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1. 发明申请

US20080060361A1 Multi-height ramp injector scramjet combustor 审中-公开
标题翻译：多高斜坡喷油器冲压燃烧器
公开(公告)号：US20080060361A1
公开(公告)日：2008-03-13
申请号：US11517019
申请日：2006-09-07
申请人： Calvin Q. Morrison , Raymond B. Edelman
发明人： Calvin Q. Morrison , Raymond B. Edelman
IPC分类号： F02K7/10
CPC分类号： F02K7/10 , Y02T50/671
摘要： A multi-height ramp injection system, for use in a supersonic propulsion system, comprises a plurality of multi-height ramp injectors for variably introducing a fuel into an airflow in a combustor. In one embodiment of the invention, the multi-height ramp injectors comprise a plurality of tall injectors for fueling an inner portion of the airflow, and a plurality of short injectors for fueling an outer portion of the airflow.
摘要翻译：用于超音速推进系统的多高度坡道喷射系统包括用于将燃料可变地引入燃烧器中的气流中的多个多高度斜坡喷射器。在本发明的一个实施例中，多高度斜坡喷射器包括多个用于对气流的内部部分进行燃料喷射的高喷射器，以及多个用于对空气流的外部部分进行燃料喷射的短喷射器。

2. 发明授权

US06968695B2 Compact lightweight ramjet engines incorporating swirl augmented combustion with improved performance 有权
标题翻译：紧凑型轻型冲压喷气发动机，结合旋转增强燃烧，性能提高
公开(公告)号：US06968695B2
公开(公告)日：2005-11-29
申请号：US10360469
申请日：2003-02-06
申请人： Stephen N. Schmotolocha , Robert J. Pederson , Calvin Q. Morrison, Jr. , Raymond B. Edelman , Donald H. Morris
发明人： Stephen N. Schmotolocha , Robert J. Pederson , Calvin Q. Morrison, Jr. , Raymond B. Edelman , Donald H. Morris
IPC分类号： F23C7/00 , F23C9/00 , F23R3/14 , F23R3/20 , F23R3/22 , F23R3/28 , F02K7/10 , F02K7/14
CPC分类号： F23C7/006 , F23C9/006 , F23C2900/09002 , F23R3/14 , F23R3/20 , F23R3/22 , F23R3/286 , Y02T50/675
摘要： A ramjet powered device 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 an inner central recirculation zone, both of which 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 and stabilizes flame propagation and accelerates combustion throughout the entire combustor. The swirl generator provides smooth combustion with no instabilities and minimum total pressure losses and enables significant reductions in the L/D ratio of the combustor. Other benefits include simplicity, reliability, wide flammability limits and high combustion efficiency and thrust performance.
摘要翻译：一种冲压喷气发动装置，其利用新颖的涡流发生器，根据需要快速有效地雾化，蒸发并将燃料混合到氧化剂中。涡流发生器将氧化剂流转化为引入燃料的湍流三维流场。涡流发生器影响环形外再循环区域和内中心再循环区域，两者都以向后流动的方式构造，其将热和燃烧副产物运送到上游，在其上用于连续点燃相邻剪切中的可燃燃料/氧化剂混合物层并稳定火焰传播并加速整个燃烧室的燃烧。涡流发生器提供平稳的燃烧，没有不稳定性和最小的总压力损失，并且能够显着降低燃烧器的L / D比。其他优点包括简单性，可靠性，广泛的可燃性极限和高燃烧效率和推力性能。

3. 发明授权

US06907724B2 Combined cycle engines incorporating swirl augmented combustion for reduced volume and weight and improved performance 失效
标题翻译：组合式循环发动机采用涡流增压燃烧，减少体积和重量，提高性能
公开(公告)号：US06907724B2
公开(公告)日：2005-06-21
申请号：US10360168
申请日：2003-02-06
申请人： Raymond B. Edelman , Calvin Q. Morrison, Jr. , Robert J. Pederson , Donald H. Morris , Stephen N. Schmotolocha
发明人： Raymond B. Edelman , Calvin Q. Morrison, Jr. , Robert J. Pederson , Donald H. Morris , Stephen N. Schmotolocha
IPC分类号： B64D27/20 , F02C7/042 , F02K7/16 , F02K7/18 , F23C7/00 , F23C9/00 , F23R3/14 , F23R3/20 , F23R3/22 , F23R3/28
CPC分类号： F23C7/006 , F02K7/16 , F02K7/18 , F23C9/006 , F23C2900/09002 , F23R3/14 , F23R3/20 , F23R3/22 , F23R3/286 , Y02T50/672 , Y02T50/675
摘要： A combined-cycle engine having at least one core engine and at least one ramjet engine. The ramjet 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 an inner central recirculation zone, both of which 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, which accelerate flame propagation throughout the core flowfield. The swirl generator provides smooth combustion with no instabilities and minimum total pressure losses and enables significant reductions in the L/D ratio of the combustor. Other benefits include simplicity, reliability, wide flammability limits, high combustion efficiency and high specific thrust performance.
摘要翻译：具有至少一个核心发动机和至少一个冲压喷气发动机的联合循环发动机。冲压喷气发动机利用新颖的涡流发生器，根据需要快速有效地雾化，蒸发，并将燃料混合到氧化剂中。涡流发生器将氧化剂流转化为引入燃料的湍流三维流场。涡流发生器影响环形外再循环区域和内中心再循环区域，两者都以向后流动的方式构造，其将热和燃烧副产物运送到上游，在其上用于连续点燃相邻剪切中的可燃燃料/氧化剂混合物层，其加速贯穿核心流场的火焰传播。涡流发生器提供平稳的燃烧，没有不稳定性和最小的总压力损失，并且能够显着降低燃烧器的L / D比。其他优点包括简单性，可靠性，广泛的可燃性极限，高燃烧效率和高比推力性能。

4. 发明申请

US20110174262A1 ROTARY ENGINE WITH EXHAUST GAS SUPPLEMENTAL COMPOUNDING 失效
标题翻译：具有排气补充组合的旋转发动机
公开(公告)号：US20110174262A1
公开(公告)日：2011-07-21
申请号：US13120468
申请日：2009-10-08
申请人： Mark David Horn , Glenn L. Havskjold , Calvin Q. Morrison, JR.
发明人： Mark David Horn , Glenn L. Havskjold , Calvin Q. Morrison, JR.
IPC分类号： F02B53/08
CPC分类号： F02B55/16 , F01C1/22 , F02B53/04 , F02B53/08 , F02B2053/005 , F02M26/11 , F02M26/41 , Y02T10/17
摘要： A rotary engine which provides a supplemental phase of compression between a first phase of compression and a second phase of compression.
摘要翻译：一种旋转发动机，其在第一压缩阶段和第二压缩阶段之间提供压缩的补充阶段。

5. 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.

6. 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。

7. 发明授权

US08689764B2 Rotary engine with exhaust gas supplemental compounding 失效
标题翻译：带排气的旋转发动机补充
公开(公告)号：US08689764B2
公开(公告)日：2014-04-08
申请号：US13120468
申请日：2009-10-08
申请人： Mark David Horn , Glenn L. Havskjold , Calvin Q. Morrison, Jr.
发明人： Mark David Horn , Glenn L. Havskjold , Calvin Q. Morrison, Jr.
IPC分类号： F02B53/08 , F02B53/04 , F02B53/00
CPC分类号： F02B55/16 , F01C1/22 , F02B53/04 , F02B53/08 , F02B2053/005 , F02M26/11 , F02M26/41 , Y02T10/17
摘要： A rotary engine which provides a supplemental phase of compression between a first phase of compression and a second phase of compression.
摘要翻译：一种旋转发动机，其在第一压缩阶段和第二压缩阶段之间提供压缩的补充阶段。

8. 发明申请

US20080098741A1 Annular isolator dual mode scramjet engine 审中-公开
标题翻译：环形隔离器双模式喷气发动机
公开(公告)号：US20080098741A1
公开(公告)日：2008-05-01
申请号：US11586074
申请日：2006-10-25
申请人： William W. Follett , Allen Lewis Goldman , Calvin Q. Morrison , Raymond B. Edelman
发明人： William W. Follett , Allen Lewis Goldman , Calvin Q. Morrison , Raymond B. Edelman
IPC分类号： F02K7/10
CPC分类号： F02K7/14 , F02K7/10 , F05D2250/232 , F05D2250/41 , Y02T50/671
摘要： A dual mode scramjet engine has an isolator that serves to minimize combustor influence on inlet operation, a combustor for operation in both ramjet and scramjet mode, and a centerbody positioned within the isolator. The centerbody has an end at an entrance to the combustor.
摘要翻译：双模式冲压喷气发动机具有隔离器，其用于使燃烧器对入口操作的影响最小化，用于在冲压喷气和冲压喷射模式下操作的燃烧器和位于隔离器内的中心体。中心体在燃烧室入口处有一端。

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. 发明申请

US20080141972A1 Rotors having flow-modifying members for use in rotary engines 审中-公开
标题翻译：具有用于旋转发动机的流动修正构件的转子
公开(公告)号：US20080141972A1
公开(公告)日：2008-06-19
申请号：US11999280
申请日：2007-12-05
申请人： Calvin Q. Morrison , Glenn L. Havskjold
发明人： Calvin Q. Morrison , Glenn L. Havskjold
IPC分类号： F02B53/00 , F01C1/00
CPC分类号： F02B55/02 , F01C1/22 , F01C21/08 , Y02T10/17
摘要： A rotor for use in a rotary internal combustion engine comprises an opening configured to receive an output shaft, a plurality of faces disposed circumferentially around the opening, a recessed pocket disposed in one of the faces, and a flow-modifying member secured to the one face. The flow-modifying member modifies fuel/air flow within the recessed pocket, and controls fuel/air mixing in a combustion chamber adjacent the recessed pocket.
摘要翻译：一种用于旋转内燃机的转子包括一个开口，该开口被构造成容纳一个输出轴，围绕开口周向设置的多个面，一个位于其中一个面上的凹陷凹槽，以及一个固定在一个表面上的流动修改构件面对。流动修正构件改变凹槽内的燃料/空气流动，并控制邻近凹槽的燃烧室中的燃料/空气混合。

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