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1. 发明授权

US07762058B2 Ultra-compact, high performance aerovortical rocket thruster 失效
标题翻译：超紧凑，高性能的航空火箭推进器
公开(公告)号：US07762058B2
公开(公告)日：2010-07-27
申请号：US11787585
申请日：2007-04-17
申请人： Robert J. Pederson , Stephen N. Schmotolocha
发明人： Robert J. Pederson , Stephen N. Schmotolocha
IPC分类号： F02K9/00
CPC分类号： F02K9/50 , F02K9/52 , F02K9/62 , F05D2250/25
摘要： An ultra-compact aerovortical swirl-enhanced combustion (ASC) system features an aerovortical swirl generator for use in rocket thrusters utilizing hypergolic or non-hypergolic propellants. The ACS thruster can be sized for diameters ranging from about 0.5 to about 2.0 inches, and producing thrust levels of approximately 5 lbf to about 250 lbf. A plurality of helicoid flow channels in the swirl generator introduces swirl into a flow stream of a first propellant within ultra-compact sized rocket thrusters. The ASC system also includes injectors for introducing a second liquid propellant into the swirling flowfield to promote rapid and efficient atomization, mixing and vigorous combustion, which, results in major improvements in combustion and propulsion performance over current rocket thrusters, but in much shorter combustor systems. Hence, the ultra-compact ASC system is a substantial improvement in small bipropellant chemical propulsion thrusters, which can be utilized in-space satellite, spacecraft maneuvering and attitude/orbit control.
摘要翻译：超紧凑型气涡旋增强燃烧（ASC）系统具有用于使用高压或非高压推进剂的火箭推进器的气涡旋发生器。 ACS推进器的尺寸可以从约0.5至约2.0英寸的尺寸，并产生约5lbf至约250lbf的推力水平。漩涡发生器中的多个螺旋流动通道将涡流引入到超小型火箭推进器内的第一推进剂的流动流中。 ASC系统还包括用于将第二液体推进剂引入旋流流场中的喷射器，以促进快速和有效的雾化，混合和剧烈燃烧，这导致燃烧和推进性能在现有火箭推进器上的主要改进，但在更短的燃烧室系统。因此，超小型ASC系统是小型双组分推进剂化学推进推进器的实质性改进，可用于太空中卫星，航天器操纵和姿态/轨道控制。

2. 发明授权

US07690192B2 Compact, high performance swirl combustion rocket engine 失效
标题翻译：紧凑，高性能的涡流燃烧火箭发动机
公开(公告)号：US07690192B2
公开(公告)日：2010-04-06
申请号：US11805016
申请日：2007-05-22
申请人： Robert J. Pederson , Stephen N. Schmotolocha
发明人： Robert J. Pederson , Stephen N. Schmotolocha
IPC分类号： F02K9/28
CPC分类号： F02K9/64 , F02K9/48 , F02K9/52
摘要： A rocket engine includes a combustor assembly for carrying out a combustion process of fuel and oxidizer rocket propellants to produce thrust. A swirl generator is positioned within the combustor assembly to produce a turbulent flowfield of the fuel and oxidizer rocket propellants within the combustor assembly.
摘要翻译：火箭发动机包括用于执行燃料和氧化剂火箭推进剂的燃烧过程以产生推力的燃烧器组件。涡流发生器定位在燃烧器组件内以产生燃烧器组件内的燃料和氧化剂火箭推进剂的湍流流场。

3. 发明授权

US06820411B2 Compact, lightweight high-performance lift thruster incorporating swirl-augmented oxidizer/fuel injection, mixing and combustion 有权
公开(公告)号：US06820411B2
公开(公告)日：2004-11-23
申请号：US10243961
申请日：2002-09-13
申请人： Robert J. Pederson , Stephen N. Schmotolocha , Donald H. Morris , Calvin Q. Morrison, Jr. , Raymond B. Edelman
发明人： Robert J. Pederson , Stephen N. Schmotolocha , Donald H. Morris , Calvin Q. Morrison, Jr. , Raymond B. Edelman
IPC分类号： F02K708
CPC分类号： F23R3/286 , F23C7/006 , F23C9/006 , F23C2900/09002 , F23R3/14 , F23R3/20 , F23R3/22 , Y02T50/675
摘要： An apparatus for providing propulsive power that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which the fuel is introduced. The swirl generator effects a toroidal outer recirculation zone and a central recirculation zone, which is positioned within the outer recirculation zone. These recirculation zones are configured in a backward-flowing manner that carries heat and combustion byproducts upstream where they are employed to continuously ignite a combustible fuel/oxidizer mixture in adjacent shear layers. The swirl generator is compatible with the throttle range of conventional gas turbine engines, provides smooth combustion with no instabilities and minimum total pressure losses, enables significant reductions the in L/D ratio of the combustor and is readily packaged into various applications. Other benefits include simplicity, reliability, wide flammability limits and high combustion efficiency/thrust performance. This concept is applicable to various propulsion systems such as such as ramjet missiles, combine cycle engines, gas turbine afterburners and energy conversion devices.

4. 发明授权

US06748735B2 Torch igniter 失效
标题翻译：火炬点火器
公开(公告)号：US06748735B2
公开(公告)日：2004-06-15
申请号：US10217972
申请日：2002-08-13
申请人： Stephen N. Schmotolocha , Donald H. Morris , Calvin Q. Morrison, Jr. , Robert J. Pederson
发明人： Stephen N. Schmotolocha , Donald H. Morris , Calvin Q. Morrison, Jr. , Robert J. Pederson
IPC分类号： F02C726
CPC分类号： F23Q13/00
摘要： An improved torch igniter for use in devices such as thrust augmenters, gas turbine engines, ramjets, combined-cycle engines and industrial burners. The torch igniter includes a housing with a combustion chamber. Fuel and oxidizer are delivered into the combustion chamber and ignited by an electronic ignition source, such as a plasma jet igniter or a spark igniter, so that an upstream recirculation zone and a downstream recirculation zone are created. The upstream recirculation zone stabilizes and pilots combustion within the combustion chamber, while the downstream recirculation zone augments the combustion event. Byproducts of the combustion event within the torch igniter provide a high mass flux with high thermal energy and strong ignition source radicals that are discharged through a neck portion of the housing and are thereafter employed to initiate a primary combustion event in a primary combustor.
摘要翻译：改进的用于诸如推力增强器，燃气涡轮发动机，压路机，联合循环发动机和工业燃烧器的装置中的割炬点火器。火炬点火器包括具有燃烧室的壳体。燃料和氧化剂被输送到燃烧室中，并被诸如等离子体喷射点火器或火花点火器的电子点火源点燃，从而产生上游再循环区域和下游再循环区域。上游再循环区域稳定并引导燃烧室内的燃烧，而下游再循环区增加燃烧事件。火炬点火器内的燃烧事件的副产物提供具有高热能的高质量通量和强烈的点火源自由基，其通过壳体的颈部部分排出，然后用于在初级燃烧器中引发初级燃烧事件。

5. 发明授权

US08800895B2 Piloted variable area fuel injector 有权
标题翻译：引航可变区域燃油喷射器
公开(公告)号：US08800895B2
公开(公告)日：2014-08-12
申请号：US12199376
申请日：2008-08-27
申请人： Paul G. Hicks , Robert J. Pederson
发明人： Paul G. Hicks , Robert J. Pederson
IPC分类号： B05B1/00 , F02M1/00 , F02M69/00
CPC分类号： B05B1/00 , F02M1/00 , F02M69/00 , F23D11/38 , F23D2900/00003
摘要： An improved fuel injection apparatus and method have a variable area injector arrangement in which a pintle defines a pilot orifice extending through a tip of the pintle for supplying a pilot flow of fuel through the fuel injector at low fuel pressures, and in particular when the pintle tip is sealed against a variable flow orifice of the variable area injector arrangement.
摘要翻译：改进的燃料喷射装置和方法具有可变区域喷射器装置，其中枢轴限定延伸穿过枢轴的尖端的先导孔口，用于以低燃料压力供应燃料的先导流通过燃料喷射器，特别是当枢栓尖端密封在可变面积喷射器装置的可变流量孔口上。

6. 发明授权

US07762077B2 Single-stage hypersonic vehicle featuring advanced swirl combustion 失效
标题翻译：具有先进旋流燃烧的单级超音速车
公开(公告)号：US07762077B2
公开(公告)日：2010-07-27
申请号：US11633836
申请日：2006-12-05
申请人： Robert J. Pederson , Stephen N. Schmotolocha , William W. Follett
发明人： Robert J. Pederson , Stephen N. Schmotolocha , William W. Follett
IPC分类号： F02K7/08
CPC分类号： B64C30/00 , B64D33/02 , B64D33/04 , B64D2033/026 , F02K7/14 , F02K7/16 , F02K7/18 , Y02T50/671
摘要： A single-stage hypersonic vehicle is comprised of a low-speed and a high-speed propulsion system. The low-speed propulsion system propels the single-stage vehicle to a threshold velocity, after which the high-speed propulsion system then takes over. The low-speed propulsion system includes a combined-cycle engine featuring a swirl generator that is integrated into a turbojet engine to provide a compact turbojet and swirl afterburner-ramjet propulsion system. The high-speed propulsion system includes a hypersonic engine that is operable at the threshold takeover velocity and beyond. In various embodiments, the high-speed propulsion system comprises a scramjet, rocket, or scramjet/rocket engine depending requirements. Benefits of the swirl generator design include its ability to rapidly and efficiently atomize, vaporize, mix and burn the fuel and oxidizer for the low speed propulsion system, significantly reduce length, weight, cooling requirements and complexity for both propulsion systems, while maintaining high propulsion performance and reducing propulsion and launch costs.
摘要翻译：单级超音速车辆由低速和高速推进系统组成。低速推进系统推动单级车辆达到阈值速度，此后高速推进系统接管。低速推进系统包括一个组合循环发动机，其特征在于涡轮发生器被集成到涡轮喷气发动机中，以提供紧凑的涡轮喷气和涡流后燃烧器 - 冲压喷气推进系统。该高速推进系统包括一个超音速发动机，其可以以阈值收购速度和超出速度操作。在各种实施例中，高速推进系统包括依照要求的冲压喷气发动机，火箭或冲击式/火箭发动机。涡流发生器设计的优点包括其快速有效地雾化，蒸发，混合和燃烧低速推进系统的燃料和氧化剂的能力，显着降低推进系统的长度，重量，冷却要求和复杂性，同时保持高推进性能和减少推进和发射成本。

7. 发明申请

US20080256925A1 Compact, high performance swirl combustion rocket engine 失效
标题翻译：紧凑，高性能的涡流燃烧火箭发动机
公开(公告)号：US20080256925A1
公开(公告)日：2008-10-23
申请号：US11805016
申请日：2007-05-22
申请人： Robert J. Pederson , Stephen N. Schmotolocha
发明人： Robert J. Pederson , Stephen N. Schmotolocha
IPC分类号： F02K9/00
CPC分类号： F02K9/64 , F02K9/48 , F02K9/52
摘要： A compact rocket engine with advanced swirl combustion can generate vacuum thrust in the 500 lbf to 100,000 lbf range. The rocket engine includes a feed system, combustor assembly, swirl generator and nozzle. The feed system delivers the oxidizer and fuel to the combustor assembly in the proper phase suitable for use with the swirl generator, which is positioned within the combustor assembly. This causes a highly turbulent three-dimensional swirling flowfield produced for rapid and efficient mixing and burning of the fuel/oxidizer combustion products, which are expanded through the nozzle to produce thrust. The aerothermochemical processes are extremely efficient, and consequently produce nearly ideal thrust levels. Swirl enhanced combustion significantly reduces combustor length, weight, complexity and cost, yet provides high propulsion efficiencies and wide rocket engine throttling operability. In one embodiment, the rocket engine is integrated into a dual-throat, expansion/deflection rocket engine to provide deep throttleability with high Isp.
摘要翻译：具有先进旋流燃烧的紧凑型火箭发动机可以在500磅/分钟至100,000磅/分的范围内产生真空推力。火箭发动机包括进料系统，燃烧器组件，涡流发生器和喷嘴。进料系统将氧化剂和燃料以合适的相位输送到燃烧器组件，该适当的相适用于位于燃烧器组件内的涡流发生器。这导致产生高度湍流的三维旋流流场，用于快速和有效地混合和燃烧燃料/氧化剂燃烧产物，其通过喷嘴膨胀以产生推力。空气热化学过程非常有效，因此产生几乎理想的推力水平。涡流增强燃烧显着降低燃烧器长度，重量，复杂性和成本，但提供高推进效率和广泛的火箭发动机节流可操作性。在一个实施例中，火箭发动机被集成到双喉，膨胀/偏转火箭发动机中，以提供具有高Isp的深度节流性。

8. 发明申请

US20080128547A1 Two-stage hypersonic vehicle featuring advanced swirl combustion 审中-公开
标题翻译：两级超音速车辆具有先进的涡流燃烧
公开(公告)号：US20080128547A1
公开(公告)日：2008-06-05
申请号：US11633837
申请日：2006-12-05
申请人： Robert J. Pederson , Stephen N. Schmotolocha , William W. Follett
发明人： Robert J. Pederson , Stephen N. Schmotolocha , William W. Follett
IPC分类号： B64D27/02 , F02K7/10 , B64D27/16 , B64D27/10 , F02K3/10
CPC分类号： B64C30/00 , F02K7/14 , F02K7/16 , F02K7/18 , F05D2220/80 , F23R3/16 , F23R3/20 , Y02T50/671
摘要： The present invention is directed toward a two-stage hypersonic vehicle, comprising a first-stage vehicle and a second stage vehicle. The first-stage vehicle includes a combined-cycle engine and a swirl generator for propelling the first-stage vehicle and the second-stage vehicle to a threshold velocity, which in one embodiment is about Mach 6. In one embodiment, the first-stage combined-cycle engine integrates a swirl generator into a gas turbine engine, providing a highly compact afterburner and a ramjet engine within the gas turbine engine. One benefit of the integrated swirl generator is the ability to significantly reduce overall first-stage gas turbine and afterburner-ramjet size and weight, while retaining high performance. The second-stage vehicle is detachably secured to the first-stage vehicle and includes a hypersonic engine. In various embodiments, the hypersonic engine may comprise one of the following engine configurations: scramjet, rocket, or scramjet/rocket depending on the mission profile and requirements.
摘要翻译：本发明涉及一种包括第一级车辆和第二级车辆的两级超音速车辆。第一级车辆包括联合循环发动机和用于将第一级车辆和第二级车辆推进到阈值速度的旋转发生器，在一个实施例中，该阈值速度约为马赫数6.在一个实施例中，第一级车辆联合循环发动机将涡流发生器集成到燃气涡轮发动机中，在燃气涡轮发动机内提供高度紧凑的加力燃烧器和冲压喷气发动机。集成涡流发电机的一个好处是能够在保持高性能的同时显着降低整体的第一级燃气轮机和后燃机冲压喷气机的尺寸和重量。第二级车辆可拆卸地固定到第一级车辆并且包括超音速发动机。在各种实施例中，超音速发动机可以包括以下发动机配置之一：取决于任务简档和要求的冲压喷气发动机，火箭或冲击式喷气式火箭/火箭。

9. 发明授权

US07137255B2 Compact swirl augmented afterburners for gas turbine engines 有权
标题翻译：燃气涡轮发动机紧凑型漩涡增强后燃烧器
公开(公告)号：US07137255B2
公开(公告)日：2006-11-21
申请号：US11095647
申请日：2005-03-31
申请人： Stephen N Schmotolocha , Donald H Morris , Robert J Pederson , Raymond B Edelman , Calvin Q Morrison, Jr.
发明人： Stephen N Schmotolocha , Donald H Morris , Robert J Pederson , Raymond B Edelman , Calvin Q Morrison, Jr.
IPC分类号： F02K3/10 , F02K3/105
CPC分类号： F23R3/286 , F02K3/10 , F23C7/006 , F23C9/006 , F23C2900/07001 , F23C2900/09002 , F23R3/14 , F23R3/20 , F23R3/22 , Y02T50/672 , Y02T50/675
摘要： An afterburner apparatus that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel and an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which the fuel is introduced. The swirl generator effects a toroidal outer recirculation zone and a central recirculation zone, which is positioned within the outer recirculation zone. These recirculation zones are configured in a backward-flowing manner that carries heat and combustion byproducts upstream where they are employed to continuously ignite a combustible fuel/oxidizer mixture in adjacent shear layers. The recirculation zones accelerate flame propagation to allow afterburning to be completed in a relatively short length. Inherent with this swirl afterburner concept are design compactness, light weight, lower cost, smooth and efficient combustion, high thrust output, wide flammability limits, continuous operation at stoichiometric fuel/oxidizer mixture ratios, no combustion instabilities, and relatively low pressure losses.
摘要翻译：一种后燃器装置，其利用新颖的涡流发生器，根据需要快速有效地雾化，蒸发并混合燃料和氧化剂。涡流发生器将氧化剂流转化为引入燃料的湍流三维流场。涡流发生器实现环形外部再循环区域和位于外部再循环区域内的中央再循环区域。这些再循环区域被构造成向后流动的方式，其将上游的热和燃烧副产物用于上游，以连续地点燃相邻剪切层中的可燃燃料/氧化剂混合物。再循环区域加速火焰传播，以允许在相对短的长度内完成后燃烧。这种涡流加热器概念的设计紧凑，重量轻，成本低，燃烧平稳有效，推力输出高，易燃性极限，化学计量燃料/氧化剂混合比连续运行，无燃烧不稳定性和相对较低的压力损失。

10. 发明授权

US4664631A Surrogate weapon for weapons effects signatures 失效
标题翻译：替代武器武器影响签名
公开(公告)号：US4664631A
公开(公告)日：1987-05-12
申请号：US793671
申请日：1985-10-31
申请人： Robert J. Pederson , Lawrence J. Gallagher , Jack V. Miller , Lauren B. Althaus , Benjamin Rubinstein , Stephen N. Schomotolocha
发明人： Robert J. Pederson , Lawrence J. Gallagher , Jack V. Miller , Lauren B. Althaus , Benjamin Rubinstein , Stephen N. Schomotolocha
IPC分类号： F41A1/04 , F41A33/04 , F41F27/00 , F41F1/04
CPC分类号： F41A1/04 , F41A33/04
摘要： The invention comprises a surrogate weapon for simulating the sound and flash of gunfire having a combustion chamber system in which a primary chamber is an elongated cavity, having a proximal end closed with a head and an open distal end. A combustible mixture is injected via electronically timed hydrocarbon fuel and oxidizer pulses into the combustion chamber near the closed end through an annular injector having a plurality of spaced apart fuel and oxidizer nozzles. The fuel nozzles are axially spaced from the oxidizer nozzles and are closer to the head. Thus the injected fuel/oxidizer charge is stratified with a fuel concentration distribution preferentially being richer at an ignition source near the head. The open distal end of the combustion chamber is in the form of an annular convergent nozzle which also comprises the proximal end of a secondary chamber that is acoustically tuned and provided at its open distal end with an annular muzzle having a cross-sectional shape capable of controlling the fundamental frequency and modifying tuned frequency overtones of the acoustic signature.One embodiment provides the fuel nozzles as a plurality of radial grooves on the proximal side of a generally flat plate transverse to the primary combustion chamber cavity and having an aperture therethrough, the aperture being flush with the inner surface of the combustion chamber cavity, and also providing oxidizer nozzles as a plurality of radial grooves on the distal side of the flat plate.
摘要翻译：本发明包括用于模拟具有燃烧室系统的炮火的声音和闪光的替代武器，其中主腔室是细长空腔，其具有用头部和敞开的远端封闭的近端。可燃混合物通过电子定时的碳氢化合物燃料和氧化剂脉冲通过具有多个间隔开的燃料和氧化剂喷嘴的环形喷射器注入到封闭端附近的燃烧室中。燃料喷嘴与氧化剂喷嘴轴向间隔开并且更靠近头部。因此，喷射的燃料/氧化剂装料分层，其燃料浓度分布优先在头部附近的点火源处更富。燃烧室的开口远端为环形会聚喷嘴的形式，该喷嘴还包括二级腔室的近端，该二级腔室的近端在其开口的远端具有环形口，该环形枪口具有能够控制基频并修改声学特征的调谐频率泛音。一个实施例将燃料喷嘴提供为在与主燃烧室腔横向的大致平板的近侧上的多个径向槽，并且具有穿过其中的孔，该孔与燃烧室腔的内表面齐平，并且还提供氧化剂喷嘴作为平板的远侧上的多个径向槽。

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