公开(公告)号：US20040226280A1

公开(公告)日：2004-11-18

申请号：US10436861

申请日：2003-05-13

Applicant: United Technologies Corporation

Inventor： Gerald R. Berg ,  Donn C. Mueller ,  Mark W. Parish

IPC: F02K001/00

CPC classification number: F02K9/68 ,  B63H21/16 ,  C06B31/00 ,  C06B47/00 ,  F02K9/425 ,  F02K9/50 ,  F41A1/04

Abstract: An apparatus and method are provided for decomposition of a propellant. The propellant includes an ionic salt and an additional fuel. Means are provided for decomposing a major portion of the ionic salt. Means are provided for combusting the additional fuel and decomposition products of the ionic salt.

Abstract translation: 提供了用于分解推进剂的装置和方法。 推进剂包括离子盐和额外的燃料。 提供了用于分解大部分离子盐的方法。 提供了用于燃烧附加燃料和离子盐分解产物的装置。

公开(公告)号：US20030159426A1

公开(公告)日：2003-08-28

申请号：US10085501

申请日：2002-02-26

Inventor： Charles A. Vickery ,  Jerry N. Mason ,  William D. Kruse ,  Mark Olmos

IPC: F02K001/00

CPC classification number: F02K1/08 ,  Y02T50/672

Abstract: Methods and arrangements for tailoring rocket exhaust plume signatures of rocket exhaust systems are disclosed. The tailoring of the rocket exhaust plume signature is accomplished by providing and locating at least one structure having materials and/or additives that modify the radiant intensity pattern of the rocket exhaust plume upon ablation or melting into the rocket exhaust plume. The materials and/or additives can be manufactured or incorporated into preexisting ablative materials of the rocket exhaust system or be provided as stand-alone structures.

Abstract translation: 公开了用于定制火箭排气系统的火箭排气羽流签名的方法和装置。 通过提供和定位至少一个具有材料和/或添加剂的结构来实现火箭排气羽流签名的定制，该结构具有在消融或熔化成火箭排气羽流时改变火箭排气羽流的辐射强度图案。 材料和/或添加剂可以制造或并入到火箭排气系统的预先存在的烧蚀材料中，或者作为独立结构提供。

公开(公告)号：US20020036241A1

公开(公告)日：2002-03-28

申请号：US09472259

申请日：1999-12-29

Inventor： JAMES STEVEN JOHNSON

IPC: F02K001/00

CPC classification number: B64D33/04 ,  F02K1/1223 ,  F02K1/822 ,  Y02T50/675

Abstract: The radius of the hinged portion of the convergent/divergent axisymmetrical exhaust nozzle of a gas turbine engine is configured at the surface seeing the flow to be contoured at a critical radius so to enhance the flow characteristics of the nozzle and improve the low observables. The liner normally associated with the convergent flap is cut back at the juncture adjacent the hinged point connecting the divergent flap to be below the radar sight at the tail of the engine.

Abstract translation: 燃气涡轮发动机的收敛/发散的轴对称排气喷嘴的铰接部分的半径被构造在表面上，以在临界半径处观察流动的轮廓，以便增强喷嘴的流动特性并改善低的可观测量。 通常与会聚翼片相关联的衬垫在靠近发动机尾部的连接发散翼片的铰接点处的接合处被切割回来。

公开(公告)号：US20040194445A1

公开(公告)日：2004-10-07

申请号：US10406107

申请日：2003-04-04

Inventor： Fernando De La Pena LIaca

IPC: F02K001/00

CPC classification number: F03H99/00 ,  F02K9/42 ,  F02K9/425 ,  F02K9/48 ,  G21B1/00 ,  G21K1/00 ,  Y02E30/10

Abstract: The invention relates to the use of the collision of matter and antimatter as a means of propulsion in a spacecraft, to the control system for said engine and to a block diagram of the connections for same, in which all of the functions are divided into modules. Said invention refers to a form of propulsion that is totally different to those know at present, which enables spacecraft to move considerably faster in outer space and to reach up to one third of the speed light owing to the controlled collision of matter and antimatter. The control system works in conjunction with the engine in order to control the collision and to maintain the optimal parameters for performing said movement.

Abstract translation: 本发明涉及使用物质和反物质的碰撞作为在航天器中的推进手段，用于所述发动机的控制系统以及用于其的连接的框图，其中所有功能被分成模块 。 所述发明涉及与目前已知的那些完全不同的推进形式，这使得宇宙飞船在外部空间中移动得相当快，并且由于物质和反物质的受控碰撞而达到速度光的三分之一。 控制系统与发动机一起工作，以便控制碰撞并维持执行所述运动的最佳参数。

公开(公告)号：US20040159090A1

公开(公告)日：2004-08-19

申请号：US10369296

申请日：2003-02-18

Inventor： Harold A. Tavarez

IPC: F02K001/00

CPC classification number: F03H99/00 ,  F03G7/10

Abstract: A Hydromagnetic inertial thruster (10) comprising a centrifugal force generator (18), a plurality of electromagnets (22), a hydromagnetic fluid (36), and a stator housing (12) to support the operation of the centrifugal generator (18). The plurality of electromagnets (22) generates a magnetic field (Ho) to attract and hold a mass of a magnetically susceptible fluid (36).The centrifugal rotor (18) and the electromagnets (22) while generating the magnetic field (Ho) rotate together with the mass of fluid (36) for about one half of a cycle of revolution to generate an unbalanced centrifugal force (Fc) with the fluid (36). The vector sums of all the centrifugal force (Fc) vectors become a directional propulsion force (Fp).

Abstract translation: 一种包括离心力发生器（18），多个电磁体（22），水磁性流体（36）和支撑离心式发电机（18）的操作的定子壳体（12）的液体惯性推进器。 多个电磁体（22）产生磁场（Ho）以吸引并保持磁性敏感流体（36）的质量。离心转子（18）和电磁体（22）同时产生磁场（Ho）旋转 以及流体（36）的质量与转动周期的大约一半以产生与流体（36）不平衡的离心力（Fc）。 所有离心力（Fc）矢量的向量和成为方向推进力（Fp）。

公开(公告)号：US20040123599A1

公开(公告)日：2004-07-01

申请号：US10335647

申请日：2002-12-31

Inventor： John F. Ackermann ,  Paul V. Arszman ,  Bangalore A. Nagaraj ,  Craig Young ,  Nicole Justis

IPC: F02K001/00

CPC classification number: F01D5/288 ,  F05D2230/90 ,  F05D2300/133 ,  F05D2300/143 ,  F05D2300/211 ,  F05D2300/504 ,  F05D2300/611 ,  F23M2900/05004 ,  F23R3/002 ,  Y02T50/67 ,  Y02T50/672 ,  Y02T50/673

Abstract: A high temperature gas turbine component for use in the gas flow path that also is a specular optical reflector. A thin layer of a high temperature reflector is applied to the gas flow path of the component, that is, the surface of the component that forms a boundary for hot combustion gases. The component typically includes a thermal barrier coating overlying the high temperature metallic component that permits the component to operate at elevated temperatures. The thermal barrier coating must be polished in order to provide a surface that can suitably reflect the radiation into the gas flow path. A thin layer of the high temperature reflector the is applied over the polished thermal barrier coating by a process that can adequately adhere the reflector to the polished surface without increasing the roughness of the surface. The high temperature reflector can be applied to any surface aft of the compressor, such as on a centerbody. The surface reflects radiation back into the hot gas flow path or into the atmosphere. The reflected radiation is not focused onto any other hardware component. The design of the component is such that the radiation is returned to the gas flow path or sent to the atmosphere rather than absorbed into a component wall that only serves to increase the temperature of the wall.

Abstract translation: 用于气体流路的高温燃气轮机部件，其也是镜面光学反射器。 将高温反射器的薄层施加到部件的气体流动路径，即构成热燃烧气体边界的部件的表面。 该部件通常包括覆盖高温金属部件的热障涂层，其允许部件在升高的温度下操作。 必须抛光热障涂层，以便提供可以适当地将辐射反射到气体流动路径中的表面。 通过能够将反射器充分地粘附到抛光表面而不增加表面粗糙度的工艺，将高温反射体的薄层施加在抛光的热障涂层上。 高温反射器可以应用于压缩机后部的任何表面，例如在中心体上。 该表面将辐射反射回热气流路或进入大气。 反射的辐射没有集中在任何其他硬件组件上。 部件的设计使得辐射返回到气体流动路径或送到大气中，而不是被吸收到仅用于增加壁的温度的部件壁中。

公开(公告)号：US20040088967A1

公开(公告)日：2004-05-13

申请号：US10698493

申请日：2003-11-03

Inventor： John R. Webster ,  Paul J. R Strange

IPC: F02K001/00

CPC classification number: F02K1/34

Abstract: A method and a system (10) for exhausting gas via a nozzle (19, 21) of a gas turbine engine, for example. The system (10) comprises a nozzle (19, 21) comprising a nozzle body portion (32, 33, 74) defining a nozzle exit (42, 43), characterised in that the nozzle body portion (32, 33, 74) comprises fluid injection means (60), positioned upstream of the exit (42, 43) relative to a fluid flow (F1, F2) created by the operation of the system, for injecting fluid (68) upstream of the exit (42, 43).

Abstract translation: 一种用于例如通过燃气涡轮发动机的喷嘴（19,21）排出气体的方法和系统（10）。 系统（10）包括喷嘴（19,21），喷嘴（19,21）包括限定喷嘴出口（42,43）的喷嘴主体部分（32,33,74），其特征在于，喷嘴主体部分（32,33,74）包括 流体注入装置（60），其相对于由系统的操作产生的流体流（F1，F2）位于出口（42,43）的上游，用于在出口（42,43）上游注入流体（68） 。

公开(公告)号：US20020152752A1

公开(公告)日：2002-10-24

申请号：US09980456

申请日：2001-11-15

Inventor： Arne Boman

IPC: F02K001/00

CPC classification number: F02K9/97

Abstract: The invention refers to an apparatus for controlling the flow separation line of rocket nozzles for reducing side loads. For obtaining this control it is suggested according to the invention that the inside of the nozzle (1) has circumferentially regular spaced areas (2) with increased surface roughness compared with the rest of the inside of the nozzle.

Abstract translation: 本发明涉及一种用于控制用于减少侧向载荷的火箭喷嘴的流动分离线的装置。 为了获得该控制，根据本发明建议，与喷嘴内部的其余部分相比，喷嘴（1）的内部具有周向上规则间隔的区域（2），其具有增加的表面粗糙度。

公开(公告)号：US20040182336A1

公开(公告)日：2004-09-23

申请号：US10788387

申请日：2004-03-01

Inventor： Yasuki Ohmori ,  Yasuo Sasaki ,  Haruhisa Fujisawa

IPC: F02B071/00 ,  F02K001/00 ,  F23R003/00 ,  B64G009/00

CPC classification number: B25C1/08

Abstract: A combustion type power tool capable of avoiding damage to seal members and a housing to prolong a service life, and capable of enhancing operability and workability. Temperature elevation of a combustion chamber frame due to combustion of a mixture of combustible gas and air is detected by a temperature sensor disposed in a housing. If the detected temperature exceeds a preset temperature, ignition of an ignition plug is prohibited by a prohibiting unit in spite of ON operation of a trigger switch. In this state, alarming is performed by a display to notify the user of inoperable sate of the tool. Similar control can be made when the temperature sensor is disposed at a cylinder, an exhaust cover and the housing.

Abstract translation: 一种燃烧式电动工具，其能够避免对密封构件和壳体的损坏，以延长使用寿命，并且能够提高可操作性和可操作性。 由可燃气体和空气的混合物的燃烧引起的燃烧室框架的温度升高由设置在壳体中的温度传感器检测。 如果检测到的温度超过预设温度，则尽管开启了触发开关，但禁止单元禁止火花塞点火。 在这种状态下，通过显示器执行报警，以通知用户该工具不可操作的状态。 当温度传感器设置在气缸，排气盖和壳体时，可以进行类似的控制。

公开(公告)号：US20040118103A1

公开(公告)日：2004-06-24

申请号：US10610635

申请日：2003-07-02

Inventor： Ryuichi Nagashima

IPC: F02K001/00

CPC classification number: F02K9/68 ,  F02K9/42 ,  F02K9/425 ,  F02K9/50

Abstract: The engine for a rocket is suitable for using for an educational program. The engine uses a liquid phase propellant having a predetermined boiling point and a heating substance having a temperature higher than the boiling point. The engine has an inner wall having a circumferential surface; an outer wall surrounding the inner wall, the outer wall having an interior surface spaced from the circumferential surface of the inner wall by a predetermined distance such that the space between the circumferential surface and the interior surface form a mixing chamber having an opening; and injector for injecting the liquid-phase propellant and the heating substance into the mixing chamber so that the propellant is evaporated by the heating substance thereby creating a jet stream moving from the opening of the mixing chamber to the outside of the mixing chamber.

Abstract translation: 用于火箭的发动机适用于教育程序。 发动机使用具有预定沸点的液相推进剂和具有高于沸点的温度的加热物质。 发动机具有具有圆周表面的内壁; 围绕所述内壁的外壁，所述外壁具有与所述内壁的周向表面间隔预定距离的内表面，使得所述圆周表面和所述内表面之间的空间形成具有开口的混合室; 以及用于将液相推进剂和加热物质注入到混合室中的喷射器，使得推进剂被加热物质蒸发，从而产生从混合室的开口移动到混合室的外部的喷射流。