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公开(公告)号：US12104699B2
公开(公告)日：2024-10-01
申请号：US17715781
申请日：2022-04-07
申请人： Blue Origin, LLC
发明人： Ryan Linderman , Jacob Mills
CPC分类号： F16J15/3432 , F02K9/48 , F16J15/34 , F16J15/3408 , F16J15/3412 , F16J15/346 , F01D11/003 , F01D11/122 , F05D2220/30 , F05D2240/55
摘要： A representative seal system (such as a seal system for a turbopump of a rocket engine) automatically adjusts a balance ratio of a seal. The system can include a ring element encircling an axis. A front side of the ring element contacts a revolving surface to form a seal with the revolving surface. The front side can include a stepped surface having two or more steps. Each step includes a sealing surface configured to contact the revolving surface to form a sealing area that is different from a sealing area of each other sealing surface. Each step is positioned and configured to wear away during operation of the machine to expose an underlying surface to the revolving surface, to change the sealing area and the balance ratio of the seal. A representative method of operating a turbomachinery system includes changing the balance ratio of a seal while rotating a rotor.
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公开(公告)号：US11846251B1
公开(公告)日：2023-12-19
申请号：US16857609
申请日：2020-04-24
CPC分类号： F02K7/18 , F02K9/48 , F02K9/64 , F02K9/74 , F05D2220/80 , F05D2240/35 , F05D2260/205
摘要： The inventors introduce the Borissov-Markusic Cycle as the new rocket engine cycle to solve the problem of low efficient open gas generator or tap-off gas generator cycles used to supply power to turbopump. A liquid rocket engine directs turbopump exhaust from a turbopump to a booster engine having an intake to accept ambient airflow, such as a variation of a ramjet, scramjet or dual mode ram scramjet engine. The turbopump is powered by combustion gases, such as from a gas generator or a tap-off manifold interfaced with the liquid rocket engine combustion chamber, and applies energy of the combustion gases to pump fuel and/or liquid oxygen to the liquid rocket engine combustion chamber. The combustion gases have a fuel-rich composition that includes unconsumed fuel from incomplete oxidation so that, upon injection into the combustion chamber of the booster engine, oxidation by ambient air of the unconsumed fuel releases energy to generate thrust with the booster engine.
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公开(公告)号：US20230332562A1
公开(公告)日：2023-10-19
申请号：US18211277
申请日：2023-06-18
发明人： Timothy Bulk , Christopher Hayes
摘要： Devices and methods of rocket propulsion are disclosed. In one aspect, a staged combustion liquid rocket engine with preburner and turbopump unit (TPU) integrated into the structure of the combustion chamber is described. An initial propellant mixture is combusted in a preburner combustion chamber formed as an annulus around a main combustion chamber, the combustion products from the preburner driving the turbine of the TPU and subsequently injected into the main combustion chamber for secondary combustion along with additional propellants, generating thrust through a supersonic nozzle. The preburner inner cylindrical wall is shared with the outer cylindrical wall of the engine's main combustion chamber and the turbine is axially aligned with the main combustion chamber. Liquid propellants supplied to the engine are utilized for regenerative cooling of the combustion chamber and preburner, where the liquid propellants are gasified in cooling manifolds before injection into the preburner and main combustion chamber.
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4.发明授权公开(公告)号：US10060356B2
公开(公告)日：2018-08-28
申请号：US14296615
申请日：2014-06-05
申请人： Reaction Engines Ltd
发明人： Alan Bond
IPC分类号： F02C7/28 , F02C1/02 , F01D11/04 , F02K7/16 , F02K7/18 , F02K9/48 , F02C1/10 , F16J15/16 , F02K9/78
CPC分类号： F02C7/28 , F01D11/04 , F02C1/02 , F02C1/10 , F02K7/16 , F02K7/18 , F02K9/48 , F02K9/78 , F05D2260/6022 , F16J15/164
摘要： A rotational machine such as a turbocompressor has a fluid recovery system for recovering leaked working fluid such as gaseous helium in a helium circuit which has leaked past a shaft seal, a purifier being provided for removing contaminants from the working fluid, and turbocompressor may have one fluid such as helium or hydrogen working through one turbo component such as a turbine thereof and a second working fluid such as air or helium working through a second turbo component such as a compressor thereof, the rotational machine being installable in an engine of a flying machine.
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公开(公告)号：US20170114753A1
公开(公告)日：2017-04-27
申请号：US15333339
申请日：2016-10-25
发明人： Valentin Hue , Serge LE GONIDEC
CPC分类号： F02K9/563 , B64G1/401 , B64G1/402 , F02K9/42 , F02K9/425 , F02K9/44 , F02K9/46 , F02K9/48 , F02K9/50 , F02K9/68 , F02K9/94 , F05D2270/301 , F05D2270/303
摘要： A method of regulating pressure within a first propellant tank of a rocket engine having a first propellant tank containing a first propellant and a second propellant tank containing a second propellant, and a regulator device for regulating pressure within the first tank, the regulator device comprising a gas generator and a heat exchanger co-operating with the gas generator so as to vaporize at least part of the first propellant prior to reintroducing it into the first tank (16), the gas generator and the heat exchanger both being fed with the first propellant by a single first motor-driven pump, while the gas generator is fed with the second propellant by a single second motor-driven pump, wherein the flow rate of the first motor-driven pump is controlled as a function of a first parameter, while the flow rate of the second motor-driven pump is controlled as a function of a second parameter.
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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：US20150000755A1
公开(公告)日：2015-01-01
申请号：US14365204
申请日：2012-12-07
申请人： SNECMA
CPC分类号： F17D3/01 , F02K9/48 , F02K9/50 , F16L53/30 , F17C5/00 , F17C2201/054 , F17C2205/0326 , F17C2221/011 , F17C2221/012 , F17C2221/017 , F17C2221/08 , F17C2223/0161 , F17C2223/033 , F17C2225/0123 , F17C2225/036 , F17C2227/0107 , F17C2227/0135 , F17C2227/0142 , F17C2227/0157 , F17C2227/0164 , F17C2227/0309 , F17C2227/0388 , F17C2270/0197 , Y02E60/321 , Y10T137/0396 , Y10T137/6579
摘要： A pressurizing device and method, for pressurizing a first tank, the device including at least a second tank configured to contain a cryogenic fluid, a first pressurizing circuit for putting the second tank into communication with the first tank, the first pressurizing circuit including at least a first heat exchanger for heating a flow of the cryogenic fluid extracted from the second tank through the first pressurizing circuit, and a second pressurizing circuit with a compressor, branched off from the first pressurizing circuit and leading to the second tank. A feed system for feeding a reaction engine with at least a first liquid propellant includes at least a first tank configured to contain the first liquid propellant, and a device for pressurizing the first tank.
摘要翻译： 一种用于对第一罐加压的加压装置和方法，所述装置至少包括构造成容纳低温流体的第二罐，用于使第二罐与第一罐连通的第一加压回路，第一加压回路至少包括 第一热交换器，用于加热通过第一加压回路从第二罐提取的低温流体的流动;以及第二加压回路，其具有从第一加压回路分支并通向第二罐的压缩机。 用于向至少第一液体推进剂供给反应引擎的进料系统包括至少第一罐，其构造成容纳第一液体推进剂，以及用于对第一罐加压的装置。
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公开(公告)号：US20140260181A1
公开(公告)日：2014-09-18
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.
摘要翻译： 一种反应推进装置，其中用于向主推进器供给第一推进剂的第一进料回路包括在第一涡轮泵的泵的下游的分支连接，该分支连接通过第一再生式热交换器和第一涡轮泵的涡轮， 并且其中用于向主推进器供给第二推进剂的第二进料回路包括在第二涡轮泵的泵的下游，通过第二再生热交换器和第二涡轮泵的涡轮的分支。 至少一个次级推进器连接在第一和第二涡轮泵的涡轮机的下游。
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公开(公告)号：US07748959B1
公开(公告)日：2010-07-06
申请号：US11787559
申请日：2007-04-17
申请人： Alex Pinera , Todd A. Ebert
发明人： Alex Pinera , Todd A. Ebert
IPC分类号： F01D5/08
CPC分类号： F01D5/08 , F02K9/48 , F05D2250/621 , F05D2300/504
摘要： A turbine disc used in a turbo-pump that is exposed to a large thermal gradient across the sides of the rotor disc. The warm side of the turbine disc is covered by a cover plate that forms a sealed space between the turbine disc and the cover plate, and this space is evacuated or insulated to form a complete vacuum or as near as a complete vacuum as possible. The surfaces of the turbine disc and cover plate that form the vacuum space are also coated with a reflective coating such as with a highly polished surface of low emissivity in order to minimize the radiation heat loss through the vacuum space. The turbine disc can have a cover plate forming a vacuum space or insulated cavity on both sides of the turbine disc. Ribs are also used within the vacuum space as supports for the cover plate due to the difference in pressure from the ambient side and the vacuum.
摘要翻译： 在涡轮泵中使用的涡轮盘，其在转子盘的侧面上暴露于大的热梯度。 涡轮盘的温暖的一侧由盖板覆盖，该盖板在涡轮盘和盖板之间形成密封空间，并且该空间被抽空或绝缘以形成尽可能接近完全真空的完全真空。 形成真空空间的涡轮盘和盖板的表面也涂覆有诸如具有低发射率的高抛光表面的反射涂层，以便使通过真空空间的辐射热损失最小化。 涡轮盘可以具有在涡轮盘的两侧形成真空空间或绝缘腔的盖板。 由于与环境侧和真空的压力差，在真空空间内还使用肋作为盖板的支撑。
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10.发明授权Dual expander cycle rocket engine with an intermediate, closed-cycle heat exchanger 失效双膨胀循环火箭发动机采用中间闭环循环换热器公开(公告)号：US07418814B1
公开(公告)日：2008-09-02
申请号：US11172666
申请日：2005-06-30
申请人： William D. Greene
发明人： William D. Greene
IPC分类号： F02K9/48
CPC分类号： F02K9/48
摘要： A dual expander cycle (DEC) rocket engine with an intermediate closed-cycle heat exchanger is provided. A conventional DEC rocket engine has a closed-cycle heat exchanger terhamlly coupled thereto. The heat exchanger utilizes heat extracted from the engine's fuel circuit to drive the engine's oxidizer turbomachinery.
摘要翻译： 提供了具有中间闭环热交换器的双膨胀循环（DEC）火箭发动机。 传统的DEC火箭发动机具有与其结合的闭环热交换器。 热交换器利用从发动机燃料回路提取的热量驱动发动机的氧化剂涡轮机。
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