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21. 发明授权

US09016066B2 Combustor assembly in a gas turbine engine 有权
标题翻译：燃气轮机发动机中的燃烧器组件
公开(公告)号：US09016066B2
公开(公告)日：2015-04-28
申请号：US13718297
申请日：2012-12-18
申请人： David J. Wiebe , Timothy A. Fox
发明人： David J. Wiebe , Timothy A. Fox
IPC分类号： F23R3/60 , F23R3/04 , F23R3/28 , F23R3/00 , F23R3/34
CPC分类号： F23R3/286 , F23R3/002 , F23R3/34 , F23R3/346 , F23R3/60
摘要： A combustor assembly in a gas turbine engine includes a combustor device, a fuel injection system, a transition duct, and an intermediate duct. The combustor device includes a flow sleeve for receiving pressurized air and a liner surrounded by the flow sleeve. The fuel injection system provides fuel to be mixed with the pressurized air and ignited in the liner to create combustion products. The intermediate duct is disposed between the liner and the transition duct so as to define a path for the combustion products to flow from the liner to the transition duct. The intermediate duct is associated with the liner such that movement may occur therebetween, and the intermediate duct is associated with the transition duct such that movement may occur therebetween. The flow sleeve includes structure that defines an axial stop for limiting axial movement of the intermediate duct.
摘要翻译：燃气涡轮发动机中的燃烧器组件包括燃烧器装置，燃料喷射系统，过渡管道和中间管道。燃烧器装置包括用于接收加压空气的流动套筒和由流动套筒包围的衬套。燃料喷射系统提供燃料以与加压空气混合并在衬套中点燃以产生燃烧产物。中间管道设置在衬套和过渡管道之间，以便限定燃烧产物从衬套流动到过渡管道的路径。中间管道与衬套相关联，使得其间可能发生运动，并且中间管道与过渡管道相关联，使得它们之间可能发生运动。流动套筒包括限定用于限制中间管道的轴向运动的轴向止动件的结构。

22. 发明授权

US08978389B2 Radial inflow gas turbine engine with advanced transition duct 有权
标题翻译：具有先进过渡管的径流入气涡轮发动机
公开(公告)号：US08978389B2
公开(公告)日：2015-03-17
申请号：US13326392
申请日：2011-12-15
申请人： David J. Wiebe
发明人： David J. Wiebe
IPC分类号： F02C1/00 , F02C3/04 , F02C3/00
CPC分类号： F02C3/14 , F01D1/08 , F01D9/023 , F05D2250/313
摘要： A gas turbine engine (10), including: a turbine having radial inflow impellor blades (38); and an array of advanced transition combustor assemblies arranged circumferentially about the radial inflow impellor blades (38) and having inner surfaces (34) that are adjacent to combustion gases (40). The inner surfaces (34) of the array are configured to accelerate and orient, for delivery directly onto the radial inflow impellor blades (38), a plurality of discrete flows of the combustion gases (40). The array inner surfaces (34) define respective combustion gas flow axes (20). Each combustion gas flow axis (20) is straight from a point of ignition until no longer bound by the array inner surfaces (34), and each combustion gas flow axis (20) intersects a unique location on a circumference defined by a sweep of the radial inflow impellor blades (38).
摘要翻译：一种燃气涡轮发动机（10），包括：具有径向流入叶轮叶片（38）的涡轮机; 以及一组先进的过渡燃烧器组件，其围绕径向流入叶轮（38）周向布置并具有与燃烧气体（40）相邻的内表面（34）。阵列的内表面（34）构造成加速和定向，以直接输送到径向流入叶轮（38）上，燃烧气体（40）的多个离散流。阵列内表面（34）限定相应的燃烧气体流动轴线（20）。每个燃烧气体流动轴线（20）从点火直线直到不再受阵列内表面（34）的约束，并且每个燃烧气体流动轴线（20）与由扫描线径向流入叶轮叶片（38）。

23. 发明授权

US08757981B2 Locking spacer assembly for a turbine engine 有权
标题翻译：用于涡轮发动机的锁定间隔件组件
公开(公告)号：US08757981B2
公开(公告)日：2014-06-24
申请号：US13096051
申请日：2011-04-28
申请人： David J. Wiebe
发明人： David J. Wiebe
IPC分类号： F01D5/32 , F01D5/30
CPC分类号： F01D5/3038 , F01D5/32 , F01D5/323
摘要： A locking spacer assembly for filling a void between adjacent components in a turbine engine. In at least one embodiment, the locking spacer assembly may be configured to be inserted between adjacent turbine blades in a disc groove in a turbine blade stage assembly. The locking spacer assembly may be formed from radially inward and outward supports coupled together with a locking device. The inward and outward supports establish the desired spacing between adjacent blade supports. The locking device may include components that prevent the locking device from accidentally loosening during use.
摘要翻译：一种用于填充涡轮发动机中的相邻部件之间的空隙的锁定间隔件组件。在至少一个实施例中，锁定间隔件组件可构造成在涡轮叶片级组件中的盘槽中插入在相邻涡轮叶片之间。锁定间隔件组件可以由与锁定装置联接在一起的径向向内和向外的支撑件形成。向内和向外的支撑件在相邻的叶片支撑件之间建立所需的间隔。锁定装置可以包括防止锁定装置在使用期间意外松动的部件。

24. 发明授权

US08622016B2 Wear indication system for compressor diaphragms of gas turbine engines 失效
标题翻译：燃气轮机发动机压缩机隔膜的磨损指示系统
公开(公告)号：US08622016B2
公开(公告)日：2014-01-07
申请号：US13252429
申请日：2011-10-04
申请人： David J. Wiebe
发明人： David J. Wiebe
IPC分类号： G01D21/00 , F16D66/02
CPC分类号： F16D66/02 , F01D11/02 , F04D27/001 , F04D29/542 , F05D2260/83
摘要： A wear indication system for use in turbine engines to measure gap closure that indicates the amount of wear found on a compressor diaphragm outer hook to prevent contact between a compressor vane attached to the compressor diaphragm outer hook and an upstream compressor blade. The wear indication system enables the wear to be serviced before failure occurs. The wear indication system may be formed from a base mounting plate having one or more wearable material layers attached thereto. In one embodiment, the wear indication system may have multiple wearable material layers. The outermost wearable layer may have a cross-sectional area less than a wearable layer to which it is attached to enable visual determination of the amount of wear that has occurred. The wearable layers may be formed from a honeycomb shaped material enabling wear to occur without threatening downstream components with damage.
摘要翻译：一种用于涡轮发动机的磨损指示系统，用于测量间隙闭合，其指示在压缩机隔膜外钩上发现的磨损量，以防止附接到压缩机隔膜外钩的压缩机叶片与上游压缩机叶片之间的接触。磨损指示系统使磨损在发生故障之前得到维护。磨损指示系统可以由具有附接到其上的一个或多个可穿戴材料层的基座安装板形成。在一个实施例中，磨损指示系统可以具有多个可穿戴材料层。最外面的可佩戴层可以具有小于其所连接的可佩戴层的横截面面积，以使得能够可视地确定所发生的磨损量。可穿戴层可以由蜂窝状材料形成，从而能够在不损害下游部件的情况下发生磨损。

25. 发明授权

US08376697B2 Gas turbine sealing apparatus 有权
标题翻译：燃气轮机密封装置
公开(公告)号：US08376697B2
公开(公告)日：2013-02-19
申请号：US12611241
申请日：2009-11-03
申请人： David J. Wiebe , Brian J. Wessell , Todd Ebert , Alexander Beeck , George Liang , Walter H. Marussich
发明人： David J. Wiebe , Brian J. Wessell , Todd Ebert , Alexander Beeck , George Liang , Walter H. Marussich
IPC分类号： F02C7/28
CPC分类号： F01D11/001 , F01D11/005
摘要： A gas turbine includes forward and aft rows of rotatable blades, a row of stationary vanes between the forward and aft rows of rotatable blades, an annular intermediate disc, and a seal housing apparatus. The forward and aft rows of rotatable blades are coupled to respective first and second portions of a disc/rotor assembly. The annular intermediate disc is coupled to the disc/rotor assembly so as to be rotatable with the disc/rotor assembly during operation of the gas turbine. The annular intermediate disc includes a forward side coupled to the first portion of the disc/rotor assembly and an aft side coupled to the second portion of the disc/rotor assembly. The seal housing apparatus is coupled to the annular intermediate disc so as to be rotatable with the annular intermediate disc and the disc/rotor assembly during operation of the gas turbine.
摘要翻译：燃气轮机包括可旋转叶片的前排和后排，在可旋转叶片的前排和后排之间的一排固定叶片，环形中间盘和密封件收纳装置。可旋转刀片的前排和后排被联接到盘/转子组件的相应的第一和第二部分。环形中间盘联接到盘/转子组件，以在燃气轮机的运行期间与盘/转子组件一起旋转。环形中间盘包括联接到盘/转子组件的第一部分的前侧和联接到盘/转子组件的第二部分的后侧。密封壳体装置联接到环形中间盘，以在燃气轮机的操作期间与环形中间盘和盘/转子组件一起旋转。

26. 发明授权

US08375726B2 Combustor assembly in a gas turbine engine 有权
标题翻译：燃气轮机发动机中的燃烧器组件
公开(公告)号：US08375726B2
公开(公告)日：2013-02-19
申请号：US12431302
申请日：2009-04-28
申请人： David J. Wiebe , Timothy A. Fox
发明人： David J. Wiebe , Timothy A. Fox
IPC分类号： F02C7/20 , F02C1/00 , F23R3/26
CPC分类号： F23R3/286 , F23R3/002 , F23R3/34 , F23R3/346 , F23R3/60
摘要： A combustor assembly in a gas turbine engine. The combustor assembly includes a combustor device coupled to a main engine casing, a first fuel injection system, a transition duct, and an intermediate duct. The combustor device includes a flow sleeve for receiving pressurized air and a liner disposed radially inwardly from the flow sleeve. The first fuel injection system provides fuel that is ignited with the pressurized air creating first working gases. The intermediate duct is disposed between the liner and the transition duct and defines a path for the first working gases to flow from the liner to the transition duct. An intermediate duct inlet portion is associated with a liner outlet and allows movement between the intermediate duct and the liner. An intermediate duct outlet portion is associated with a transition duct inlet section and allows movement between the intermediate duct and the transition duct.
摘要翻译：燃气涡轮发动机中的燃烧器组件。燃烧器组件包括联接到主发动机壳体，第一燃料喷射系统，过渡管道和中间管道的燃烧器装置。燃烧器装置包括用于接收加压空气的流动套筒和从流动套管径向向内设置的衬套。第一燃料喷射系统提供燃料，其被加压空气点燃以产生第一工作气体。中间管道设置在衬套和过渡管道之间并且限定用于第一工作气体从衬套流动到过渡管道的路径。中间管道入口部分与衬套出口相关联并允许中间管道和衬套之间的移动。中间管道出口部分与过渡管道入口部分相关联并且允许中间管道和过渡管道之间的运动。

27. 发明申请

US20110067402A1 Fuel Nozzle Assembly for Use in a Combustor of a Gas Turbine Engine 有权
标题翻译：用于燃气轮机发动机燃烧器的燃油喷嘴组件
公开(公告)号：US20110067402A1
公开(公告)日：2011-03-24
申请号：US12566222
申请日：2009-09-24
申请人： David J. Wiebe , Timothy A. Fox
发明人： David J. Wiebe , Timothy A. Fox
IPC分类号： F02C7/22 , F02C3/14
CPC分类号： F23R3/283 , F23R3/08 , F23R3/346 , F23R3/54 , F23R3/60
摘要： A fuel nozzle assembly for use in a combustor apparatus of a gas turbine engine. An outer housing of the fuel nozzle assembly includes an inner volume and provides a direct structural connection between a duct structure and a fuel manifold. The duct structure defines a flow passage for combustion gases flowing within the combustor apparatus. The fuel manifold defines a fuel supply channel therein in fluid communication with a source of fuel. A fuel injector of the fuel nozzle assembly is provided in the inner volume of the outer housing and defines a fuel passage therein. The fuel passage is in fluid communication with the fuel supply channel of the fuel manifold for distributing the fuel from the fuel supply channel into the flow passage of the duct structure.
摘要翻译：一种用于燃气涡轮发动机的燃烧器装置的燃料喷嘴组件。燃料喷嘴组件的外壳包括内部容积并且在管道结构和燃料歧管之间提供直接的结构连接。管道结构限定了在燃烧器装置内流动的燃烧气体的流动通道。燃料歧管在其中限定了与燃料源流体连通的燃料供应通道。燃料喷嘴组件的燃料喷射器设置在外部壳体的内部容积中并且在其中限定燃料通道。燃料通道与燃料歧管的燃料供应通道流体连通，用于将燃料从燃料供应通道分配到管道结构的流动通道中。

28. 发明申请

US20100018210A1 COMBUSTOR APPARATUS IN A GAS TURBINE ENGINE 有权
标题翻译：燃气涡轮发动机中的燃烧器装置
公开(公告)号：US20100018210A1
公开(公告)日：2010-01-28
申请号：US12233903
申请日：2008-09-19
申请人： Timothy A. Fox , David J. Wiebe , David M. Ritland , John Carl Glessner
发明人： Timothy A. Fox , David J. Wiebe , David M. Ritland , John Carl Glessner
IPC分类号： F02C7/22 , F23R3/28
CPC分类号： F23R3/16 , F23R3/283 , F23R3/346 , F23R2900/00005
摘要： A combustion apparatus in a gas turbine engine comprises a combustor shell for receiving air, a fuel injection system associated with the combustor shell, a first fuel supply structure, and a shield structure. The fuel supply structure is in fluid communication with a source of fuel for delivering fuel from the source of fuel to the fuel injection system and comprises a first fuel supply elements including a first section extending along a first path having a component in an axial direction and a second section extending from the first section along a second path having a component in a circumferential direction. The shield structure is associated with at least a portion of the second section of the first fuel supply element.
摘要翻译：燃气涡轮发动机中的燃烧装置包括用于接收空气的燃烧器壳体，与燃烧器壳体相关联的燃料喷射系统，第一燃料供应结构和屏蔽结构。燃料供应结构与燃料源流体连通，用于将燃料从燃料源输送到燃料喷射系统，并且包括第一燃料供应元件，其包括沿着沿轴向方向具有部件的第一路径延伸的第一部分，以及第二部分沿着沿圆周方向具有部件的第二路径从第一部分延伸。屏蔽结构与第一燃料供应元件的第二部分的至少一部分相关联。

29. 发明授权

US09316153B2 Purge and cooling air for an exhaust section of a gas turbine assembly 有权
标题翻译：用于燃气轮机组件的排气部分的吹扫和冷却空气
公开(公告)号：US09316153B2
公开(公告)日：2016-04-19
申请号：US13746486
申请日：2013-01-22
申请人： Harry Patat , Cheryl A. Schopf , Jerome H. Katy , Adam Wallace , David J. Wiebe
发明人： Harry Patat , Cheryl A. Schopf , Jerome H. Katy , Adam Wallace , David J. Wiebe
IPC分类号： F01D25/12 , F01D9/02 , F01D9/06 , F01D25/16 , F01D25/30 , F02C6/08 , F02C7/18
CPC分类号： F02C7/18 , F01D9/02 , F01D9/065 , F01D25/12 , F01D25/125 , F01D25/162 , F01D25/30 , F02C6/08 , F05D2240/15
摘要： A turbine exhaust casing having an outer casing, an inner casing, an annular exhaust gas path defined between outer and inner flow path walls, and a turbine exhaust casing cavity located radially outward and radially inward from the gas path. A plurality of structural struts support the inner casing to the outer casing, and a fairing surrounds each of the struts in an area extending between the outer and inner flow path walls. A first purge air path extends through at least one of the struts for conducting purge cooling air radially inward to the inner casing, and a second purge air path extends through the strut for further conducting the purge cooling air radially outward to provide a flow of purge air to a location of the exhaust casing cavity radially outward from the outer flow path wall.
摘要翻译：具有外壳，内壳，限定在外流路壁和内流路壁之间的环形排气通道的涡轮机排气外壳以及从气体路径径向向外和径向向内定位的涡轮排气壳体腔。多个结构支柱将内壳支撑到外壳，并且整流罩围绕在外流路壁和内流路壁之间延伸的区域中的每个支柱。第一吹扫空气路径延伸穿过支柱中的至少一个，用于将吹扫冷却空气径向向内引导到内部壳体，并且第二吹扫空气路径延伸穿过支柱，以进一步将吹扫冷却空气径向向外引导以提供吹扫流空气从外部流路壁向径向外侧排出到排气套管腔的位置。

30. 发明授权

US09115600B2 Insulated wall section 有权
标题翻译：绝缘墙段
公开(公告)号：US09115600B2
公开(公告)日：2015-08-25
申请号：US13221156
申请日：2011-08-30
申请人： David J. Wiebe
发明人： David J. Wiebe
IPC分类号： F01D25/26 , F01D25/24
CPC分类号： F01D25/26 , F01D25/24
摘要： A turbine section of a turbine engine includes rotatable structure, an outer casing disposed about the rotatable structure, and an inner casing disposed about the rotatable structure and suspended radially inwardly from the outer casing. Rotation of the rotatable structure during operation drives at least one of a compressor and a generator. The inner casing defines a hot gas flow path through which hot combustion gases pass during operation. The inner casing comprises a plurality of wall sections. Each wall section includes a panel having an inner portion and an outer portion opposed from and affixed to the inner portion. The inner portion at least partially defines the hot gas flow path and the inner portion is radially spaced from the outer portion such that a substantially fluid tight chamber is formed therebetween. The fluid tight chamber reduces thermal energy transfer from the inner portion to the outer portion.
摘要翻译：涡轮发动机的涡轮机部分包括旋转结构，围绕可旋转结构设置的外壳，以及围绕可旋转结构设置并从外壳径向向内悬挂的内壳。在操作期间可旋转结构的旋转驱动压缩机和发电机中的至少一个。内壳限定了在运行期间热燃气通过的热气流路径。内壳包括多个壁部。每个壁部分包括具有内部部分和与内部部分相对并固定到内部部分的外部部分的面板。所述内部部分至少部分地限定所述热气体流动路径，并且所述内部部分与所述外部部分径向间隔开，从而在其间形成基本上流体密封的腔室。流体密封室减少从内部到外部的热能传递。

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