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公开(公告)号：US5779150A
公开(公告)日：1998-07-14
申请号：US723589
申请日：1996-10-01
CPC分类号： F02K1/383 , F02K1/1223 , Y02T50/671
摘要： An aircraft ejector nozzle includes a plug assembly (26) located between upper and lower cowlings (18, 20) and upright sidewalls (22). The plug assembly (26) includes separable upper and lower diverters (28, 30). Each diverter includes multiple subsections pivotably attached end-to-end. In one embodiment, first, second, and third subsections (90, 92, 94) are provided. Stationary ejectors (40, 42) located in the cowlings (18, 20) input ambient airflow (44) into an exhaust stream (32). Preferably the ejectors (40, 42) include mixing components (46). Upper and lower aft flaps (48, 50) further tailor the exhaust path shape. An actuation assembly (52) moves the diverters (28, 30) and aft flaps (48, 50) between their various positions. One actuation assembly embodiment includes a number of rotatable disks (118, 120, 132, 134, 142) for guiding the upper and lower diverters (28, 30) and the aft flaps (48, 50). In a first plug assembly configuration the diverter forward ends (84) are positioned together and the diverter aft ends (86) are positioned together. The first configuration forces exhaust (32) around the diverters (28, 30). In a second plug assembly configuration the diverter forward ends (84) are positioned apart and the diverter aft ends (86) are positioned apart. The second configuration forces exhaust (32) between the diverters (28, 30) while simultaneously covering the ejectors (40, 42). Acoustic linings (100) are provided at various locations within the nozzle and are exposed to the exhaust flow only during noise suppression configurations, thus minimizing liner wear and contamination.
摘要翻译： 飞行器喷射器喷嘴包括位于上部和下部整流罩（18,20）和直立侧壁（22）之间的插塞组件（26）。 插头组件（26）包括可分离的上部和下部分流器（28,30）。 每个分流器包括多个子节点可枢转地连接到端对端。 在一个实施例中，提供了第一，第二和第三子部分（90,92,94）。 位于整流罩（18,20）中的固定喷射器（40,42）将环境气流（44）输入排气流（32）。 优选地，喷射器（40,42）包括混合部件（46）。 上下翼片（48,50）进一步调整排气路径形状。 致动组件（52）在其各个位置之间移动转向器（28,30）和后挡板（48,50）。 一个致动组件实施例包括用于引导上部和下部转向器（28,30）和后部翼片（48,50）的多个可旋转盘（118,120,132,134,142）。 在第一插头组件配置中，分流器前端（84）被定位在一起，并且分流器后端（86）被定位在一起。 第一构造迫使排气（32）围绕转向器（28,30）。 在第二插头组件构造中，分流器前端（84）定位成分开，并且分流器后端（86）被定位成分开。 第二结构迫使分流器（28,30）之间的排气（32）同时覆盖喷射器（40,42）。 声学衬垫（100）设置在喷嘴内的各个位置处，并且仅在噪声抑制构造期间暴露于排气流，从而最小化衬垫磨损和污染。
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公开(公告)号：US5884843A
公开(公告)日：1999-03-23
申请号：US743105
申请日：1996-11-04
CPC分类号： F02K1/36 , F02K1/34 , Y02T50/672
摘要： A moderately high bypass ratio turbofan engine nozzle (36) is provided including an outer structure (46) and one or more ejectors (38). The ejectors (38) include inner and outer doors (82), (80) for closing off an ejector passage (76) extending through the outer structure (46). The ejectors (38) are sized to entrain exterior air (40) at aspiration ratios of generally less than 60%. The exterior air (40) is mixed with engine exhaust (42), resulting in a lower combined airflow velocity which in turn reduces jet exhaust noise. Mixing components formed as turning vanes (108) are located in the ejector passage (76) for encouraging further mixing of the airflows (40), (42). In preferred embodiments, the nozzle (36) further includes a translatable centerbody (52), an aft flap assembly (112), and a control system (122) for controlling the movements of the nozzle components. A method of suppressing aircraft moderately high bypass ratio turbofan engine exhaust noise including entraining exterior air to engine exhaust at an aspiration ratio of less than about 60%.
摘要翻译： 提供了一种适度高的旁路比涡轮风扇发动机喷嘴（36），其包括外部结构（46）和一个或多个喷射器（38）。 喷射器（38）包括用于封闭延伸穿过外部结构（46）的喷射器通道（76）的内门和外门（82），（80）。 喷射器（38）的尺寸设定成以通常小于60％的吸气比夹带外部空气（40）。 外部空气（40）与发动机排气（42）混合，导致较低的组合气流速度，这又降低喷射排气噪声。 形成为转动叶片（108）的混合部件位于喷射器通道（76）中，用于鼓励气流（40），（42）的进一步混合。 在优选实施例中，喷嘴（36）还包括可平移的中心体（52），后翼片组件（112）和用于控制喷嘴部件运动的控制系统（122）。 一种抑制飞机适度高旁通比的涡轮风扇发动机排气噪声的方法，包括以小于约60％的吸气比将外部空气引入发动机排气。
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公开(公告)号：US5941065A
公开(公告)日：1999-08-24
申请号：US743104
申请日：1996-11-04
摘要： An ejector nozzle (10) including an first cowling (12), a second cowling (14), and opposed upright sidewalls (16) that together form an internal nozzle exhaust path is provided. A reconfigurable plug assembly (18) having separable first and second diverters (20), (22) is located in the exhaust path to direct engine exhaust (24) in either dual paths formed around diverter outer surfaces (76), or dual paths formed between the diverter inner surfaces (74) and centerbody exterior surfaces. When the diverters direct exhaust airflow between themselves, first and second ejectors (26), (28) formed in the first and second cowlings (12), (14), respectively, are available to entrain ambient air (30) into the exhaust stream (24). The preferred ejectors include translatable aft flaps (32), (34). Mixing devices, such as a lobed mixer (90) are incorporated into the diverters (20), (22) to improve engine noise suppression. When the diverters (20), (22) direct exhaust airflow around themselves, the ejectors are closed and the mixing devices are positioned such that they are not significantly exposed to the engine exhaust 24. An actuation assembly moves the diverters (20), (22) and ejectors between various positions.
摘要翻译： 提供了包括一起形成内部喷嘴排气路径的第一整流罩（12），第二整流罩（14）和相对的直立侧壁（16）的喷射器喷嘴（10）。 具有可分离的第一和第二分支器（20），（22）的可重新配置的插头组件（18）位于排气路径中，以将引擎排气（24）引导到形成在分流器外表面（76）周围的双路径中，或者形成双重路径 在分流器内表面（74）和中心体外表面之间。 当分流器在它们之间引导排气气流时，分别形成在第一和第二整流罩（12），（14）中的第一和第二喷射器（26），（28）可用于将环境空气（30）夹带到排气流 （24）。 优选的喷射器包括可翻转的后翼片（32），（34）。 混合装置，例如叶片混合器（90）被并入转向器（20），（22）中以改善发动机噪声抑制。 当分流器（20），（22）引导自身周围排出气流时，喷射器关闭，并且混合装置被定位成使得它们不会明显地暴露于发动机排气24.致动组件移动分流器（20）， 22）和各种位置之间的喷射器。
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公开(公告)号：US07500348B2
公开(公告)日：2009-03-10
申请号：US11090753
申请日：2005-03-24
申请人： Kirk R. Lupkes , Gary L. Lidstone
发明人： Kirk R. Lupkes , Gary L. Lidstone
IPC分类号： F02C5/02
CPC分类号： F02K7/06 , F02C5/02 , F02C5/12 , F05D2250/323 , F05D2250/324 , F05D2250/52 , F23R7/00
摘要： A pulse combustion device has a number of combustors with upstream bodies and downstream nozzles. Coupling conduits provide communication between the combustors. For each given combustor this includes a first communication between a first location upstream of the nozzle thereof and a first location along the nozzle of another. There is second communication between a second location upstream of the nozzle and a second communication between a second location upstream of the nozzle of a second other combustor and a second nozzle location along the nozzle of the given combustor.
摘要翻译： 脉冲燃烧装置具有多个具有上游体和下游喷嘴的燃烧器。 耦合管道提供燃烧器之间的连通。 对于每个给定的燃烧器，其包括在其喷嘴的上游的第一位置和沿着另一个的喷嘴的第一位置之间的第一连通。 在喷嘴上游的第二位置与第二另一个燃烧器的喷嘴的上游的第二位置和沿着给定燃烧器的喷嘴的第二喷嘴位置之间的第二连通处之间存在第二连通。
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公开(公告)号：US6003301A
公开(公告)日：1999-12-21
申请号：US827278
申请日：1997-03-27
申请人： Thomas E. Bratkovich , Kevin E. Williams , Thomas R. A. Bussing , Gary L. Lidstone , John B. Hinkey
发明人： Thomas E. Bratkovich , Kevin E. Williams , Thomas R. A. Bussing , Gary L. Lidstone , John B. Hinkey
CPC分类号： B05B7/0006 , F02K7/075 , F02K9/972 , F02K9/974
摘要： A nozzle for a detonative combustion engine, the engine having multiple combustor tubes, comprises a common plenum communicating with the combustor tubes. The common plenum combines separate exhaust streams from the combustor tubes into a compound subsonic exhaust stream. A compound flow throat communicates with the common plenum. The compound flow throat converts the compound subsonic exhaust stream into a compound sonic exhaust stream. The common plenum and compound flow throat cooperate to maintain a predetermined upstream combustor pressure regardless of down stream pressure exiting the expansion section. Optionally, an interface section is inserted between the plenum and the engine such that it communicates with the common plenum section and with outlets of the combustor tubes. The interface section is compartmentalized into flow passages with each flow passage having a cross-sectional area that increases from that of a particular nozzle intake port connected to a conductor tube exit. Additionally, an expansion section communicates with the outlet of the compound flow throat and has a diameter greater than the diameter of the compound flow throat. The expansion section converts the compound sonic exhaust stream into a compound supersonic exhaust stream thus expanding the exhaust stream to predetermined lower pressure.
摘要翻译： 用于爆炸内燃机的喷嘴，具有多个燃烧器管的发动机包括与燃烧器管连通的公共气室。 公共气室将来自燃烧器管的分离的废气流组合成复合亚音速排气流。 复合流通道与公共气室连通。 复合流动喉将化合物亚音速排气流转化为复合声音排气流。 常见的集气室和复合流道喉部协作以保持预定的上游燃烧器压力，而不管离开膨胀段的下游流压。 可选地，接口部分插入在气室和发动机之间，使得其与公共气室部分和燃烧器管的出口连通。 接口部分被分隔成流动通道，每个流动通道的横截面面积从连接到导体管出口的特定喷嘴进口的横截面面积增加。 此外，膨胀部分与复合流动喉部的出口连通并且具有大于化合物流动喉部的直径的直径。 膨胀部分将化合物声音排气流转化为化合物超音速排气流，从而将排气流扩展到预定的较低压力。
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公开(公告)号：US07775460B2
公开(公告)日：2010-08-17
申请号：US11585597
申请日：2006-10-24
摘要： A fluid flow system for use with a gas turbine engine includes an exhaust nozzle, a primary air supply valve, a distribution manifold connected to the primary fluid supply valve and in fluid communication therewith, and a plurality of fluid injector assemblies positioned at the exhaust nozzle and connected in fluid communication with the distribution manifold. Each fluid injector assembly includes a first tube, a secondary air valve positioned at least partially within the first tube and in fluid communication with the distribution manifold, a fuel valve positioned at least partially within the first tube and located downstream of the air valve, an igniter extending into the first tube downstream of the fuel valve, and an outlet in fluid communication with the first tube and connected in fluid communication with the exhaust nozzle. The outlet has a different geometry than the first tube.
摘要翻译： 与燃气涡轮发动机一起使用的流体流动系统包括排气喷嘴，一次空气供应阀，连接到主要流体供应阀并与其连通的分配歧管，以及多个位于排气喷嘴处的流体喷射器组件 并与分配歧管流体连通。 每个流体注射器组件包括第一管，二次空气阀，其至少部分位于第一管内并且与分配歧管流体连通;燃料阀，至少部分位于第一管内并位于空气阀的下游， 点燃器延伸到燃料阀下游的第一管，以及与第一管流体连通并与排气喷嘴流体连通的出口。 出口具有与第一管不同的几何形状。
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公开(公告)号：US07448200B2
公开(公告)日：2008-11-11
申请号：US11090754
申请日：2005-03-24
申请人： Kirk R. Lupkes , Gary L. Lidstone , Mark W. Parish
发明人： Kirk R. Lupkes , Gary L. Lidstone , Mark W. Parish
CPC分类号： F23R7/00 , F02C3/16 , F02C3/165 , F02C5/02 , F02C5/04 , F02C5/12 , F02K3/075 , F02K7/02 , F02K7/04 , F02K7/06 , F02K7/075 , F02K7/08 , F23C15/00
摘要： A pulse combustion device has a number of combustors with upstream bodies and downstream nozzles. Coupling conduits provide communication between the combustors. For each given combustor this includes a first communication between a first location upstream of the nozzle thereof and a first location along the nozzle of another. There is second communication between a second location upstream of the nozzle and a second communication between a second location upstream of the nozzle of a second other combustor and a second nozzle location along the nozzle of the given combustor.
摘要翻译： 脉冲燃烧装置具有多个具有上游体和下游喷嘴的燃烧器。 耦合管道提供燃烧器之间的连通。 对于每个给定的燃烧器，其包括在其喷嘴的上游的第一位置和沿着另一个的喷嘴的第一位置之间的第一连通。 在喷嘴上游的第二位置与第二另一个燃烧器的喷嘴的上游的第二位置和沿着给定燃烧器的喷嘴的第二喷嘴位置之间的第二连通处之间存在第二连通。
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公开(公告)号：US20080092543A1
公开(公告)日：2008-04-24
申请号：US11585597
申请日：2006-10-24
IPC分类号： F02C1/00
摘要： A fluid flow system for use with a gas turbine engine includes an exhaust nozzle, a primary air supply valve, a distribution manifold connected to the primary fluid supply valve and in fluid communication therewith, and a plurality of fluid injector assemblies positioned at the exhaust nozzle and connected in fluid communication with the distribution manifold. Each fluid injector assembly includes a first tube, a secondary air valve positioned at least partially within the first tube and in fluid communication with the distribution manifold, a fuel valve positioned at least partially within the first tube and located downstream of the air valve, an igniter extending into the first tube downstream of the fuel valve, and an outlet in fluid communication with the first tube and connected in fluid communication with the exhaust nozzle. The outlet has a different geometry than the first tube.
摘要翻译： 与燃气涡轮发动机一起使用的流体流动系统包括排气喷嘴，一次空气供应阀，连接到主要流体供应阀并与其连通的分配歧管，以及多个位于排气喷嘴处的流体喷射器组件 并与分配歧管流体连通。 每个流体注射器组件包括第一管，二次空气阀，其至少部分位于第一管内并且与分配歧管流体连通;燃料阀，至少部分位于第一管内并位于空气阀的下游， 点燃器延伸到燃料阀下游的第一管，以及与第一管流体连通并与排气喷嘴流体连通的出口。 出口具有与第一管不同的几何形状。
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公开(公告)号：US5222359A
公开(公告)日：1993-06-29
申请号：US722944
申请日：1991-06-28
申请人： Garry W. Klees , Gary L. Lidstone , Mark L. Sloan
发明人： Garry W. Klees , Gary L. Lidstone , Mark L. Sloan
CPC分类号： F02C7/04 , F02K1/386 , F02K3/075 , B64D2033/026 , F05D2220/80
摘要： A supersonic jet engine for improved noise abatement and thrust augmentation. There is an intake section, an engine, a mixing section, an exhaust section, and a secondary air passageway. Ambient air is directed into the engine and into the secondary air passageway. Exhaust from the engine and the secondary air are directed into primary and secondary segments to mix in a stream direction as supersonic flow. Selectively controllable primary bypass passageways are provided at the primary passageway segments and are operated to bypass the primary flow through the primary segments at times when greater primary flow area is required.
摘要翻译： 一种超音速喷气发动机，用于改善噪声消除和推力增大。 有进气段，发动机，混合段，排气段和二次空气通道。 环境空气被引导到发动机中并进入二次空气通道。 来自发动机和二次空气的排气被引导到一级和二级段，以在流动方向上作为超音速流动混合。 在主通道段处设置选择性可控的主旁通通路，并且在需要更大的主流动区域的时候，操作以旁通通过主段的主流。
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