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111. 发明授权

US09322558B2 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：US09322558B2
公开(公告)日：2016-04-26
申请号：US13928476
申请日：2013-06-27
申请人： Stephen A. Ramier , David J. Wiebe , Lawrence P. Budnick , Mark L. Adamson , Daniel W. Garan , Robert H. Bartley , Yadollah Naghian
发明人： Stephen A. Ramier , David J. Wiebe , Lawrence P. Budnick , Mark L. Adamson , Daniel W. Garan , Robert H. Bartley , Yadollah Naghian
IPC分类号： F23R3/60 , F23R3/28 , F23R3/54 , F16L19/06 , F23R3/34
CPC分类号： F23R3/283 , F16L19/061 , F23R3/286 , F23R3/34 , F23R3/346 , F23R3/54 , F23R3/60
摘要： A combustor apparatus defining a combustion zone where air and fuel are burned to create high temperature combustion products. The combustor apparatus comprises an outer wall including a fuel inlet opening for receiving a fuel feed pipe. A coupling assembly is engaged with the fuel feed pipe at the fuel inlet opening to attach the fuel feed pipe to the outer wall. A fuel injection system is located in the interior volume of the outer wall and comprises fuel supply structure including a fuel feed block having a fuel intake passage aligned with the outlet portion of the fuel feed pipe. A coupling fastener is engaged against an exterior outer face of the fuel feed block to create a sealed coupling for containing fuel passing from the fuel feed pipe into the fuel feed block, and to secure the fuel feed block relative to the coupling assembly.
摘要翻译：一种限定燃烧区域的燃烧器装置，其中燃烧空气和燃料以产生高温燃烧产物。燃烧器装置包括外壁，其包括用于接收燃料供给管的燃料入口。联接组件在燃料入口处与燃料供给管接合以将燃料供给管附接到外壁。燃料喷射系统位于外壁的内部容积中，并且包括燃料供给结构，其包括具有与燃料供给管的出口部分对准的燃料进入通道的燃料供给块。联接紧固件抵靠燃料供给块的外部外表面接合以产生密封联接件，用于容纳从燃料供给管道进入燃料供给块的燃料，并且相对于联接组件固定燃料供给块。

112. 发明授权

US09249978B2 Retaining collar for a gas turbine combustion liner 有权
标题翻译：用于燃气轮机燃烧衬套的挡圈
公开(公告)号：US09249978B2
公开(公告)日：2016-02-02
申请号：US13540718
申请日：2012-07-03
申请人： Brian K. Richardson , Alfredo Cires , John Henriquez , Daniel J. Sullivan , Kevin B. Powell
发明人： Brian K. Richardson , Alfredo Cires , John Henriquez , Daniel J. Sullivan , Kevin B. Powell
IPC分类号： F23R3/28 , F23R3/02 , F23R3/60 , F23R3/06 , F02C7/266
CPC分类号： F23R3/283 , F02C7/266 , F23D2207/00 , F23R3/02 , F23R3/06 , F23R3/60 , F23R2900/00005 , F23R2900/00012 , F23R2900/03042 , F23R2900/03043
摘要： A gas turbine combustion liner having a novel and improved system for receiving a peripheral device through a floating collar is disclosed. The retaining collar assembly provides planar movement for receiving the peripheral device while preventing the floating collar from rotational movement through an anti-rotation tab on the collar and a collar cap, resulting in reduced wear to the peripheral device. The collar cap can include different configurations for reducing any vibratory effects caused by an oncoming airflow directly contacting the floating collar.
摘要翻译：公开了一种具有用于通过浮动套环接收外围设备的新颖且改进的系统的燃气轮机燃烧衬套。保持套环组件提供用于接收外围设备的平面运动，同时防止浮动环通过套环上的防旋转凸片和套环帽的旋转运动，导致外围设备的磨损减少。套环帽可以包括不同的构造，用于减少由直接接触浮动套环的迎面而来的气流引起的任何振动效应。

113. 发明申请

US20150377491A1 COMBUSTION TURBINE ENGINE COMBUSTOR BASKET IGNITER PORT ALIGNMENT VERIFICATION TOOL AND METHOD FOR VALIDATING IGNITER ALIGNMENT 有权
标题翻译：燃油涡轮发动机燃烧器篮子IGNITER端口对准验证工具和确定IGNITER对准的方法
公开(公告)号：US20150377491A1
公开(公告)日：2015-12-31
申请号：US14314109
申请日：2014-06-25
申请人： Siemens Energy, Inc.
发明人： Peter C. Sullivan , Michael J. Olejarski
IPC分类号： F23R3/60 , G01B5/24 , B33Y50/02
CPC分类号： F23R3/60 , B29C64/386 , B33Y50/02 , B33Y80/00 , F23R2900/00017 , G01B5/25
摘要： A combustion turbine engine combustor igniter port alignment and dimensional verification tool is insertable in guide tube and igniter boss portions of the igniter port. The tool has concentrically nested outer and inner sleeves, having respective circumferential profiles that are separately slidably insertable within corresponding igniter port guide tube and igniter boss portions that have inner circumferential profiles in conformance with minimal dimension specifications. Concentric alignment of the guide tube and igniter boss is validated by inserting the nested outer and inner sleeves into the igniter port. The verification tool is capable of validating igniter port alignment and dimensions before the combustor is installed in a combustion turbine engine.
摘要翻译：燃气涡轮发动机燃烧器点火器端口对准和尺寸验证工具可插入点火器端口的引导管和点火器凸台部分。该工具具有同心嵌套的外套筒和内套筒，其具有分别可滑动地插入到相应的点火器口引导管和具有符合最小尺寸规格的内圆周轮廓的点火器凸台部分的相应圆周轮廓。引导管和点火器凸台的同心对准通过将嵌套的外套筒和内套管插入点火器端口来验证。验证工具能够在燃烧器安装在燃气涡轮发动机之前验证点火器端口对准和尺寸。

114. 发明授权

US09091445B2 Guiding a sparkplug in a turbine engine combustion chamber 有权
标题翻译：在涡轮发动机燃烧室中引导火花塞
公开(公告)号：US09091445B2
公开(公告)日：2015-07-28
申请号：US13512802
申请日：2010-12-03
申请人： Jacques Marcel Arthur Bunel , Mario Cesar De Sousa , Nicolas Christian Raymond Leblond , Guillaume Sevi , Denis Jean Maurice Sandelis , Christophe Pieussergues
发明人： Jacques Marcel Arthur Bunel , Mario Cesar De Sousa , Nicolas Christian Raymond Leblond , Guillaume Sevi , Denis Jean Maurice Sandelis , Christophe Pieussergues
IPC分类号： F02C7/266 , F23R3/60 , F23R3/50 , F23R3/00
CPC分类号： F23R3/50 , F02C7/266 , F23D2207/00 , F23R3/002 , F23R3/60
摘要： A turbine engine combustion chamber including at least one ignition sparkplug carried by an outer casing and extending through a guide mechanism carried by a wall forming a body of revolution of the chamber. The guide mechanism includes a tubular guide having the sparkplug passing axially therethrough, which guide is mounted with axial and transverse clearance on a chimney fastened to the wall of the chamber and opening out therein. The guide includes an annular collar engaged with clearance in an internal annular groove of the chimney. The annular collar is urged to press against a wall of the groove by a resilient member mounted in the groove.
摘要翻译：一种涡轮发动机燃烧室，包括至少一个点火火花塞，其由外壳承载并延伸穿过由形成所述腔的旋转体的壁承载的引导机构。引导机构包括一个管状引导件，其具有穿过其中的火花塞，该引导件以固定在腔室壁上并在其中打开的烟囱安装有轴向和横向间隙。引导件包括与烟囱的内部环形槽中的间隙接合的环形套环。通过安装在槽中的弹性构件推动环形套环压靠槽的壁。

115. 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。

116. 发明授权

US09003852B2 Sheet metal blank 有权
标题翻译：钣金空白
公开(公告)号：US09003852B2
公开(公告)日：2015-04-14
申请号：US11808692
申请日：2007-06-12
申请人： Richard Green , Michael Annear
发明人： Richard Green , Michael Annear
IPC分类号： F01D25/24 , F23R3/60 , F23R3/00 , B21J1/00
CPC分类号： F01D25/24 , B21J1/00 , F05D2230/26 , F23R3/002 , F23R3/60
摘要： A sheet metal blank for the manufacture of a casing of a gas turbine engine comprising a sheet of substantially constant wall thickness and a raised or thicker region extending along substantially the full length of the sheet metal blank. A raised or thicker region is provided between edges of the sheet metal blank. The raised or thicker region comprises at least one boss and at least one ridge extending way from the or each boss.
摘要翻译：一种用于制造燃气涡轮发动机壳体的金属板坯，其包括基本上恒定的壁厚的片材和沿着金属片坯料的大致整个长度延伸的升高或更厚的区域。在金属片坯料的边缘之间提供凸起或较厚的区域。凸起或较厚区域包括至少一个凸台和至少一个从该凸台或每个凸台延伸的脊。

117. 发明授权

US08978388B2 Load member for transition duct in turbine system 有权
标题翻译：涡轮系统中过渡管的负载构件
公开(公告)号：US08978388B2
公开(公告)日：2015-03-17
申请号：US13152638
申请日：2011-06-03
申请人： James Scott Flanagan , Jeffrey Scott LeBegue , Kevin Weston McMahan , Ronnie Ray Pentecost
发明人： James Scott Flanagan , Jeffrey Scott LeBegue , Kevin Weston McMahan , Ronnie Ray Pentecost
IPC分类号： F23R3/60 , F23R3/42 , F23R3/00 , F01D9/02 , F01D25/28
CPC分类号： F23R3/425 , F01D9/023 , F01D25/28 , F05D2250/314 , F05D2260/30 , F23R3/002 , F23R3/60
摘要： A loading assembly for a turbine system is disclosed. The loading assembly includes a transition duct and a load member. The transition duct extends between a fuel nozzle and a turbine section, and has an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The load member extends from the transition duct and is configured to transfer a load between the transition duct and an adjacent transition duct along at least one of the longitudinal axis, the radial axis, or the tangential axis.
摘要翻译：公开了一种用于涡轮机系统的装载组件。装载组件包括过渡管道和负载构件。过渡管道在燃料喷嘴和涡轮机部分之间延伸，并且具有入口，出口和在入口和出口之间延伸并限定纵向轴线，径向轴线和切向轴线的通道。过渡管道的出口沿着纵向轴线和切线轴线从入口偏移。负载构件从过渡管道延伸并且构造成沿着纵向轴线，径向轴线或切线轴线中的至少一个在过渡管道和相邻过渡管道之间传递负载。

118. 发明授权

US08925326B2 System and method for turbine combustor mounting assembly 有权
标题翻译：用于涡轮燃烧器安装组件的系统和方法
公开(公告)号：US08925326B2
公开(公告)日：2015-01-06
申请号：US13115009
申请日：2011-05-24
申请人： David William Cihlar , Patrick Benedict Melton , Robert Joseph Rohrssen
发明人： David William Cihlar , Patrick Benedict Melton , Robert Joseph Rohrssen
IPC分类号： F02C1/00 , F02G3/00 , F23R3/60 , F23R3/00
CPC分类号： F23R3/60 , F23D2900/14004 , F23R3/002 , F23R2900/03043 , Y02T50/675
摘要： A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and an aerodynamic mounting assembly disposed in the air passage. The aerodynamic mounting assembly is configured to retain the combustion liner within the flow sleeve. The aerodynamic mounting assembly includes a flow sleeve mount coupled to the flow sleeve and a liner stop coupled to the combustion liner. The flow sleeve mount includes a first portion of an aerodynamic shape and the liner stop includes a second portion of the aerodynamic shape, which is configured to direct an airflow into a wake region downstream of the aerodynamic mounting assembly. The flow sleeve mount and the liner stop couple with one another to define the aerodynamic shape.
摘要翻译：一种系统包括燃气轮机燃烧器，其包括围绕燃烧区域设置的燃烧衬套，围绕燃烧衬套设置的流动套筒，燃烧衬套和流动套筒之间的空气通道以及设置在空气通道中的空气动力学安装组件。空气动力学安装组件构造成将燃烧衬套保持在流动套筒内。空气动力学安装组件包括联接到流动套管的流动套筒安装件和联接到燃烧衬套的衬套止动件。流动套管安装件包括空气动力学形状的第一部分，并且衬套止动件包括空气动力学形状的第二部分，其被构造成将气流引导到空气动力学安装组件下游的尾流区域。流动套筒安装件和衬套止动件彼此联接以限定空气动力学形状。

119. 发明授权

US08893382B2 Combustion system and method of assembling the same 有权
标题翻译：燃烧系统及其组装方法
公开(公告)号：US08893382B2
公开(公告)日：2014-11-25
申请号：US13249868
申请日：2011-09-30
申请人： David Bruce Patterson , Donald Michael Corsmeier , Craig Douglas Young , Donald Lee Gardner , James Edward Thompson , Daniel Dale Brown , Glenn Edward Wiehe , Donald Scott Yeager , Mark Willard Marusko , Michael Joseph Zerbe
发明人： David Bruce Patterson , Donald Michael Corsmeier , Craig Douglas Young , Donald Lee Gardner , James Edward Thompson , Daniel Dale Brown , Glenn Edward Wiehe , Donald Scott Yeager , Mark Willard Marusko , Michael Joseph Zerbe
IPC分类号： B23P17/00 , F23R3/50 , F23R3/00 , F23R3/60
CPC分类号： F23R3/50 , F23R3/002 , F23R3/60 , Y02E20/16 , Y10T29/49229 , Y10T29/4932
摘要： A method of assembling a combustion system for a gas turbine engine includes providing a combustion chamber frame, an inner casing structure, and an outer casing structure. The method also includes mounting the combustion chamber frame between the inner casing structure and the outer casing structure such that the combustion chamber frame is coupled to the inner casing structure and the outer casing structure.
摘要翻译：一种组装燃气涡轮发动机的燃烧系统的方法包括提供燃烧室框架，内壳结构和外壳结构。该方法还包括将燃烧室框架安装在内壳结构和外壳结构之间，使得燃烧室框架联接到内壳结构和外壳结构。

120. 发明授权

US08863525B2 Combustor with fuel staggering for flame holding mitigation 有权
标题翻译：燃料燃烧惊人的火焰保持缓解
公开(公告)号：US08863525B2
公开(公告)日：2014-10-21
申请号：US12983342
申请日：2011-01-03
申请人： David Kaylor Toronto , Kwanwoo Kim , Abdul Rafey Khan , Luis Flamand
发明人： David Kaylor Toronto , Kwanwoo Kim , Abdul Rafey Khan , Luis Flamand
IPC分类号： F23R3/12 , F23R3/14 , F23R3/60 , F23R3/34 , F23R3/28 , F23R3/16
CPC分类号： F23R3/286 , F23D2900/14004 , F23D2900/14021 , F23R3/16 , F23R3/34 , F23R3/346 , F23R2900/03045
摘要： The present application provides a combustor. The combustor may include an air flow path with a flow of air therein. A flow obstruction may be positioned within the air flow path and cause a wake or a recirculation zone downstream thereof. A number of fuel injectors may be positioned downstream of the flow obstruction. The fuel injectors may inject a flow of fuel into the air flow path such that the flows of fuel and air in the wake or the recirculation zone do not exceed a flammability limit.
摘要翻译：本申请提供了一种燃烧器。燃烧器可包括其中具有空气流的气流通道。流动障碍物可以位于空气流动路径内并且在其下游引起尾流或再循环区域。多个燃料喷射器可以位于流动障碍物的下游。燃料喷射器可将燃料流注入空气流动路径，使得尾气或再循环区域中的燃料和空气流不超过可燃性极限。

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