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61. 发明申请

US20160108754A1 Splitter Nose With Plasma De-Icing For Axial Turbine Engine Compressor 审中-公开
标题翻译：用于轴流涡轮发动机压缩机的等离子体去除器的分流鼻
公开(公告)号：US20160108754A1
公开(公告)日：2016-04-21
申请号：US14918041
申请日：2015-10-20
申请人： Techspace Aero S.A.
发明人： Ghislain Herbaut , David Bouillon
IPC分类号： F01D25/02 , F01D25/24 , H05H1/24 , F01D9/04
CPC分类号： F01D25/02 , B64D15/12 , B64D15/163 , B64D33/02 , B64D2033/0226 , B64D2033/0233 , F01D9/041 , F01D25/24 , F02C7/047 , F05D2220/30 , F05D2240/12 , F05D2270/172 , F05D2300/40 , F05D2300/603 , H05H1/2406 , H05H2001/2425 , Y02T50/672
摘要： The invention deals with a splitter nose delimiting the inlet of a low-pressure compressor of an axial turbine engine. The splitter nose comprises a separation surface with an upstream circular edge suitable for separating a flow entering into the turbine engine into a primary flow and a secondary flow, and a plasma de-icing device. The device comprises two annular layers of dielectric material (42; 44) partially forming the separation surface, an electrode forming the upstream edge, an electrode forming an outer wall of the splitter nose, an electrode forming an outer shroud which supports blades, an electrode delimiting the primary flow. The device generates plasmas (46; 48; 50) opposing the presence of ice on the partitions of the splitter nose. The invention also deals with a turbine engine with a splitter nose that is provided with a de-icing system downstream of the fan.
摘要翻译：本发明涉及一种限定轴向涡轮发动机的低压压缩机的入口的分流器鼻子。分流器鼻部包括具有适于将进入涡轮发动机的流分离为主流和次流的上游圆形边缘的分离表面，以及等离子体除冰装置。该装置包括部分地形成分离表面的两个介电材料（42; 44）的环形层，形成上游边缘的电极，形成分流鼻的外壁的电极，形成支撑叶片的外护罩的电极，划分主流。该装置产生与分流器鼻部的分隔壁上的冰的存在相反的等离子体（46; 48; 50）。本发明还涉及具有分流器鼻部的涡轮发动机，其在风扇的下游设置有除冰系统。

62. 发明申请

US20160090870A1 GAS TURBINE ENGINE MODULE ADAPTER TO A CARRIER 有权
标题翻译：气体涡轮发动机模块适配器
公开(公告)号：US20160090870A1
公开(公告)日：2016-03-31
申请号：US14962320
申请日：2015-12-08
申请人： Pratt & Whitney Canada Corp.
发明人： GREGORY REINHARDT , JOSEPH SWIDERSKI , DOUGLAS POLLOCK , REAL BARRETTE , STEPHANE MONGEAU
IPC分类号： F01D25/28 , F01D25/24
CPC分类号： F01D25/285 , B66C11/04 , F01D25/24 , F01D25/28 , F05D2220/30 , F05D2220/32 , F05D2220/36 , F05D2230/60 , F05D2230/68 , F05D2230/72 , F05D2240/91 , Y02T50/671 , Y10T29/49229 , Y10T29/49826
摘要： An engine mounting arrangement is provided for supporting a gas turbine engine. The mounting arrangement comprises a module adaptor mounted to an overhead or a ground based carrier for rotation about a substantially horizontal axis. The module adaptor extends horizontally from a base to an axially-opposed distal end having a first mounting interface configured for attachment to a module of the engine. The module adaptor holds the engine by the module to which it is attached and with the other engine modules projecting in a cantilever fashion from the supported module.
摘要翻译：提供用于支撑燃气涡轮发动机的发动机安装装置。安装装置包括安装到顶部或基于地面的载体上的模块适配器，用于围绕基本上水平的轴线旋转。模块适配器从基座水平延伸到具有构造成附接到发动机的模块的第一安装接口的轴向相对的远端。模块适配器通过其所连接的模块将引擎保持在发动机上，而其它发动机模块以悬臂方式从支撑的模块突出。

63. 发明申请

US20160084502A1 TURBINE ENGINE DIFFUSER ASSEMBLY WITH AIRFLOW MIXER 审中-公开
标题翻译：涡轮发动机发动机组装与气流混合器
公开(公告)号：US20160084502A1
公开(公告)日：2016-03-24
申请号：US14853368
申请日：2015-09-14
申请人： United Technologies Corporation
发明人： Frank J. Cunha , Stanislav Kostka
IPC分类号： F23R3/04 , F02C9/16 , F23R3/00 , F02C7/04
CPC分类号： F23R3/04 , F01D9/02 , F01D9/065 , F02C6/06 , F02C7/04 , F02C9/16 , F04D29/44 , F05D2210/12 , F05D2210/13 , F05D2220/30 , F05D2240/35 , F23R3/005 , F23R3/02
摘要： A diffuser assembly is provided for a turbine engine. This diffuser assembly includes a. diffuser module with a combustor plenum and a mixing chamber. The diffuser module is configured to receive first and second airflows into the mixing chamber and direct a mixed airflow out of the mixing chamber. The diffuser module includes a mixer configured to mix the first and the second airflows together within the mixing chamber to provide the mixed airflow.
摘要翻译：为涡轮发动机提供扩散器组件。该扩散器组件包括a。扩散器模块，具有燃烧室增压室和混合室。扩散器模块被配置为将第一和第二气流接收到混合室中并将混合气流引导出混合室。扩散器模块包括混合器，该混合器构造成将混合室内的第一和第二气流混合在一起以提供混合气流。

64. 发明申请

US20160046107A1 SIZED GLASS FIBERS FOR FIBER-CONTAINING COMPOSITE ARTICLES AND METHODS OF MAKING THEM 审中-公开
标题翻译：含纤维复合材料的大尺寸玻璃纤维及其制造方法
公开(公告)号：US20160046107A1
公开(公告)日：2016-02-18
申请号：US13915023
申请日：2013-06-11
申请人： Johns Manville
发明人： Mingfu Zhang , Jawed Asrar , Klaus Friedrich Gleich , Asheber Yohannes
IPC分类号： B32B27/12 , B32B27/34 , B32B5/02 , B29C65/02 , F03D1/06 , C08K7/14 , C08K5/544 , C08K5/5455 , F01D5/28 , C03C25/32 , C08J5/24
CPC分类号： B32B27/12 , B29B15/105 , B29C65/02 , B32B5/024 , B32B27/34 , B32B2262/101 , B32B2439/00 , B32B2509/00 , B32B2603/00 , B32B2605/08 , B32B2605/18 , C03C25/32 , C03C25/328 , C08J5/08 , C08J5/24 , C08J2377/02 , C08J2377/06 , C08K5/5442 , C08K5/5455 , C08K7/14 , F01D5/282 , F03D1/0675 , F05D2220/30 , F05D2230/30 , F05D2300/43 , F05D2300/6012 , F05D2300/611 , Y02E10/721
摘要： Methods of making prepregs are described. The methods include the steps of forming a fiber-containing substrate, and contacting the fiber-containing substrate with a resin mixture. The resin mixture may include polymer particles mixed in a liquid medium, and the polymer particles may be coated on the fiber-containing substrate to form a coated substrate. The liquid medium may be removed from the coated substrate to form the prepreg. The prepregs may be used to make fiber-reinforced articles.
摘要翻译：描述制备预浸料的方法。所述方法包括以下步骤：形成含纤维基材，并使含纤维基材与树脂混合物接触。树脂混合物可以包括混合在液体介质中的聚合物颗粒，并且聚合物颗粒可以涂覆在含纤维的基材上以形成涂布的基材。液体介质可以从涂覆的基底上移除以形成预浸料。预浸料可用于制造纤维增强制品。

65. 发明申请

US20160040555A1 COMPRESSOR CASE SNAP ASSEMBLY 审中-公开
标题翻译：压缩机壳体组件
公开(公告)号：US20160040555A1
公开(公告)日：2016-02-11
申请号：US14775726
申请日：2014-02-26
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Richard K. Hayford , Paul M. Lutjen
IPC分类号： F01D25/28 , F02C7/28 , F01D25/24 , F02C3/04
CPC分类号： F01D25/28 , F01D11/08 , F01D25/24 , F01D25/243 , F02C3/04 , F02C7/28 , F04D29/023 , F04D29/083 , F04D29/164 , F04D29/526 , F04D29/644 , F05D2220/30 , F05D2230/31 , F05D2230/60 , F05D2240/11 , F05D2240/55 , F05D2300/50212
摘要： A turbine engine case spacer includes an air seal and a flange. The air seal is snap fit to the flange, and each flange includes at least two distinct material layers.
摘要翻译：涡轮发动机壳体间隔件包括空气密封件和凸缘。空气密封件与凸缘卡扣配合，并且每个凸缘包括至少两个不同的材料层。

66. 发明申请

US20160032773A1 CIRCULATING LUBRICANT THROUGH A TURBINE ENGINE COMPONENT WITH PARALLEL PUMPS 审中-公开
标题翻译：通过涡轮发动机组件与并联泵循环润滑剂
公开(公告)号：US20160032773A1
公开(公告)日：2016-02-04
申请号：US14775921
申请日：2014-03-14
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Denman H. James , Reade W. James
IPC分类号： F01D25/20 , F02C7/06 , F01D25/16 , F01D5/02 , F01D15/12
CPC分类号： F01D25/20 , F01D5/02 , F01D15/12 , F01D25/16 , F02C7/06 , F05D2220/30 , F05D2240/24 , F05D2240/50 , F05D2260/98
摘要： A system for a turbine engine includes a turbine engine component, a lubricant collection device and a plurality of lubricant circuits. The lubricant collection device is fluidly coupled with the turbine engine component. The lubricant circuits are fluidly coupled between the lubricant collection device and the turbine engine component. The lubricant circuits include a first circuit and a second circuit configured in parallel with the first circuit. Each of the lubricant circuits includes a lubricant pump. The first and the second circuits receive lubricant from the lubricant collection device, and direct the received lubricant to the turbine engine component.
摘要翻译：涡轮发动机的系统包括涡轮发动机部件，润滑剂收集装置和多个润滑剂回路。润滑剂收集装置与涡轮发动机部件流体耦合。润滑剂回路流体地联接在润滑剂收集装置和涡轮发动机部件之间。润滑剂回路包括与第一回路并联配置的第一回路和第二回路。每个润滑剂回路包括润滑剂泵。第一和第二回路从润滑剂收集装置接收润滑剂，并将接收到的润滑剂引导到涡轮发动机部件。

67. 发明申请

US20160024933A1 BLADING WITH BRANCHES ON THE SHROUD OF AN AXIAL-FLOW TURBOMACHINE COMPRESSOR 审中-公开
标题翻译：在轴流式涡轮压缩机的裂缝上分支
公开(公告)号：US20160024933A1
公开(公告)日：2016-01-28
申请号：US14804522
申请日：2015-07-21
申请人： Techspace Aero S.A.
发明人： Stephane Hiernaux
IPC分类号： F01D5/14 , F01D25/24 , F01D9/04 , F01D5/02 , F01D5/22
CPC分类号： F01D5/146 , F01D5/02 , F01D5/225 , F01D9/041 , F01D25/24 , F04D29/544 , F05D2220/30 , F05D2240/12 , F05D2240/20 , Y02T50/673
摘要： The invention relates to an axial-flow turbomachine blading comprising a semi-circular row of blades extending radially. Each blade comprises a airfoil and lateral branches or lateral legs. Each branch has an end joined to the airfoil and an end opposite the airfoil. The blading comprises a first shroud segment connected to at least two opposite ends of two adjacent branches of two adjacent blades and/or of the same blade so as to connect the airfoils to the shroud segment via the lateral branches of the airfoils. The blading also comprises a second shroud segment concentric with the first shroud segment. The segments are connected to one another via the airfoils and the branches. The blading forms a rigid casing and is provided by additive manufacturing with a titanium-based powder.
摘要翻译：本发明涉及一种轴向涡轮机叶片，其包括径向延伸的半圆形叶片。每个叶片包括翼型和侧向分支或侧向腿。每个分支具有连接到翼型的端部和与翼型相对的端部。叶片包括连接到两个相邻叶片和/或相同叶片的两个相邻分支的至少两个相对端部的第一护罩段，以便经由翼型件的侧向分支将翼型件连接到护罩段。叶片还包括与第一护罩区段同心的第二护罩区段。这些段通过翼型件和分支件相互连接。叶片形成刚性壳体，并且通过用钛基粉末的添加剂制造提供。

68. 发明申请

US20160010550A1 MANIFOLD FOR GAS TURBINE 有权
标题翻译：燃气涡轮发动机
公开(公告)号：US20160010550A1
公开(公告)日：2016-01-14
申请号：US14866204
申请日：2015-09-25
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Stephanie Baker , John Otto
IPC分类号： F02C7/06 , F02C3/04 , F01D15/12
CPC分类号： F02C7/06 , F01D15/12 , F01D25/18 , F02C3/04 , F02C7/36 , F02K3/06 , F05D2220/30 , F05D2240/60 , F05D2260/40311 , F05D2260/98 , F16H57/04
摘要： In various embodiments, a manifold assembly (64) for conducting one or more fluids to a gear assembly (60) in a gas turbine engine (20) is provided. The manifold assembly (64) may comprise a first plate (66) and a second plate (68) that rotatably couple together. The manifold assembly (64) may be retained and/or held together by a channel (72) and engagement member (70) arrangement.
摘要翻译：在各种实施例中，提供了用于将一种或多种流体传导到燃气涡轮发动机（20）中的齿轮组件（60）的歧管组件（64）。歧管组件（64）可以包括可旋转地联接在一起的第一板（66）和第二板（68）。歧管组件（64）可以通过通道（72）和接合构件（70）的布置来保持和/或保持在一起。

69. 发明申请

US20160010461A1 METHOD FOR DETUNING A ROTOR-BLADE CASCADE 有权
标题翻译：拆卸转子叶片的方法
公开(公告)号：US20160010461A1
公开(公告)日：2016-01-14
申请号：US14764062
申请日：2014-01-23
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： Thomas Gronsfelder , Jan Walkenhorst , Armin de Lazzer
IPC分类号： F01D5/16
CPC分类号： F01D5/16 , F05D2220/30 , F05D2230/10 , F05D2260/961
摘要： A method for detuning a rotor-blade cascade of a turbomachine having a plurality of rotor blades includes: a) establishing at least one target natural frequency for at least one vibration mode; b) setting up a value table having discrete mass values and radial centre-of-gravity positions, and determining respective natural frequency; c) measuring the mass and radial centre-of-gravity position of one of the rotor blades; d) determining an actual natural frequency by interpolating the measured mass and radial centre-of-gravity position in the value table; e) if actual natural frequency is outside a tolerance around target natural frequency, selecting a value pair that at least approximates target natural frequency, and removing material from the rotor blade in such a way that mass and radial centre-of-gravity position correspond to the value pair; f) repeating steps c) to e) until actual natural frequency is within the tolerance around target natural frequency.
摘要翻译：一种用于使具有多个转子叶片的涡轮机的转子叶片级联失谐的方法包括：a）为至少一个振动模式建立至少一个目标固有频率; b）建立具有离散质量值和径向重心位置的值表，并确定相应的固有频率; c）测量一个转子叶片的质量和径向重心位置; d）通过内插测量质量和径向重心位置来确定实际固有频率; e）如果实际固有频率在目标固有频率之外的公差之外，选择至少近似于目标固有频率的值对，并且以使质量和径向重心位置对应于转子叶片的方式从转子叶片中去除材料价值对; f）重复步骤c）至e），直到实际固有频率在目标固有频率范围内。

70. 发明申请

US20160003095A1 UNDULATING STATOR FOR REDUCING THE NOISE PRODUCED BY INTERACTION WITH A ROTOR 审中-公开
标题翻译：用于减少与转子相互产生的噪音的定位器
公开(公告)号：US20160003095A1
公开(公告)日：2016-01-07
申请号：US14790964
申请日：2015-07-02
申请人： SNECMA
发明人： Pascal Jérôme Romano , Norman Bruno André Jodet
IPC分类号： F01D25/04 , F01D5/02 , F01D9/04
CPC分类号： F01D25/04 , F01D5/02 , F01D5/141 , F01D5/145 , F01D9/041 , F04D29/544 , F04D29/663 , F04D29/681 , F05D2220/30 , F05D2240/121 , F05D2240/122 , F05D2240/123 , F05D2240/124 , F05D2250/184 , F05D2250/611 , F05D2260/961 , Y02T50/673
摘要： A stator designed to be placed radially in a flow which passes through one or more rotors which share the same axis of rotation, with a leading edge and a trailing edge. The leading edge and trailing edge are connected by a lower face and an upper face, wherein at least one of the faces of the stator has radial undulations which extend axially from the leading edge to the trailing edge. The radial undulations can have at least two bosses in the same azimuth direction, the amplitude of which is at least one centimeter on at least part of the axial length of the stator. A propulsion assembly formed by the rotor and the stator, and to a turbine engine comprising such assembly is also provided.
摘要翻译：定子被设计成径向地放置在流过一个或多个转子的流动中，该转子共享相同的旋转轴线，具有前缘和后缘。前缘和后缘通过下表面和上表面连接，其中定子的至少一个面具有从前缘到后缘轴向延伸的径向波状。径向起伏可以在相同的方位角方向上具有至少两个凸台，其振幅在定子的轴向长度的至少一部分上至少为一厘米。还提供了由转子和定子以及包括这种组件的涡轮发动机形成的推进组件。

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