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1. 发明申请

US20130055718A1 DEVICE FOR REDUCING THE NOISE EMITTED BY THE JET OF AN AIRCRAFT PROPULSION ENGINE 有权
标题翻译：用于减少由飞机推进发动机喷射的噪音的装置
公开(公告)号：US20130055718A1
公开(公告)日：2013-03-07
申请号：US13696821
申请日：2011-05-11
申请人： Guillaume Bodard , Alexandre Alfred Gaston Vuillemin
发明人： Guillaume Bodard , Alexandre Alfred Gaston Vuillemin
IPC分类号： F02K1/34 , F02C7/00
CPC分类号： F02K1/34 , F02K1/46 , F05D2240/40 , F05D2250/11 , F05D2250/13 , F05D2260/96
摘要： A gas exhaust nozzle for aircraft propulsion includes at least a downstream part with a trailing edge of chevron type formed of chevrons distributed along the periphery of the nozzle. Each chevron extends downstream between an upstream transverse plane and a downstream transverse plane with free edges oriented in two converging downstream directions and defining the trailing edge. The chevrons generate vortices at the boundary of the jet emitted by the nozzle. The gas exhaust nozzle includes a device to inject auxiliary gas jets upstream of the free edges of the chevrons in the main jet through orifices placed upstream of the upstream plane in such a way as to discharge upstream of the upstream plane of the chevrons to generate the vortices upstream of the free edges of the chevrons.
摘要翻译：用于飞行器推进的排气喷嘴至少包括具有由沿着喷嘴的周边分布的人字形形成的人字形的后缘的下游部分。每个人字形在上游横向平面和下游横向平面之间的下游延伸，其中自由边缘在两个会聚的下游方向上定向并限定后缘。人字纹在喷嘴发射的喷嘴的边界处产生涡流。气体排气喷嘴包括一个装置，用于通过设置在上游平面上游的孔口在主射流中的人字形自由边缘的上游注入辅助气体喷射，以便在人字形的上游平面的上游排放，以产生漩涡在人字纹的自由边缘的上游。

2. 发明申请

US20090084111A1 TURBOMACHINE NOZZLE COWL HAVING JET NOISE REDUCTION PATTERNS 审中-公开
标题翻译：涡轮喷嘴具有喷射噪声减少模式
公开(公告)号：US20090084111A1
公开(公告)日：2009-04-02
申请号：US12210533
申请日：2008-09-15
申请人： Sebastien Jean-Paul AEBERLI , Pierre Philippe Marie Loheac , Stephane Jacques Francois Thomas , Alexandre Alfred Gaston Vuillemin , Kamel Zeggai
发明人： Sebastien Jean-Paul AEBERLI , Pierre Philippe Marie Loheac , Stephane Jacques Francois Thomas , Alexandre Alfred Gaston Vuillemin , Kamel Zeggai
IPC分类号： F02K1/44 , F01N1/08 , F01N1/14
CPC分类号： F02K1/386 , F02K1/48 , F02K3/06 , F05D2250/16
摘要： The invention relates to a cowl for a turbomachine nozzle, the cowl including a plurality of repetitive patterns disposed to extend a trailing edge of said cowl and spaced circumferentially apart from one another. Each pattern is in the form of a quadrilateral having a base that is formed by a portion of the trailing edge of the cowl and two vertices that are spaced downstream from the base and that are connected thereto via two sides, each side having the shape of a parabola. Each pattern is asymmetrical relative to a midplane of the pattern containing a longitudinal axis of said cowl, and it comprises a first portion inclined radially towards the inside of the cowl, and a second portion inclined radially towards the outside of the cowl.
摘要翻译：本发明涉及一种用于涡轮机喷嘴的整流罩，整流罩包括多个重复图案，其设置成延伸所述整流罩的后缘并且彼此周向地间隔开。每个图案是四边形的形式，其具有由整流罩的后缘的一部分形成的基部和两个顶点，该顶点与底座间隔开并且经由两侧与其连接，每个侧面的形状为抛物线每个图案相对于包含所述整流罩的纵向轴线的图案的中平面是不对称的，并且其包括朝向罩的内部径向倾斜的第一部分和朝向罩的外部径向倾斜的第二部分。

3. 发明授权

US08827199B2 Turboshaft engine supporting pylon covered with a porous material and turboshaft engine/pylon assembly 有权
标题翻译：涡轮轴发动机支撑塔覆盖有多孔材料和涡轮轴发动机/塔架组件
公开(公告)号：US08827199B2
公开(公告)日：2014-09-09
申请号：US13636864
申请日：2011-03-21
申请人： Sebastien Jean-Paul Aeberli , Alexandre Alfred Gaston Vuillemin
发明人： Sebastien Jean-Paul Aeberli , Alexandre Alfred Gaston Vuillemin
IPC分类号： B64C1/40 , B64C23/00 , B64D27/00 , F02K1/34 , B64D29/02
CPC分类号： B64D33/06 , B64D29/02
摘要： A turboshaft engine supporting pylon covered with a porous material and a turboshaft engine/pylon assembly. The pylon supports a turboshaft engine on an aircraft, and includes an outer surface covered at least partially with a porous material to reduce amplitude of acoustic waves leaving the turboshaft engine. The assembly includes a turboshaft engine and a pylon, in which the pylon extends longitudinally from upstream to downstream and includes an upper part for securing to the aircraft, a lower part for securing to the turboshaft engine, and an absorption part extending in an exhaust stream from the turboshaft engine and including an internal absorption part extending inside the turboshaft engine and an external absorption part extending downstream of the turboshaft engine. The outer surface of the upstream end of the external absorption part of the pylon is covered with a porous material to limit noise formation downstream of the engine.
摘要翻译：支撑多孔材料的涡轮轴发动机支撑塔和涡轮轴发动机/塔架组件。塔架支撑飞机上的涡轮轴发动机，并且包括至少部分地被多孔材料覆盖的外表面，以减小离开涡轮轴发动机的声波的振幅。组件包括涡轮轴发动机和塔架，其中塔架从上游到下游纵向延伸，并且包括用于固定到飞机的上部，用于固定到涡轮轴发动机的下部和在排气流中延伸的吸收部分并且包括在所述涡轮轴发动机内部延伸的内部吸收部以及在所述涡轮轴发动机的下游延伸的外部吸收部。托架的外部吸收部分的上游端的外表面被多孔材料覆盖以限制发动机下游的噪声形成。

4. 发明申请

US20130009002A1 TURBOSHAFT ENGINE SUPPORTING PYLON COVERED WITH A POROUS MATERIAL AND TURBOSHAFT ENGINE/PYLON ASSEMBLY 有权
标题翻译：涡轮发动机支撑着多孔材料和涡轮发动机/ PYLON总成的PYLON
公开(公告)号：US20130009002A1
公开(公告)日：2013-01-10
申请号：US13636864
申请日：2011-03-21
申请人： Sébastien Jean-Paul Aeberli , Alexandre Alfred Gaston Vuillemin
发明人： Sébastien Jean-Paul Aeberli , Alexandre Alfred Gaston Vuillemin
IPC分类号： B64C1/40 , B64D27/26
CPC分类号： B64D33/06 , B64D29/02
摘要： A turboshaft engine supporting pylon covered with a porous material and a turboshaft engine/pylon assembly. The pylon supports a turboshaft engine on an aircraft, and includes an outer surface covered at least partially with a porous material to reduce amplitude of acoustic waves leaving the turboshaft engine. The assembly includes a turboshaft engine and a pylon, in which the pylon extends longitudinally from upstream to downstream and includes an upper part for securing to the aircraft, a lower part for securing to the turboshaft engine, and an absorption part extending in an exhaust stream from the turboshaft engine and including an internal absorption part extending inside the turboshaft engine and an external absorption part extending downstream of the turboshaft engine. The outer surface of the upstream end of the external absorption part of the pylon is covered with a porous material to limit noise formation downstream of the engine.
摘要翻译：支撑多孔材料的涡轮轴发动机支撑塔和涡轮轴发动机/塔架组件。塔架支撑飞机上的涡轮轴发动机，并且包括至少部分地被多孔材料覆盖的外表面，以减小离开涡轮轴发动机的声波的振幅。组件包括涡轮轴发动机和塔架，其中塔架从上游到下游纵向延伸，并且包括用于固定到飞机的上部，用于固定到涡轮轴发动机的下部和在排气流中延伸的吸收部分并且包括在所述涡轮轴发动机内部延伸的内部吸收部以及在所述涡轮轴发动机的下游延伸的外部吸收部。托架的外部吸收部分的上游端的外表面被多孔材料覆盖以限制发动机下游的噪声形成。

5. 发明申请

US20090064658A1 BYPASS TURBOMACHINE WITH REDUCTION OF JET NOISE 有权
标题翻译：旁路涡轮减少喷气机噪音
公开(公告)号：US20090064658A1
公开(公告)日：2009-03-12
申请号：US12188472
申请日：2008-08-08
申请人： Bruno Albert Beutin , Jacky Raphael Michel Derenes , Frederic Paul Eichstadt , Alexandre Alfred Gaston Vuillemin
发明人： Bruno Albert Beutin , Jacky Raphael Michel Derenes , Frederic Paul Eichstadt , Alexandre Alfred Gaston Vuillemin
IPC分类号： F02K1/34 , F02K3/02
CPC分类号： F02K1/34 , F02K1/46 , F02K1/72 , F05D2260/96
摘要： In a bypass turbomachine, at least one air takeoff orifice is provided in the primary channel, said orifice leading to an air takeoff pipe housed inside an air inlet sleeve of the nacelle. The air takeoff pipe opens out in the vicinity of the pylon into two air diffusion pipes each secured to a respective maintenance cover, each air diffusion pipe opening out into an air injection pipe secured to a thrust reverser cover and itself opening out to the outside of the nacelle via the trailing edge thereof, each air injection pipe being suitable for uncoupling from the corresponding air diffusion pipe when the corresponding thrust reverser cover slides downstream.
摘要翻译：在旁路涡轮机中，在主通道中设置有至少一个空气引出孔，所述孔通向容纳在机舱的空气入口套筒内的空气取出管。空气引出管在塔架附近通入两个空气扩散管，每个空气扩散管固定到相应的维护盖上，每个空气扩散管通向一个空气注入管，该空气注入管固定在推力反向器盖上，机舱经由其后缘，每个空气喷射管适合于当相应的推力反向器盖向下游滑动时与相应的空气扩散管解耦。

6. 发明申请

US20130115083A1 TURBINE ENGINE HAVING TWO UNDUCTED PROPELLERS 审中-公开
标题翻译：具有两台发动机的涡轮发动机
公开(公告)号：US20130115083A1
公开(公告)日：2013-05-09
申请号：US13810833
申请日：2011-07-13
申请人： Alexandre Alfred, Gaston Vuillemin
发明人： Alexandre Alfred, Gaston Vuillemin
IPC分类号： F04D19/02
CPC分类号： F04D19/024 , B64C11/003 , B64C11/06 , B64C11/306 , B64C11/48 , B64D2027/026 , F02K3/072 , F04D29/324 , F04D29/362 , F04D29/666 , Y02T50/66
摘要： A turbine engine including two outer coaxial counter-rotating unducted propellers, of an upstream propeller and a downstream propeller, respectively. The blades of the downstream propeller are retractable in the lengthwise direction thereof so as to reduce the diameter of the propeller. The reduction in the diameter of the downstream propeller makes it possible to reduce noise caused by vortices generated by the upstream propeller.
摘要翻译：一种涡轮发动机，分别包括上游螺旋桨和下游螺旋桨的两个外部同轴反向旋转的未被牵引的螺旋桨。下游螺旋桨的叶片在其长度方向可缩回，以减小螺旋桨的直径。下游螺旋桨的直径的减小使得可以减少由上游螺旋桨产生的涡流引起的噪声。

7. 发明申请

US20130043343A1 METHOD OF PROCESSING ACOUSTIC WAVES EMITTED AT THE OUTLET OF A TURBO ENGINE OF AN AIRCRAFT WITH A DIELECTRIC-BARRIER DISCHARGE DEVICE AND AIRCRAFT COMPRISING SUCH A DEVICE 有权
标题翻译：在具有电介质障碍物放电装置的飞机的涡轮发动机出口处发射的声波的方法和包含这种装置的飞机
公开(公告)号：US20130043343A1
公开(公告)日：2013-02-21
申请号：US13643382
申请日：2011-04-18
申请人： Alexandre Alfred Gaston Vuillemin
发明人： Alexandre Alfred Gaston Vuillemin
IPC分类号： B64C1/40 , H01T23/00
CPC分类号： G10K11/1788 , B64C1/40 , B64C7/02 , B64C23/005 , B64C2220/00 , B64C2230/12 , B64C2230/14 , B64D33/06 , B64D2033/0206 , B64D2033/0286 , G10K11/178
摘要： A method of processing acoustic waves emitted at an outlet of a turbo engine of an aircraft with a dielectric barrier discharge device, and an aircraft including such a device. The method includes activating the dielectric barrier discharge device so as to emit an electric wind in a direction of acoustic waves so as to attenuate the acoustic waves. An aircraft can include such a dielectric barrier discharge device.
摘要翻译：一种处理在具有电介质阻挡物排出装置的飞行器的涡轮发动机的出口处发出的声波的方法，以及包括这种装置的飞机。该方法包括激活介质阻挡放电装置，以便在声波方向上发出电风，以衰减声波。飞机可以包括这种介电阻挡放电装置。

8. 发明授权

US08037687B2 Bypass turbomachine with reduction of jet noise 有权
标题翻译：绕过涡轮机，减少喷气噪音
公开(公告)号：US08037687B2
公开(公告)日：2011-10-18
申请号：US12188472
申请日：2008-08-08
申请人： Bruno Albert Beutin , Jacky Raphael Michel Derenes , Frederic Paul Eichstadt , Alexandre Alfred Gaston Vuillemin
发明人： Bruno Albert Beutin , Jacky Raphael Michel Derenes , Frederic Paul Eichstadt , Alexandre Alfred Gaston Vuillemin
IPC分类号： F02K3/02
CPC分类号： F02K1/34 , F02K1/46 , F02K1/72 , F05D2260/96
摘要： In a bypass turbomachine, at least one air takeoff orifice is provided in the primary channel, said orifice leading to an air takeoff pipe housed inside an air inlet sleeve of the nacelle. The air takeoff pipe opens out in the vicinity of the pylon into two air diffusion pipes each secured to a respective maintenance cover, each air diffusion pipe opening out into an air injection pipe secured to a thrust reverser cover and itself opening out to the outside of the nacelle via the trailing edge thereof, each air injection pipe being suitable for uncoupling from the corresponding air diffusion pipe when the corresponding thrust reverser cover slides downstream.
摘要翻译：在旁路涡轮机中，在主通道中设置有至少一个空气引出孔，所述孔通向容纳在机舱的空气入口套筒内的空气取出管。空气引出管在塔架附近通入两个空气扩散管，每个空气扩散管固定到相应的维护盖上，每个空气扩散管通向一个空气注入管，该空气注入管固定在推力反向器盖上，机舱经由其后缘，每个空气喷射管适合于当相应的推力反向器盖向下游滑动时与相应的空气扩散管解耦。

9. 发明授权

US07827802B2 Variable-section flow mixer for a double-flow turbojet for a supersonic airplane 有权
标题翻译：用于超音速飞机的双流涡轮喷气发动机的可变截面流量混合器
公开(公告)号：US07827802B2
公开(公告)日：2010-11-09
申请号：US12020242
申请日：2008-01-25
申请人： Laurent Christophe Dussillols , Olivier Roland Longeville , Alexandre Alfred Gaston Vuillemin
发明人： Laurent Christophe Dussillols , Olivier Roland Longeville , Alexandre Alfred Gaston Vuillemin
IPC分类号： F02K1/00
CPC分类号： F02K1/383 , F05D2250/15 , Y02T50/671
摘要： The invention relates to a variable-section flow mixer for a double-flow turbojet for a supersonic airplane, the mixer comprising a central body, a primary cover, a secondary cover, and a nozzle extending the secondary cover. The nozzle has a plurality of external-air admission openings having mounted therein lobes that are movable between two positions: a closed position in which they close the openings; and a deployed position in which they disengage said openings and deploy into the nozzle so as to allow external air to be admitted. All of the lobes present a common azimuth component in a common direction, and the mixer further includes a plurality of longitudinal grooves occupying at least a portion of the central body, all of the grooves presenting a common azimuth component in a common direction that is opposite to the direction of the azimuth component of the lobes.
摘要翻译：本发明涉及一种用于超音速飞机的双流涡轮喷气发动机的可变截面流动混合器，该混合器包括中央主体，主盖，辅助盖和延伸辅助盖的喷嘴。喷嘴具有多个外部空气进入口，其中安装有可在两个位置之间移动的凸角：关闭位置，在该关闭位置，它们关闭开口; 以及展开位置，在该展开位置中，它们脱离所述开口并且展开到喷嘴中，以允许外部空气进入。所有的叶片在共同的方向上呈现共同的方位角分量，并且混合器还包括占据中心体的至少一部分的多个纵向凹槽，所有的凹槽在共同的方向上呈现相反的共同方位分量到叶片的方位角分量的方向。

10. 发明授权

US07810335B2 Core exhaust mixer, having a variable area, for turbo-fan jet engines of supersonic aircraft 有权
标题翻译：具有可变区域的核心排气混合器，用于超音速飞机的涡轮风扇喷气发动机
公开(公告)号：US07810335B2
公开(公告)日：2010-10-12
申请号：US11620295
申请日：2007-01-05
申请人： Laurent Dussillols , Alexandre Alfred Gaston Vuillemin
发明人： Laurent Dussillols , Alexandre Alfred Gaston Vuillemin
IPC分类号： F02K1/00
CPC分类号： F02K1/383 , F02K1/36 , F05D2260/96 , Y02T50/671
摘要： The invention relates to a core exhaust mixer, having a variable area, for turbo-fan jet engines of supersonic aircraft, comprising a nozzle (24) intended to be arranged about a gas generator of the jet engine, the nozzle comprising a plurality of external air intake apertures (30) emerging in a convergence zone between cold and hot flows from the gas generator and in which lobes (32), movable between two positions, are mounted; a first position in which they block the apertures (30) of the nozzle (24) and a second position, different from the first, in which they unblock said apertures and extend radially into the nozzle (24) in order to admit external air, the lobes (32) having an azimuthal component in the same direction in order to give a swirling motion to the external air admitted into the convergence zone when the lobes are in the second position.
摘要翻译：本发明涉及一种用于超音速飞行器的涡轮风扇喷气发动机的具有可变区域的排气混合器，其包括旨在围绕喷气发动机的气体发生器布置的喷嘴（24），所述喷嘴包括多个外部出现在冷和热之间的会聚区中的进气孔（30）从气体发生器流出并且其中可安装在两个位置之间的凸角（32）; 第一位置，其阻挡喷嘴（24）的孔（30）和不同于第一位置的第二位置，在该第二位置，它们解锁所述孔并径向延伸到喷嘴（24）中以便允许外部空气，叶片（32）具有相同方向的方位角分量，以便当叶片处于第二位置时，向进入会聚区域的外部空气产生旋转运动。

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