containing such an excess of fuel is combusted in the detonation chamber that the combustion product stream is at a temperature enabling ignition and after-combustion with liquid oxygen or partially vaporized liquid oxygen supplied downstream of the detonation chamber.
The subject of the invention is also an installation for raising the temperature of any of the propellant components of a rocket engine to a higher temperature, which consists of a chamber ( 2 ) for initial evaporation of a liquid cryogenic component, concentrically combined with a chamber ( 1 ) for detonation combustion of mixtures highly enriched in fuel (low in oxidizer), which has a common wall with the chamber ( 1 ) enabling the flow of heat from the products of rotating detonation to the stream of the liquid component of the propellant mixture and from the mixing zone ( 3 ) of the partially evaporated cryogenic component with hot products of detonation combustion, in which the heat is gradually reduced to zero. the difference in the diameters of the two concentric spaces ( 1, 2 ), and the wall separating them is perforated.-
公开(公告)号：EP3591210B1
公开(公告)日：2021-04-07
申请号：EP17905551.2
申请日：2017-11-16
发明人： SUZUKI, Kenji , MINOYA, Makoto
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公开(公告)号：EP3438437A1
公开(公告)日：2019-02-06
申请号：EP18173751.1
申请日：2018-05-23
申请人： The Boeing Company
摘要： A scramjet (100) includes a converging inlet (110), a combustor (120) configured to introduce a fuel stream (132) into an air stream in a combustion chamber (130) and to combust the fuel air mixture stream (134) to create an exhaust stream, and a diverging exit nozzle configured to accelerate the exhaust stream (136). The combustor includes a fuel injection system (150) including at least one arcjet (160). A method (300) of creating thrust for an aircraft (10) includes compressing (310) a supersonic incoming air stream (112) in a converging inlet (110), injecting (320) a fuel stream (132) into the air stream in a combustion chamber (130) to create a fuel air mixture stream (134), igniting (330) the fuel air mixture stream to create an exhaust stream, and exhausting (350) the exhaust stream from a diverging exit nozzle (220). The injecting the fuel stream into the air stream includes injecting the fuel stream at a fuel speed sufficient to create shear between the fuel stream and the air stream.
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公开(公告)号：EP2483545A2
公开(公告)日：2012-08-08
申请号：EP10820987.5
申请日：2010-08-26
申请人： WOODWARD, INC.
发明人： SMITH, David S.
CPC分类号： F02M61/14 , F02M61/08 , F02M61/162 , F02M61/20 , F02M2200/50 , F02M2200/852
摘要： A nested fuel injector that includes an injector housing having a bore longitudinally therethrough, and a pintle assembled to the housing and positioned substantially within the bore. The pintle has a head located at an end of a cylindrical portion, wherein the head is seated in one end of the bore, and the seating of the head defines a variable-area exit orifice. A wave spring is assembled onto the pintle and configured to urge the pintle into the seating position. The bore is configured for the passage of a pressurized flow of fuel. The fuel pressure urges the pintle head away from the exit orifice to permit the pressurized fuel to flow from the bore out through the exit orifice.
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