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1. 发明授权

US06584765B1 Pulse detonation engine having an aerodynamic valve 有权
标题翻译：具有气动阀的脉冲爆震发动机
公开(公告)号：US06584765B1
公开(公告)日：2003-07-01
申请号：US10026236
申请日：2001-12-21
申请人： David E. Tew , Torger J. Anderson , Roy N. Guile , David R. Sobel , Wendell V. Twelves, Jr. , Gary D. Jones
发明人： David E. Tew , Torger J. Anderson , Roy N. Guile , David R. Sobel , Wendell V. Twelves, Jr. , Gary D. Jones
IPC分类号： F02K702
CPC分类号： F23C15/00 , B64G1/401 , B64G1/402 , F02K7/06 , F02K7/067 , F23C2205/10 , F23C2205/20 , Y02T50/67 , Y02T50/671 , Y10T137/86405 , Y10T137/86743
摘要： A pulse detonation engine (10) is provided with an aerovalve (14) for controlling the pressure of injected propellants (Ox, Fuel) in an open-ended detonation chamber (26). The propellants are injected at such pressure and velocity, and in a direction generally toward a forward thrust wall end (16) of the detonation chamber (26), an aerovalve (14) is formed which effectively inhibits or prevents egress of the propellant from the detonation chamber (26). A shock wave (34) formed by the injected propellant acts, after reflection by the thrust wall end (16) and in combination with the aerovalve (14), to compress and conserve, or increase, the pressure of the injected propellant. Carefully timed ignition (28) effects a detonation pulse under desired conditions of maintained, or increased, pressure. Termination of the propellant injection serves to “open” the aerovalve (14), and exhaust of the combusted propellants occurs to produce thrust. Alternate embodiments of propellant injection mechanisms (12, 112) provide pulse valves (24, 122, 124) each having a fixed slotted disk (40, 140, 240) and a rotating slotted disk (42, 142, 242) to provide the desired high speed valving of discrete pulses of propellant for injection.
摘要翻译：脉冲爆震发动机（10）设置有空气阀（14），用于控制开放式爆震室（26）中喷射的推进剂（Ox，Fuel）的压力。推进剂以这样的压力和速度被注入，并且在大致朝向引爆室（26）的向前推力壁端部（16）的方向上注入，形成了一个空气阀（14），其有效地抑制或防止推进剂从爆震室（26）。由喷射的推进剂形成的冲击波（34）在被推力壁端部（16）反射并与空气阀（14）组合之后作用，以压缩并保存或增加喷射推进剂的压力。仔细定时点火（28）会在保持或增加压力的期望条件下产生爆震脉冲。推进剂喷射的终止用于“打开”空气阀（14），并且发生燃烧的推进剂的排气以产生推力。推进剂喷射机构（12,112）的替代实施例提供脉冲阀（24,122,124），每个脉冲阀具有固定的开槽圆盘（40,140,240）和旋转的开槽圆盘（42,142,242）以提供期望的用于注射的推进剂的离散脉冲的高速阀。

2. 发明授权

US4379679A Supersonic/supersonic fluid ejector 失效
标题翻译：超音速/超声流体喷射器
公开(公告)号：US4379679A
公开(公告)日：1983-04-12
申请号：US211613
申请日：1980-12-01
申请人： Roy N. Guile
发明人： Roy N. Guile
IPC分类号： F04F5/18 , F04F5/46
CPC分类号： F04F5/465 , F04F5/18 , Y10S261/78
摘要： An ejector for pumping a low pressure, supersonic driven stream to a high pressure is disclosed. Effective pressure recovery in a relatively short axial length is sought.The low pressure driven stream is flowed at supersonic velocities into the ejector. A high energy driving stream is flowed laterally of the driven stream at a supersonic velocity greater than the supersonic velocity of the driven stream and a static pressure above the static pressure of the driven stream to cause compression of the driven stream at supersonic velocities.
摘要翻译：公开了一种用于将低压超音速驱动流泵送到高压的喷射器。寻求在相对短的轴向长度内有效的压力恢复。低压驱动流以超音速流动到喷射器中。高能量驱动流在驱动流的横向流动，其超声速度大于被驱动流的超音速，并且超过被驱动流的静态压力的静态压力，以引起被驱动流以超音速速度的压缩。

3. 发明授权

US4138777A Single nozzle free-vortex aerodynamic window 失效
公开(公告)号：US4138777A
公开(公告)日：1979-02-13
申请号：US685946
申请日：1976-05-13
申请人： C. Edward Kepler , Roy N. Guile
发明人： C. Edward Kepler , Roy N. Guile
IPC分类号： H01S3/034 , H01S3/22
CPC分类号： H01S3/0343 , Y10T29/49432
摘要： A gas laser emits an output laser beam from a low pressure region to a region having a higher pressure. This is done through an opening in the side of a laser device. Under normal circumstances, the provision of such an opening would incur a flow of air from the high pressure side, externally of the laser device, to the low pressure side within the device. To prevent this, an aerodynamic window is placed in a passageway leading from said opening in the laser device through which the laser beam passes. A gas flow is passed across said passageway which will provide a flow which represents the flow of a segment of a free-vortex flow field having a pressure differential across the segment which is equal to that between the low and high pressure regions. A single nozzle, specifically contoured to produce a segment of a free-vortex flow field directs the gas into the passageway and an opening collects the flow onto the other side of said passageway. A method of constructing such a nozzle is set forth.

4. 发明授权

US07753036B2 Compound cycle rotary engine 有权
标题翻译：复合循环旋转发动机
公开(公告)号：US07753036B2
公开(公告)日：2010-07-13
申请号：US11824645
申请日：2007-07-02
申请人： Charles E. Lents , Stephen P. Zeppieri , Roy N. Guile , Vincent C. Nardone , Jonathan Lauter , Arindam Dasgupta
发明人： Charles E. Lents , Stephen P. Zeppieri , Roy N. Guile , Vincent C. Nardone , Jonathan Lauter , Arindam Dasgupta
IPC分类号： F02B33/00
CPC分类号： F01C11/008 , F01C1/22 , F02B29/0437 , F02B37/00 , F02B41/10 , F02B53/04 , F02B2275/32 , Y02T10/142 , Y02T10/144 , Y02T10/163 , Y02T10/17
摘要： A compound cycle engine system has a rotary engine, which rotary engine generates exhaust gas. The system further has a compressor for increasing the pressure of inlet air to be supplied to the engine to a pressure in the range of from 3.0 to 5.0 atmospheres and an intercooler for providing the inlet air to the engine at a temperature in the range of from 150 to 250 degrees Fahrenheit. The system further has one or more turbines for extracting energy from the exhaust gas. The Miller Cycle is implemented in the rotary engine, enabling the compression ratio to be lower than the expansion ratio, allowing the overall cycle to be optimized for lowest weight and specific fuel consumption.
摘要翻译：复合循环发动机系统具有旋转发动机，该旋转发动机产生废气。该系统还具有用于将供给发动机的入口空气的压力提高到3.0-5.0大气压的压缩机，以及用于在从...的范围内的温度下向发动机提供入口空气的中间冷却器 150至250华氏度。该系统还具有用于从废气中提取能量的一个或多个涡轮机。米勒循环在旋转发动机中实现，使压缩比低于膨胀比，从而可以优化整体循环，以获得最低的重量和特定的燃油消耗。

5. 发明申请

US20090007882A1 Compound cycle rotary engine 有权
标题翻译：复合循环旋转发动机
公开(公告)号：US20090007882A1
公开(公告)日：2009-01-08
申请号：US11824645
申请日：2007-07-02
申请人： Charles E. Lents , Stephen P. Zeppieri , Roy N. Guile , Vincent C. Nardone , Jonathan Lauter , Arindam Dasgupta
发明人： Charles E. Lents , Stephen P. Zeppieri , Roy N. Guile , Vincent C. Nardone , Jonathan Lauter , Arindam Dasgupta
IPC分类号： F02B53/02
CPC分类号： F01C11/008 , F01C1/22 , F02B29/0437 , F02B37/00 , F02B41/10 , F02B53/04 , F02B2275/32 , Y02T10/142 , Y02T10/144 , Y02T10/163 , Y02T10/17
摘要： A compound cycle engine system has a rotary engine, which rotary engine generates exhaust gas. The system further has a compressor for increasing the pressure of inlet air to be supplied to the engine to a pressure in the range of from 3.0 to 5.0 atmospheres and an intercooler for providing the inlet air to the engine at a temperature in the range of from 150 to 250 degrees Fahrenheit. The system further has one or more turbines for extracting energy from the exhaust gas. The Miller Cycle is implemented in the rotary engine, enabling the compression ratio to be lower than the expansion ratio, allowing the overall cycle to be optimized for lowest weight and specific fuel consumption.
摘要翻译：复合循环发动机系统具有旋转发动机，该旋转发动机产生废气。该系统还具有用于将供给发动机的入口空气的压力提高到3.0-5.0大气压的压缩机，以及用于在从...的范围内的温度下向发动机提供入口空气的中间冷却器 150至250华氏度。该系统还具有用于从废气中提取能量的一个或多个涡轮机。米勒循环在旋转发动机中实现，使压缩比低于膨胀比，从而可以优化整体循环，以获得最低的重量和特定的燃油消耗。

6. 发明授权

US08313056B2 Engine heat exchanger with thermoelectric generation 有权
标题翻译：发电机热交换器与热电发电
公开(公告)号：US08313056B2
公开(公告)日：2012-11-20
申请号：US11185638
申请日：2005-07-19
申请人： David C. Jarmon , Rhonda R. Willigan , Roy N. Guile
发明人： David C. Jarmon , Rhonda R. Willigan , Roy N. Guile
IPC分类号： B64D41/00
CPC分类号： H01L35/30 , F01D15/10 , F01D25/12 , F02C7/32 , Y02T50/672 , Y02T50/675
摘要： A vehicle has a body and a source of a propellant. An engine is carried by the body. The engine reacts the propellant to produce thrust. The engine has a heat exchanger transferring heat from the reaction to at least a component of the propellant and generating electricity thermoelectrically.
摘要翻译：车辆有一个主体和一个推进剂的来源。发动机由身体携带。发动机使推进剂反应产生推力。发动机具有将热量从反应器传递到至少推进剂的组分并且热电发电的热交换器。

7. 发明授权

US07296965B2 Cryogenic bearings 有权
标题翻译：低温轴承
公开(公告)号：US07296965B2
公开(公告)日：2007-11-20
申请号：US10925320
申请日：2004-08-23
申请人： Clark V. Cooper , William K. Tredway , Roy N. Guile , Chris C. Rhemer , Alan B. Minick , Leonard W. Chapman
发明人： Clark V. Cooper , William K. Tredway , Roy N. Guile , Chris C. Rhemer , Alan B. Minick , Leonard W. Chapman
IPC分类号： F04D29/56 , C23C14/00
CPC分类号： F16C33/14 , C22C14/00 , C22C19/055 , C22C19/056 , C22C30/00 , C22C38/02 , C22C38/06 , C22C38/105 , C22C38/12 , C22C38/14 , F16C7/023 , F16C9/04 , F16C23/041 , F16C33/121 , F16C33/128 , F16C2223/60 , Y10T428/2495 , Y10T428/264 , Y10T428/31678
摘要： The bearing system includes a first component having a first substrate and a first coating. The first coating includes a DLC layer and a DLN layer between the DLC layer and the substrate. A second component is in sliding engagement with the first component.
摘要翻译：轴承系统包括具有第一基底和第一涂层的第一部件。第一涂层包括在DLC层和衬底之间的DLC层和DLN层。第二部件与第一部件滑动接合。

8. 发明授权

US4821512A Piloting igniter for supersonic combustor 失效
标题翻译：超音速燃烧器的引燃点火器
公开(公告)号：US4821512A
公开(公告)日：1989-04-18
申请号：US46072
申请日：1987-05-05
申请人： Roy N. Guile , William T. Peschke
发明人： Roy N. Guile , William T. Peschke
IPC分类号： F02K7/10 , F02K7/14 , F23R3/20 , F02C7/264
CPC分类号： F02K7/10 , F23R3/20 , F05D2260/20 , Y02T50/675
摘要： A piloting fuel injector assembly for a supersonic ramjet engine has a cowl 24, 70 confining a pilot air portion of the airstream. A conical member 34, 74 produces a subsonic recirculation zone 30, 76 and a shock wave falling within the cowl. Pilot fuel injected 40, 82 upstream of the recirculation zone burns stoichiometrically. The exhaust 38, 86 from the cowl is sonic, producing a shock wave which facilitates ignition of the main fuel injected 46, 84 upstream of the cowl exhaust.
摘要翻译：用于超音速冲压喷气发动机的驾驶式燃料喷射器组件具有限制气流的先导空气部分的整流罩24,70。圆锥形构件34,74产生亚音速再循环区域30,76和落在整流罩内的冲击波。在再循环区上游40,82的先导燃料以化学计量燃烧。来自整流罩的排气38,86是声波的，产生冲击波，这促使在整流罩排气上游喷射的主燃料46,84点燃。

9. 发明授权

US4559628A Shear layer control in a free-vortex aerodynamic window 失效
标题翻译：自由涡旋空气动力学窗口中的剪切层控制
公开(公告)号：US4559628A
公开(公告)日：1985-12-17
申请号：US488838
申请日：1983-04-26
申请人： Bruce V. Johnson , Roy N. Guile
发明人： Bruce V. Johnson , Roy N. Guile
IPC分类号： H01S3/034 , H01S3/08
CPC分类号： H01S3/0343 , H01S3/034
摘要： A boundary-controlled aerodynamic window positioned adjacent the exit aperture of a gas laser is transparent to the laser beam emitted from the cavity of the laser. The boundary-controlled aerodynamic window is formed by a high velocity gas flow directed by a duct across the exit aperture for the laser beam isolating the low pressure region of the cavity from the high pressure of the atmosphere. The exit aperture is enlarged and an auxiliary gas flow injected along the sidewall of the duct adjacent the exit aperture to expand the thickness of the boundary layer. In a second embodiment, particulate matter is fixedly attached to the sidewall of the duct to increase the roughness of the wall surface. A third embodiment uses a plurality of nozzles, each injecting gas with a predetermined velocity.
摘要翻译：位于气体激光器出口孔附近的边界控制的空气动力学窗对从激光器腔发射的激光束是透明的。边界控制的空气动力学窗口由导管穿过出口孔的高速气流形成，用于将空腔的低压区域与大气压的高压隔离。出口孔被扩大，辅助气流沿着管道的侧壁与出口孔相邻地注入，以扩大边界层的厚度。在第二实施例中，颗粒物质固定地附接到管道的侧壁以增加壁表面的粗糙度。第三实施例使用多个喷嘴，每个喷嘴以预定的速度喷射气体。

10. 发明授权

US3973218A Single nozzle free-vortex aerodynamic window 失效
标题翻译：单喷嘴自由涡流气动窗
公开(公告)号：US3973218A
公开(公告)日：1976-08-03
申请号：US561021
申请日：1975-03-21
申请人： C. Edward Kepler , Roy N. Guile
发明人： C. Edward Kepler , Roy N. Guile
IPC分类号： H01S3/034 , H01S3/22 , G02B5/00
CPC分类号： H01S3/0343 , Y10T29/49432
摘要： A gas laser emits an output laser beam from a low pressure region to a region having a higher pressure. This is done through an opening in the side of a laser device. Under normal circumstances, the provision of such an opening would incur a flow of air from the high pressure side, externally of the laser device, to the low pressure side within the device. To prevent this, an aerodynamic window is placed in a passageway leading from said opening in the laser device through which the laser beam passes. A gas flow is passed across said passageway which will provide a flow which represents the flow of a segment of a free-vortex flow field having a pressure differential across the segment which is equal to that between the low and high pressure regions. A single nozzle, specifically contoured to produce a segment of a free-vortex flow field directs the gas into the passageway and an opening collects the flow onto the other side of said passageway. A method of constructing such a nozzle is set forth.
摘要翻译：气体激光器将输出激光束从低压区域发射到具有较高压力的区域。这是通过激光装置侧面的开口来实现的。在正常情况下，设置这样的开口会使空气从激光装置的外部的高压侧流向装置内的低压侧。为了防止这种情况，将空气动力学窗口放置在通过激光束通过的激光装置中的所述开口的通道中。气流通过所述通道，其将提供代表自由涡流场的段的流动的流动，所述自由涡流流场的横跨该段的压力差等于低压区域和高压区域之间的压力差。具体地形成为产生自由涡流流场的段的单个喷嘴将气体引导到通道中，并且开口将流体收集到所述通道的另一侧。阐述了构造这种喷嘴的方法。

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