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51. 发明申请

US20160186579A1 HYBRID GAMMA TiAl ALLOY COMPONENT 审中-公开
标题翻译： HYBRID GAMMA钛合金组件
公开(公告)号：US20160186579A1
公开(公告)日：2016-06-30
申请号：US14868951
申请日：2015-09-29
申请人： United Technologies Corporation
发明人： Gabriel L. Suciu , James D. Hill
IPC分类号： F01D5/28 , F01D9/04 , F01D25/06 , F01D5/14
CPC分类号： F01D5/28 , B23K35/0233 , B23K35/0244 , B23K35/025 , B23K35/325 , C23C24/00 , F01D5/147 , F01D9/041 , F01D9/042 , F01D25/06 , F01D25/246 , F05D2230/23 , F05D2230/236 , F05D2230/60 , F05D2240/80 , F05D2300/174 , F05D2300/175 , F05D2300/5023
摘要： A hybrid component for a turbine engine having a casing includes a first part of a gamma TiAl intermetallic alloy and a second part of a material of at least one of nickel, a nickel base, a cobalt base, an iron base superalloy or mixtures thereof. The second part is coupled to and configured to attach the first part to the casing of the engine. The first and second parts are attached to each other by transient liquid phase (TLP) bonding.
摘要翻译：用于具有壳体的涡轮发动机的混合部件包括伽马TiAl金属间合金的第一部分和镍，镍基，钴基，铁基超级合金或其混合物中的至少一种的材料的第二部分。第二部分联接并构造成将第一部分附接到发动机的壳体。第一和第二部分通过瞬态液相（TLP）结合而相互连接。

52. 发明申请

US20160177749A1 BLADING MEMBER FOR A FLUID FLOW MACHINE 审中-公开
标题翻译：流体流动机叶片成员
公开(公告)号：US20160177749A1
公开(公告)日：2016-06-23
申请号：US14965244
申请日：2015-12-10
申请人： ALSTOM Technology Ltd
发明人： Herbert BRANDL , Eribert BENZ
IPC分类号： F01D5/30
CPC分类号： F01D5/3007 , F01D5/02 , F01D5/225 , F01D5/3023 , F01D9/042 , F01D9/044 , F05D2220/32 , F05D2240/30 , F05D2240/80 , F05D2260/30
摘要： A blading member for a fluid flow machine, for example, for use in gas turbine engines. The blading member includes a platform member and an airfoil member. The platform member and airfoil member are designed to allow for easy assembly/disassembly and replacement of members independent of other members.
摘要翻译：用于例如用于燃气涡轮发动机的流体流动机的叶片构件。叶片构件包括平台构件和翼型构件。平台构件和翼型构件被设计成允许容易地组装/拆卸和更换独立于其它构件的构件。

53. 发明授权

US09366150B2 Method for mounting a stator blading of a turbomachine, an engine casing and a turbomachine comprising at least one stator blading mounted on this engine casing 有权
标题翻译：一种用于安装涡轮机，发动机壳体和涡轮机的定子叶片的方法，包括安装在该发动机壳体上的至少一个定子叶片
公开(公告)号：US09366150B2
公开(公告)日：2016-06-14
申请号：US13659404
申请日：2012-10-24
申请人： SNECMA
发明人： Maurice Guy Judet , Jerome Etienne Robert Cameau , Fabrice Marcel Noel Garin , Alain Paul Madec
IPC分类号： F01D9/04 , F01D25/24
CPC分类号： F01D9/042 , F01D25/246 , F05D2230/60 , F05D2250/70 , F05D2260/30 , F05D2270/114 , F05D2300/501 , Y02T50/672 , Y10T29/49316
摘要： The present disclosure aims at achieving a mounting of a turbomachine stator blading while avoiding a delicate machining process of the engine casing. It also aims at simplifying the mounting as well as at reducing the costs, and at decreasing the number of item references for the engine. To achieve these objects, the turbomachine uses an extension of the engine casing. A turbomachine comprises at least one stator blading for air or gas stream flowing on the internal engine casing. The stator blading comprises a rim which is assembled on a radial extension of engine casing with an axial fastener. In a preferred embodiment of the turbomachine, the engine casing presents an annular wall provided with fingers originating axially from this wall and extending according to a curvature so that they present a radial extension tip against the rim of the stator blading.
摘要翻译：本公开旨在实现涡轮机定子叶片的安装，同时避免发动机壳体的精细加工过程。它还旨在简化安装以及降低成本，并减少引擎的项目参考数量。为了实现这些目的，涡轮机使用发动机外壳的延伸部分。涡轮机包括用于在内部发动机壳体上流动的空气或气流的至少一个定子叶片。定子叶片包括轮缘，该轮辋组装在具有轴向紧固件的发动机壳体的径向延伸部上。在涡轮机的优选实施例中，发动机壳体呈现环形壁，该环形壁设有从该壁轴向产生并且根据曲率延伸的指状物，使得它们呈现抵靠定子叶片边缘的径向延伸尖端。

54. 发明授权

US09335051B2 Ceramic matrix composite combustor vane ring assembly 有权
标题翻译：陶瓷基复合燃烧器叶片环组件
公开(公告)号：US09335051B2
公开(公告)日：2016-05-10
申请号：US13181898
申请日：2011-07-13
申请人： David C. Jarmon , Peter G. Smith
发明人： David C. Jarmon , Peter G. Smith
IPC分类号： F23R3/60 , F23R3/16 , F01D9/04 , F01D5/28 , F01D9/02 , F23R3/00 , F23R3/06
CPC分类号： F23R3/16 , F01D5/284 , F01D9/023 , F01D9/042 , F23M2900/05002 , F23R3/002 , F23R3/005 , F23R3/06 , F23R3/60 , F23R2900/00012 , F23R2900/03042
摘要： A vane assembly has an outer support ring, an inner support ring, an outer liner ring, an inner liner ring, and a circumferential array of vanes. Each vane has a shell extending from an inboard end to an outboard end and at least partially through an associated aperture in the inner liner ring and an associated aperture in the outer liner ring. There is at least one of: an outer compliant member compliantly radially positioning the vane; and an inner compliant member compliantly radially positioning the vane.
摘要翻译：叶片组件具有外支撑环，内支撑环，外衬垫环，内衬环和周向阵列的叶片。每个叶片具有壳体，其从内侧端部延伸到外侧端部，并且至少部分地穿过内部衬套环中的相关联的孔和外部衬套环中的相关联的孔。至少一个：外部柔顺部件顺从地径向定位叶片; 以及顺应性地顺向地定位叶片的内部顺应构件。

55. 发明授权

US09334756B2 Liner and method of assembly 有权
标题翻译：衬套和组装方法
公开(公告)号：US09334756B2
公开(公告)日：2016-05-10
申请号：US13656906
申请日：2012-10-22
申请人： United Technologies Corporation
发明人： Mark David Ring , David Cassella , Jonathan Earl , Eric Kuehne , Charles Warner
IPC分类号： F01D9/04 , F01D25/24 , F01D11/00
CPC分类号： F01D25/246 , F01D5/32 , F01D9/041 , F01D9/042 , F01D11/003 , F05D2220/32 , F05D2240/12 , F05D2240/90 , Y10T29/49323
摘要： An assembly includes a plurality of vanes, a forward liner segment, and an aft liner segment. The forward liner segment and the aft liner segment are mounted to the plurality of vanes and each segment comprises an arc of less than 360° in length.
摘要翻译：一种组件包括多个叶片，前向衬垫段和后衬层段。前部衬垫段和后部衬套段安装到多个叶片上，并且每个段包括长度小于360°的弧。

56. 发明申请

US20160108931A1 MOUNTING ARRANGEMENT FOR VARIABLE STATOR VANE 有权
标题翻译：可变定位器的安装布置
公开(公告)号：US20160108931A1
公开(公告)日：2016-04-21
申请号：US14876113
申请日：2015-10-06
申请人： ROLLS-ROYCE PLC
发明人： Ning WANG , Ewan F. THOMPSON
IPC分类号： F04D29/64 , F04D29/54 , F04D29/56 , F04D19/00
CPC分类号： F04D29/644 , F01D9/042 , F01D17/162 , F04D19/002 , F04D27/002 , F04D29/542 , F04D29/563 , F05D2250/13 , F05D2300/43
摘要： The present invention provides a mounting arrangement for mounting a variable stator vane within a gas turbine engine. The mounting arrangement comprises an inner shroud having a radially- and circumferentially-extending slot and at least one insert which, in use, is retained within said slot. The or each insert has at least one bore for receiving a spindle portion of the variable stator vane. The at least one insert is formed of a plastics material and/or the slot and the at least one insert each have a respective axial cross section with a respective first width (axial dimension) which is greater than and radially inwards from a respective second width, the first width of the at least one insert being greater than the second width of the slot and there being a smooth transition between the respective first and second widths.
摘要翻译：本发明提供一种用于将可变定子叶片安装在燃气涡轮发动机内的安装装置。安装装置包括具有径向和周向延伸的狭槽的内部护罩和至少一个在使用中保持在所述狭槽内的插入件。该或每个插入件具有至少一个用于容纳可变定子叶片的心轴部分的孔。所述至少一个插入件由塑料材料和/或所述槽形成，并且所述至少一个插入件各自具有相应的轴向横截面，所述相应的轴向横截面具有相应的第一宽度（轴向尺寸），所述第一宽度（轴向尺寸）大于和径向向内，所述至少一个插入件的第一宽度大于所述槽的第二宽度，并且在相应的第一和第二宽度之间具有平滑过渡。

57. 发明申请

US20160102568A1 POWER TURBINE HEAT SHIELD ARCHITECTURE 有权
标题翻译：动力涡轮机热风建筑
公开(公告)号：US20160102568A1
公开(公告)日：2016-04-14
申请号：US14512523
申请日：2014-10-13
申请人： PW POWER SYSTEMS, INC.
发明人： Fernando K. Grant , Fabian D. Betancourt , John J. Korzendorfer , Andrew P. Boursy , Alexander Sankovich , Henry K. Webster , Christopher W. Moore , Charles C. Wu
IPC分类号： F01D9/06 , F01D25/12 , F01D9/04
CPC分类号： F01D9/065 , F01D9/042 , F01D11/005 , F01D25/12 , F01D25/246
摘要： A power turbine section for a gas turbine engine includes a heat shield assembly mounted to a bearing support, the heat shield assembly forms an outer diameter directed toward an inner vane platform of the power turbine vane array.
摘要翻译：用于燃气涡轮发动机的动力涡轮机部分包括安装到轴承支撑件的隔热罩组件，所述隔热罩组件形成指向动力涡轮叶片阵列的内叶片平台的外径。

58. 发明授权

US09303520B2 Double fan outlet guide vane with structural platforms 有权
标题翻译：双风扇出风导叶带结构平台
公开(公告)号：US09303520B2
公开(公告)日：2016-04-05
申请号：US13652955
申请日：2012-10-16
申请人： General Electric Company
发明人： William Howard Hasting , Courtney James Tudor
IPC分类号： F01D9/04 , F01D25/24 , F01D9/02
CPC分类号： F01D9/02 , F01D9/042 , F01D25/246 , F05D2240/12 , F05D2300/6033 , Y02T50/672 , Y02T50/673
摘要： The assembly has a first guide vane having a first end, a second end opposed to the first end, and a second guide vane having a first end, a second end opposed to its first end. A first end structure spans between the first guide vane first end and the second guide vane first end. A second end structure spans between the first guide vane second end and the second guide vane second end. The first guide vane, the second guide vane, the first end structure, and the second end structure are integrally formed together to form a double vane with a continuous outer surface, and a continuous inner surface.
摘要翻译：组件具有第一导叶，其具有第一端，与第一端相对的第二端和具有第一端的第二导叶，与第一端相对的第二端。第一端结构跨越第一导叶第一端和第二导叶第一端。第二端部结构跨越第一导叶第二端和第二导叶第二端。第一导向叶片，第二导向叶片，第一端部结构和第二端部结构一体地形成在一起，形成具有连续外表面的双叶片和连续的内表面。

59. 发明申请

US20160047257A1 MOUNTING ARRANGEMENT FOR AEROFOIL BODY 审中-公开
标题翻译： AEROFOIL BODY安装安排
公开(公告)号：US20160047257A1
公开(公告)日：2016-02-18
申请号：US14817784
申请日：2015-08-04
申请人： ROLLS-ROYCE PLC
发明人： Steven Aleksy RADOMSKI , Matthew Paul JEVONS
IPC分类号： F01D9/04
CPC分类号： F01D9/042 , F01D5/282 , F01D5/284 , F01D9/041 , F04D29/023 , F04D29/542 , F04D29/644 , F05D2220/32 , F05D2230/23 , F05D2240/125 , F05D2240/80 , F05D2250/181 , F05D2300/20 , F05D2300/2102 , F05D2300/224 , F05D2300/43 , F05D2300/603
摘要： The present disclosure provides an aerofoil body comprising a root portion and a tip portion, each having a pressure surface and a suction surface. The pressure surface and suction surface of the root and/or tip portion each comprise a respective ridge portion. Each ridge portion has an inclined first face and an oppositely inclined second face. Each ridge portion may be, for example, a triangular or semi-circular prism.
摘要翻译：本公开提供了一种机翼主体，其包括根部和尖端部分，每个具有压力表面和吸力表面。根部和/或尖端部分的压力表面和吸力表面各自包括相应的脊部分。每个脊部分具有倾斜的第一面和相对倾斜的第二面。每个脊部可以是例如三角形或半圆形棱镜。

60. 发明申请

US20160032744A1 SELECTIVE COATING REMOVAL OR MASKING FOR GROUND PATH 有权
标题翻译：选择性涂层去除或掩蔽地面路径
公开(公告)号：US20160032744A1
公开(公告)日：2016-02-04
申请号：US14776341
申请日：2014-03-14
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Thomas B. Hyatt , Carl Brian Klinetob
IPC分类号： F01D9/04 , F01D25/00
CPC分类号： F01D9/042 , B64D45/02 , F01D5/288 , F01D25/005 , F01D25/243 , F05D2220/327 , F05D2260/31 , F05D2300/17 , F05D2300/173 , F05D2300/174 , F05D2300/50
摘要： A device for providing a grounding path between an outer surface of a gas turbine aircraft engine and an inner surface of a gas turbine aircraft engine uses a structural guide vane (SGV) with a nonconductive coating on the surface. Bolts are put in bolt holes that have a bolt receiving cavity without the nonconductive coating. A washer and bolt are used so that attachment of the SGV to a surface provides a ground path from the SGV through the bolt, washer and nut for electrical engagement with a surface to which the bolt attaches the SGV.
摘要翻译：用于在燃气涡轮机飞行器发动机的外表面和燃气涡轮机飞机发动机的内表面之间提供接地路径的装置使用在表面上具有非导电涂层的结构导叶（SGV）。螺栓被放入螺栓孔中，螺栓孔具有不带非导电涂层的螺栓接收腔。使用垫圈和螺栓，使得SGV附接到表面提供了从SGV通过螺栓，垫圈和螺母的接地路径，用于与螺栓附接到SGV的表面电接合。

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