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公开(公告)号：US09995181B2
公开(公告)日：2018-06-12
申请号：US13307741
申请日：2011-11-30
CPC分类号： F01D25/305 , F02K1/40 , F02K1/822 , Y02T50/672 , Y02T50/675
摘要： An exhaust impingement cooling device for reducing heating effects of an exhaust plume on an impinged surface. An exhaust nozzle exit screen is positioned across an exhaust plume flow path, and includes a plurality of flowpath diverging apertures that spread at least a portion of an exhaust plume that is being emitted along the exhaust plume flow path from an exhaust plume source. Flow control jets are arrayed within the exhaust plume flow path in respective positions where their operation will augment the flow of exhaust plume gases through the screen, thereby increasing the momentum and mixing of the exhaust plume with cooler ambient air.
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2.发明申请TURBINE ENGINE NOZZLE HAVING CONFLUENT STREAMS AND INCLUDING A CORE COWL WITH OVERLAPPING FLAPS 审中-公开涡轮发动机喷嘴具有混凝土流动性，并包括具有重叠油面的核心油公开(公告)号：US20160237949A1
公开(公告)日：2016-08-18
申请号：US15023952
申请日：2014-09-16
申请人： SNECMA
CPC分类号： F02K1/46 , F02K1/386 , F02K1/40 , F05D2220/30 , F05D2240/127 , F05D2250/36
摘要： A turbine engine nozzle having confluent streams, the nozzle including a core cowl arranged around an annular central body and co-operating therewith to define a core annular channel for passing a flow of a core stream, the core stream on entry into the nozzle possessing an azimuth component driving residual gyratory movement of the core stream in two opposite gyratory flow directions corresponding to two operating speeds of the engine, the core cowl having an annular upstream portion that is extended downstream by an annular terminal portion having longitudinal cuts forming a plurality of flaps that overlap radially in pairs via their respective side edges in such a manner that, for each flap, one of the two side edges of the flap is positioned internally relative to the corresponding side edge of one of the adjacent flaps, while the other side edge of the flap is positioned externally relative to the corresponding side edge of the other adjacent flap.
摘要翻译： 具有汇合流的涡轮发动机喷嘴，所述喷嘴包括围绕环形中心体布置并与之配合的芯罩，以限定用于使芯流的流动通过的芯环形通道，所述芯流进入具有 方位角分量驱动核心流在对应于发动机的两个操作速度的两个相对的旋转流动方向上的残余回转运动，所述芯整流罩具有环形上游部分，该环形上游部分由环形端部部分延伸，所述环形端部部分具有形成多个折翼的纵向切口 通过它们各自的侧边缘成对地径向重叠，使得对于每个翼片，翼片的两个侧边缘中的一个相对于相邻翼片的相应侧边缘位于内部，而另一侧边缘 的翼片相对于另一相邻翼片的相应侧边缘位于外部。
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公开(公告)号：US07845156B2
公开(公告)日：2010-12-07
申请号：US11627643
申请日：2007-01-26
CPC分类号： B64D33/04 , F02K1/40 , F02K1/52 , F05D2260/96 , Y02T50/671
摘要： A turbofan exhaust system includes at least one exhaust nozzle with a trailing edge having an upper edge, a lower edge, an inner lateral edge-and an outer lateral edge. The upper edge is upstream with respect to the lower edge. The outer lateral edge of the exhaust nozzle is also upstream of the inner lateral edge. This arrangement makes it possible to reduce the noise perceived in the cabin of the aircraft at the same time as the noise perceived on the ground.
摘要翻译： 涡轮风扇排气系统包括至少一个具有后边缘的排气喷嘴，其具有上边缘，下边缘，内侧边缘和外侧边缘。 上边缘相对于下边缘是上游的。 排气喷嘴的外侧边缘也在内侧边缘的上游。 这种布置使得可以在与地面上感知到的噪声同时降低飞机机舱感知的噪音。
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公开(公告)号：US20040083713A1
公开(公告)日：2004-05-06
申请号：US10691956
申请日：2003-10-23
发明人： Larry T. Clark
IPC分类号： F02K001/00 , F03H001/00 , F23R003/00 , B64G009/00 , B63H011/00
CPC分类号： F02K1/386 , F02K1/40 , Y02T50/671
摘要： A jet engine assembly having a jet engine and an unsteady flow ejector. The unsteady flow ejector segregates the exhaust flow from the jet engine into a plurality of rotating high velocity, low density jets and a plurality of rotating low pressure voids. The low pressure voids are employed to entrain at least a portion of a secondary flow of air which is mixed with the jets to produce a mixed flow having a relatively higher flow rate and a relatively lower velocity than the exhaust flow. A method for attenuating the noise that is produced by the exhaust flow of a jet engine is also provided.
摘要翻译： 具有喷气发动机和不稳定流动喷射器的喷气发动机组件。 不稳定流动喷射器将来自喷气发动机的排气流分离成多个旋转的高速，低密度射流和多个旋转的低压空隙。 使用低压空隙来夹带与喷流混合的二次空气流的一部分以产生具有比排气流更高流速和相对较低速度的混合流。 还提供了一种用于衰减由喷气发动机的排气流产生的噪声的方法。
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公开(公告)号：US5369954A
公开(公告)日：1994-12-06
申请号：US65307
申请日：1993-05-24
申请人： Alan R. Stuart
发明人： Alan R. Stuart
摘要： A turbofan engine bypass and exhaust system has a double-hoop configuration in which a fan exhaust passageway comprises shells of a constant circular contour to resolve air pressure induced stresses and increase in bypass passageway area asymmetrically in the horizontal direction without substantially increasing the overall engine height.
摘要翻译： 涡轮风扇发动机旁通和排气系统具有双箍结构，其中风扇排气通道包括恒定圆形轮廓的壳体以分解空气压力引起的应力并且在水平方向上不对称地增加旁路通道面积，而基本上不增加总体发动机高度 。
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公开(公告)号：US4311291A
公开(公告)日：1982-01-19
申请号：US968226
申请日：1978-12-11
CPC分类号： F02K1/46 , B64C23/00 , F02K1/40 , F05D2250/182 , Y02T50/671 , Y10S239/01
摘要： A nozzle for a jet stream in which the rear edge of the nozzle has a number of notches spaced therealong to widen the jet stream while directing the jet stream rearwardly of the nozzle. Each notch has a narrow front apex and a rear opening substantially wider than the apex, and each notch widens substantially smoothly and progressively from its apex to its rear opening, each notch having sides which at least over a major portion of their length diverge from each other at an angle of at least 60 degrees, and preferably at least 90 degrees. The nozzle will commonly blow into a diffuser to provide thrust augmentation but may also be used simply to blow over a flap, or it may be used without any diffusers or flaps, simply to provide noise reduction. So long as the notch divergence angle is wide enough, loss of nozzle efficiency is minimized, and when a diffuser is used, thrust augmentation is increased. In another embodiment, fairings are placed between the notches to guide and confine the flow to the notches, permitting a large reduction in the notch angle.
摘要翻译： 一种用于喷射流的喷嘴，其中喷嘴的后边缘具有间隔开的多个凹口以加宽喷射流，同时将喷射流引导到喷嘴的后方。 每个凹口具有窄的前顶点和基本上比顶点宽的后开口，并且每个凹口从其顶点到其后开口基本上平滑地逐渐变宽，每个凹口具有至少在其长度的大部分上的侧面与每个 其它角度为至少60度，优选为至少90度。 喷嘴通常会吹入扩散器以提供推力增加，但是也可以简单地用于吹过翼片，或者可以使用没有任何扩散器或翼片的简单地提供降噪。 只要凹口发散角度足够宽，喷嘴效率的损失最小化，当使用扩散器时，会增加推力。 在另一个实施例中，整流罩放置在凹口之间以引导流体并将其限制在凹口中，从而允许切口角度大大减小。
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7.发明授权
公开(公告)号：US4279382A
公开(公告)日：1981-07-21
申请号：US115847
申请日：1980-01-28
申请人： Paul Wilson, Jr.
发明人： Paul Wilson, Jr.
摘要： Minimum thrust at idle speed, and maximum thrust with minimum losses at speeds above idle, are provided in a gas turbine engine by the use of a plurality of adjacent, successively overlapping, annularly disposed, pivotable, exhaust nozzle-forming fairings which are opened during idle to direct the exhaust gases overboard in radial directions between the opened fairings, and which are closed during speeds above idle to direct the exhaust gases overboard in an axial direction through an axially aligned rearwardly located exit opening of the exhaust nozzle.
摘要翻译： 怠速时的最小推力和空转速度最小的最大推力在燃气涡轮发动机中通过使用多个相邻的连续重叠的环形设置的可枢转的排气喷嘴形成整流罩来设置， 怠速以将排气沿径向方向排列在打开的整流罩之间，并且在空转之前的速度期间关闭，以将排气沿轴向方向排列穿过排气喷嘴的轴向对齐的后向定位的出口。
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公开(公告)号：US3905445A
公开(公告)日：1975-09-16
申请号：US38100073
申请日：1973-07-20
发明人： SCHARTON TERRY D
CPC分类号： F01N13/082 , F02K1/40
摘要： This disclosure deals with structures for suppressing a substantial percentage of noise that normally is attendant upon vortex generation from jet engines, blown flaps, turbine outlets and the like, involving successive tubular sections of successively reduced width disposed longitudinally, preferably along a common axis.
摘要翻译： 本公开涉及用于抑制通常伴随着来自喷气发动机，吹风翼，涡轮出口等的涡流产生的相当大百分比的噪声的结构，其包括连续缩小的宽度的连续管状部分，纵向地，优选地沿公共轴线布置。
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公开(公告)号：US3837579A
公开(公告)日：1974-09-24
申请号：US37165973
申请日：1973-06-19
发明人： CAMBOULIVES A , LE MAOUT T , VANDENBROUCKE R , CHAMBON J , JOURDAIN G
CPC分类号： F02K1/40 , F02K1/1207 , Y02T50/672
摘要： A variable-geometry nozzle for a jet engine is of the type which comprises a fixed structure, flaps adjustable in position with respect to the fixed structure, and control means for adjusting the position of the flaps. A plurality of swivelling frames are arranged around the circumference of the nozzle and are separately hinged to the fixed structure for pivotal adjustment about axes perpendicular to the longitudinal direction of the nozzle. The control means comprise jacks operable to pivot the frames about their respective axes, and the adjustable flaps are connected to the frames. The flaps comprise, in resect of each frame, two flaps each of which is hinged to the corresponding frame for positional angular adjustment with reference to that frame about an axis which has a component perpendicular to the pivotal axis of the frame concerned.
摘要翻译： 用于喷气发动机的可变几何形喷嘴是包括固定结构，相对于固定结构可调节的翼片的类型，以及用于调节翼片位置的控制装置。 多个旋转框架布置在喷嘴的圆周周围，并且分别铰接到固定结构上，用于围绕垂直于喷嘴纵向方向的轴线进行枢转调节。 控制装置包括可操作以使框架围绕它们各自的轴线枢转的插座，并且可调节的翼片连接到框架。 翼片在每个框架的切割中包括两个翼片，每个翼片铰接到相应的框架上，用于相对于该框架围绕具有垂直于相关框架的枢转轴线的分量的轴线进行位置角度调整。
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公开(公告)号：US3650348A
公开(公告)日：1972-03-21
申请号：US3650348D
申请日：1970-02-19
发明人： COLEBROOK ROSS W , ELLIS PETER H
CPC分类号： F02K1/48 , F02K1/40 , Y02T50/672
摘要： A jet exhaust nozzle having articulated variable geometry segments attached to the downstream end of an exhaust duct and an actuator to articulate the segments between a corrugated subsonic noise suppression configuration and a divergent expansion surface supersonic cruise configuration. When applied to a multi-tube exhaust nozzle, closeable apertures are provided in a surrounding nacelle shroud to ventilate the spaces between the tubes.
摘要翻译： 具有连接到排气管道的下游端的铰接可变几何段的喷射式排气喷嘴和用于在波纹亚音速噪声抑制配置和发散膨胀表面超音速巡航配置之间铰接节段的致动器。 当应用于多管排气喷嘴时，在周围的机舱罩中设置可密闭的孔，以使管之间的空间通风。
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