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1. 发明授权

US09291410B2 Cooling device for cooling combustion gases from recoilless anti-tank weapons 有权
标题翻译：用于冷却反坦克武器燃烧气体的冷却装置
公开(公告)号：US09291410B2
公开(公告)日：2016-03-22
申请号：US13811036
申请日：2010-07-22
申请人： Lars Nilsson
发明人： Lars Nilsson
IPC分类号： F02K11/00 , F41A1/10 , F02K9/40 , F02K9/97 , F41A13/00 , F41A13/04
CPC分类号： F41A1/10 , F02K9/40 , F02K9/972 , F41A13/00 , F41A13/04
摘要： The present invention relates to a cooling device (2) for cooling combustion gases from a rocket motor (1) in an antitank weapon. The cooling device (2) comprises a coolant reservoir (3, 21) containing a coolant (4). The coolant reservoir (3, 21) is arranged such that the coolant (4) is transferred from the coolant reservoir (3, 21) to the combustion gases in the gas outlets (6) of the rocket motor (1) in response to a pressure increase in the rocket motor (1). The coolant reservoir (3, 21) constitutes an integral part of the rocket motor (1) and is connected to the combustion chamber (7) by at least two gas inlets (8) for pressurization of the coolant (4). The coolant reservoir is furthermore connected to the rocket motor nozzle (9) by at least two coolant outlets (10) for transfer of coolant (4) from the coolant reservoir (3, 21) to the rocket motor nozzle (9).
摘要翻译：本发明涉及一种用于冷却来自反坦克武器的火箭发动机（1）的燃烧气体的冷却装置（2）。冷却装置（2）包括容纳冷却剂（4）的冷却剂储存器（3,21）。冷却剂储存器（3,21）被布置成使得冷却剂（4）响应于冷却剂储存器（3,21）从冷却剂储存器（3,21）转移到火箭发动机（1）的气体出口（6）中的燃烧气体火箭发动机（1）的压力增加。冷却剂储存器（3,21）构成火箭发动机（1）的一体部分，并且通过至少两个用于冷却剂（4）加压的气体入口（8）连接到燃烧室（7）。冷却剂储存器还通过至少两个用于将冷却剂（4）从冷却剂储存器（3,21）传递到火箭发动机喷嘴（9）的冷却剂出口（10）连接到火箭发动机喷嘴（9）。

2. 发明授权

US09222439B2 Rocket engine with cryogenic propellants 有权
标题翻译：火箭发动机带低温推进剂
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
IPC分类号： F02K9/50 , F02K9/97 , F02K9/64
CPC分类号： F02K9/972 , F02K9/50 , F02K9/64
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。

3. 发明授权

US09127622B2 Reversible flow discharge orifice 有权
标题翻译：可逆流量排放口
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。

4. 发明授权

US09115666B2 Slotted multi-nozzle grid with integrated cooling channels 有权
标题翻译：带有集成冷却通道的开槽多喷嘴格栅
公开(公告)号：US09115666B2
公开(公告)日：2015-08-25
申请号：US13647599
申请日：2012-10-09
申请人： Raytheon Company
发明人： Daniel Chasman , Stephen D. Haight , James K. Villarreal
IPC分类号： F02K9/30 , F02K9/97
CPC分类号： F02K9/30 , F02K9/97 , F02K9/972 , Y10T29/49346
摘要： An apparatus includes a slotted multi-nozzle grid with a plate having multiple elongated slotlettes through the plate. Each of at least some of the slotlettes has a convergent input, a divergent output, and a narrower throat portion separating the convergent input and the divergent output. At least some of the slotlettes are arranged in multiple rows. The plate further includes multiple cooling channels through the plate. At least some of the cooling channels are located between the rows of slotlettes. Each cooling channel is configured to transport coolant through the plate in order to cool the plate, such as to cool the plate as hot combustion gases pass through the plate. Each of at least some of the rows may include at least two slotlettes, and two adjacent slotlettes in one row may be separated by a structural ligament (which may have a tear-drop cross-sectional shape).
摘要翻译：一种装置包括带槽的多喷嘴格栅，其具有穿过该板的具有多个细长槽的板。至少一些小缝隙中的每一个具有收敛输入，发散输出和分离收敛输入和发散输出的较窄喉部。至少一些小行星排列成多行。板还包括穿过板的多个冷却通道。至少一些冷却通道位于行槽之间。每个冷却通道被构造成运输冷却剂通过板以便冷却板，例如当热燃气通过板时冷却板。至少一些行中的每一行可以包括至少两个开槽元件，并且一行中的两个相邻的开槽元件可以被结构韧带（其可能具有泪滴横截面形状）分开。

5. 发明授权

US08708647B2 Liner for a turbine section, a turbine section, a gas turbine engine and an aeroplane provided therewith 有权
标题翻译：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
CPC分类号： F02K9/64 , F02C7/12 , F02K1/82 , F02K1/822 , F02K1/825 , F02K9/972
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。

6. 发明申请

US20140096510A1 SLOTTED MULTI-NOZZLE GRID WITH INTEGRATED COOLING CHANNELS 有权
标题翻译：带集成式冷却通道的多孔多孔网
公开(公告)号：US20140096510A1
公开(公告)日：2014-04-10
申请号：US13647599
申请日：2012-10-09
申请人： RAYTHEON COMPANY
发明人： Daniel Chasman , Stephen D. Haight , James K. Villarreal
IPC分类号： F02K9/97 , B21D53/00 , F02K99/00
CPC分类号： F02K9/30 , F02K9/97 , F02K9/972 , Y10T29/49346
摘要： An apparatus includes a slotted multi-nozzle grid with a plate having multiple elongated slotlettes through the plate. Each of at least some of the slotlettes has a convergent input, a divergent output, and a narrower throat portion separating the convergent input and the divergent output. At least some of the slotlettes are arranged in multiple rows. The plate further includes multiple cooling channels through the plate. At least some of the cooling channels are located between the rows of slotlettes. Each cooling channel is configured to transport coolant through the plate in order to cool the plate, such as to cool the plate as hot combustion gases pass through the plate. Each of at least some of the rows may include at least two slotlettes, and two adjacent slotlettes in one row may be separated by a structural ligament (which may have a tear-drop cross-sectional shape).
摘要翻译：一种装置包括带槽的多喷嘴格栅，其具有穿过该板的具有多个细长槽的板。至少一些小缝隙中的每一个具有收敛输入，发散输出和分离收敛输入和发散输出的较窄喉部。至少一些小行星排列成多行。板还包括穿过板的多个冷却通道。至少一些冷却通道位于行槽之间。每个冷却通道被构造成运输冷却剂通过板以便冷却板，例如当热燃气通过板时冷却板。至少一些行中的每一行可以包括至少两个开槽元件，并且一行中的两个相邻的开槽元件可以被结构韧带（其可能具有泪滴横截面形状）分开。

7. 发明申请

US20130276426A1 Cooling Jacket with Porous Matrix 审中-公开
标题翻译：多孔矩阵冷却夹克
公开(公告)号：US20130276426A1
公开(公告)日：2013-10-24
申请号：US13857064
申请日：2013-04-04
申请人： Firestar Engineering, LLC
发明人： Gregory S. Mungas , David J. Fisher , Adam Pollok London , Jack Merrill Fryer
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。

8. 发明申请

US20130160427A1 COOLING DEVICE FOR COOLING COMBUSTION GASES FROM RECOILLESS ANTI-TANK WEAPONS 有权
标题翻译：冷却装置，用于从回收的反坦克武器冷却燃烧气体
公开(公告)号：US20130160427A1
公开(公告)日：2013-06-27
申请号：US13811036
申请日：2010-07-22
申请人： Lars Nilsson
发明人： Lars Nilsson
IPC分类号： F02K9/40
CPC分类号： F41A1/10 , F02K9/40 , F02K9/972 , F41A13/00 , F41A13/04
摘要： The present invention relates to a cooling device (2) for cooling combustion gases from a rocket motor (1) in an antitank weapon. The cooling device (2) comprises a coolant reservoir (3, 21) containing a coolant (4). The coolant reservoir (3, 21) is arranged such that the coolant (4) is transferred from the coolant reservoir (3, 21) to the combustion gases in the gas outlets (6) of the rocket motor (1) in response to a pressure increase in the rocket motor (1). The coolant reservoir (3, 21) constitutes an integral part of the rocket motor (1) and is connected to the combustion chamber (7) by at least two gas inlets (8) for pressurization of the coolant (4). The coolant reservoir is furthermore connected to the rocket motor nozzle (9) by at least two coolant outlets (10) for transfer of coolant (4) from the coolant reservoir (3, 21) to the rocket motor nozzle (9).
摘要翻译：本发明涉及一种用于冷却来自反坦克武器的火箭发动机（1）的燃烧气体的冷却装置（2）。冷却装置（2）包括容纳冷却剂（4）的冷却剂储存器（3,21）。冷却剂储存器（3,21）被布置成使得冷却剂（4）响应于冷却剂储存器（3,21）从冷却剂储存器（3,21）转移到火箭发动机（1）的气体出口（6）中的燃烧气体火箭发动机（1）的压力增加。冷却剂储存器（3,21）构成火箭发动机（1）的一体部分，并且通过至少两个用于冷却剂（4）加压的气体入口（8）连接到燃烧室（7）。冷却剂储存器还通过至少两个用于将冷却剂（4）从冷却剂储存器（3,21）传递到火箭发动机喷嘴（9）的冷却剂出口（10）连接到火箭发动机喷嘴（9）。

9. 发明申请

US20130126335A1 DEVICE AND A METHOD FOR APPLYING A COATING ON A WORKPIECE BY ELECTRODEPOSITION 审中-公开
标题翻译：装置和通过电沉积施加工件上的涂层的方法
公开(公告)号：US20130126335A1
公开(公告)日：2013-05-23
申请号：US13739238
申请日：2013-01-11
申请人： Jean-Louis Thomas , Alain Le Cleac'h
发明人： Jean-Louis Thomas , Alain Le Cleac'h
IPC分类号： C25D5/48 , C25D17/02 , C25D7/04 , C25D17/06
CPC分类号： C25D5/48 , C25D5/08 , C25D5/22 , C25D7/04 , C25D17/00 , C25D17/02 , C25D17/06 , C25D17/12 , C25D21/10 , C25D21/14 , F02K9/64 , F02K9/972 , F05D2230/31
摘要： The invention relates to a device and a method of applying a coating on a workpiece by electrodeposition. A vessel is provided that is suitable for filling with a bath of electrolyte, anode-forming conductor means being placed in the vessel and connected to a current generator, a cathode-forming workpiece mounted on the mandrel of a lathe, and guidance and movement means for guiding and moving the vessel relative to the lathe, the guidance and movement means enabling the workpiece to be immersed in full or in part in the bath of electrolyte.
摘要翻译：本发明涉及通过电沉积将涂层施加在工件上的装置和方法。提供适于填充电解液池的容器，阳极形成导体装置放置在容器中并连接到电流发生器，安装在车床心轴上的阴极成形工件，以及引导和移动装置用于引导和移动容器相对于车床的引导和移动装置使得工件能够全部或部分地浸入电解液浴中。

10. 发明授权

US08127443B2 Method of fabricating a rocket engine nozzle using pressure brazing 有权
标题翻译：使用压力钎焊制造火箭发动机喷嘴的方法
公开(公告)号：US08127443B2
公开(公告)日：2012-03-06
申请号：US12271920
申请日：2008-11-16
申请人： Jeffry A. Fint , Michael B. Hankins , Myron L. Jew , Donald G. Ulmer , Brian L. Wherley , William D. Romine , Frederick M. Kuck , Douglas S. Ades
发明人： Jeffry A. Fint , Michael B. Hankins , Myron L. Jew , Donald G. Ulmer , Brian L. Wherley , William D. Romine , Frederick M. Kuck , Douglas S. Ades
IPC分类号： B21K25/00 , F02K9/00
CPC分类号： F02K9/972 , F02K9/97 , F05D2230/237 , Y10S29/004 , Y10T29/49323 , Y10T29/49346 , Y10T29/49432
摘要： A method of fabrication of a rocket engine nozzle assembly using pressure brazing generally includes initially assembling a rocket engine nozzle liner into a rocket engine nozzle jacket for a rocket engine nozzle assembly. The rocket engine nozzle assembly may then be sealed. Prior to pressure brazing the rocket engine nozzle assembly, pressure brazing parameters may be determined. The pressure brazing may be performed with the determined pressure brazing parameters to complete the fabrication of the rocket engine nozzle. The rocket engine nozzle assembly may include a rocket engine nozzle jacket and a rocket engine nozzle liner having a plurality of channels, with the space between each channel defining a land, and the rocket engine nozzle liner having at least a pair of endlands disposed at each end thereof. The rocket engine nozzle liner is bonded to the rocket engine nozzle jacket by the endlands being bonded to the nozzle jacket and the lands being pressure brazed to the nozzle jacket.
摘要翻译：使用压力钎焊制造火箭发动机喷嘴组件的方法通常包括首先将火箭发动机喷嘴衬套组装到用于火箭发动机喷嘴组件的火箭发动机喷嘴护套中。然后可以密封火箭发动机喷嘴组件。在对火箭发动机喷嘴组件进行压力钎焊之前，可以确定压力钎焊参数。压力钎焊可以用确定的压力钎焊参数进行，以完成火箭发动机喷嘴的制造。火箭发动机喷嘴组件可以包括火箭发动机喷嘴护套和具有多个通道的火箭发动机喷嘴衬套，每个通道之间的空间限定了一个平台，而火箭发动机喷嘴衬套具有至少一对端部，结束。火箭发动机喷嘴衬套通过端部粘合到火箭发动机喷嘴护套上，端部被接合到喷嘴护套，并且焊盘被压焊到喷嘴护套上。

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