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1. 发明授权

US07114323B2 Jet exhaust noise reduction system and method 有权
标题翻译：喷气排气降噪系统及方法
公开(公告)号：US07114323B2
公开(公告)日：2006-10-03
申请号：US10794968
申请日：2004-03-05
申请人： Robert Schlinker , Satish Narayanan , Wesley K. Lord , Gregory A. Kohlenberg , Ramons Reba , John Simonich , Marios C. Soteriou , Thierry Maeder
发明人： Robert Schlinker , Satish Narayanan , Wesley K. Lord , Gregory A. Kohlenberg , Ramons Reba , John Simonich , Marios C. Soteriou , Thierry Maeder
IPC分类号： B63H11/00 , B64G9/00 , F02K9/00 , F03H9/00 , F23R9/00
CPC分类号： F02K1/386 , Y02T70/56
摘要： A system for reducing jet noise emission from an internally mixed gas turbine engine exhaust, comprising a fan/core flow mixer having a plurality of mixer lobes and a common flow nozzle having an equal number of tabs located along a circumferential edge of an aft end of the nozzle. There is a predetermined clocking relationship between the plurality of mixer lobes and the plurality of nozzle tabs that results in reduced exhaust noise emission, most evident in the lower frequency range. A method for reducing jet noise emission from an internally mixed gas turbine engine exhaust comprises selectively aligning a circumferential distribution of a mixed flow vorticity field produced by a fan/core mixer with a circumferentially distributed exhaust flow vorticity field produced by a modified common flow nozzle at an exit plane of the engine exhaust.
摘要翻译：一种用于减少来自内部混合燃气涡轮发动机排气的喷射噪声发射的系统，包括具有多个混合器叶片的风扇/芯流混合器和具有相同数量的翼片的公共流动喷嘴，所述翼片沿着沿着喷嘴。在多个混合器叶片和多个喷嘴翼片之间存在预定的时钟关系，其导致减少的排气噪声发射，在较低的频率范围中最明显。一种用于减少内部混合燃气涡轮发动机废气排放的喷射噪声的方法包括：选择性地将由风扇/核心混合器产生的混合涡流场的周向分布与由改进的公共流动喷嘴产生的周向分布的排气涡流场对齐发动机排气口的出口面。

2. 发明授权

US06983587B2 Method and apparatus for thrust augmentation for rocket nozzles 有权
标题翻译：火箭喷嘴推力增大的方法和装置
公开(公告)号：US06983587B2
公开(公告)日：2006-01-10
申请号：US10282219
申请日：2002-10-28
申请人： James Shumate
发明人： James Shumate
IPC分类号： B63H11/00 , B64G9/00 , F02K9/00 , F03H9/00 , F23R9/00
CPC分类号： F02K9/97 , F02K9/82 , F05D2240/128 , F05D2240/1281 , Y02T70/56
摘要： A method and apparatus for augmenting thrust in a rocket traveling through atmospheric gas. Rocket motor designs are provided where a throat(s) from one or more rocket motors eject high-speed primary exhaust gas in a configuration which peripherally surrounds an outlet for induced, secondary gas. The secondary gas is mixed with the jet of primary exhaust gas to add momentum, and therefore thrust. Either expansion deflection or plug type rocket discharge nozzles can be utilized. In one embodiment, a thrust augmentation of over one hundred percent is achieved. In another embodiment, a plurality of rocket motor assemblies each containing a thrust augmenting rocket motor design is affixed to a rocket body. Such rocket motors enhance rocket thrust performance, and enables more efficient payload to rocket motor selection, or, alternatively, allows higher loads to be carried with the same amount of thrust.
摘要翻译：一种用于增加在大气中行驶的火箭的推力的方法和装置。提供火箭发动机设计，其中来自一个或多个火箭发动机的喉部以周围围绕用于感应的二次气体的出口的构造喷射高速初级废气。二次气体与一次排气的喷气混合，增加动量，因此推力。可以使用膨胀偏转或塞子型火箭喷射喷嘴。在一个实施例中，实现了超过百分之一的推力增加。在另一个实施例中，每个包含推力增强火箭发动机设计的多个火箭发动机组件固定在火箭体上。这种火箭发动机提高了火箭推力性能，并且使得能够更有效地进行火箭发动机的选择，或者允许以相同的推力承载更高的负载。

3. 发明授权

US07174704B2 Split shroud exhaust nozzle 有权
标题翻译：分流罩排气喷嘴
公开(公告)号：US07174704B2
公开(公告)日：2007-02-13
申请号：US10898035
申请日：2004-07-23
申请人： Bernard James Renggli
发明人： Bernard James Renggli
IPC分类号： B63H11/00 , B64G9/00 , F02K9/00 , F03H9/00 , F23R9/00
CPC分类号： F02K1/09 , F02K1/386 , F05D2250/11 , F05D2250/311 , Y02T50/671
摘要： A variable geometry convergent-divergent nozzle for a gas turbine engine includes a centerbody extending rearward along a longitudinal axis of the engine which has a throat section of increased diameter. An inner shroud surrounds the centerbody and cooperates with the centerbody to define the throat of the nozzle. An outer shroud surrounds the inner shroud and cooperates with the centerbody to define the exit area of the nozzle. Both shrouds are independently translatable to provide independent control of the nozzle throat area and the nozzle expansion ratio.
摘要翻译：用于燃气涡轮发动机的可变几何收敛扩散喷嘴包括沿着发动机的纵向轴线向后延伸的中心体，该中心体具有直径增大的喉部。内护罩围绕中心体并与中心体配合以限定喷嘴的喉部。外护罩围绕内护罩并与中心体配合以限定喷嘴的出口区域。两个护罩可独立地平移以提供喷嘴喉部区域和喷嘴膨胀比的独立控制。

4. 发明授权

US06948306B1 Apparatus and method of using supersonic combustion heater for hypersonic materials and propulsion testing 失效
标题翻译：超音速燃烧加热器用于超音速材料和推进测试的装置和方法
公开(公告)号：US06948306B1
公开(公告)日：2005-09-27
申请号：US10337667
申请日：2002-12-24
申请人： Kenneth J. Wilson , Timothy P. Parr , Ken Yu , Jaul Warren
发明人： Kenneth J. Wilson , Timothy P. Parr , Ken Yu , Jaul Warren
IPC分类号： B63H11/00 , B64G1/40 , B64G1/58 , B64G7/00 , B64G99/00 , F02K7/10 , F02K7/14 , F02K9/00 , F23R5/00 , B64G9/00 , F03H9/00 , F23R9/00
CPC分类号： B64G7/00 , B64G1/401 , B64G1/58 , F02K7/10 , F02K7/14 , F05D2220/10 , F05D2250/51 , F05D2250/52 , F23R5/00
摘要： A supersonic combustion apparatus and method of using the same including a side wall cavity having an enhanced mixing system with ground-based oxygen injection for hypersonic material and engine testing.
摘要翻译：一种超音速燃烧装置及其使用方法，其包括具有增强的混合系统的侧壁空腔，其具有用于超音速材料和发动机测试的基于地面的氧气喷射。

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