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11.发明授权公开(公告)号：US09429106B2
公开(公告)日：2016-08-30
申请号：US13381431
申请日：2010-07-08
申请人： Daniel Cornu
发明人： Daniel Cornu
CPC分类号： F02K9/97 , F02K9/64 , F02K9/974 , F05D2260/231 , F05D2300/2118
摘要： The invention concerns a combustion chamber (10) comprising a neck (15) downstream of the injection (11) of gases, and downstream of this neck a divergent section (20) whereof the outer face of the wall (30), when in operation, is cooled by a cooling system using a cryogenic product and surrounding this outer face. This divergent section (20), on the inner face (32) of its wall (30), comprises a coating (40) acting as temperature compensator so that the temperature of the inner face (42) of the coating (40) is higher than the condensation temperature of the combustion gases on this inner face (42) under operating conditions, such that no condensation is formed on this inner face (42).
摘要翻译： 本发明涉及一种燃烧室（10），其包括在喷射（11）气体下游的颈部（15），并且在该颈部的下游具有在运行中的壁（30）的外表面的扩散部分（20） 由使用低温产品的冷却系统冷却并围绕该外表面。 在其壁（30）的内表面（32）上的该扩散部分（20）包括作为温度补偿器的涂层（40），使得涂层（40）的内表面（42）的温度更高 比在该内表面（42）上的燃烧气体在操作条件下的冷凝温度低，使得在该内表面（42）上不形成冷凝。
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公开(公告)号：US20160200457A1
公开(公告)日：2016-07-14
申请号：US14994376
申请日：2016-01-13
申请人： Ventions, LLC
发明人： Lloyd J. Droppers
CPC分类号： B64G1/402 , B64G1/10 , B64G1/401 , F02K9/42 , F02K9/58 , F02K9/64 , F02K9/88 , F05D2250/80 , F05D2260/202
摘要： A small satellite propulsion system using a gaseous oxidizer and a gaseous fuel as primary propellants with a liquid as a film coolant for the inner surface of the rocket motor. The gaseous fuel is also used as a pressurant for the coolant and as a cold gas propellant for attitude control system (hereinafter “ACS”) thrusters. The oxidizer, fuel, and coolant tanks, as well as most valves and plumbing, are integrated into a single core unit along with the rocket motor, rocket motor plumbing, and safety valves. Attitude control thrusters may be remotely located with plumbing to the fuel tank. The core unit is four inches high and less than four inches deep and wide. The small satellite propulsion system uses no pyrotechnics and no hazardous toxic materials.
摘要翻译： 使用气体氧化剂和气体燃料作为主要推进剂的小卫星推进系统，其中液体作为用于火箭发动机内表面的薄膜冷却剂。 气态燃料也用作冷却剂的加压剂，也用作姿态控制系统（以下简称“ACS”）推进器的冷气推进剂。 氧化剂，燃料和冷却剂罐以及大多数阀门和管道，与火箭发动机，火箭发动机管道和安全阀一起集成到单个核心单元中。 姿态控制推进器可以远程位于带有管道的燃料箱中。 核心单元是四英寸高，不到四英寸深和宽。 小型卫星推进系统不使用烟火，无危险有毒物质。
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公开(公告)号：US09222439B2
公开(公告)日：2015-12-29
申请号：US13384477
申请日：2010-07-16
申请人： Olivier Dobek , Daniel Le Dortz
发明人： Olivier Dobek , Daniel Le Dortz
摘要： A cryogenic-propellant rocket engine includes: at least a first tank for a first liquid propellant; a second tank for a second liquid propellant; a third tank for an inert fluid; an axisymmetrical nozzle including a combustion chamber, a device for injecting first and second liquid propellants into the combustion chamber, a nozzle throat, and a divergent section; and a heater device including at least one duct for conveying the inert fluid and arranged outside the nozzle in immediate proximity thereof, but without making contact therewith, to recover energy of thermal radiation emitted when the rocket engine is in operation and to heat the inert fluid.
摘要翻译： 低温推进剂火箭发动机包括：用于第一液体推进剂的至少第一罐; 用于第二液体推进剂的第二罐; 用于惰性流体的第三罐; 包括燃烧室的轴对称喷嘴，用于将第一和第二液体推进剂喷射到燃烧室中的装置，喷嘴喉部和发散部分; 以及加热器装置，其包括用于输送惰性流体并且布置在喷嘴外部的至少一个管道，其直接邻近但不与其接触，以回收当火箭发动机运行时发射的热辐射的能量并且加热惰性流体 。
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公开(公告)号：US09127622B2
公开(公告)日：2015-09-08
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： F02K9/56 , F16L55/027
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：US20150090774A1
公开(公告)日：2015-04-02
申请号：US14381287
申请日：2013-02-19
CPC分类号： B23K1/0008 , B23K1/19 , B23K1/20 , F02K9/34 , F02K9/64 , F05D2230/237
摘要： According to this brazing method, a first base member having a non-plated surface, a metal layer for functioning as a diffusion barrier layer, a brazing foil, and a second base member having a surface are arranged in this order so that the non-plated surface of the first base member and the surface of the second base member are faced with each other. The first base member and the second base member are brazed by using the brazing foil. The cost of providing a diffusion barrier layer between the first base member and the brazing foil is thereby reduced.
摘要翻译： 根据该钎焊方法，按顺序排列具有非镀面的第一基材，用作扩散阻挡层的金属层，钎焊箔和具有表面的第二基材， 第一基体的镀敷面和第二基材的表面相互面对。 通过使用钎焊箔钎焊第一基底构件和第二基底构件。 从而降低了在第一基底和钎焊箔之间设置扩散阻挡层的成本。
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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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17.发明申请公开(公告)号：US20140216003A1
公开(公告)日：2014-08-07
申请号：US14245317
申请日：2014-04-04
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 gas turbine engine includes a fan, a compressor section, a combustion section, and a turbine section. A fan drive gear system is configured for driving the fan at a speed different than the turbine section. A lubricant system includes a lubricant pump delivering lubricant to an outlet line. The outlet line splits into at least a hot line and into a cool line. The hot line is directed primarily to locations in the gas turbine engine that are not intended to receive cooler lubricant. The cool line is directed through one or more heat exchangers at which the lubricant is cooled, and the cool line then is routed to the fan drive gear system. At least one of the one or more heat exchangers is a fuel/oil cooler at which lubricant will be cooled by fuel leading to the combustion section. The fuel/oil cooler is downstream of a point where the outlet line splits into the at least the hot line and the cool line, such that the hot line is not directed through the fuel/oil cooler. A method is also disclosed.
摘要翻译： 燃气涡轮发动机包括风扇，压缩机部，燃烧部和涡轮部。 风扇驱动齿轮系统构造成以不同于涡轮部分的速度驱动风扇。 润滑剂系统包括将润滑剂输送到出口管线的润滑剂泵。 出口线分成至少一条热线，并进入冷线。 热线主要针对燃气涡轮发动机中不用于接收较冷润滑剂的位置。 冷却管线被引导通过一个或多个热交换器，在该热交换器处润滑剂被冷却，然后将冷却管线路由到风扇驱动齿轮系统。 一个或多个热交换器中的至少一个是燃料/油冷却器，在该燃料/油冷却器处，通过燃料通向燃烧部分的润滑剂将被冷却。 燃料/油冷却器在出口管线分成至少热管线和冷却管线的点的下游，使得热管线不被引导通过燃料/油冷却器。 还公开了一种方法。
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18.发明授权Liner for a turbine section, a turbine section, a gas turbine engine and an aeroplane provided therewith 有权用于涡轮机部分的涡轮机部分，涡轮机部分，燃气涡轮发动机和与其配备的飞机公开(公告)号：US08708647B2
公开(公告)日：2014-04-29
申请号：US12518101
申请日：2006-12-06
申请人： Arne Boman
发明人： Arne Boman
IPC分类号： F01D25/12
摘要： A liner for a turbine section includes a first wall, a plurality of webs interconnected with and projecting from the first wall, and a plurality of cooling channels, each of the cooling channels being delimited by two adjacent webs and the first wall, wherein each cooling channel presents a height corresponding to the height of its delimiting webs, and a width corresponding to the distance between its delimiting webs. At least one of the cooling channels has a width/height ratio of below 5 or/and the material of the webs has a higher thermal conductivity than the material of the first wall. A turbine section, a gas turbine engine and an aeroplane provided with such a liner are also disclosed.
摘要翻译： 用于涡轮部分的衬套包括第一壁，与第一壁互连并且从第一壁突出的多个腹板和多个冷却通道，每个冷却通道由两个相邻腹板和第一壁限定，其中每个冷却 通道具有对应于其分隔腹板的高度的高度，以及对应于其分隔腹板之间的距离的宽度。 冷却通道中的至少一个具有低于5的宽度/高度比或/和幅材的材料具有比第一壁的材料更高的热导率。 还公开了一种涡轮机部分，燃气涡轮发动机和设有这种衬管的飞机。
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公开(公告)号：US20130276426A1
公开(公告)日：2013-10-24
申请号：US13857064
申请日：2013-04-04
IPC分类号： F02K9/00
CPC分类号： F02K9/00 , F02K9/34 , F02K9/40 , F02K9/64 , F02K9/972 , F05D2260/20 , Y10T29/49346
摘要： The fluids and heat transfer theory for regenerative cooling of a rocket combustion chamber with a porous media coolant jacket is presented. This model is useful for calculating temperature distributions in a coolant fluid and combustion chamber or heat source as well as the associated fluid pressure drop through the coolant jacket. This model for fluids and heat transfer theory can be used to design a regeneratively cooled rocket engine.
摘要翻译： 介绍了具有多孔介质冷却剂护套的火箭燃烧室再生冷却的流体和热传递理论。 该模型可用于计算冷却剂流体和燃烧室或热源中的温度分布以及通过冷却剂套管的相关流体压降。 该流体和热传递理论模型可用于设计再生冷却火箭发动机。
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20.发明申请公开(公告)号：US20130199571A1
公开(公告)日：2013-08-08
申请号：US13675786
申请日：2012-11-13
IPC分类号： B08B7/00
CPC分类号： B08B7/0071 , B08B9/00 , F02K9/64
摘要： There is disclosed a method of cleaning a liquid hydrocarbon-cooled bipropellant rocket engine. In an embodiment, method includes heating the engine to a temperature. The method includes applying ozone for a period of time. The method includes determining the temperature and the period of time are each sufficient to remove carbonaceous deposits. In another embodiment, the method may further include thermally imaging the heat transfer surfaces. There is disclosed apparatus for cleaning a liquid hydrocarbon-cooled bipropellant rocket engine. In one embodiment, the apparatus includes a heater, an ozone source, and a thermal camera. Other embodiments are also disclosed.
摘要翻译： 公开了一种清洗液体烃冷式双组元推进剂火箭发动机的方法。 在一个实施例中，方法包括将发动机加热到一个温度。 该方法包括在一段时间内施加臭氧。 该方法包括确定温度和时间段各自足以除去碳质沉积物。 在另一个实施例中，该方法还可以包括热传递表面的成像。 公开了一种用于清洗液体烃冷式双组元推进剂火箭发动机的装置。 在一个实施例中，该装置包括加热器，臭氧源和热摄像机。 还公开了其他实施例。
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