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公开(公告)号：US10018054B2
公开(公告)日：2018-07-10
申请号：US14921023
申请日：2015-10-23
发明人： Michael J. Verrilli , Mark Eugene Noe , Mark Willard Marusko , Paul Izon , Robert Tyler , Christopher Hasse
CPC分类号： F01D5/282 , C04B35/6269 , C04B37/001 , C04B2235/602 , C04B2235/604 , C04B2237/38 , F01D5/147 , F01D5/30 , F01D11/00 , F05D2220/32 , F05D2230/21 , F05D2230/60 , F05D2240/30 , F05D2250/313 , F05D2300/6033 , Y02T50/672 , Y02T50/673
摘要： Methods for fabricating a component of a gas turbine engine are provided. In one embodiment, the method includes molding a CMC material to form a first portion of the gas turbine engine component, processing the first portion to form a first assembly, preparing the first assembly and a second portion of the gas turbine engine component for processing, and processing the first assembly and second portion to form a second assembly. In another embodiment, the method includes processing a first plurality of CMC plies to form a first assembly; positioning the first assembly and a second plurality of CMC plies on a tool for processing, the first assembly defining a first plane, the second plurality of plies defining a second plane, wherein the second plane is perpendicular to the first plane; and processing the first assembly and the second plurality of plies to form a second assembly.
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公开(公告)号：US20180112596A1
公开(公告)日：2018-04-26
申请号：US15805339
申请日：2017-11-07
IPC分类号： F02C7/047
CPC分类号： F02C7/047 , F01D25/02 , F02K3/02 , F02K3/06 , F04D29/321 , F05D2220/323 , F05D2240/12 , F05D2250/313 , F05D2260/20
摘要： The invention relates to a de-icing splitter nose (22) of an axial turbine engine, notably a de-icing splitter nose of a turbo-jet engine compressor. The splitter nose includes an annular row of vanes (26), each of which has a radially extending leading edge (36), and a de-icing system (28) based on hot-air injection. The injection is pulsed, i.e. discontinuous. The system (28) includes an annular row of injection orifices for injecting de-icing fluid (44) onto the vanes (26) in respective injection directions (46). Each injection orifice is associated with a vane such that the injection directions thereof are substantially parallel to the leading edge (36) of the related vane, enabling said vane (26) to be de-iced.
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公开(公告)号：US20160146041A1
公开(公告)日：2016-05-26
申请号：US14943686
申请日：2015-11-17
申请人： MTU Aero Engines AG
发明人： Andreas Hartung , Hermann Klingels , Patrick Wackers , Manfred Feldmann , Frank Stiehler , Markus Schlemmer
CPC分类号： F01D25/06 , F01D5/10 , F01D5/16 , F01D5/26 , F01D9/02 , F01D9/041 , F04D29/324 , F04D29/662 , F04D29/668 , F05D2220/32 , F05D2220/3212 , F05D2220/3215 , F05D2220/3217 , F05D2220/3219 , F05D2240/129 , F05D2240/30 , F05D2250/12 , F05D2250/121 , F05D2250/131 , F05D2250/141 , F05D2250/313 , F05D2260/96 , Y02T50/671
摘要： The present invention relates to a blade (100) or vane for a turbomachine, having at least one impulse element housing (1.1, 1.2) with a first impact cavity (10), in which an impulse element (11) is arranged with play of movement, wherein the impulse element housing has at least one second impact cavity (20), which is in alignment with the first impact cavity in a first matrix direction (A) and in which an impulse element (21) is arranged with play of movement, and has at least one third impact cavity (30), which is in alignment with the first impact cavity in a second matrix direction (B) crosswise to the first matrix direction and in which an impulse element (31) is arranged with play of movement.
摘要翻译： 本发明涉及一种用于涡轮机的叶片（100）或叶片，其具有至少一个具有第一冲击腔（10）的脉冲元件壳体（1.1,1.2），其中脉冲元件（11）布置成 运动，其中所述脉冲元件壳体具有至少一个第二冲击腔（20），所述第二冲击腔在第一矩阵方向（A）上与所述第一冲击腔对准，并且其中脉冲元件（21）布置成具有运动 ，并且具有至少一个第三冲击腔（30），其在与第一矩阵方向交叉的第二矩阵方向（B）上与第一冲击腔对准，其中脉冲元件（31）布置成与 运动。
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公开(公告)号：US20160131082A1
公开(公告)日：2016-05-12
申请号：US14535015
申请日：2014-11-06
申请人： Rohr, Inc.
发明人： Timothy Gormley
CPC分类号： F02K1/766 , F02K1/625 , F02K1/72 , F02K1/763 , F05D2250/313 , F05D2260/50 , F05D2260/532
摘要： Aspects are directed to a system that includes an outer structure of a thrust reverser, a blocker door, and a plurality of four-bar mechanisms arranged in series with one another that couple the outer structure and the blocker door. Aspects are directed to a system for a thrust reverser of an aircraft that includes a blocker door, a kinematic mechanism configured to actuate the blocker door, and a pressure shelf, where the blocker door is configured to reside below the pressure shelf in proximity to a duct of the thrust reverser, and where at least a portion of the kinematic mechanism is configured to reside above the pressure shelf.
摘要翻译： 方面涉及一种系统，其包括推力反向器，阻挡门以及彼此串联布置的多个四杆机构的外部结构，该外部结构联接外部结构和阻挡门。 方面涉及一种用于飞行器的推力反向器的系统，该系统包括阻挡门，构造成致动阻挡门的运动机构和压力架，其中阻挡门构造成位于靠近压力架的压力架附近 推力反向器的管道，并且其中运动机构的至少一部分被配置为驻留在压力架上方。
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公开(公告)号：US20160010561A1
公开(公告)日：2016-01-14
申请号：US14764105
申请日：2013-01-30
CPC分类号： F02C7/32 , B64D29/06 , F02C3/04 , F05D2250/313 , F05D2250/75
摘要： An example gas turbine engine includes, among other things, a nacelle having an inner wall providing a bypass duct of a gas turbine engine, and an outer wall; an accessory gearbox is received between the inner wall and the outer wall of the nacelle; and an accessory drive of the accessory gearbox is configured to rotate about an accessory drive axis that is transverse to a central axis of the gas turbine engine.
摘要翻译： 一个示例性的燃气涡轮发动机包括其中具有提供燃气涡轮发动机的旁路管道的内壁的机舱和外壁; 附件齿轮箱被容纳在机舱的内壁和外壁之间; 并且附件齿轮箱的附件驱动器被配置为围绕横向于燃气涡轮发动机的中心轴线的附件驱动轴线旋转。
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公开(公告)号：US09039355B2
公开(公告)日：2015-05-26
申请号：US13485325
申请日：2012-05-31
CPC分类号： F02C9/22 , F01D17/162 , F04D29/563 , F05D2250/312 , F05D2250/313 , F05D2260/31 , F05D2260/56 , F16H21/44 , Y10T74/18888 , Y10T74/20012
摘要： An actuator system mounted to a gas turbine engine that communicates mechanical power for positioning variable guide vanes within the gas turbine engine. The actuator system includes a torque box having components for communicating mechanical power to the variable guide vanes for positioning the vanes and an actuator mechanically coupled to provide mechanical power to the components of the torque box used to communicate the provided mechanical power to the inlet guide vanes. The actuator is mounted to the torque box via a plurality of bolts.
摘要翻译： 安装到燃气涡轮发动机的致动器系统，其传达用于在燃气涡轮发动机内定位可变导向叶片的机械动力。 致动器系统包括具有用于将机械动力传递到用于定位叶片的可变导向叶片的部件的扭矩盒，以及致动器，其机械联接以向用于将所提供的机械动力传递到入口导向叶片的扭矩箱的部件提供机械动力 。 致动器通过多个螺栓安装到扭矩箱。
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公开(公告)号：US08955304B2
公开(公告)日：2015-02-17
申请号：US13370743
申请日：2012-02-10
CPC分类号： F02K3/06 , F02C3/107 , F02C7/04 , F02C7/36 , F05D2210/40 , F05D2250/313 , F05D2250/314 , Y10T29/4932 , Y10T29/49323
摘要： A separate propulsion unit incorporating a free turbine and a fan receives gases from a plurality of core engines. The core engines each include a compressor, a turbine and a combustion section. The core engines in combination pass gases across the free turbine. A method is also disclosed.
摘要翻译： 结合有自由涡轮机和风扇的单独的推进单元接收来自多个核心发动机的气体。 核心发动机各自包括压缩机，涡轮机和燃烧部分。 核心发动机组合通过自由涡轮机的气体。 还公开了一种方法。
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公开(公告)号：US08932004B2
公开(公告)日：2015-01-13
申请号：US13291201
申请日：2011-11-08
CPC分类号： F02C7/057 , F02C7/045 , F02C7/047 , F02C9/18 , F05D2250/313 , F05D2270/101
摘要： An embodiment of the present invention takes the form of an IBH system that has two conduits, which are positioned close to a downstream end of a silencer section. This arrangement may reduce the overall pressure drop associated with the inlet system. This arrangement may also promote a substantially uniform mixing between the cooler ambient air and the warmer heated air.
摘要翻译： 本发明的一个实施例采用IBH系统的形式，其具有两个导管，其位于靠近消声器部分的下游端。 这种布置可以减少与入口系统相关联的整体压降。 这种布置还可以促进较冷的环境空气和较热的加热空气之间的基本上均匀的混合。
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公开(公告)号：US20140238027A1
公开(公告)日：2014-08-28
申请号：US13725114
申请日：2012-12-21
发明人： Donald W. Peters
IPC分类号： F02C7/24
CPC分类号： F02C7/24 , F01D25/12 , F02K1/822 , F02K3/10 , F05D2220/80 , F05D2230/54 , F05D2230/642 , F05D2240/15 , F05D2250/12 , F05D2250/14 , F05D2250/313 , F05D2260/202 , F05D2300/501 , Y02T50/675
摘要： A stiffener for a liner assembly of a gas turbine engine includes a second resilient member arranged on a first resilient member at substantially ninety (90) degree orientation.
摘要翻译： 用于燃气涡轮发动机的衬套组件的加强件包括以基本上九十（90）度取向布置在第一弹性构件上的第二弹性构件。
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公开(公告)号：US20130115061A1
公开(公告)日：2013-05-09
申请号：US13291201
申请日：2011-11-08
IPC分类号： F04D29/58
CPC分类号： F02C7/057 , F02C7/045 , F02C7/047 , F02C9/18 , F05D2250/313 , F05D2270/101
摘要： An embodiment of the present invention takes the form of an IBH system that has two conduits, which are positioned close to a downstream end of a silencer section. This arrangement may reduce the overall pressure drop associated with the inlet system. This arrangement may also promote a substantially uniform mixing between the cooler ambient air and the warmer heated air.
摘要翻译： 本发明的一个实施例采用IBH系统的形式，其具有两个导管，其位于靠近消声器部分的下游端。 这种布置可以减少与入口系统相关联的整体压降。 这种布置还可以促进较冷的环境空气和较热的加热空气之间的基本上均匀的混合。
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