-
1.发明授权公开(公告)号：US06731241B2
公开(公告)日：2004-05-04
申请号：US09880423
申请日：2001-06-13
申请人： Pyong K. Park , Sang H. Kim , Joseph M. Anderson , Jack H. Anderson , Kevin P. Grabe , David Y. Kim , Richard M. Oestreich
发明人： Pyong K. Park , Sang H. Kim , Joseph M. Anderson , Jack H. Anderson , Kevin P. Grabe , David Y. Kim , Richard M. Oestreich
IPC分类号： H01Q1310
CPC分类号： H01Q21/0006 , H01Q21/064 , H01Q21/24
摘要： A dual-polarization common aperture antenna having fully populated common aperture dual polarized arrays. The inventive antenna includes a first and second arrays of radiating slots disposed in a faceplate. The second array is generally orthogonal and therefor cross-polarized relative to the first array. The first array is waveguide fed and the second array is stripline fed. In the illustrative implementation, the first array and the second array share a common aperture. The common aperture is fully populated and each array uses the aperture in its entirety. The first and second arrays of slots are arranged for four-way symmetry. Each slot in the first array is a vertically oriented, iris-excited shunt slot fed by a rectangular waveguide and centered on a broad wall thereof. The second array is a standing wave array in which each slot is an air cavity backed slot fed by an inverted micro-stripline offset from a center thereof.
摘要翻译： 具有完全填充的共同孔径双极化阵列的双极化公共孔径天线。 本发明的天线包括设置在面板中的第一和第二辐射槽阵列。 第二阵列通常是正交的并且相对于第一阵列交叉极化。 第一阵列是波导馈送的，第二阵列是带状线馈电的。 在说明性实现中，第一阵列和第二阵列共享公共孔径。 公共孔径完全填充，每个阵列全部使用孔径。 第一和第二槽阵列被布置成四通对称。 第一阵列中的每个槽是由矩形波导馈送并以其宽壁为中心的垂直取向的虹膜激发的分流槽。 第二阵列是驻波阵列，其中每个狭槽是由其中心偏移的反向微带线片馈送的空气腔支撑槽。
-
公开(公告)号：US08069647B2
公开(公告)日：2011-12-06
申请号：US11491993
申请日：2006-07-25
申请人： Jack H. Anderson
发明人： Jack H. Anderson
CPC分类号： F02K1/48 , F02K1/46 , F02K1/70 , F02K3/02 , Y10T29/49346
摘要： An external jet nozzle mixer includes identically formed lobes. The external mixer works with the internal mixer further to mix the engine internal bypass flow with the internal jet engine core flow to level the disparate flow velocities, to reduce the peak velocities from the jet engine core and increase the lower bypass velocities of the engine internal bypass flow, and thereby reduce noise. The internal lobe contours act as lifting flutes, causing mixing of the primary hot and cold flows to mix before exiting the nozzle. The external lobe contours act as venturi chutes, accelerating the cooler ambient secondary air flow. The lobes thus act collectively as an injector to force the cooler ambient secondary flow into the previously mixed primary flow as it exits the nozzle. Also obtained is an increased thrust efficiency and, consequently, decreased fuel consumption and engine emissions.
摘要翻译： 外部喷嘴混合器包括相同形状的凸角。 进一步，外部混合器与内部混合器进一步混合，以将发动机内部旁路流与内部喷气发动机芯流混合，以平衡不同的流速，从而降低来自喷气发动机内芯的峰值速度，并增加发动机内部的较低旁路速度 旁路流，从而降低噪音。 内部叶轮轮廓作为提升槽，使得在流出喷嘴之前混合初级热和冷流混合。 外部叶轮轮廓作为文丘里斜槽，加速了较冷的环境二次空气流。 因此，叶片作为喷射器共同作用，以在其离开喷嘴时迫使冷却器环境二次流入先前混合的初级流。 还获得了增加的推力效率，因此降低了燃料消耗和发动机排放。
-
公开(公告)号：US06854260B2
公开(公告)日：2005-02-15
申请号：US10314101
申请日：2002-12-07
申请人： Jack H. Anderson
发明人： Jack H. Anderson
CPC分类号： F02K1/48 , F02K1/46 , F02K1/70 , F02K3/02 , Y10T29/49346
摘要： An external jet nozzle mixer (20) includes identically formed lobes (48), equal in number those of the internal mixer (42). External mixer (20) works with internal mixer (42), further to mix the engine internal bypass flow with the internal jet engine core flow, to level the disparate exhaust flow velocities, to reduce the peak velocities from the jet engine core and increase the lower bypass velocities of the engine internal bypass flow, and thereby to reduce noise. The internal lobe contours act as lifting flutes, causing mixing of the primary hot and cold flows before exiting the nozzle. The external lobe contours act as venturi chutes, accelerating the cooler ambient air secondary flow. The lobes thus act collectively as an injector to force the cooler ambient secondary flow into the previously mixed primary flow as it exits the nozzle. Also obtained is an increased thrust efficiency and a consequently decreased fuel consumption and engine emissions.
摘要翻译： 外部喷嘴混合器（20）包括与内混合器（42）相同数量的相同形状的凸角（48）。 外部混合器（20）与内混合器（42）一起工作，进一步将发动机内部旁路流与内部喷气发动机芯流混合，以平衡不同的排气流速度，以减少来自喷气发动机内核的峰值速度，并增加 降低发动机内部旁路流的旁路速度，从而降低噪音。 内部叶轮轮廓作为提升槽，在离开喷嘴之前引起初级热流和冷流的混合。 外部波瓣轮廓作为文丘里斜槽，加速了较冷的环境空气二次流。 因此，叶片作为喷射器共同作用，以在其离开喷嘴时迫使冷却器环境二次流入先前混合的初级流。 还获得了增加的推力效率并因此降低了燃料消耗和发动机排放。
-
公开(公告)号：US07111448B2
公开(公告)日：2006-09-26
申请号：US11027981
申请日：2005-01-04
申请人： Jack H. Anderson
发明人： Jack H. Anderson
CPC分类号： F02K1/48 , F02K1/46 , F02K1/70 , F02K3/02 , Y10T29/49346
摘要： An external jet nozzle mixer includes identically formed lobes. The external mixer works with the internal mixer further to mix the engine internal bypass flow with the internal jet engine core flow to level the disparate flow velocities, to reduce the peak velocities from the jet engine core and increase the lower bypass velocities of the engine internal bypass flow, and thereby reduce noise. The internal lobe contours act as lifting flutes, causing mixing of the primary hot and cold flows to mix before exiting the nozzle. The external lobe contours act as venturi chutes, accelerating the cooler ambient secondary air flow. The lobes thus act collectively as an injector to force the cooler ambient secondary flow into the previously mixed primary flow as it exits the nozzle. Also obtained is an increased thrust efficiency and a consequently decreased fuel consumption and engine emissions.
摘要翻译： 外部喷嘴混合器包括相同形状的凸角。 进一步，外部混合器与内部混合器进一步混合，以将发动机内部旁路流与内部喷气发动机芯流混合，以平衡不同的流速，从而降低来自喷气发动机内芯的峰值速度，并增加发动机内部的较低旁路速度 旁路流，从而降低噪音。 内部叶轮轮廓作为提升槽，使得在流出喷嘴之前混合初级热和冷流混合。 外部叶轮轮廓作为文丘里斜槽，加速了较冷的环境二次空气流。 因此，叶片作为喷射器共同作用，以在其离开喷嘴时迫使冷却器环境二次流入先前混合的初级流。 还获得了增加的推力效率并因此降低了燃料消耗和发动机排放。
-
公开(公告)号：US07017331B2
公开(公告)日：2006-03-28
申请号：US10783839
申请日：2004-02-20
申请人： Jack H. Anderson
发明人： Jack H. Anderson
摘要： A second stage external jet nozzle mixer (20) includes identically formed lobes which equal in number the lobes of the first stage internal mixer. The external mixer works with the internal mixer, and furthers the mixing of the jet engine internal bypass flow with the internal jet engine core flow. This mixing levels the disparate flow velocities attendant with the jet engine exhaust, reduces the peak velocities from the jet engine core and increases the lower bypass velocities of the jet engine internal bypass flow. The lobes include complex curvatures that greatly enhance mixing of the gases and ambient cooling air, and thereby reduce noise. At the lobe terminus, the lobe dimensional characteristics may be adjusted to thereby adjust the total terminus area to achieve a match to a jet engine to cause that jet engine to run at a determined RPM and noise level. Noise attenuation may also be adjusted by changing lobe dimensions. Prior existing second stage exhaust jet nozzle mixers may be retrofitted to allow alteration of their total terminus area by employing the disclosed device and method.
-
6.发明授权Jet engine cascade thrust reverser for use with mixer/ejector noise suppressor 有权喷气发动机级联推力反向器用于混合器/喷射器噪声抑制器公开(公告)号：US06311928B1
公开(公告)日：2001-11-06
申请号：US09477849
申请日：2000-01-05
IPC分类号： B64C2568
摘要： A cascade thrust reverser for use with a mixer/ejector noise suppressor has a set of internal blocker doors controllably moveable between a stowed position, where engine exhaust passes through and out the tailpipe, and a deployed position, where engine exhaust is blocked and redirected out a pair of cascades or louvers. External cascade doors cover the cascades from the outside during flight, but are moved aft, exposing the cascades, when the blocker doors are deployed subsequent landing. In a preferred embodiment, the cascade doors and the blocker doors are interconnected through a pair of actuation mechanisms, whereby movement of the cascade doors is sequenced to the motion of the blocker doors. The blocker doors and the cascade doors are shaped to provide a clean aerodynamic profile when stowed, so that the noise suppressor functions optimally. The actuation mechanisms also preferably include lock mechanisms for only allowing the thrust reversers to be deployed just subsequent landing. Also, the thrust reverser can directly replace one of an airplane's existing thrust reversers without any modifications to the plane's hydraulic system or controls or instrumentation.
摘要翻译： 用于混合器/喷射器噪声抑制器的级联推力反向器具有一组内部阻挡门，其可控制地在收起位置（其中发动机排气通过和排出尾管）之间移动，以及展开位置，其中发动机排气被阻挡并重定向 一对瀑布或百叶窗。 外部级联门在飞行期间覆盖外部的级联，但是当阻塞门部署在后续着陆时，它们将在后方移动，暴露级联。 在一个优选实施例中，级联门和阻挡门通过一对致动机构相互连接，由此级联门的移动与阻挡门的运动相一致。 阻塞门和级联门的形状可在收起时提供清洁的空气动力学特性，从而使噪音抑制器发挥最佳的作用。 致动机构还优选地包括仅允许推力反向器刚刚部署的锁定机构。 此外，推力反向器可以直接替换飞机现有的推力反向器之一，而不需要对飞机的液压系统或控制装置进行任何修改。
-
-
-
-
-
搜索结果
6 条记录 (耗时 0.031 秒)
