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1. 发明授权

US11959438B2 Ultra quiet split flow thrust reverser 有权
公开(公告)号：US11959438B2
公开(公告)日：2024-04-16
申请号：US17678583
申请日：2022-02-23
申请人： Medhat Osman
发明人： Medhat Osman
IPC分类号： F02K1/44 , F02K1/60 , F02K1/76
CPC分类号： F02K1/44 , F02K1/605 , F02K1/766
摘要： A thrust reverser system for jet aircraft comprising an exhaust tailpipe mounted to the turbine engine aft turbine flange and two clamshell doors, actuators and a locking system to prevent inadvertent deployment of the clamshell doors in-flight. Two improved design clamshell doors configurations, either one or a combination of both, mounted on either side of the top and bottom of the exhaust tailpipe, fitted with two patented design actuators mounted one on each side of the external sides of the tailpipe between the clamshell doors and the tailpipe, possibly in a depression in the tailpipe called blister, assuming them to be hydraulic actuators for discussion purposes. The actuators drive the clamshell doors using improved floating linkages loosely pivoted to the exterior of the exhaust tailpipe. The actuators are connected to the doors through mechanical linkages, to deploy the doors aft of the tailpipe exhaust area during deceleration after landing, diverting the exhaust gases forward to slow down the aircraft, and the actuators also drive two movable fairings during thrust reverser operation to enclose the reversed exhaust flow forward to prevent its impingement on the skin of the aircraft and provide a ram inlet area with the sides of the clamshell doors allowing ram air from the surrounding free stream to be scooped through the gap between the movable fairing and clamshell doors thereby provide cooling of the door surface in contact with the exhaust gases and mix with the engine exhaust gases in reverse thrust mode thereby augmenting reverse thrust mass flow and energy. The exhaust tailpipe can have a circular or any geometric exhaust section or in other configuration can be fitted in with a flow mixer with the surrounding ambient air to reduce shear noise resulting from the high velocity exhaust gases for noise attenuation. The flow mixer can also be perforated to allow for suction of ambient air by the lower static pressure engine exhaust gases to reduce shear noise and increase mixing and thrust. Two fixed fairings, above and below the tailpipe at the exit section can have perforations and also perforations on the movable fairings to educt surrounding air also to reduce shear noise between surrounding air and the engine exhaust flow during forward thrust based on SAE Aerospace Information Report AIR-1191 and method of calculation. Other configurations for the trailing edges of the fixed and movable fairings can have wavy contour lines to increase the contact area between the engine exhaust gases and the surrounding air to reduce shear noise as well. Fixed circular shape or rolling bodies, depicted as wheels for discussion purpose, but they can be of any shape, mounted on the top and bottom of the tailpipe at the forward end which get lodged in the upper and lower forward frames of the clamshell doors in the stow position to provide one of the mechanical locking systems. A second mechanical locking system is a high strength compression steel spring which is part of the linkages used to deploy and stow the clamshell doors, which at the end of the stow stroke is buckled to prevent the clamshell doors deploy mechanism from moving, thereby keeping the doors securely stowed. A third locking mechanism consisting of electrically actuated locks which engage the clamshell doors in the stow position and lock the movable fairings to prevent them from being entrained by the free stream during flight.

2. 发明公开

US20230213001A1 ULTRA QUIET SPLIT FLOW THRUST REVERSER 审中-公开
公开(公告)号：US20230213001A1
公开(公告)日：2023-07-06
申请号：US17678583
申请日：2022-02-23
申请人： Medhat Osman
发明人： Medhat Osman
IPC分类号： F02K1/44 , F02K1/60
CPC分类号： F02K1/44 , F02K1/605
摘要： A thrust reverser system for jet aircraft comprising an exhaust tailpipe mounted to the turbine engine aft turbine flange, clamshell doors, actuators and locking systems to prevent inadvertent deployment of the clamshell doors. Improved design clamshell doors shrouding the tailpipe fitted with two patented design actuators, enclosed between the doors and the tailpipe. The actuators throw the doors behind the tailpipe exhaust exit area using improved linkages attached to the tailpipe and the doors, to reverse the exhaust gases forward. The tailpipe can be of circular or any geometric shape. Reverse Exhaust gases are enclosed between the doors and two movable fairings. Several sound attenuation configurations provisions for the tailpipe, the fixed and movable fairings. Three independent locking systems provisions to prevent inadvertent deployment of the doors.

3. 发明授权

US08579078B2 Acoustic panel for a turbojet engine nacelle, with in-built fasteners 失效
标题翻译：用于涡轮喷气发动机机舱的隔音板，内置紧固件
公开(公告)号：US08579078B2
公开(公告)日：2013-11-12
申请号：US13749215
申请日：2013-01-24
申请人： Aircelle
发明人： Herve Hurlin , Nicolas Dezeustre , Wouter Balk , Bertrand Desjoyeaux
IPC分类号： E04B1/82
CPC分类号： B32B3/10 , B64D33/02 , B64D33/06 , B64D2033/0206 , B64D2033/0286 , F01D25/243 , F01D25/28 , F02C7/045 , F02K1/44 , F02K1/827 , F05B2260/301 , F05D2220/36 , F05D2250/283 , F05D2300/603 , G10K11/172 , Y02T50/672
摘要： An acoustic panel is provided that includes at least one cellular core arranged between at least an internal skin and an external skin, wherein the external skin incorporates at least one fastener able to collaborate in a disconnectable fashion with a complementary fastener associated with a structure to which it is to be attached.
摘要翻译：提供一种声学面板，其包括布置在至少内部皮肤和外部皮肤之间的至少一个细胞芯，其中所述外部皮肤包括至少一个紧固件，所述至少一个紧固件能够以可断开的方式与与其结构相关联的互补的紧固件协作它是附加的。

4. 发明申请

US20120240587A1 NOISE REDUCTION SYSTEM 有权
标题翻译：噪声减少系统
公开(公告)号：US20120240587A1
公开(公告)日：2012-09-27
申请号：US13504195
申请日：2010-10-26
申请人： Nozomi Tanaka , Shinya Kusuda , Tsutomu Oishi , Yoshinori Oba
发明人： Nozomi Tanaka , Shinya Kusuda , Tsutomu Oishi , Yoshinori Oba
IPC分类号： F02K1/34
CPC分类号： F02K1/34 , F02C6/08 , F02K1/38 , F02K1/44 , F02K1/46 , F02K1/52 , F05D2220/323 , F05D2260/96
摘要： A noise reduction system includes: a microjet ring (16) provided at an exhaust side peripheral edge of a main nozzle of a jet engine, and has a plurality of injection pipes (26) formed in a circumferential direction thereof at regular intervals; and a supply path configured to take part of compressed air in from a flow path in an upstream side of a combustor in the jet engine, and to guide the part of compressed air to the plurality of injection pipes (26), wherein the plurality of injection pipes (26) is configured to inject the part of compressed air to a jet flow.
摘要翻译：一种降噪系统，包括：设置在喷气发动机的主喷嘴的排气侧周边的微喷射环（16），并且具有以规定间隔沿圆周方向形成的多个喷射管（26）以及供给路径，被构造成从喷气发动机的燃烧器的上游侧的流路中取出一部分压缩空气，并将压缩空气的一部分引导到多个喷射管（26），其中，喷射管（26）构造成将一部分压缩空气喷射到喷射流。

5. 发明授权

US08047004B2 Stave and ring CMC nozzle 有权
标题翻译：梯形和环形CMC喷嘴
公开(公告)号：US08047004B2
公开(公告)日：2011-11-01
申请号：US12030112
申请日：2008-02-12
申请人： John Joseph Brown , William Preston Keith
发明人： John Joseph Brown , William Preston Keith
IPC分类号： F02K1/00 , F02C7/20 , F02C1/00
CPC分类号： F02K1/80 , F01D25/243 , F02K1/44 , F02K1/822 , F05D2230/61 , F05D2300/21 , Y02T50/672 , Y02T50/675
摘要： An engine exhaust nozzle comprises a plurality of CMC staves attached to one or more support rings arranged axially. The support rings provide a circumferential load path between the staves and for attaching the exhaust nozzle to the metallic engine components. The staves are fixed to the support rings with a spacing intended to accommodate for relative movement due to the difference in CTE for the CMC and metallic components and due to thermal gradients through the wall thickness. The resulting apparatus is lightweight, relieves the nozzle of thermal stresses, and is easier to manufacture and repair.
摘要翻译：发动机排气喷嘴包括连接到轴向布置的一个或多个支撑环的多个CMC条。支撑环提供了板条之间的周向负载路径，并且用于将排气喷嘴附接到金属发动机部件。由于CMC和金属部件的CTE差异以及通过壁厚度的热梯度，板条固定到支撑环上，间距用于适应相对运动。所得到的装置重量轻，减轻喷嘴的热应力，并且更容易制造和修理。

6. 发明授权

US07753311B2 Propulsion system, aircraft comprising the propulsion system and an outlet device for a jet engine 失效
标题翻译：推进系统，包括推进系统的飞行器和用于喷气发动机的出口装置
公开(公告)号：US07753311B2
公开(公告)日：2010-07-13
申请号：US11718430
申请日：2005-10-20
申请人： Bernhard Gustafsson
发明人： Bernhard Gustafsson
IPC分类号： B64D33/04
CPC分类号： F02K1/44 , B64D33/04 , B64D2033/045 , F02C7/04 , F02K1/52 , F02K1/78 , F02K1/825 , F02K3/12 , F05D2250/25 , F05D2250/312 , F05D2250/33
摘要： A propulsion system for a craft includes two jet engines which are arranged parallel to one another. The system further includes an inlet and/or outlet device for each jet engine. Each device includes a duct for carrying a gas, the duct having a gas inlet and a gas outlet. The gas outlet is arranged offset in relation to the gas inlet transversely to the longitudinal direction of the duct, so that the jet engine is hidden from external view.
摘要翻译：用于工艺的推进系统包括彼此平行布置的两个喷气发动机。该系统还包括用于每个喷气发动机的入口和/或出口装置。每个装置包括用于承载气体的管道，该管道具有气体入口和气体出口。气体出口被布置成相对于气体入口横向于管道的纵向方向偏移，使得喷气发动机从外部看不见。

7. 发明授权

US07581692B2 Fluidic chevrons and configurable thermal shield for jet noise reduction 有权
标题翻译：流动人字形和可配置的热屏蔽，用于降低喷射噪音
公开(公告)号：US07581692B2
公开(公告)日：2009-09-01
申请号：US10610718
申请日：2003-06-30
申请人： Paolo Graziosi , Kevin Kirtley , Ramani Mani
发明人： Paolo Graziosi , Kevin Kirtley , Ramani Mani
IPC分类号： B64C1/40
CPC分类号： F02K1/48 , F02K1/34 , F02K1/44 , F02K1/827 , F05D2260/96
摘要： A system for jet engine noise control of a jet engine having a main jet stream exiting an exhaust nozzle and flowing along a jet axis includes a thermal acoustic shield directed at a non-zero angle relative to the jet axis. The thermal acoustic shield may be configurable about the main jet stream. The system may further include at least a fluidic chevron injected at a location relative to the nozzle exit for enhancing mixing in the main jet stream and creating a non-circular jet stream.
摘要翻译：用于具有离开排气喷嘴并沿喷流轴流动的主喷流的喷气发动机的喷气发动机噪声控制系统包括相对于喷射轴线以非零角度定向的热声屏蔽。热声屏蔽可以围绕主喷射流配置。该系统还可以包括至少一个在相对于喷嘴出口的位置处喷射的流体人字形，用于增强主喷射流中的混合并产生非圆形喷射流。

8. 发明授权

US07311175B2 Acoustic liner with bypass cooling 有权
标题翻译：隔音带旁路冷却
公开(公告)号：US07311175B2
公开(公告)日：2007-12-25
申请号：US11200617
申请日：2005-08-10
申请人： William Proscia , Christopher D. Jones
发明人： William Proscia , Christopher D. Jones
IPC分类号： E04B1/82 , B64C1/40 , B64C1/38
CPC分类号： F01D25/30 , F02C7/045 , F02C7/24 , F02K1/44 , F02K1/827 , F02K3/10 , F05D2260/96 , F23M20/005 , G10K11/172
摘要： An acoustic liner 20 includes a remote panel 26, a proximate panel 28 transversely spaced from the remote panel and a resonator chamber 34b residing between the panels. Perforations 38 penetrate the proximate panel in registration with the resonator chamber 34b. A neck 56 with an inlet 58 recessed from the proximate panel establishes communication between the chamber and a fluid stream G flowing past the proximate panel. A bypass coolant passage 66 guides coolant through the perforations without guiding it through the resonator chamber.
摘要翻译：声学衬垫20包括远程面板26，与远程面板横向间隔开的邻近面板28和驻留在面板之间的谐振室34b。穿孔38穿过与谐振腔34b对准的邻近面板。具有从邻近面板凹入的入口58的颈部56建立腔室与流过邻近面板的流体流G之间的连通。旁路冷却剂通道66引导冷却剂穿过穿孔而不引导冷却剂通过谐振腔。

9. 发明授权

US06969028B2 Scarf nozzle for a jet engine and method of using the same 有权
标题翻译：用于喷气发动机的围巾喷嘴及其使用方法
公开(公告)号：US06969028B2
公开(公告)日：2005-11-29
申请号：US10351159
申请日：2003-01-22
申请人： Roy Dun
发明人： Roy Dun
IPC分类号： B64D33/04 , F02K1/44 , F02K1/52 , B64D27/00
CPC分类号： B64C7/02 , B64D33/04 , F02K1/44 , F02K1/52 , Y02T50/671
摘要： A scarf nozzle for a jet engine supported within a nacelle. The scarf nozzle is at an aft end of the nacelle. The scarf nozzle includes a first trailing edge portion and a second trailing edge portion. The second trailing edge portion is disposed aft of the first trailing edge portion. The scarf nozzle is configured to allow the nacelle to be integrated closer to a wing without adversely affecting the pressure gradient between the nacelle and the wing. The scarf nozzle allows a portion of an exhaust plume exiting the aft end of the nacelle to interact more favorably with an airflow along one or more surfaces adjacent the nacelle, thus delaying the onset of adverse pressure gradients and the formation of shock waves between the nacelle and the adjacent surfaces and between the adjacent surfaces and the exhaust plume.
摘要翻译：用于支撑在机舱内的喷气发动机的围巾喷嘴。围巾喷嘴位于机舱的后端。围巾喷嘴包括第一后缘部分和第二后缘部分。第二后缘部分设置在第一后缘部分的后方。围巾喷嘴构造成允许机舱更靠近机翼集成，而不会不利地影响机舱和机翼之间的压力梯度。围巾喷嘴允许离开机舱的后端的一部分排气羽流与沿着机舱相邻的一个或多个表面的气流更有利地相互作用，从而延迟不利压力梯度的开始和在机舱之间形成冲击波和相邻表面之间以及相邻表面和排气羽流之间。

10. 发明申请

US20050150207A1 FLUIDIC DIVERTER VALVE WITH A VARIABLE VALVE-BORE CLEARANCE 失效
标题翻译：具有可变阀芯间隙的流体流量阀
公开(公告)号：US20050150207A1
公开(公告)日：2005-07-14
申请号：US10732932
申请日：2003-12-10
申请人： Donald Christensen
发明人： Donald Christensen
IPC分类号： F02K1/44 , F02K9/80 , F02K9/88 , F16K11/056 , F02K1/00
CPC分类号： F42B10/663 , F02K1/44 , F02K9/805 , F02K9/88 , F05D2270/18 , F16K11/056 , Y10T137/2218 , Y10T137/87788
摘要： A fluidic diverter valve includes valve element freely disposed within a valve bore. The valve bore has a cross sectional area that varies. As a result, the clearance between the valve element and an inner surface of the valve bore also varies. This variation in cross sectional area, and thus clearance, is such that a force of sufficient magnitude to move the valve element from a seated position is initially applied to the valve element, but the force on the valve element is reduced once it is moved from the seated position. Thus, the impact force upon attaining another seated position is reduced.
摘要翻译：流体分流阀包括自由地设置在阀孔内的阀元件。阀孔具有变化的横截面积。结果，阀元件与阀孔的内表面之间的间隙也变化。这种横截面积的变化以及因此的间隙使得足够大的力将阀元件从就座位置移动的力最初被施加到阀元件，但是当阀元件从就座位置。因此，达到另一个就座位置时的冲击力降低。

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