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公开(公告)号：US20160215698A1
公开(公告)日：2016-07-28
申请号：US14527860
申请日：2014-10-30
申请人： Siemens Energy, Inc.
发明人： Andrew Carlson , William W. Pankey
IPC分类号： F02C7/20
CPC分类号： F01D25/28 , F01D9/023 , F02C7/20 , F05D2230/642 , F05D2240/90 , F05D2250/241 , F05D2260/31 , F23R3/60
摘要： A support arrangement (10) for a transition piece (12) of a gas turbine engine (14). The support arrangement includes a mounting bracket (16) for the transition piece and a pin (18) supporting the mounting bracket in an interior (20) of the gas turbine engine and extending through an opening (22) in a casing (24) to an exterior (26) of the as turbine engine. The support arrangement further includes a spherical washer (28, 38) positioned between the pin and either the mounting bracket or the casing
摘要翻译： 一种用于燃气涡轮发动机（14）的过渡件（12）的支撑装置（10）。 支撑装置包括用于过渡件的安装支架（16）和将燃料涡轮发动机的内部（20）支撑安装支架的销（18），并延伸穿过壳体（24）中的开口（22）至 作为涡轮发动机的外部（26）。 支撑装置还包括定位在销和安装支架或壳体之间的球形垫圈（28,38）
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公开(公告)号：US09394830B2
公开(公告)日：2016-07-19
申请号：US14134024
申请日：2013-12-19
发明人： Kelly J. McCormick
CPC分类号： F02C7/264 , F23D2207/00 , F23R3/002 , F23R3/60 , F23R2900/00012
摘要： An igniter tube assembly includes an igniter, an igniter tower with a radially extending portion, a ferrule with a radially extending portion, and a retainer with a radially extending portion. The ferrule and retainer capture the radially extending portion of the igniter tower and sealing surface provides an area for the ferrule to interface with the igniter tower. The igniter moves relative to the casing in which it is secured while a fluid seal between the igniter and ferrule controls air flow.
摘要翻译： 点火管组件包括点火器，具有径向延伸部分的点火塔，具有径向延伸部分的套圈和具有径向延伸部分的保持器。 套管和保持器捕获点火器塔的径向延伸部分，并且密封表面提供用于套圈与点火器塔相接合的区域。 点火器相对于其固定的壳体移动，而点火器和套圈之间的流体密封控制空气流动。
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公开(公告)号：US09377197B2
公开(公告)日：2016-06-28
申请号：US13387905
申请日：2010-07-20
CPC分类号： F23R3/002 , F23R3/04 , F23R3/60 , F23R2900/03044
摘要： A gas turbine combustion chamber has a housing (1), a flame tube (2) received therein, and a perforated plate (3) which at least partially surrounds the latter and which is fastened at both of its end faces (3.1, 3.2) to the housing.
摘要翻译： 燃气轮机燃烧室具有壳体（1），容纳在其中的火焰管（2）和多孔板（3），其多孔板（3）至少部分地围绕所述多孔板（3）并且紧固在其两个端面（3.1,3.2）上， 到房屋
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公开(公告)号：US20160169513A1
公开(公告)日：2016-06-16
申请号：US14965689
申请日：2015-12-10
CPC分类号： F23M20/005 , F23R3/002 , F23R3/60 , F23R2900/00014
摘要： The present invention relates to dampers for gas turbines and, for example, to a compensation assembly for a damper of a gas turbine for reducing the pulsations occurring in the combustion chamber. The damper can include a resonator cavity with a neck tube in flow communication with the interior of the combustion chamber, wherein the compensation assembly includes a spherical joint associated to the neck tube and configured to allow relative rotation between the combustion chamber and the resonator cavity, and having a bulb portion disposed around the neck tube and a spherical socket configured to internally host the bulb portion, wherein the spherical socket can have a top collar portion and a bottom collar portion connected to each other.
摘要翻译： 本发明涉及用于燃气轮机的阻尼器，例如涉及一种用于减少在燃烧室中发生的脉动的燃气轮机的阻尼器的补偿组件。 阻尼器可以包括谐振腔，其具有与燃烧室的内部流动连通的颈管，其中补偿组件包括与颈管相关联并被构造成允许燃烧室和谐振腔之间的相对旋转的球形接头， 并且具有设置在所述颈管周围的灯泡部分和被配置为内部地容纳所述灯泡部分的球形插座，其中所述球形插座可以具有彼此连接的顶部套环部分和底部套环部分。
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公开(公告)号：US09360217B2
公开(公告)日：2016-06-07
申请号：US13845485
申请日：2013-03-18
发明人： Richard Martin DiCintio , Patrick Benedict Melton , Lucas John Stoia , Christopher Paul Willis , Ronnie Ray Pentecost
CPC分类号： F23R3/20 , F02C7/22 , F23R3/005 , F23R3/34 , F23R3/46 , F23R3/60 , F23R2900/00017 , F23R2900/03043 , F23R2900/03045
摘要： A combustion module for a combustor of a gas turbine includes an annular fuel distribution manifold disposed at an upstream end of the combustion module. The fuel distribution manifold includes an annular support sleeve having an inner surface. The combustion module further includes a fuel injection assembly having an annular combustion liner that extends downstream from the fuel distribution manifold and that terminates at an aft frame, and an annular flow sleeve that circumferentially surrounds the combustion liner. The flow sleeve extends downstream from the fuel distribution manifold and terminates at the aft frame. The flow sleeve extends continuously between the support sleeve and the aft frame. A forward portion of the flow sleeve is positioned concentrically within the support sleeve where the forward portion is slidingly engaged with the inner surface of the support sleeve.
摘要翻译： 用于燃气轮机的燃烧器的燃烧模块包括设置在燃烧模块的上游端的环形燃料分配歧管。 燃料分配歧管包括具有内表面的环形支撑套筒。 燃烧模块还包括燃料喷射组件，该燃料喷射组件具有环形燃烧衬套，所述环形燃烧衬套从燃料分配歧管的下游延伸并终止在后部框架处;以及环形流动套筒，其环绕燃烧衬套。 流动套筒从燃料分配歧管的下游延伸并终止于后部框架。 流动套筒在支撑套筒和后架之间连续延伸。 流动套筒的前部部分同心地定位在支撑套筒内，其中前部部分与支撑套筒的内表面滑动接合。
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66.发明申请公开(公告)号：US20160153659A1
公开(公告)日：2016-06-02
申请号：US14904608
申请日：2014-06-18
CPC分类号： F23R3/007 , C09J5/00 , C09J2400/123 , C09J2400/163 , F01D5/284 , F01D9/02 , F01D25/246 , F05D2230/236 , F05D2230/642 , F05D2240/11 , F23R3/002 , F23R3/60 , F23R2900/00005 , F23R2900/00017 , Y02T50/672
摘要： A gas turbine engine component assembly includes a ceramic component having a first thermal characteristic. A metallic component has a second thermal characteristic. A bonding material secures the ceramic component to the metallic component. The bonding material includes at least one of a transient liquid phase bond and a partial transient liquid phase bond. The bonding material is configured to withstand a shear stress parameter relating to a differential between the first and second thermal characteristics.
摘要翻译： 燃气涡轮发动机部件组件包括具有第一热特性的陶瓷部件。 金属部件具有第二热特性。 粘结材料将陶瓷组分固定在金属组分上。 接合材料包括瞬态液相和部分瞬态液相键中的至少一种。 接合材料被配置为承受与第一和第二热特性之间的差异相关的剪切应力参数。
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公开(公告)号：US09328926B2
公开(公告)日：2016-05-03
申请号：US13426070
申请日：2012-03-21
申请人： Stefan Penz , Miklos Gerendas , Sermed Sadig
发明人： Stefan Penz , Miklos Gerendas , Sermed Sadig
CPC分类号： F23R3/60 , F23R3/002 , F23R3/10 , F23R3/283 , F23R2900/00012 , F23R2900/00014
摘要： A combustion chamber head for a gas turbine, with the gas turbine having a substantially annular outer combustion chamber wall, at least one substantially annular inner combustion chamber wall, and several burners 106 distributed around a circumference of the gas turbine. Several segment-like head segments are arranged over the circumference in equal number to the number of burners and extend in the radial direction between the inner combustion chamber wall and the outer combustion chamber wall and in the circumferential direction between radial planes formed by the burner axes.
摘要翻译： 一种用于燃气轮机的燃烧室头部，其中燃气轮机具有基本上环形的外部燃烧室壁，至少一个基本上环形的内部燃烧室壁和分布在燃气轮机周围的多个燃烧器106。 在圆周上布置几个段状的头部段，其数量与燃烧器的数量相等，并且在径向方向上在内燃机室壁和外部燃烧室壁之间以及在由燃烧器轴形成的径向平面之间的圆周方向上延伸 。
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68.发明授权Transition support system for combustion transition ducts for turbine engines 有权用于涡轮发动机燃烧过渡管道的过渡支撑系统公开(公告)号：US09328664B2
公开(公告)日：2016-05-03
申请号：US14074911
申请日：2013-11-08
申请人： Keith W. Piersall , Yevgeniy Shteyman , Robert Angel , Ashley N. Girdich , Robert T. Brooks , James Alfonso , James Marshall
发明人： Keith W. Piersall , Yevgeniy Shteyman , Robert Angel , Ashley N. Girdich , Robert T. Brooks , James Alfonso , James Marshall
CPC分类号： F02C7/20 , F01D9/023 , F01D25/04 , F02C9/16 , F05D2260/30 , F05D2260/96 , F23R3/46 , F23R3/60 , F23R2900/00014
摘要： An adjustable transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas turbine inlet of a turbine engine. The adjustable transition duct support system includes an adjustable forward transition flexible support assembly in contact with a transition duct body, whereby the forward transition flexible support assembly may be formed from a base extending toward the transition duct body and first and second side support arms extending from the base to the transition duct body. The first and second side support arms may be formed from a plurality of flex plates spaced from each other with spacers that provide rigidity in circumferential and radial directions and flexibility in an axial direction. The number of flex plates used may be varied to accommodate different turbine engines. The adjustable transition duct support system may have natural frequencies for circumferential and radial modes above two engine orders.
摘要翻译： 用于过渡管道的可调节的过渡管道支撑系统，其将来自燃烧器出口的热气体引导到涡轮发动机的燃气涡轮机入口。 可调节的过渡管道支撑系统包括与过渡管道本体接触的可调节的向前过渡的柔性支撑组件，由此前向过渡的柔性支撑组件可由朝向过渡管道本体延伸的基部形成，并且第一和第二侧支撑臂从 基座到过渡管体。 第一侧支撑臂和第二侧支撑臂可以由多个彼此间隔开的柔性板形成，间隔件在周向和径向方向上提供刚性并且在轴向方向上具有柔性。 所使用的柔性板的数量可以变化以适应不同的涡轮发动机。 可调节的过渡管道支撑系统可以具有高于两个发动机顺序的周向和径向模式的固有频率。
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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
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。
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公开(公告)号：US20160054004A1
公开(公告)日：2016-02-25
申请号：US14462646
申请日：2014-08-19
CPC分类号： F23R3/283 , F02C7/18 , F05B2260/201 , F23R3/002 , F23R3/04 , F23R3/10 , F23R3/60 , F23R2900/03041 , F23R2900/03044 , Y02T50/675
摘要： A combustor cap assembly includes an annular shroud and an impingement plate coupled to the shroud. The impingement plate at least partially defines a plurality of impingement cooling holes and a cooling flow return passage. A cap plate is coupled to the impingement plate. The cap plate includes an impingement side which faces a second side portion of the impingement plate where the impingement side is axially spaced from the second side portion to define an impingement air plenum therebetween. The cooling flow return passage is in fluid communication with the impingement air plenum. A fluid conduit extends from a first side portion of the impingement plate towards a first end portion of the shroud. The fluid conduit is in fluid communication with the cooling flow return passage and provides for fluid communication out of the impingement air plenum.
摘要翻译： 燃烧器盖组件包括环形护罩和联接到护罩的冲击板。 冲击板至少部分地限定多个冲击冷却孔和冷却流回流通道。 盖板联接到冲击板。 盖板包括面对冲击板的第二侧部的冲击侧，其中冲击侧与第二侧部轴向间隔开，以在其间限定冲击空气增压室。 冷却回流通道与冲击空气通风室流体连通。 流体导管从冲击板的第一侧部朝向护罩的第一端部延伸。 流体导管与冷却流回流通道流体连通，并提供流体连通到冲击空气通风室外。
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