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1. 发明申请

WO2009123770A3 PROPULSION SYSTEM WITH MOVABLE THERMAL CHOKE 审中-公开
公开(公告)号：WO2009123770A3
公开(公告)日：2009-10-08
申请号：PCT/US2009/030185
申请日：2009-01-06
申请人： AEROJET-GENERAL CORPORATION , BULMAN, Melvin, J.
发明人： BULMAN, Melvin, J.
IPC分类号： B63H25/46
摘要： High thrust at sea level and high Isp at high altitudes with low ambient pressure are obtained in a vehicle with an engine of fixed geometry including an exit of non-changing cross section, by incorporating a series of propellant injectors in a divergent section of the engine, spaced apart along the engine axis at points of different engine cross section. At takeoff, the injectors at sites with a large cross section are used, and as the vehicle climbs, these injectors are successively closed leaving injectors activated at sites of successively smaller cross sections. The injectors establish thermal choke points, and the area ratio of the cross section at the exit to the cross section at the thermal choke point thus increases as the vehicle climbs from low to high altitudes.

2. 发明申请

WO2008076318A2 COMBINED CYCLE INTEGRATED COMBUSTOR AND NOZZLE SYSTEM 审中-公开
标题翻译：组合式循环混合气体和喷嘴系统
公开(公告)号：WO2008076318A2
公开(公告)日：2008-06-26
申请号：PCT/US2007/025522
申请日：2007-12-12
申请人： AEROJET-GENERAL CORPORATION , BULMAN, Melvin, J.
发明人： BULMAN, Melvin, J.
IPC分类号： F02K7/08
CPC分类号： F02K7/18 , F02K7/10 , F02K7/14 , F02K7/16 , F05D2220/10 , Y02T50/67
摘要： An engine (20) that operates and produces the entire required vehicle thrust below Mach 4 is useful for a Hypersonic combined cycle vehicle by saving vehicle and engine development costs. One such engine (20) is a combined cycle engine having both a booster (30) and a dual mode ramjet (DMRJ). The booster (30) and the DMRJ are integrated to provide effective thrust from Mach 0 to in excess of Mach 4. As the booster (30) accelerates the vehicle from Mach 0 to in excess of Mach 4, from Mach 0 to about Mach 2 incoming air (28) delivered to the DMRJ is accelerated by primary ejector thrusters (34) that may receive oxidizer from either on-board oxidizer tanks (31) or from booster (30) compressor discharge air. As the Combined Cycle Engine further accelerates the vehicle from about Mach 0 to in excess of Mach 4 exhaust from the booster (30) and exhaust from the DMRJ are combined in a common nozzle (42) disposed downstream of a combustor portion (32) of said DMRJ functioning as an aerodynamic choke.
摘要翻译：通过节省车辆和发动机开发成本，在Hypersonic联合循环车辆上操作并产生整个所需车辆推力的发动机（20）在Mach4以下。一个这样的发动机（20）是具有增压器（30）和双模式冲压喷气发动机（DMRJ）的组合循环发动机。增压器（30）和DMRJ被一体化以提供从马赫0到超过马赫数4的有效推力。随着助力器（30）将车辆从马赫0加速到超过马赫数4，从马赫0到大约马赫数2 传送到DMRJ的进入空气（28）通过可从车载氧化剂罐（31）或增压器（30）压缩机排出空气接收氧化剂的主喷射推进器（34）加速。当组合循环发动机进一步将车辆从大约马赫0加速到来自增压器（30）的超过马赫4排气时，并且来自DMRJ的排气被组合在设置在燃烧器部分（32）的下游的公共喷嘴（42）中， DMRJ表现为空气动力学扼流圈。

3. 发明申请

WO2010048194A3 SUPERCONDUCTING POWER AND TRANSPORT SYSTEM 审中-公开
标题翻译：超导电力和运输系统
公开(公告)号：WO2010048194A3
公开(公告)日：2010-07-15
申请号：PCT/US2009061340
申请日：2009-10-20
申请人： METADIGM LLC , KLEY VICTOR B , BULMAN MELVIN J
发明人： KLEY VICTOR B , BULMAN MELVIN J
IPC分类号： B60L13/10
CPC分类号： B60L13/10 , B60L2200/26 , B61B1/00 , B61B13/08 , B61B13/10 , B61C3/00 , B61K13/00 , G06Q50/165 , Y02T30/30
摘要： A transport and power system having a plurality of tubes or tunnels, a magnetic levitation and linear motor train, and a superconducting power cable. One of the tubes can be an escape, power distribution, and maintenance tunnel. These tubes can be above ground, below ground, at ground, or under water.
摘要翻译：具有多个管或隧道，磁悬浮和线性动力传动系以及超导电缆的运输和动力系统。其中一个管可以是逃生，配电和维护隧道。这些管可以在地上，地下，地面或水下。

4. 发明申请

WO2006057653A2 INTEGRATED AIR INLET SYSTEM FOR MULTI-PROPULSION AIRCRAFT ENGINES 审中-公开
标题翻译：用于多推进飞机发动机的集成空气入口系统
公开(公告)号：WO2006057653A2
公开(公告)日：2006-06-01
申请号：PCT/US2005/004893
申请日：2005-02-16
申请人： AEROJET-GENERAL CORPORATION , BULMAN, Melvin, J. , BILLIG, Frederick, S.
发明人： BULMAN, Melvin, J. , BILLIG, Frederick, S.
IPC分类号： F02K9/78
CPC分类号： F02K7/10 , B64C30/00 , B64D33/02 , F02C7/042 , F02K7/14 , F02K7/16 , F02K9/18 , F05D2220/34 , Y10T137/0536
摘要： An air inlet duct for an air-breathing combined-cycle aircraft engines is internally divided into separate channels for low-speed and high-speed components of the engine, and contains one or more movable panels that are fully contained within the duct and pivotal between an open position in which incoming air is directed to both channels and a closed position in which all incoming air is directed to the channel leading to the high-speed engine. This integrated duct utilizes all incoming air at all stages of flight with no change in either the geometry of the air capture portion of the engine or the engine itself, and no exposure of movable leading edges. The result is a minimum of shock waves and a high degree of efficiency in operation of the engine.
摘要翻译：用于空气呼吸联合循环飞机发动机的空气入口管道被内部分成用于发动机的低速和高速部件的单独的通道，并且包含一个或多个完全容纳在管道内的可移动的面板，并且枢转地在进入的空气被引导到两个通道的打开位置和其中所有进入的空气被引导到通向高速发动机的通道的关闭位置。这种集成的管道在飞行的所有阶段都使用所有进入的空气，而不改变发动机或发动机本身的空气捕获部分的几何形状，也不会使可动的前缘暴露。结果是最小的冲击波和发动机运转的高效率。

5. 发明申请

WO2008076318A3 COMBINED CYCLE INTEGRATED COMBUSTOR AND NOZZLE SYSTEM 审中-公开
标题翻译：组合式循环混合气体和喷嘴系统
公开(公告)号：WO2008076318A3
公开(公告)日：2008-10-09
申请号：PCT/US2007025522
申请日：2007-12-12
申请人： AEROJET GENERAL CO , BULMAN MELVIN J
发明人： BULMAN MELVIN J
IPC分类号： F02K7/08
CPC分类号： F02K7/18 , F02K7/10 , F02K7/14 , F02K7/16 , F05D2220/10 , Y02T50/67
摘要： An engine (20) that operates and produces the entire required vehicle thrust below Mach 4 is useful for a Hypersonic combined cycle vehicle by saving vehicle and engine development costs. One such engine (20) is a combined cycle engine having both a booster (30) and a dual mode ramjet (DMRJ). The booster (30) and the DMRJ are integrated to provide effective thrust from Mach 0 to in excess of Mach 4. As the booster (30) accelerates the vehicle from Mach 0 to in excess of Mach 4, from Mach 0 to about Mach 2 incoming air (28) delivered to the DMRJ is accelerated by primary ejector thrusters (34) that may receive oxidizer from either on-board oxidizer tanks (31 ) or from booster (30) compressor discharge air.
摘要翻译：通过节省车辆和发动机开发成本，在Hypersonic联合循环车辆上操作并产生整个所需车辆推力的发动机（20）在Mach4以下。一个这样的发动机（20）是具有增压器（30）和双模式冲压喷气发动机（DMRJ）的组合循环发动机。增压器（30）和DMRJ被一体化以提供从马赫0到超过马赫数4的有效推力。随着助力器（30）将车辆从马赫0加速到超过马赫数4，从马赫0到大约马赫数2 传送到DMRJ的进入空气（28）通过可从车载氧化剂罐（31）或增压器（30）压缩机排出空气接收氧化剂的主喷射推进器（34）加速。

6. 发明申请

WO2008091307A2 CORE BURNING FOR SCRAMJET ENGINES 审中-公开
公开(公告)号：WO2008091307A2
公开(公告)日：2008-07-31
申请号：PCT/US2007/022058
申请日：2007-10-15
申请人： AEROJET-GENERAL CORPORATION , BULMAN, Melvin, J.
发明人： BULMAN, Melvin, J.
IPC分类号： B64G1/40
CPC分类号： F02K7/10
摘要： A pilot for a scramjet provides a flame front 28 whose arrival at the wall of the scramjet combustor 18 is delayed thereby reducing combustor 18 heat load. By combining in-stream injection of fuel 19 with an interior pilot and a lean (fuel-poor) outer annulus, the bulk of combustion is confined to the scramjet combustor 18 center. This concept, referred to as "core-burning," further reduces combustor 18 heat load. One such pilot is for a two dimensional scramjet 40 effective to propel a vehicle. This pilot includes a plurality of spaced apart struts 44 separated by ducts and a strut pilot 43 contained within each strut 44. A second such pilot is for an axisymmetric scramjet engine has, in sequence and in fluid communication, an air intake 16, an open bore scramjet isolator 50 and a scramjet combustor 18. This centerbody pilot pod includes a pilot isolator 50 disposed between the air intake 16 and a pilot diffuser 52, the pilot diffuser 52 disposed between the pilot isolator 50 and a pilot 54 with the pilot 54 disposed between the pilot diffuser 52 and a pilot combustor 56. The pilot pod is in axis symmetry around a central axis of the scramjet isolator and supported by a plurality of struts 44 extending from an inner wall of the open bore to an outer surface of the centerbody pilot pod.
摘要翻译：用于冲击式喷气发动机的飞行员提供了一个火焰前沿28，其到达喷气式燃烧器18的壁处的延迟，从而减少燃烧器18的热负荷。通过将燃料19的内流喷射与内部先导和贫（燃料不足）的外环结合在一起，大部分燃烧被限制在冲击式喷射燃烧器18的中心。这种被称为“燃烧燃烧”的概念进一步减少燃烧器18的热负荷。一个这样的飞行员是用于有效地推动车辆的二维冲击喷射器40。这个飞行员包括多个间隔开的支柱44，这些支柱44被管道分隔开，并且支柱导引器43包含在每个支柱44内。第二个这样的导向装置用于轴对称冲击式喷气发动机，依次和流体连通地具有进气口16，该中心体导向舱包括设置在进气口16和先导扩散器52之间的先导隔离器50，设置在先导隔离器50和先导式离合器50之间的引燃扩散器52，其中飞行员54设置在引燃扩散器52和引燃燃烧器56之间。引导舱围绕着冲击式隔离器的中心轴线对称，并由多个从开孔的内壁延伸到中心体的外表面的支柱44支撑飞行员舱

7. 发明申请

WO2007033043A3 THRUST AUGMENTATION IN PLUG NOZZLES AND EXPANSION-DEFLECTION NOZZLES 审中-公开
公开(公告)号：WO2007033043A3
公开(公告)日：2007-03-22
申请号：PCT/US2006/035218
申请日：2006-09-08
申请人： AEROJET-GENERAL CORPORATION , LAUSTEN, Merlyn , BULMAN, Melvin, J.
发明人： LAUSTEN, Merlyn , BULMAN, Melvin, J.
IPC分类号： F02K9/62
摘要： Thrust augmentation in a rocket nozzle is achieved by incorporating injectors for the introduction of unburnt fuel and oxidizer into a nozzle to combust in the nozzle and thereby supplement the primary thrust that is supplied by fuel and oxidizer that are combusted prior to entry into the nozzle. These secondary injectors are incorporated into the design of expansion-deflection nozzles and plug nozzles. In expansion-deflection nozzles, the injectors are either in the flow deflector itself or in the wall of the divergent section of the nozzle. In plug nozzles, the injectors are either in a shell of the nozzle surrounding the forward end of the centerbody or in the centerbody itself.

8. 发明申请

WO2009142674A1 ROCKET NOZZLES FOR UNCONVENTIONAL VEHICLES 审中-公开
标题翻译：用于非常规车辆的ROCKET喷嘴
公开(公告)号：WO2009142674A1
公开(公告)日：2009-11-26
申请号：PCT/US2009/001132
申请日：2009-02-23
申请人： AEROJET-GENERAL CORPORATION , BULMAN, Melvin, J.
发明人： BULMAN, Melvin, J.
IPC分类号： F02K1/00
CPC分类号： F02K9/88
摘要： Improved rocket nozzle (110) designs for vehicles with nozzles (110) embedded in or protruding from surfaces remote from the desired thrust axis (47). The nozzle (110) configurations are for rocket vehicles where the nozzles (110) are not located at the optimal thrust axis (47) of the vehicle. Two examples include nozzles (110) located on the forward end of the vehicle (also called tractor nozzles) and attitude control nozzles located on the periphery of the vehicle. More particularly, the disclosed nozzle (110) shapes enhance the axial thrusts (56) and/or maneuver torques on the vehicle. These unconventional nozzle (110) shapes improve vehicle performance.
摘要翻译：改进的火箭喷嘴（110）设计用于具有嵌入在远离期望的推力轴线（47）的表面中或从其突出的喷嘴（110）的车辆。喷嘴（110）构造用于火箭车辆，其中喷嘴（110）不位于车辆的最佳推力轴线（47）处。两个实例包括位于车辆前端（也称为拖拉机喷嘴）的喷嘴（110）和位于车辆周边的姿态控制喷嘴。更具体地，所公开的喷嘴（110）的形状增强了车辆上的轴向推力（56）和/或操纵扭矩。这些非常规喷嘴（110）的形状改善了车辆性能。

9. 发明申请

WO2009123770A2 PROPULSION SYSTEM WITH MOVABLE THERMAL CHOKE 审中-公开
标题翻译：带可移动热咀的推进系统
公开(公告)号：WO2009123770A2
公开(公告)日：2009-10-08
申请号：PCT/US2009030185
申请日：2009-01-06
申请人： AEROJET GENERAL CO , BULMAN MELVIN J
发明人： BULMAN MELVIN J
IPC分类号： F02C9/20
CPC分类号： F02K9/82 , F02K9/86
摘要： High thrust at sea level and high Isp at high altitudes with low ambient pressure are obtained in a vehicle with an engine of fixed geometry including an exit of non-changing cross section, by incorporating a series of propellant injectors in a divergent section of the engine, spaced apart along the engine axis at points of different engine cross section. At takeoff, the injectors at sites with a large cross section are used, and as the vehicle climbs, these injectors are successively closed leaving injectors activated at sites of successively smaller cross sections. The injectors establish thermal choke points, and the area ratio of the cross section at the exit to the cross section at the thermal choke point thus increases as the vehicle climbs from low to high altitudes.
摘要翻译：在具有固定几何形状的发动机的车辆中，通过在发动机的发散部分中结合一系列推进剂喷射器，在具有低环境压力的高海拔处的高推力和高Isp，包括不变横截面的出口沿着发动机轴线在不同的发动机横截面的点处间隔开。起飞时，使用大横截面现场的喷油器，随着车辆爬升，这些喷油器依次关闭，喷油器在连续较小横截面的位置上激活。喷射器建立热扼流点，并且随着车辆从低到高的高度上升，出口处的横截面与热扼流点处的横截面的面积比率因此增加。

10. 发明申请

WO2010048194A2 SUPERCONDUCTING POWER AND TRANSPORT SYSTEM 审中-公开
标题翻译：超导电力和运输系统
公开(公告)号：WO2010048194A2
公开(公告)日：2010-04-29
申请号：PCT/US2009/061340
申请日：2009-10-20
申请人： METADIGM LLC , KLEY, Victor, B. , BULMAN, Melvin, J.
发明人： KLEY, Victor, B. , BULMAN, Melvin, J.
IPC分类号： B61B3/00
CPC分类号： B60L13/10 , B60L2200/26 , B61B1/00 , B61B13/08 , B61B13/10 , B61C3/00 , B61K13/00 , G06Q50/165 , Y02T30/30
摘要： A transport and power system having a plurality of tubes or tunnels, a magnetic levitation and linear motor train, and a superconducting power cable. One of the tubes can be an escape, power distribution, and maintenance tunnel. These tubes can be above ground, below ground, at ground, or under water.
摘要翻译：具有多个管或隧道的运输和动力系统，磁悬浮和线性电动机列车以及超导电力电缆。其中一个管子可以是逃生，配电和维护隧道。这些管可以在地上，地下，地面或水下。

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