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公开(公告)号：US11867139B1
公开(公告)日：2024-01-09
申请号：US17843484
申请日：2022-06-17
申请人： Blue Origin, LLC
CPC分类号： F02K9/62 , F23R3/002 , F23R2900/00014
摘要： A modular damper plug forming a multi-volume acoustic resonator in an acoustic liner of a rocket engine is provided. In one aspect, the damper plug includes a main body including a top surface spaced from a bottom surface by a first height, a left surface spaced from a right surface by a width, and an exterior surface spaced from an interior surface by a length. A chamber within the main body extends along a part of the height, a part of the width, and a part of the length, and communicates with the top surface through an opening. The chamber also communicates with the interior surface through one or more ducts. The main body is sized and shaped to be received in any one of a plurality of cavities in the acoustic liner. The chamber includes an upstream volume of the acoustic resonator, and the one or more ducts communicate with a downstream volume of the acoustic resonator when the damper plug is received in any one of the plurality of cavities.
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公开(公告)号：US11719194B2
公开(公告)日：2023-08-08
申请号：US17463609
申请日：2021-09-01
申请人： ArianeGroup GmbH
发明人： Chris Udo Maeding
摘要： A combustion chamber for a rocket engine, the combustion chamber including a combustion chamber body enclosing a combustion chamber volume and a nozzle portion tapering in a longitudinal direction of the combustion chamber and adjoining the combustion chamber body. The combustion chamber body has at least one first portion and a second portion, wherein an inner surface of the at least one first portion facing the combustion chamber volume is closer to a cross-sectional center of the combustion chamber body than an inner surface of the second portion of the combustion chamber body. Furthermore, a additive layer manufacturing method for manufacturing such a combustion chamber is described.
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公开(公告)号：US20220307450A1
公开(公告)日：2022-09-29
申请号：US17641961
申请日：2019-11-22
摘要： A monopropellant thruster according to an exemplary aspect of the present disclosure includes, among other things, a first part having a catalyst bed, a thrust chamber, and a nozzle. The first part is integrally formed via a single additive manufacturing process. The thruster further includes a second part, which is a closeout. A method is also disclosed.
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公开(公告)号：US11384713B1
公开(公告)日：2022-07-12
申请号：US17324000
申请日：2021-05-18
摘要： A liquid rocket engine integrates tap-off openings at a combustion chamber wall to direct exhaust from the combustion chamber to a tap-off manifold that provides the exhaust to one or more auxiliary systems, such as a turbopump that pumps oxygen and/or fuel into the combustion chamber. The tap-off opening passes through a fuel channel formed in that combustion chamber exterior wall and receives fuel through a fuel opening that interfaces the fuel channel and tap-off opening. The tap-off manifold nests within a fuel manifold for thermal management. The fuel channel directs fuel into the combustion chamber through fuel port openings formed in the combustion chamber, the fuel port openings located closer to a headend of the combustion chamber than the tap-off openings.
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公开(公告)号：US11236702B2
公开(公告)日：2022-02-01
申请号：US14897313
申请日：2014-06-10
申请人： 8801541 CANADA INC.
发明人： Luc Laforest , Timothy S. Rupcich
摘要： The jet engine comprising a ramjet air path extending from an intake, into a combustion chamber, and out an exhaust nozzle, a fuel inlet leading into the combustion chamber, an oxidizer inlet leading into the combustion chamber and a partition being operable to selectively close the ramjet air path upstream of the combustion chamber to allow operation of the jet engine in rocket mode and open the ramjet air path to allow operation of the jet engine in ramjet mode.
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公开(公告)号：US20210293205A1
公开(公告)日：2021-09-23
申请号：US17176418
申请日：2021-02-16
发明人： Seiki NISHIKAWA , Chiyako MIHARA , Tasuku SUZUKI , Katsunori IEKI
摘要： A multi-pulse gas generator includes a pressure vessel, first and second propellants, a barrier membrane that separates the first propellant and the second propellant, an igniter device that produces combustion gas of igniter charge, and an igniter charge combustion gas exhaust device having exhaust holes configured to exhaust the combustion gas of the igniter charge against the second propellant. The barrier membrane includes: a concavely-deformable portion; and a convexly-deformable portion. A flow rate of the combustion gas of the igniter charge exhausted against a portion of the second propellant located outside of the concavely-deformable portion is larger than that of the combustion gas of the igniter charge exhausted against a portion of the second propellant located outside of the convexly-deformable portion.
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公开(公告)号：US11008977B1
公开(公告)日：2021-05-18
申请号：US16584449
申请日：2019-09-26
摘要： A liquid rocket engine integrates tap-off openings at a combustion chamber wall to direct exhaust from the combustion chamber to a tap-off manifold that provides the exhaust to one or more auxiliary systems, such as a turbopump that pumps oxygen and/or fuel into the combustion chamber. The tap-off opening passes through a fuel channel formed in that combustion chamber exterior wall and receives fuel through a fuel opening that interfaces the fuel channel and tap-off opening. The tap-off manifold nests within a fuel manifold for thermal management. The fuel channel directs fuel into the combustion chamber through fuel port openings formed in the combustion chamber, the fuel port openings located closer to a headend of the combustion chamber than the tap-off openings.
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公开(公告)号：US20180320634A1
公开(公告)日：2018-11-08
申请号：US15771256
申请日：2016-10-20
摘要： An injection device, a combustor, and a rocket engine include a device main body partitioned into a fuel manifold and an oxidant manifold, and a plurality of injectors arranged at predetermined intervals in the device main body to inject fuel and oxidant into a combustion chamber, each of the injectors includes a LOx channel including a proximal end portion communicating with the oxidant manifold and a distal end portion communicating with the combustion chamber, a restrictor provided on the proximal end portion of the LOx channel and a GH2 channel including a proximal end portion communicating with the fuel manifold and a distal end portion communicating with the combustion chamber, and the restrictors have different shapes.
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公开(公告)号：US20170101963A1
公开(公告)日：2017-04-13
申请号：US15288521
申请日：2016-10-07
CPC分类号： F02K9/58 , F02K9/46 , F02K9/48 , F02K9/563 , F02K9/62 , F05D2220/80 , F05D2240/24
摘要： The invention relates to the field of rocket engines, and in particular to a method and a circuit for regulating a rocket engine (1) comprising at least one combustion chamber (3) and a first liquid propellant feed circuit (10) with a first pump (12) for pumping a first liquid propellant and a first turbine (14) for actuating the first pump (12), a first feed valve (15), and a regulator device for regulating the first turbine (14). In the regulation method and circuit, an opening command (DVCH) for opening the first feed valve (15) is calculated from an external command (Cext) in application of an open loop control relationship; a command for the regulator device of the first turbine (14) is calculated on the basis of said external command (Cext) and at least one feedback value, in application of a closed loop control relationship; and the first feed valve (15) and the regulator device of the first turbine (14) are controlled in application of the respective commands.
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公开(公告)号：US20160333826A1
公开(公告)日：2016-11-17
申请号：US15138508
申请日：2016-04-26
申请人： Busek Co., Inc.
发明人： Michael M. Tsay , Michael Robin , Kurt W. Hohman
CPC分类号： F02K9/50 , F02K9/605 , F05D2260/20
摘要： A post launch pressurized gas production system and method includes a cell containing a pressurized gas producing medium, such as anhydrous sodium bicarbonate producing CO2 gas when heated. A plenum tank is in fluid communication with the cell. A heater heats the cell to produce gas delivered to the plenum tank storing the gas therein under pressure. A pressure vessel includes a propellant therein pressurized by the gas and in fluid communication with a thruster for delivery of the propellant to the thruster after pressurization by the gas.
摘要翻译： 后发射加压气体生产系统和方法包括含有加压气体产生介质的电池，例如当加热时产生CO 2气体的无水碳酸氢钠。 增压箱与电池流体连通。 加热器加热电池以产生输送到压力储存其中的气体的气室中的气体。 压力容器包括其中由气体加压并与推进器流体连通的推进剂，用于在气体加压之后将推进剂输送到推进器。
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