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41. 发明申请

US20120073262A1 AIR DISCHARGING DEVICE FOR AN AIRCRAFT DOUBLE-FLOW TURBINE ENGINE 有权
标题翻译：用于飞机双流涡轮发动机的空气排放装置
公开(公告)号：US20120073262A1
公开(公告)日：2012-03-29
申请号：US13235706
申请日：2011-09-19
申请人： Guillaume BULIN , Thierry Surply
发明人： Guillaume BULIN , Thierry Surply
IPC分类号： F02K3/02
CPC分类号： F02K1/70 , B64D29/00 , F02K1/12 , F02K1/827 , Y02T50/671
摘要： An air discharging device (20) for an aircraft turbine engine, comprising at least one door (24) displaceable between an open and a closed position of a corresponding orifice (30) and comprising two valves (26, 28), which delimit between them a conduit (68) for guiding a portion (74) of the secondary flow (76) outwards in the downstream direction, and which are integral with each other and are hinged around a pivot axis (58), so that in said open position, the upstream end of said internal valve (26) protrudes from the inner side relative to the internal surface (12), the downstream end of said external valve (28) protrudes from the external side relative to the external surface (14), and said internal valve (26) is spaced away from the fixed structure (22) so that an air passage exists downstream of said internal valve (26), between the latter and said fixed structure (22).
摘要翻译：一种用于飞行器涡轮发动机的排气装置（20），包括至少一个门（24），所述门可在对应的孔口（30）的打开和关闭位置之间移动并且包括两个阀门（26,28），其在它们之间界定用于沿下游方向向外引导二次流（76）的一部分（74）并彼此成一体并围绕枢转轴线（58）铰接的导管（68），使得在所述打开位置，所述内阀（26）的上游端相对于内表面（12）从内侧突出，所述外阀（28）的下游端相对于外表面（14）从外侧突出，并且所述内部阀（26）与固定结构（22）间隔开，使得在所述内部阀（26）的下游，后者和所述固定结构（22）之间存在空气通道。

42. 发明申请

US20120055169A1 TURBINE ENGINE COMPRISING AN EXHAUST-GAS GUIDE CONE WITH A SOUND SUPPRESSOR 审中-公开
标题翻译：涡轮发动机，包括一个排气管导向锥与声压抑制器
公开(公告)号：US20120055169A1
公开(公告)日：2012-03-08
申请号：US13319125
申请日：2010-05-27
申请人： Eric Jean-Louis Bouty , Pierre-Luc Regaud , Antoine Vallon
发明人： Eric Jean-Louis Bouty , Pierre-Luc Regaud , Antoine Vallon
IPC分类号： F02C3/10
CPC分类号： F02K1/827 , Y02T50/671
摘要： A gas turbine engine, in which gases flow upstream to downstream, including a combustion chamber, a high-pressure turbine placed downstream from the combustion chamber, arranged so as to receive combustion gases from the combustion chamber, a free turbine, and an exhaust-gas guide cone attached to the free turbine downstream from the free turbine, the turbine engine emitting sound waves during operation. The guide cone includes a sound suppressor, for example with a Helmholtz resonator structure, with a resonant cavity and a resonator neck in communication with an opening, arranged so as to suppress the sound waves emitted by the turbine engine.
摘要翻译：一种燃气涡轮发动机，其中气体向上游流动，包括燃烧室，位于燃烧室下游的高压涡轮机，其布置成接收来自燃烧室，自由涡轮机和排气的燃烧气体，气体导向锥连接到自由涡轮机下游的自由涡轮机，涡轮发动机在运行期间发出声波。引导锥体包括例如具有亥姆霍兹共振器结构的声抑制器，具有谐振腔和与开口连通的谐振器颈部，其布置成抑制涡轮发动机发出的声波。

43. 发明授权

US08111832B2 Method of adjusting acoustic impedances for impedance-tunable acoustic segments 有权
标题翻译：调节阻抗可调声段的声阻抗的方法
公开(公告)号：US08111832B2
公开(公告)日：2012-02-07
申请号：US12424793
申请日：2009-04-16
申请人： Kennie H Jones , Douglas M. Nark , Michael G. Jones , Tony L. Parrott , Kenneth N. Lodding
发明人： Kennie H Jones , Douglas M. Nark , Michael G. Jones , Tony L. Parrott , Kenneth N. Lodding
IPC分类号： G10K11/16
CPC分类号： F02K1/827 , F01D17/08 , F02C7/045 , F05D2260/962 , F05D2270/70 , F05D2270/707 , G10K11/172
摘要： A method is provided for making localized decisions and taking localized actions to achieve a global solution. In an embodiment of the present invention, acoustic impedances for impedance-tunable acoustic segments are adjusted. A first acoustic segment through an N-th acoustic segment are defined. To start the process, the first acoustic segment is designated as a leader and a noise-reducing impedance is determined therefor. This is accomplished using (i) one or more metrics associated with the acoustic wave at the leader, and (ii) the metric(s) associated with the acoustic wave at the N-th acoustic segment. The leader, the N-th acoustic segment, and each of the acoustic segments exclusive of the leader and the N-th acoustic segment, are tuned to the noise-reducing impedance. The current leader is then excluded from subsequent processing steps. The designation of leader is then given one of the remaining acoustic segments, and the process is repeated for each of the acoustic segments through an (N−1)-th one of the acoustic segments.
摘要翻译：提供了一种用于进行本地化决策并采取本地化操作以实现全局解决方案的方法。在本发明的一个实施例中，调整阻抗可调谐声段的声阻抗。定义穿过第N声段的第一声段。为了开始该过程，将第一声段指定为前导，并且确定降噪阻抗。这是通过使用（i）与导频上的声波相关联的一个或多个度量，以及（ii）与第N个声音段的声波相关联的度量而完成的。引导者，第N个声音段以及排除前导和第N个声音段的每个声音段被调谐到降低噪声的阻抗。当前的领导者然后被排除在随后的处理步骤之外。然后给出领导者的指定一个剩余的声音段，并且通过第（N-1）个声音段对每个声音段重复该过程。

44. 发明申请

US20110290333A1 METHOD FOR MANUFACTURING A STRUCTURE WITH CELLULAR CORES FOR A TURBOJET NACELLE 审中-公开
标题翻译：用于制造用于涡轮喷射器的细孔结构的方法
公开(公告)号：US20110290333A1
公开(公告)日：2011-12-01
申请号：US13148057
申请日：2010-01-08
申请人： Bertrand Desjoyeaux , Thierry Deschamps , John Moutier
发明人： Bertrand Desjoyeaux , Thierry Deschamps , John Moutier
IPC分类号： F02K99/00 , B32B3/12 , B31D3/02
CPC分类号： F02C7/04 , B32B3/12 , B32B3/18 , B32B3/266 , B32B5/142 , B32B5/24 , B32B7/12 , B32B15/04 , B32B15/14 , B32B15/20 , B32B37/12 , B32B38/0012 , B32B2038/0052 , B32B2307/102 , B32B2307/50 , B32B2307/546 , B32B2307/724 , B32B2307/7242 , B32B2605/18 , F02K1/827 , G10K11/172 , Y02T50/672 , Y10T137/0536 , Y10T156/1003 , Y10T428/192 , Y10T428/24149
摘要： The invention relates to a method for manufacturing a structure with cellular cores (202) that can be used in the structural panel of a turbojet nacelle, including at least one block of cellular cores (A, B) having a central portion (5a, 5b) with core honeycomb cells (7a, 7b) and at least two side portions (9a, 9a′, 9b, 9b′) each including side honeycomb cells (11a, 11b), wherein said method includes the following steps: A) forming junction walls on the side honeycomb cells (11a, 11b), the junction walls being capable of interacting for forming a junction area (213); B) unfolding the junction walls thus formed; and C) joining the walls thus unfolded (46) and belonging to two different side portions (9a, 9b) end-to-end so that said junction walls (46) are fitted together so as to form a junction area (213). The invention also relates to a structural panel and to a nacelle including a structure with cellular cores obtained by said method.
摘要翻译：本发明涉及一种用于制造具有可用于涡轮喷气发动机舱的结构板中的多孔芯（202）的结构的方法，其包括至少一块具有中心部分（5a，5b）的多孔芯（A，B））和具有蜂窝蜂窝单元（11a，11b）的至少两个侧部（9a，9a'，9b，9b'），其中所述方法包括以下步骤：A）形成接合部侧蜂窝单元（11a，11b）上的壁，所述接合壁能够相互作用以形成接合区域（213）; B）展开如此形成的接合壁; 并且C）将如此展开的壁（46）接合并且端对端地属于两个不同的侧部（9a，9b），使得所述接合壁（46）装配在一起以形成接合区域（213）。本发明还涉及一种结构面板以及包括通过所述方法获得的具有多孔芯的结构的机舱。

45. 发明授权

US08037967B2 Acoustic treatment device for turbine and combustion noises 有权
标题翻译：用于涡轮和燃烧噪声的声处理装置
公开(公告)号：US08037967B2
公开(公告)日：2011-10-18
申请号：US12523059
申请日：2008-01-30
申请人： Florent Mercat
发明人： Florent Mercat
IPC分类号： E04B1/82
CPC分类号： F02K1/827 , F05D2250/283 , F05D2260/96
摘要： An acoustic treatment device for an internal primary ejection duct from a turbojet pod, including an upstream zone and a downstream zone relative to an airflow direction in the primary ejection duct, the upstream and downstream zones being located on each side of a separating wall with a first face on the side of the upstream side and a second face on the side of the downstream side. The separating wall is a micro-porous wall and the face of the separating wall located on the side of the downstream side is covered by a honeycomb structure to attenuate high frequency acoustic waves. Such a device may find application to treatment of combustion and turbine noises.
摘要翻译：一种用于来自涡轮喷气发动机舱的内部主喷射管道的声学处理装置，包括相对于主喷射管道中的气流方向的上游区域和下游区域，上游区域和下游区域位于分隔壁的每一侧，具有第一面在上游侧的一侧和第二面在下游侧。分隔壁是微孔壁，位于下游侧的分隔壁的表面被蜂窝结构覆盖以衰减高频声波。这种装置可以应用于燃烧和涡轮噪声的处理。

46. 发明申请

US20110211943A1 PANELLED ASSEMBLY 审中-公开
标题翻译：面板总成
公开(公告)号：US20110211943A1
公开(公告)日：2011-09-01
申请号：US13023929
申请日：2011-02-09
申请人： Paul S. BELBECK , Paul R. WALTON , Richard H. EVANS
发明人： Paul S. BELBECK , Paul R. WALTON , Richard H. EVANS
IPC分类号： F04D29/42 , B32B3/14 , B32B37/12
CPC分类号： F01D11/12 , F02C7/045 , F02K1/827 , F02K3/06 , F04D29/164 , F04D29/526 , Y10T428/187
摘要： A panelled assembly has a spacer 26 of cuboid, or rectangular prism, shape located between adjacent first panels 16 in order to maintain separation of the panels 16 at a desired minimum distance during mounting of the panels. During installation, the spacer 26 abuts the first side edge 16b of one panel, and then the second side edge 16d of the circumferentially adjacent panel is made to abut the opposed side of the spacer. This results in an axially extending gap 28 of a constant width between adjacent first panels 16. Similarly, spacers 26 are located between adjacent second panels 18, adjacent third liner panels 20, adjacent fourth panels 22 and adjacent panels 24 as the panels are installed to make up the assembly. This results in axially extending gaps 28, each of a constant width, between circumferentially adjacent panels. The material from which the spacers are made is substantially the same as filler material which is used to fill the gaps between adjacent panels caused by the presence of the spacers. Thus the need for removal of the spacers is obviated.
摘要翻译：镶板组件具有位于相邻的第一面板16之间的立方体或矩形棱镜的间隔件26，以便在安装面板期间将面板16保持在期望的最小距离处。在安装过程中，间隔件26邻接一个面板的第一侧边缘16b，然后使周向相邻面板的第二侧边缘16d邻接间隔件的相对侧。这导致在相邻的第一面板16之间具有恒定宽度的轴向延伸间隙28.类似地，当面板安装到相邻的第一面板16之间时，间隔件26位于相邻的第二面板18之间，邻近第三衬垫面板20，相邻的第四面板22和相邻的面板24 组装大会这导致在周向相邻的板之间的轴向延伸的间隙28，每个间隙具有恒定的宽度。制造间隔件的材料与填充材料基本相同，该填充材料用于填充由间隔物的存在引起的相邻面板之间的间隙。因此，消除了对间隔物的去除的需要。

47. 发明授权

US07980357B2 Exhaust silencer for microturbines 失效
标题翻译：微型涡轮排气消音器
公开(公告)号：US07980357B2
公开(公告)日：2011-07-19
申请号：US11670669
申请日：2007-02-02
申请人： Andrew J. Edwards
发明人： Andrew J. Edwards
IPC分类号： F01N1/08 , F01N1/10 , F01N1/00
CPC分类号： F02K1/827 , F01D25/30 , F05D2250/82 , F05D2260/96
摘要： Methods, systems, and apparatuses for exhaust silencers for engines, such as microturbines, are described. An exhaust silencer reduces noise produced by an engine. While passing through an exhaust silencer, an exhaust stream from the engine makes one or more turns, thereby reducing turbine noise. An exhaust silencer includes a body, a cavity in the body, a baffle plate that partially divides the central cavity, an inlet port formed in a first surface of the body, and an outlet port formed in a second surface of the body. The inlet port is configured to receive an exhaust stream that flows through the cavity, around the baffle plate. The outlet port is configured to discharge the exhaust stream from the body.
摘要翻译：描述了诸如微型涡轮发动机的排气消音器的方法，系统和装置。排气消声器可减少发动机产生的噪音。当通过排气消声器时，来自发动机的排气流进行一个或多个匝，从而降低涡轮噪声。排气消声器包括主体，主体中的空腔，部分地分隔中心腔的挡板，形成在主体的第一表面中的入口端口和形成在主体的第二表面中的出口。入口端口被配置为接收在挡板周围流过空腔的排气流。出口端口被配置为排出来自主体的废气流。

48. 发明授权

US07784283B2 Sound-absorbing exhaust nozzle center plug 有权
标题翻译：吸音排气喷头中心插头
公开(公告)号：US07784283B2
公开(公告)日：2010-08-31
申请号：US11417274
申请日：2006-05-03
申请人： Jia Yu , Eugene W. Chien
发明人： Jia Yu , Eugene W. Chien
IPC分类号： F02K1/00
CPC分类号： F02K1/04 , F02K1/827 , F05D2230/13 , F05D2250/283 , F05D2260/96
摘要： A sound-absorbing exhaust nozzle center plug for an aircraft gas turbine engine can include an outer skin and at least one forward cavity within the outer skin. At least one aft cavity can be located within the outer skin and substantially aft of the forward cavity. A perforated wall including a plurality of first openings can be disposed between the forward and aft cavities. The outer skin can include a second plurality of openings providing an acoustic pathway through the outer skin and into the forward cavity. The forward and aft cavities can be configured to absorb and dissipate relatively low-frequency sound energy emitted from an aircraft gas turbine engine's combustor.
摘要翻译：用于飞机燃气涡轮发动机的吸声排气喷嘴中心塞可以包括外皮和外皮内的至少一个前腔。至少一个后腔可以位于外皮内并且基本上位于前腔的后方。包括多个第一开口的穿孔壁可以设置在前部和后部空腔之间。外皮可以包括第二多个开口，其提供穿过外皮并进入前腔的声学路径。前空腔和后空腔可以被配置为吸收和消散从飞机燃气涡轮发动机的燃烧器发射的相对低频的声能。

49. 发明申请

US20100155016A1 COMBINED SURFACE COOLER AND ACOUSTIC ABSORBER FOR TURBOMACHINES 有权
标题翻译：组合式表面冷却器和气动吸收器
公开(公告)号：US20100155016A1
公开(公告)日：2010-06-24
申请号：US12342466
申请日：2008-12-23
申请人： Trevor Howard Wood , Todd Garrett Wetzel , Jonathan Glenn Luedke , Thomas Michael Tucker
发明人： Trevor Howard Wood , Todd Garrett Wetzel , Jonathan Glenn Luedke , Thomas Michael Tucker
IPC分类号： F24H9/00 , F28F1/10 , F28F13/00 , B21D53/02
CPC分类号： F02K1/827 , F01D25/12 , F02C7/045 , F02C7/12 , F05D2300/224 , F05D2300/612 , Y02T50/675 , Y10T29/4935
摘要： A surface cooler for turbomachines is provided. The surface cooler comprises an inner layer and an outer layer disposed adjacent to the inner layer and comprising a metal foam, a carbon foam, or a combination thereof, wherein the metal foam, the carbon foam or a combination thereof is configured to augment heat transfer and enhance acoustic absorption. Further, the outer layer comprises a plurality of fins, wherein the plurality of fins is configured to augment heat transfer and enhance acoustic absorption, and wherein the plurality of fins comprises metal foam, a carbon foam, or a combination thereof.
摘要翻译：提供了用于涡轮机的表面冷却器。表面冷却器包括内层和邻近内层设置的外层，并且包括金属泡沫，碳泡沫或其组合，其中金属泡沫，碳泡沫或其组合构造成增加热传递并增强吸声。此外，外层包括多个翅片，其中多个翅片被配置为增强热传递和增强声学吸收，并且其中多个翅片包括金属泡沫，碳泡沫或其组合。

50. 发明授权

US07735601B1 Engine noise 有权
标题翻译：发动机噪音
公开(公告)号：US07735601B1
公开(公告)日：2010-06-15
申请号：US11366747
申请日：2006-03-03
申请人： Rory D. Stieger , Kevin M. Britchford , Paul J. R. Strange
发明人： Rory D. Stieger , Kevin M. Britchford , Paul J. R. Strange
IPC分类号： F02K1/00
CPC分类号： F02K1/48 , B64D33/06 , F02K1/46 , F02K1/827 , F05D2240/127 , F05D2260/96 , Y02T50/671
摘要： In order to provide noise suppression, bumps or undulations are provided on a nozzle surface in order to vary the convergent-divergent ratio between that surface and an opposed nozzle surface. By such an approach, a circumferential variation in the shock cell pattern is created and the flow is deflected so as to enhance turbulent mixing thereby suppressing noise.
摘要翻译：为了提供噪声抑制，为了改变该表面和相对的喷嘴表面之间的会聚 - 发散比，在喷嘴表面上提供凸起或起伏。通过这种方法，产生冲击电池图形的周向变化并且流动被偏转，以便增强湍流混合从而抑制噪声。

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