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111. 发明申请

US20150143812A1 Exhaust Plume Cooling 有权
标题翻译：排气冷却
公开(公告)号：US20150143812A1
公开(公告)日：2015-05-28
申请号：US14092147
申请日：2013-11-27
申请人： Lockheed Martin Corporation
发明人： Dan J. Baruzzini , Neal David Domel , Daniel N. Miller
IPC分类号： F02K1/82
CPC分类号： F02K1/822 , B64D33/04 , B64D41/00 , B64D2041/002 , F01D25/30 , F02C7/12 , F02K1/386 , F02K1/46 , F05D2220/50 , Y02T50/675
摘要： An exhaust plume cooling device for cooling an exhaust gas plume to reduce deleterious heat effects on impinged and surrounding surfaces. The device is supportable in a position downstream of an exhaust nozzle of an exhaust gas plume-producing engine and configured to periodically interrupt the flow of exhaust gases.
摘要翻译：一种排气羽流冷却装置，用于冷却废气羽流以减少对冲击和周围表面的有害热影响。该装置可以在排气烟囱产生用发动机的排气喷嘴的下游位置支撑，并且能够周期性地中断废气的流动。

112. 发明申请

US20150118023A1 ACOUSTIC STRUCTURE FOR A GAS TURBINE ENGINE 有权
标题翻译：气体涡轮发动机的声学结构
公开(公告)号：US20150118023A1
公开(公告)日：2015-04-30
申请号：US14228375
申请日：2014-03-28
申请人： Pratt & Whitney Canada Corp.
发明人： STEPHEN CAULFEILD , BRYAN OLVER , KIN-LEUNG CHEUNG
IPC分类号： F02C7/25 , F23M20/00 , F02K1/82
CPC分类号： F02C7/25 , F02C7/24 , F02K1/827 , F05D2220/327 , F05D2240/14 , F05D2240/15 , F05D2250/283 , F05D2260/96 , F05D2300/44 , F05D2300/502 , F23M20/005 , Y02T50/672
摘要： An acoustic structure for a gas turbine engine comprising an noise reduction layer and a fire protector layer connected to the noise reduction layer. The noise reduction includes a perforated inner wall adapted to be in contact with a first fluidic environment, and an noise reduction adjacent to the inner wall. The fire protector layer includes a non-perforated outer wall adapted to be in contact with a second fluidic environment having potentially a fire, a fire protector adjacent to the outer wall, and a pressure resisting wall disposed between the fire protector and the noise reduction. The second fluidic environment is under a pressure lower than a pressure of the first fluidic environment. The inner and outer walls are load-bearing walls of the acoustic structure
摘要翻译：一种用于燃气涡轮发动机的声学结构，包括连接到降噪层的降噪层和防火器层。降噪包括适于与第一流体环境接触的穿孔内壁和邻近内壁的噪音降低。防火层包括适于与潜在地发生火灾的第二流体环境接触的非穿孔外壁，邻近外壁的防火器以及设置在防火器和降噪之间的耐压壁。第二流体环境的压力低于第一流体环境的压力。内墙和外墙是声学结构的承重墙

113. 发明申请

US20150108248A1 THRUST REVERSER FAN RAMP WITH NOISE SUPPRESSION 审中-公开
标题翻译：具有噪音抑制的反向风扇风扇
公开(公告)号：US20150108248A1
公开(公告)日：2015-04-23
申请号：US14060194
申请日：2013-10-22
申请人： Rohr, Inc.
发明人： Michael Aten
IPC分类号： F02K1/82 , F02K1/62
CPC分类号： F02K1/827 , F02K1/72 , F05D2260/96
摘要： A fan ramp for use in a thrust reverser portion of a nacelle is disclosed. The nacelle is included in a propulsion system. The fan ramp extends circumferentially about an axial fan ramp centerline. The fan ramp includes a forward edge, an aft edge, and a noise suppression feature. The forward edge is disposed proximate an aft end of a fan case. The fan case at least partially surrounds a fan section of a gas turbine engine. The aft edge is disposed proximate a forward end of an array of cascades. The array of cascades is operable to permit a bypass airstream to pass there through during a thrust reversing operation. The noise suppression feature is operable to suppress noise within the propulsion system.
摘要翻译：公开了一种用于机舱的推力反向器部分的风扇斜坡。机舱被包括在推进系统中。风扇斜坡沿轴向风扇斜坡中心线周向延伸。风扇斜坡包括前沿，后边缘和噪声抑制功能。前缘设置在风扇壳体的后端附近。风扇壳体至少部分地围绕燃气涡轮发动机的风扇部分。后边缘靠近级联阵列的前端设置。级联阵列可操作以允许旁路气流在推力反向操作期间通过其中。噪声抑制特征可操作以抑制推进系统内的噪声。

114. 发明申请

US20150071704A1 EXHAUST DUCT LINER ROD HANGER 有权
标题翻译：排气管内胆吊架
公开(公告)号：US20150071704A1
公开(公告)日：2015-03-12
申请号：US14478171
申请日：2014-09-05
申请人： United Technologies Corporation
发明人： Paul R. Senofonte , Jose E. Ruberte Sanchez
IPC分类号： F02K1/80 , F02K1/82 , B23P19/04
CPC分类号： F02K1/80 , F02K1/82 , Y02T50/671 , Y10T29/49895 , Y10T403/56
摘要： A hanger is disclosed that has a movable component and a bracket. The movable component has a shaft with a threaded portion, a slider connected to the shaft, and a cap configured to join with the threaded portion. The bracket defines a racetrack aperture and an ingress/egress aperture. The racetrack aperture and the ingress/egress aperture are connected.
摘要翻译：公开了一种具有可移动部件和支架的衣架。可移动部件具有带有螺纹部分的轴，连接到轴的滑块和构造成与螺纹部分连接的盖。支架定义了一个跑道孔和入口/出口孔。跑道孔径和入口/出口孔径已连接。

115. 发明授权

US08925295B2 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排气装置
公开(公告)号：US08925295B2
公开(公告)日：2015-01-06
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： F02K3/075 , F02K1/12 , F02K1/70 , B64D29/00 , F02K1/82
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。

116. 发明授权

US08899512B2 Acoustic attenuation panel for aircraft for engine nacelle 有权
标题翻译：用于发动机舱的飞机的声衰减面板
公开(公告)号：US08899512B2
公开(公告)日：2014-12-02
申请号：US13056822
申请日：2009-07-28
申请人： Guy Bernard Vauchel , Guillaume Ruckert
发明人： Guy Bernard Vauchel , Guillaume Ruckert
IPC分类号： B64C1/40 , B64D15/00 , F02K1/82 , F02C7/045 , F02C7/24 , F02C7/047 , B64D33/02
CPC分类号： F02C7/045 , B64D33/02 , B64D2033/0206 , B64D2033/0233 , B64D2033/0286 , F02C7/047 , F02C7/24 , F02K1/827 , F05D2300/224 , F05D2300/612 , Y02T50/672
摘要： An aircraft turbojet engine air intake structure includes an air intake lip provided with a first acoustic attenuation panel which contains a structuring skin and, as an acoustic absorption material, a porous material fastened on the skin. The air intake structure also includes a pneumatic de-icing compartment defined by the lip and by an inner partition. The first acoustic attenuation panel is of the type including an open-cell porous material which is capable of resisting a temperature of up to 200° C. and having high heat conductivity.
摘要翻译：飞机涡轮喷气发动机进气结构包括设置有第一声衰减板的进气口，该第一声衰减板包含结构化皮肤，以及作为吸声材料，紧固在皮肤上的多孔材料。进气结构还包括由唇缘和内隔板限定的气动除冰室。第一声衰减板是包括能够耐受高达200℃的温度并具有高导热性的开孔多孔材料的类型。

117. 发明授权

US08863893B2 Engine inlet varying impedance acoustic liner section 有权
标题翻译：发动机入口变化阻抗声衬套
公开(公告)号：US08863893B2
公开(公告)日：2014-10-21
申请号：US13655911
申请日：2012-10-19
申请人： Spirit AeroSystems, Inc.
发明人： Joe Everet Sternberger , Judith Marie Gallman
IPC分类号： B64D33/02 , F02K1/00 , F02K1/82 , E04B1/82 , B64C1/40 , B64C23/00 , F01K1/00 , F01N1/00 , B64D29/00
CPC分类号： B64D33/02 , B64D29/00 , B64D2033/0206 , F01K1/00 , F01N1/00
摘要： An inlet for an aircraft engine nacelle having an acoustic barrel panel, a septum buried or sandwiched within the acoustic barrel panel, and a perforated face sheet. The inlet may be located forward of an engine and/or an engine fan housed within the aircraft engine nacelle. Both the septum and the perforated face sheet may have perforations or holes therein of varying sizes and varying distances apart from each other. The smaller the area of the perforations or holes and the further apart they are from each other, the higher the impedance of a given area of the septum or the perforated face sheet. The impedance of the septum and/or the perforated face sheet may progressively increase in a direction away from the engine fan.
摘要翻译：用于具有声筒面板，埋在或夹在声筒面板内的隔膜的飞机发动机机舱的入口和穿孔面板。入口可以位于发动机和/或容纳在飞机发动机机舱内的发动机风扇的前方。隔垫和穿孔表面片可以在其中具有不同尺寸和彼此不同距离的穿孔或孔。穿孔或孔的面积越小，并且彼此越远，隔膜或穿孔面片的给定面积的阻抗越高。隔膜和/或穿孔面板的阻抗可以沿远离发动机风扇的方向逐渐增加。

118. 发明授权

US08826669B2 Gas turbine exhaust case 有权
标题翻译：燃气轮机排气箱
公开(公告)号：US08826669B2
公开(公告)日：2014-09-09
申请号：US13292289
申请日：2011-11-09
申请人： Richard Bouchard , John Pietrobon , Eric Durocher
发明人： Richard Bouchard , John Pietrobon , Eric Durocher
IPC分类号： F02C7/08 , F03G1/00 , F02G3/00 , F02K1/82 , F02C7/24
CPC分类号： F02C7/24 , F02K1/04 , F02K1/78 , F02K1/80 , F02K1/827
摘要： A turbine exhaust case for a turbofan engine comprises a plurality of arcuate acoustic panels assembled into a circumferentially extending inner shroud with circumferential gaps between adjacent acoustic panels. An outer shroud extends circumferentially about the inner shroud. The inner shroud and the outer shroud define an annular gaspath therebetween. A plurality of circumferentially spaced-apart exhaust struts extends radially across the annular gaspath and structurally connects the individual acoustic panels forming the inner shroud to the outer shroud.
摘要翻译：用于涡轮风扇发动机的涡轮机排气箱包括组装成周向延伸的内护罩的多个弓形声波面板，在相邻的声学面板之间具有圆周间隙。外护罩围绕内护罩周向延伸。内护罩和外护罩在其间限定了环形气路。多个周向间隔开的排气支柱径向延伸穿过环形气体路径，并将构成内护罩的各个隔音板结构连接到外护罩上。

119. 发明申请

US20140237990A1 VARIABLE AREA FAN NOZZLE WITH WALL THICKNESS DISTRIBUTION 有权
标题翻译：可变区域风扇喷嘴与壁厚分布
公开(公告)号：US20140237990A1
公开(公告)日：2014-08-28
申请号：US13834123
申请日：2013-03-15
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Oliver V. Atassi , Oleg Petrenko
IPC分类号： F02K1/82
CPC分类号： F02K1/15 , F02C3/04 , F02C7/36 , F02K1/06 , F02K1/82 , F02K3/06 , F05D2220/323 , F05D2240/35 , F05D2260/81 , F05D2300/173 , F05D2300/6033 , Y02T50/672
摘要： A gas turbine engine includes a core engine that has at least a compressor section, a combustor section and a turbine section disposed along a central axis. A fan is coupled to be driven by the turbine section. A fan nacelle is arranged around the fan, and a bypass passage extends between the fan nacelle and the core engine. A variable area fan nozzle (VAFN) extends at least partially around the central axis and defines an exit area of the bypass passage. The VAFN is selectively movable to vary the exit area. The VAFN includes a body that defines an airfoil cross-section shape. The VAFN includes a wall that has a mechanical property distribution in accordance with a computer-simulated vibration profile of a flutter characteristic of the VAFN.
摘要翻译：燃气涡轮发动机包括至少具有压缩机部分，燃烧器部分和沿中心轴线布置的涡轮部分的核心发动机。风扇被联接以由涡轮部分驱动。风扇周围布置有风扇机舱，并且旁通通道在风扇机舱和核心发动机之间延伸。可变区域风扇喷嘴（VAFN）至少部分地围绕中心轴延伸并且限定旁路通道的出口区域。 VAFN选择性地可移动以改变出口区域。 VAFN包括限定翼型横截面形状的主体。 VAFN包括具有根据VAFN的颤振特性的计算机模拟振动分布的机械特性分布的壁。

120. 发明授权

US08733496B2 Acoustic damper, combustor, and gas turbine 有权
标题翻译：声阻尼器，燃烧器和燃气轮机
公开(公告)号：US08733496B2
公开(公告)日：2014-05-27
申请号：US13876772
申请日：2012-02-20
申请人： Masaki Ono , Tetsu Konishi
发明人： Masaki Ono , Tetsu Konishi
IPC分类号： F02K1/82 , F01N1/02 , F02K1/00 , F01N1/00
CPC分类号： F01N13/00 , F02C7/24 , F05D2260/963 , F05D2260/964 , F23M20/005 , F23R3/002 , F23R3/005 , F23R3/06 , F23R2900/00014 , F23R2900/03041
摘要： An acoustic damper is fixed to a vibration source to be provided along an outer surface of the vibration source, forms a passage that takes in air vibration generated by the vibration source, and is provided with an acoustic portion having a partition member closing the downstream side of the passage with respect to the propagation of the air vibration to serve as resistance against the air vibration, in which the acoustic portion allows air vibration to propagate in a reverse direction, and has partition members arranged so as to serve as resistance against the air vibration in respective directions. This allows to prevent from generating stress due to pressure fluctuation caused when reducing vibration, and to achieve a relatively compact size.
摘要翻译：声阻尼器固定在沿着振动源的外表面设置的振动源上，形成一个通过振动源产生的空气振动的通道，并且设有一个声学部分，该声部分具有一个分隔构件，相对于空气振动的传播而作为抵抗空气振动的通道，其中声学部分允许空气振动沿相反方向传播，并且具有布置成用作抵抗空气的隔离构件各方向振动。这允许防止由于减少振动时引起的压力波动而产生应力，并且实现相对紧凑的尺寸。

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