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61. 发明授权

US08938978B2 Gas turbine engine combustor with lobed, three dimensional contouring 有权
标题翻译：燃气涡轮发动机燃烧器具有叶片，三维轮廓
公开(公告)号：US08938978B2
公开(公告)日：2015-01-27
申请号：US13099938
申请日：2011-05-03
申请人： Donald Mark Bailey , Jonathan Dwight Berry , Luis Manuel Flamand , Kwanwoo Kim , Patrick Benedict Melton , Robert Joseph Rohrssen , John Drake Vanselow
发明人： Donald Mark Bailey , Jonathan Dwight Berry , Luis Manuel Flamand , Kwanwoo Kim , Patrick Benedict Melton , Robert Joseph Rohrssen , John Drake Vanselow
IPC分类号： F23R3/28 , F23R3/46 , F23R3/54
CPC分类号： F23R3/283 , F23D2900/00003 , F23R3/286 , F23R3/46 , F23R3/54 , F23R2900/00017 , F23R2900/00018
摘要： A gas turbine engine combustor is provided and includes an array of fuel nozzles, a combustion casing assembly disposed about the array of fuel nozzles and an end cap assembly disposed within the combustion casing assembly to define with the combustion casing assembly an axis-symmetric annulus through which fluid travels into each of the fuel nozzles, at least one of the combustion casing assembly and the end cap assembly being formed with lobed, three-dimensional contouring.
摘要翻译：提供了一种燃气涡轮发动机燃烧器，其包括燃料喷嘴阵列，围绕燃料喷嘴阵列设置的燃烧壳体组件和设置在燃烧壳体组件内的端盖组件，以便与燃烧壳体组件形成轴对称的环通过所述流体行进到每个燃料喷嘴中，燃烧壳体组件和端盖组件中的至少一个形成有叶状的三维轮廓。

62. 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。

63. 发明授权

US08919137B2 Assemblies and apparatus related to integrating late lean injection into combustion turbine engines 有权
标题翻译：与后期精馏注入燃气涡轮发动机相关的装置和装置
公开(公告)号：US08919137B2
公开(公告)日：2014-12-30
申请号：US13204340
申请日：2011-08-05
申请人： Richard Martin DiCintio , Patrick Benedict Melton , Lucas John Stoia
发明人： Richard Martin DiCintio , Patrick Benedict Melton , Lucas John Stoia
IPC分类号： F23R3/34 , F23R3/04
CPC分类号： F23R3/346 , F23R3/045
摘要： An assembly for use in a late lean injection system of a combustor of a combustion turbine engine, wherein the combustor includes an inner radial wall, which defines a primary combustion chamber downstream of a primary fuel nozzle, and an outer radial wall, which surrounds the inner radial wall forming a flow annulus therebetween, the assembly comprising: a boss rigidly secured to the inner radial wall, the boss being configured to define a hollow passageway through the inner radial wall; a transfer tube slideably engaged within the boss; a stop formed on the transfer tube; and damping means positioned between the boss and the stop.
摘要翻译：一种用于燃气涡轮发动机的燃烧器的后期稀注射系统的组件，其中所述燃烧器包括限定主燃料喷嘴下游的主燃烧室的内径向壁，以及外径向壁围绕所述内部径向壁在其间形成流动环空，所述组件包括：刚性地固定到所述内部径向壁的凸台，所述凸起构造成限定通过所述内部径向壁的中空通道; 转移管可滑动地接合在所述凸台内; 形成在转移管上的止动件; 以及位于凸台和止挡件之间的阻尼装置。

64. 发明授权

US08820086B2 Gas turbine combustor endcover assembly with integrated flow restrictor and manifold seal 有权
标题翻译：具有集成流量限制器和歧管密封件的燃气轮机燃烧器整流器组件
公开(公告)号：US08820086B2
公开(公告)日：2014-09-02
申请号：US13008399
申请日：2011-01-18
申请人： Donald Mark Bailey , Donald Timothy Lemon , Kwanwoo Kim , Patrick Benedict Melton
发明人： Donald Mark Bailey , Donald Timothy Lemon , Kwanwoo Kim , Patrick Benedict Melton
IPC分类号： F02C1/00
CPC分类号： F23R3/283 , F23K5/14 , F23K2900/05142 , F23R2900/00005 , F23R2900/00012
摘要： An endcover assembly for a turbine combustor adapted to support one or more combustor nozzles includes a substantially flat plate having one side which in use, faces a combustion chamber and an opposite side which, in use, faces away from the combustion chamber. At least one fuel passage extends through the substantially flat plate. A fuel manifold porting block is secured to the opposite side of the flat plate with at least one port aligned with the at least one passage. A fuel restrictor insert formed with multiple flow orifices is located between the flat plate and the fuel manifold porting block in alignment with the at least one fuel passage and the at least one port.
摘要翻译：适于支撑一个或多个燃烧器喷嘴的用于涡轮机燃烧器的封盖组件包括基本平坦的板，其具有一个侧面，其在使用中面向燃烧室，在使用中相对侧面远离燃烧室。至少一个燃料通道延伸穿过基本平坦的板。燃料歧管移动块被固定到平板的相对侧，其中至少一个端口与至少一个通道对准。形成有多个流动孔的燃料限制器插件位于平板和燃料歧管移动块之间，与至少一个燃料通道和至少一个端口对准。

65. 发明授权

US08601820B2 Integrated late lean injection on a combustion liner and late lean injection sleeve assembly 有权
标题翻译：在燃烧衬套和后期精密注射套筒组件上集成后期精馏
公开(公告)号：US08601820B2
公开(公告)日：2013-12-10
申请号：US13153944
申请日：2011-06-06
申请人： William Byrne , Patrick Benedict Melton , David William Cihlar , Lucas Stoia
发明人： William Byrne , Patrick Benedict Melton , David William Cihlar , Lucas Stoia
IPC分类号： F02C3/00 , F02C7/22 , F02C1/04 , F02C7/224
CPC分类号： F23R3/346 , F23R3/06 , F23R3/283 , F23R3/286
摘要： A late lean injection sleeve assembly allows the injection of fuel at the aft end of a gas turbine liner, before the transition piece, into the combustion gases downstream of a turbine combustor's fuel nozzles. The late lean injection enables fuel injection downstream of the fuel nozzles to create a secondary/tertiary (with quaternary injection upstream of the fuel nozzles) combustion zone while reducing/eliminating the risk of fuel leaking into the combustor discharge case. The fuel is delivered by the flow sleeve into one or more nozzles that mix the fuel with CDC air before injecting it into the combustor's liner.
摘要翻译：后期的稀薄注射套筒组件允许将燃料涡轮机衬套的后端处的燃料喷射到涡轮机燃烧器的燃料喷嘴下游的燃烧气体中。后期的稀薄喷射使得燃料喷嘴下游的燃料喷射能够在减少/消除燃料泄漏到燃烧器排出壳体中的风险的同时产生二级/三级（在燃料喷嘴的上游具有四级注入）燃烧区域。燃料由流动套管输送到一个或多个喷嘴中，该喷嘴将燃料与CDC空气混合，然后将其注入到燃烧器的衬套内。

66. 发明申请

US20130269820A1 Method, Systems, And Apparatuses For Transition Piece Contouring 有权
标题翻译：方法，系统和设备转换片轮廓
公开(公告)号：US20130269820A1
公开(公告)日：2013-10-17
申请号：US13446751
申请日：2012-04-13
申请人： Richard Martin DiCintio , Patrick Benedict Melton , Lucas John Stoia
发明人： Richard Martin DiCintio , Patrick Benedict Melton , Lucas John Stoia
IPC分类号： F16L9/00 , G06F17/50 , B23P15/00
CPC分类号： F01D9/023 , F05D2230/00 , F05D2250/70 , G06F17/5009 , G06F17/5086 , G06F2217/80 , Y10T29/49234
摘要： Disclosed herein are apparatuses, methods, and systems for transition piece contouring. In an embodiment, a high thermal stress section of a transition piece and a low thermal stress section of a transition piece is a determined The low thermal stress section of the transition piece may be contoured to intercept hot gas flow.
摘要翻译：本文公开了用于过渡件轮廓加工的装置，方法和系统。在一个实施例中，确定过渡件的高热应力部分和过渡件的低热应力部分。过渡件的低热应力部分可以被轮廓化以截取热气流。

67. 发明申请

US20130263604A1 SYSTEM AND METHOD FOR SUPPORTING FUEL NOZZLES INSIDE A COMBUSTOR 有权
标题翻译：用于支持燃油喷射器的系统和方法
公开(公告)号：US20130263604A1
公开(公告)日：2013-10-10
申请号：US13439973
申请日：2012-04-05
申请人： Lucas John Stoia , Patrick Benedict Melton
发明人： Lucas John Stoia , Patrick Benedict Melton
IPC分类号： F02C7/232 , B23P11/00
CPC分类号： F23R3/60 , F23R3/283 , Y10T29/4932
摘要： A system for supporting fuel nozzles inside a combustor includes a ring that circumferentially surrounds the fuel nozzles inside the combustor, a support plate that extends radially inside at least a portion of the ring, and a first connection between the support plate and at least one of the fuel nozzles inside the combustor. A second connection is between the support plate and the ring. A method for supporting fuel nozzles in a combustor includes surrounding the fuel nozzles with a ring, connecting a support plate to the ring, and connecting the support plate to at least one fuel nozzle.
摘要翻译：用于在燃烧器内部支撑燃料喷嘴的系统包括周向围绕燃烧器内的燃料喷嘴的环，支撑板，其在环的至少一部分的径向内延伸，以及在支撑板和至少一个之间的第一连接燃烧器内部的燃料喷嘴。第二连接在支撑板和环之间。用于在燃烧器中支撑燃料喷嘴的方法包括用环围绕燃料喷嘴，将支撑板连接到环上，并将支撑板连接到至少一个燃料喷嘴。

68. 发明申请

US20130232986A1 COMBUSTOR AND METHOD FOR REDUCING THERMAL STRESSES IN A COMBUSTOR 审中-公开
标题翻译：用于减少燃烧器中的热应力的COMBUSTOR和方法
公开(公告)号：US20130232986A1
公开(公告)日：2013-09-12
申请号：US13417409
申请日：2012-03-12
申请人： Lucas John Stoia , Patrick Benedict Melton , Richard Martin DiCintio
发明人： Lucas John Stoia , Patrick Benedict Melton , Richard Martin DiCintio
IPC分类号： F02C7/22 , F23R3/28
CPC分类号： F23R3/28 , F02C7/222 , F05D2260/231 , F05D2260/941 , F23R2900/00005
摘要： A combustor includes a combustion chamber and a casing that circumferentially surrounds the combustion chamber to at least partially define an annular passage between the casing and the combustion chamber. A fuel plenum extends radially through the casing to provide fluid communication through the casing to the annular passage, and a liner extends inside at least a portion of the fuel plenum to prevent fuel from directly impinging upon at least a portion of the fuel plenum. A method of reducing thermal stresses in a combustor includes flowing a fuel inside a fuel plenum that extends radially through a casing, shielding at least a portion of the fuel plenum from direct impingement by the fuel radially inward of the casing, and flowing the fuel from the fuel plenum into an annular passage between the casing and a combustion chamber.
摘要翻译：燃烧器包括燃烧室和围绕燃烧室的壳体，以至少部分地限定壳体和燃烧室之间的环形通道。燃料增压室径向地延伸穿过壳体以提供通过壳体到环形通道的流体连通，并且衬套在燃料增压室的至少一部分内部延伸，以防止燃料直接撞击在燃料增压室的至少一部分上。一种降低燃烧器中的热应力的方法包括将燃料通过一个径向延伸穿过壳体的燃料增压室流动，从而屏蔽至少一部分燃料压力室不受壳体径向向内的燃料的直接冲击，并使燃料从燃料增压室进入壳体和燃烧室之间的环形通道。

69. 发明申请

US20130227964A1 TRANSITION PIECE AFT FRAME ASSEMBLY HAVING A HEAT SHIELD 有权
标题翻译：具有热屏蔽的过渡边缘组合框架组件
公开(公告)号：US20130227964A1
公开(公告)日：2013-09-05
申请号：US13410417
申请日：2012-03-02
申请人： Christopher Paul Willis , William Lawrence Byrne , David William Cihlar , Donald Timothy Lemon , Patrick Benedict Melton
发明人： Christopher Paul Willis , William Lawrence Byrne , David William Cihlar , Donald Timothy Lemon , Patrick Benedict Melton
IPC分类号： F02C7/12 , F01D25/14
CPC分类号： F01D9/023
摘要： A transition piece aft frame assembly is provided, and includes a transition piece aft frame and a heat shield. The transition piece aft frame has an aft face. At least a portion of the aft face is exposed to an exhaust gas stream. The heat shield is connected to the transition piece aft frame. The heat shield is oriented to generally deflect the exhaust gas stream away from the aft face of the transition piece aft frame.
摘要翻译：提供过渡件后框架组件，并且包括过渡件后框架和隔热罩。过渡件后框架有一个后面。后表面的至少一部分暴露于排气流。隔热罩与过渡件后框架连接。隔热罩被定向成使废气流大致偏离过渡件后框架的后表面。

70. 发明申请

US20130213051A1 COMBUSTOR AND METHOD FOR SUPPLYING FUEL TO A COMBUSTOR 有权
标题翻译：用于向燃烧器供应燃料的燃烧器和方法
公开(公告)号：US20130213051A1
公开(公告)日：2013-08-22
申请号：US13400248
申请日：2012-02-20
申请人： James Harold Westmoreland, III , Patrick Benedict Melton
发明人： James Harold Westmoreland, III , Patrick Benedict Melton
IPC分类号： F02C7/22 , F02C3/20
CPC分类号： F23R3/286 , F23D14/62 , F23R3/36
摘要： A combustor includes an end cap having upstream and downstream surfaces and a cap shield surrounding the upstream and downstream surfaces. First and second sets of premixer tubes extend from the upstream surface through the downstream surface. A first fuel conduit supplies fuel to the first set of premixer tubes. A casing circumferentially surrounds the cap shield to define an annular passage, and a second fuel conduit supplies fuel through the annular passage to the second set of premixer tubes. A method for supplying fuel to a combustor includes flowing a working fluid through first and second sets of premixer tubes, flowing a first fuel into the first set of premixer tubes, and flowing a second fuel through an annular passage surrounding the end cap and into the second set of premixer tubes.
摘要翻译：燃烧器包括具有上游和下游表面的端盖和围绕上游表面和下游表面的盖罩。第一组和第二组预混合管从上游表面延伸穿过下游表面。第一燃料管道向第一组预混合器管供应燃料。壳体周向地围绕盖罩以限定环形通道，并且第二燃料管道将燃料通过环形通道供应到第二组预混合器管。用于向燃烧器供应燃料的方法包括使工作流体流过第一组和第二组预混合器管，将第一燃料流入第一组预混合器管，并使第二种燃料流过围绕端盖的环形通道并进入第二组预混管。

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