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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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4.发明授权Aircraft thrust reverser system with linearly translating inner and outer doors 失效具有线性平移内门和外门的飞机推力反向器系统
公开(公告)号：US5794434A
公开(公告)日：1998-08-18
申请号：US727952
申请日：1996-10-09
申请人： Imre A. Szupkay
发明人： Imre A. Szupkay
CPC分类号： F02K1/625 , F05D2250/34 , Y02T50/672
摘要： A thrust reverser system including a reverse thrust airflow duct (44) extending through an outer structure (46) of an aircraft engine aft nozzle (32) is disclosed. The reverse thrust duct (44) connects a nozzle exhaust duct (34) with the surrounding atmosphere (46). The duct (44) includes an inlet (72) and an outlet (70). A plurality of slats (50) are located within the reverse thrust duct to direct nozzle exhaust (38) from the nozzle exhaust duct (34) in an outward and/or forward direction. One or more outer doors (54) are formed near the outer structure exterior surface (90) for closing off the reverse thrust duct outlet (70) to the atmosphere. One or more inner doors (56) are provided for closing off the duct inlet (72) at the exhaust duct (34). An actuation system moves the inner and outer doors (56), (54) between open and closed positions. In the open position, the inner and outer doors (56), (54) are moved away from the duct (44) to open the airflow duct inlet and outlet. A portion (98) of the inner door blocks off the nozzle exhaust duct (34) by moving aftward to contact a nozzle centerbody (36). The exhaust air (38) is forced to exit the nozzle (32) via the duct (44) causing reverse thrust.
摘要翻译： 公开了一种推力反向器系统，其包括延伸穿过飞行器发动机尾部喷嘴（32）的外部结构（46）的反向推力气流通道（44）。 反推力管道（44）将喷嘴排出管道（34）与周围大气（46）连接。 管道（44）包括入口（72）和出口（70）。 多个板条（50）位于反向推力管道内，以在向外和/或向前的方向上引导喷嘴排气（38）从喷嘴排出管道（34）。 在外部结构外表面（90）附近形成有一个或多个外门（54），用于将逆向推进管道出口（70）关闭到大气中。 提供一个或多个内门（56），用于在排气管（34）处封闭管道入口（72）。 致动系统使内外门（56），（54）在打开位置和关闭位置之间移动。 在打开位置，内外门（56），（54）远离管道（44）移动以打开气流通道入口和出口。 内门的一部分（98）通过向后移动而与喷嘴中心体（36）接触而阻挡喷嘴排出管道（34）。 废气（38）被迫通过导管（44）离开喷嘴（32），引起反向推力。
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