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1. 发明公开

EP2084386A2 COMBINED CYCLE MISSILE ENGINE SYSTEM 有权
标题翻译：组合循环导弹发动机系统
公开(公告)号：EP2084386A2
公开(公告)日：2009-08-05
申请号：EP07873472.0
申请日：2007-11-09
申请人： AEROJET-GENERAL CORPORATION
发明人： BULMAN, Melvin, J. , SIEBENHAAR, Adam
IPC分类号： F02K3/00
CPC分类号： F42B15/10 , F02K7/10 , F02K7/18 , F02K9/763
摘要： An insensitive combined cycle missile 10 propulsion system includes a solid fuel 16 contained within a first section of the missile 10, and a liquid oxidizer 14 contained within a second section of the missile 10. A first conduit 18 has a first valve 18a communicating the fuel 16 and the oxidizer 14 and a second conduit 20, spatially removed from the first conduit 18, has a second valve 20a communicating the fuel 16 and the oxidizer 14. An inlet system 22 for delivering atmospheric oxygen for combustion with the fuel rich gases 34 generated within the missile 10 and a nozzle 24 exhausts combustion products that result from combustion of the fuel 16, the liquid and solid oxidizers 14, and air.
摘要翻译：一种不敏感的联合循环导弹10推进系统包括装在导弹10第一部分内的固体燃料16和装在导弹10第二部分内的液态氧化器14.第一导管18具有第一阀18a，从第一导管18空间移除的氧化器14和第二导管20具有使燃料16与氧化器14连通的第二阀20a。用于输送大气氧用于燃烧富燃料气体34的入口系统22 在导弹10内和喷嘴24内排出由燃料16，液体和固体氧化剂14以及空气的燃烧产生的燃烧产物。

2. 发明公开

EP2074324A2 CORE BURNING FOR SCRAMJET ENGINES 有权
标题翻译： CORE烧了超燃冲压引擎
公开(公告)号：EP2074324A2
公开(公告)日：2009-07-01
申请号：EP07872631.2
申请日：2007-10-15
申请人： AEROJET-GENERAL CORPORATION
发明人： BULMAN, Melvin, J.
IPC分类号： F02K7/10
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 ιn-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.

3. 发明公开

EP1931871A2 THRUST AUGMENTATION IN PLUG NOZZLES AND EXPANSION-DEFLECTION NOZZLES 审中-公开
标题翻译：在塞式喷嘴和扩张式喷嘴中推力增加
公开(公告)号：EP1931871A2
公开(公告)日：2008-06-18
申请号：EP06814412.0
申请日：2006-09-08
申请人： AEROJET-GENERAL CORPORATION
发明人： LAUSTEN, Merlyn , BULMAN, Melvin, J.
IPC分类号： F02K9/62
CPC分类号： F02K9/90 , F02K9/62 , F02K9/82 , F05D2240/1281
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.
摘要翻译：在火箭喷嘴中的推力增加是通过结合喷嘴将未燃烧燃料和氧化剂引入喷嘴中以在喷嘴中燃烧并由此补充由进入喷嘴之前燃烧的燃料和氧化剂供应的主推力而实现的。这些二次喷射器被结合到膨胀偏转喷嘴和塞喷嘴的设计中。在膨胀偏转喷嘴中，喷射器或者位于导流板本身内，或者位于喷嘴发散部分的壁内。在塞式喷嘴中，喷射器要么位于围绕中心体前端的喷嘴壳体中，要么位于中心体本身中。

4. 发明授权

EP2084386B1 COMBINED CYCLE MISSILE ENGINE SYSTEM 有权
标题翻译：组合循环导弹发动机系统
公开(公告)号：EP2084386B1
公开(公告)日：2013-01-30
申请号：EP07873472.0
申请日：2007-11-09
申请人： AEROJET-GENERAL CORPORATION
发明人： BULMAN, Melvin, J. , SIEBENHAAR, Adam
IPC分类号： F02K7/10 , F02K1/00 , F42B15/10 , F02K7/18
CPC分类号： F42B15/10 , F02K7/10 , F02K7/18 , F02K9/763

5. 发明授权

EP1718857B1 INTEGRATED AIR INLET SYSTEM FOR MULTI-PROPULSION AIRCRAFT ENGINES 有权
标题翻译：综合进气系统多个驱动飞机搭载DRIVE WORKS
公开(公告)号：EP1718857B1
公开(公告)日：2012-08-08
申请号：EP05851149.4
申请日：2005-02-16
申请人： AEROJET-GENERAL CORPORATION
发明人： BULMAN, Melvin, J. , BILLIG, Frederick, S.
IPC分类号： B64D33/02 , F02K7/16 , B64C30/00 , F02C7/042 , F02K9/18 , F02K7/10 , F02K7/14
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.

6. 发明授权

EP2074324B1 CORE BURNING FOR SCRAMJET ENGINES 有权
标题翻译： CORE烧了超燃冲压引擎
公开(公告)号：EP2074324B1
公开(公告)日：2013-02-27
申请号：EP07872631.2
申请日：2007-10-15
申请人： AEROJET-GENERAL CORPORATION
发明人： BULMAN, Melvin, J.
IPC分类号： F02K7/10
CPC分类号： F02K7/10

7. 发明公开

EP2238020A2 PROPULSION SYSTEM WITH MOVABLE THERMAL CHOKE 审中-公开
标题翻译：随着便携式热反应器驱动系统
公开(公告)号：EP2238020A2
公开(公告)日：2010-10-13
申请号：EP09727555.6
申请日：2009-01-06
申请人： Aerojet-General Corporation
发明人： BULMAN, Melvin, J.
IPC分类号： B63H25/46
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.

8. 发明授权

EP1402166B1 ROCKET VEHICLE THRUST AUGMENTATION WITHIN DIVERGENT SECTION OF NOZZLE 有权
标题翻译：火箭车辆采用的发散部分中排气喷管装置抗剪加固
公开(公告)号：EP1402166B1
公开(公告)日：2009-07-22
申请号：EP02749714.8
申请日：2002-06-28
申请人： AEROJET-GENERAL CORPORATION
发明人： BULMAN, Melvin, J.
IPC分类号： F02K1/30 , F02K9/80 , F02K9/97
CPC分类号： F02K1/30 , F02K9/12 , F02K9/18 , F02K9/82 , F02K9/97 , F02K9/974
摘要： Augmentation of the thrust achieved by a supersonic nozzle (11) of continuous curvature is achieved by causing secondary combustion to occur in an annular region (25) of the combustion that complements the primary combustion gas (26) passing through the nozzle and maintains a wall pressure that is greater or equal to the ambient pressure at low altitudes, eliminating the negative component of the thrust in an overexpanded nozzle at takeoff.

9. 发明公开

EP1718857A2 INTEGRATED AIR INLET SYSTEM FOR MULTI-PROPULSION AIRCRAFT ENGINES 有权
标题翻译：综合进气系统多个驱动飞机搭载DRIVE WORKS
公开(公告)号：EP1718857A2
公开(公告)日：2006-11-08
申请号：EP05851149.4
申请日：2005-02-16
申请人： AEROJET-GENERAL CORPORATION
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.

10. 发明公开

EP1402166A1 ROCKET VEHICLE THRUST AUGMENTATION WITHIN DIVERGENT SECTION OF NOZZLE 有权
标题翻译：火箭车在喷嘴的不连续部分推动增强
公开(公告)号：EP1402166A1
公开(公告)日：2004-03-31
申请号：EP02749714.8
申请日：2002-06-28
申请人： AEROJET-GENERAL CORPORATION
发明人： BULMAN, Melvin, J.
IPC分类号： F02K1/30
CPC分类号： F02K1/30 , F02K9/12 , F02K9/18 , F02K9/82 , F02K9/97 , F02K9/974
摘要： Augmentation of the thrust achieved by a supersonic nozzle (11) of continuous curvature is achieved by causing secondary combustion to occur in an annular region (25) of the combustion that complements the primary combustion gas (26) passing through the nozzle and maintains a wall pressure that is greater or equal to the ambient pressure at low altitudes, eliminating the negative component of the thrust in an overexpanded nozzle at takeoff.
摘要翻译：由具有连续曲率的超音速喷嘴（11）实现的推力的增大通过使得在补充通过喷嘴的主燃烧气体（26）的补充的燃烧的环形区域（25）中发生二次燃烧并且保持壁压力大于或等于低海拔处的环境压力，消除起飞时过度膨胀喷嘴中推力的负分量。

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