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1. 发明申请

WO2015199694A1 CONVERGING FLOW JOINT INSERT SYSTEM AT AN INTERSECTION BETWEEN ADJACENT TRANSITIONS DUCT BODIES 审中-公开
标题翻译：在相邻过渡部门之间的交汇处的汇流流水线插入系统
公开(公告)号：WO2015199694A1
公开(公告)日：2015-12-30
申请号：PCT/US2014/044289
申请日：2014-06-26
申请人： SIEMENS ENERGY, INC.
发明人： BROOKS, Robert T.
IPC分类号： F01D9/02 , F02C3/14 , F23R3/42
CPC分类号： F01D9/023 , F02C3/14 , F05D2250/25 , F05D2250/37 , F05D2250/38 , F05D2260/941 , F23R3/002 , F23R3/425 , F23R3/60 , F23R2900/00019
摘要： A transition duct system (100) for routing a gas flow from a combustor (102) to the first stage (104) of a turbine section (106) in a combustion turbine engine (108), wherein the transition duct system (100) includes one or more converging flow joint inserts (120) forming a trailing edge (122) at an intersection (124) between adjacent transition ducts (126, 128) is disclosed. The transition duct system (100) includes first and second transition ducts (126, 128) having an internal passage (130) extending between an inlet (132, 184) to an outlet (134, 186) and expelling gases into the first stage turbine (104) with a tangential component. The converging flow joint insert (120) is positioned within a recess (300) of the converging flow joint at the downstream end of the flow joint to form a trailing edge of the flow joint. The converging flow joint insert (120) may be removable such that the insert (120) can be replaced once worn beyond design limits.
摘要翻译： 1.一种用于将来自燃烧器（102）的气流引导到燃气涡轮发动机（108）中的涡轮部分（106）的第一级（104）的过渡管道系统（100），其中所述过渡管道系统（100）包括公开了在相邻过渡管道（126,128）之间的交叉点（124）处形成后缘（122）的一个或多个会聚流动接头插入件（120）。过渡管道系统（100）包括第一和第二过渡管道（126,128），其具有在入口（132,184）到出口（134,186）之间延伸的内部通道（130），并将气体排入第一级涡轮机（104）具有切向分量。会聚流动接头插入件（120）位于流动接头的下游端处的会聚流动接头的凹部（300）内，以形成流动接头的后缘。会聚流动接头插入件（120）可以是可移除的，使得插入件（120）可以被佩戴超过设计限制。

2. 发明申请

WO2013028163A1 TANGENTIAL AND FLAMELESS ANNULAR COMBUSTOR FOR USE ON GAS TURBINE ENGINES 审中-公开
标题翻译：用于气体涡轮发动机的通风和无风口环形燃烧器
公开(公告)号：WO2013028163A1
公开(公告)日：2013-02-28
申请号：PCT/US2011/048581
申请日：2011-08-22
申请人： TOQAN, Majed , GREGORY, Brent, Allan , REGELE, Jonathan, David , YAMANE, Ryan, Sadao
发明人： TOQAN, Majed , GREGORY, Brent, Allan , REGELE, Jonathan, David , YAMANE, Ryan, Sadao
IPC分类号： F23R3/00
CPC分类号： F23R3/425 , F23R3/58 , F23R2900/00002 , Y02E20/342 , Y02E20/344 , Y02T50/678
摘要： A combustion device used in gas turbine engines that produces propulsion or rotates a shaft for power generation includes an annular combustor with a system of fuel and air inlet passages and nozzles that results in a flameless combustor, such that there is not an anchored flame as in typical gas turbine combustors. The fuel and air inlets are placed at various longitudinal locations and circumferentially spaced, and take on several different configurations where some nozzles inject only air and others inject a rich fuel-air mixture. The combustion device provides an optimal mixing of fuel and air as well as creates an environment for combustion that reduces pollutant emissions reducing the need for costly pollution control devices, and enhances ignition and flame stability, reduces piloting issues and improves vibration reduction.
摘要翻译：用于产生推进或旋转轴用于发电的燃气涡轮发动机中的燃烧装置包括具有燃料和空气入口通道和喷嘴系统的环形燃烧器，其导致无焰燃烧器，使得不存在锚定的火焰，如典型的燃气轮机燃烧器。燃料和空气入口被放置在各种纵向位置并且周向间隔开，并且具有几种不同的构造，其中一些喷嘴仅喷射空气，而其它喷嘴注入富燃料 - 空气混合物。燃烧装置提供燃料和空气的最佳混合，并且产生燃烧环境，其减少污染物排放，减少对昂贵的污染控制装置的需要，并且增强点燃和火焰稳定性，减少驾驶问题并改善减振。

3. 发明申请

WO2010036426A3 MODULAR TRANSVANE ASSEMBLY 审中-公开
标题翻译：模块化变电站组件
公开(公告)号：WO2010036426A3
公开(公告)日：2011-03-10
申请号：PCT/US2009047213
申请日：2009-08-27
申请人： SIEMENS ENERGY INC , WILSON JODY W , NORDLUND RAYMOND S , CHARRON RICHARD C
发明人： WILSON JODY W , NORDLUND RAYMOND S , CHARRON RICHARD C
IPC分类号： F01D9/02 , F23R3/42 , F23R3/46
CPC分类号： F01D9/023 , F05D2240/40 , F05D2250/121 , F05D2250/141 , F05D2250/322 , F05D2250/323 , F05D2250/324 , F23R3/425 , F23R3/46
摘要： An arrangement for delivering gasses from can combustors of a can annular gas turbine combustion engine to a turbine first stage section including a first row of turbine blades, the arrangement including a flow-directing structure for each combustor, wherein each flow-directing structure includes a straight path and an annular chamber end, wherein the annular chamber ends together define an annular chamber for delivering the gas flow to the turbine first stage section, wherein gasses flow from respective combustors, through respective straight paths, and into the annular chamber as respective straight gas flows, and wherein the annular chamber is configured to unite the respective straight gas flows along respective shear planes to form a singular annular gas flow, and wherein the annular chamber is configured to impart circumferential motion to the singular annular gas flow before the singular annular gas flow exits the annular chamber to the first row of blades.
摘要翻译：一种用于将罐状罐式燃气轮机燃烧器的气体输送到包括第一排涡轮机叶片的涡轮机第一级部分的装置，该装置包括用于每个燃烧器的流动导向结构，其中每个流动导向结构包括直线路径和环形室端部，其中环形室端部一起限定了用于将气流输送到涡轮机第一级段的环形室，其中气体通过相应的直线路径从相应的燃烧器流动，并作为相应的直线气体流动，并且其中所述环形室被构造成沿着相应的剪切平面联合相应的直的气体流以形成奇异的环形气流，并且其中所述环形室被构造成在所述单个环形气流气流离开环形室到第一排叶片。

4. 发明申请

WO2010056520A1 MULTI-TUBE, CAN-ANNULAR PULSE DETONATION COMBUSTOR BASED ENGINE 审中-公开
标题翻译：多管，CAN-ANNULAR PULSE爆炸燃烧器基于发动机
公开(公告)号：WO2010056520A1
公开(公告)日：2010-05-20
申请号：PCT/US2009/062328
申请日：2009-10-28
申请人： GENERAL ELECTRIC COMPANY , KENYON, Ross, Hartley , JOSHI, Narendra, Digamber , TANGIRALA, Venkat, Eswarlu , DEAN, Anthony, John , RASHEED, Adam , GLASER, Aaron, Jerome
发明人： KENYON, Ross, Hartley , JOSHI, Narendra, Digamber , TANGIRALA, Venkat, Eswarlu , DEAN, Anthony, John , RASHEED, Adam , GLASER, Aaron, Jerome
IPC分类号： F23R7/00 , F02C5/02 , F23C15/00 , F02C5/12
CPC分类号： F02C5/02 , F02C5/12 , F05D2250/322 , F23C15/00 , F23D14/42 , F23R3/425 , F23R7/00 , F23R2900/00014
摘要： An engine (100) contains a compressor stage (101), a pulse detonation combustion stage (105) and a turbine stage (103). The pulse detonation combustion stage contains at least one pulse detonation combustor (109) which has an inlet portion (111). The pulse detonation combustor is oriented longitudinally and/or tangentially with respect to a centerline of the engine. A plenum (115), a casing (107), a diffuser (119) and a shroud (113) can be added in this combustion stage to achieve better performances.
摘要翻译：发动机（100）包括压缩机级（101），脉冲爆燃燃烧级（105）和涡轮级（103）。脉冲爆震燃烧阶段包含至少一个具有入口部分（111）的脉冲爆震燃烧器（109）。脉冲爆震燃烧器相对于发动机的中心线纵向和/或切向地定向。可以在该燃烧阶段添加增压室（115），壳体（107），扩散器（119）和护罩（113）以实现更好的性能。

5. 发明申请

WO2010019175A2 TRANSITION WITH A LINEAR FLOW PATH FOR USE IN A GAS TURBINE ENGINE 审中-公开
标题翻译：用于在气体涡轮发动机中使用的线性流动路径的过渡
公开(公告)号：WO2010019175A2
公开(公告)日：2010-02-18
申请号：PCT/US2009/000980
申请日：2009-02-17
申请人： SIEMENS ENERGY, INC. , CHARRON, Richard , MONTGOMERY, Matthew , SNYDER, Gary
发明人： CHARRON, Richard , MONTGOMERY, Matthew , SNYDER, Gary
IPC分类号： F01D9/02
CPC分类号： F01D9/023 , F05D2240/128 , F05D2250/25 , F23R3/425 , Y02T50/675
摘要： A transition duct (94) for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct (94) may have an internal passage (102) extending between an inlet (98) to an outlet (100). An axis (130) of the transition duct body (96) may be generally linear such that gases expelled from the transition duct body (96) flow in a proper direction into the downstream turbine blades.
摘要翻译：公开了一种用于将来自燃烧器的气流引导到燃气涡轮发动机中的涡轮部分的第一级的过渡管道（94）。过渡管道（94）可以具有在入口（98）到出口（100）之间延伸的内部通道（102）。过渡管体（96）的轴线（130）可以是大致直线的，使得从过渡管体（96）排出的气体沿适当的方向流入下游的涡轮叶片。

6. 发明申请

WO2017018982A1 GAS TURBINE TRANSITION DUCT WITH LATE LEAN INJECTION HAVING REDUCED COMBUSTION RESIDENCE TIME 审中-公开
标题翻译：具有降低燃烧停留时间的轻度注射的气体涡轮转换管
公开(公告)号：WO2017018982A1
公开(公告)日：2017-02-02
申请号：PCT/US2015/041948
申请日：2015-07-24
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： LASTER, Walter Ray , PORTILLO BILBAO, Juan Enrique , FOX, Timothy A. , POWERS, Grant L.
IPC分类号： F23R3/42 , F23R3/06 , F23R3/28 , F23R3/34 , F23R3/46 , F01D9/02
CPC分类号： F01D9/023 , F23R3/06 , F23R3/286 , F23R3/346 , F23R3/425 , F23R3/46
摘要： An improved gas turbine combustion system having a reduced combustion residence time in a combustion turbine engine is provided. The combustion system includes a flow-accelerating structure (16, 51), such as a transition duct, having an inlet (26) and an outlet (28). The inlet (26) of the flow-accelerating structure () is fluidly coupled to receive a flow of combustion gases from a combustor outlet. At least one fuel injector (32, 64, 66) is disposed between the inlet (26) and the outlet (28) of the flow-accelerating structure (16, 51). The flow-accelerating structure (16, 51) causes an increasing speed to the flow of combustion gases, and, as a result, the flow of combustion gases in the flow-accelerating structure (16, 51) experiences a decreased static temperature and a reduced combustion residence time, each of which is effective to reduce NOx emissions at the high firing temperatures of the turbine engine.
摘要翻译：提供了一种在燃气轮机中具有减少的燃烧停留时间的改进的燃气轮机燃烧系统。燃烧系统包括具有入口（26）和出口（28）的流动加速结构（16,51），例如过渡管道。流动加速结构（）的入口（26）流体耦合以接收来自燃烧器出口的燃烧气体流。至少一个燃料喷射器（32,64,66）设置在流动加速结构（16,51）的入口（26）和出口（28）之间。流动加速结构（16,51）对燃烧气体的流动造成增加的速度，结果，流动加速结构（16,51）中的燃烧气体的流动经历降低的静态温度和减少的燃烧停留时间，其中每个都有效地减少在涡轮发动机的高燃烧温度下的NOx排放。

7. 发明申请

WO2015126587A1 GAS FLOW PATH FOR A GAS TURBINE ENGINE 审中-公开
标题翻译：用于气体涡轮发动机的气体流路
公开(公告)号：WO2015126587A1
公开(公告)日：2015-08-27
申请号：PCT/US2015/013402
申请日：2015-01-29
申请人： SIEMENS ENERGY, INC.
发明人： MONTGOMERY, Matthew D. , CHARRON, Richard C. , SNYDER, Gary D. , PANKEY, William W. , MAYER, Clinton A. , HETTINGER, Benjamin G.
IPC分类号： F01D9/02 , F23R3/42 , F23R3/46 , F23R3/00
CPC分类号： F23R3/46 , F01D9/023 , F23R3/425 , F23R3/60 , F23R2900/00017 , F23R2900/03342
摘要： A duct arrangement in a can annular gas turbine engine. The gas turbine engine has a gas delivery structure for delivering gases from a plurality of combustors to an annular chamber that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis for delivering the gas flow to a first row of blades. A gas flow path is formed by the duct arrangement between a respective combustor and the annular chamber for conveying gases from each combustor to the first row of turbine blades. The duct arrangement includes at least one straight section having a centerline that is misaligned with a centerline of the combustor.
摘要翻译：罐式环形燃气涡轮发动机中的管道装置。燃气涡轮发动机具有气体输送结构，用于将气体从多个燃烧器输送到周向延伸的环形室，并且与气体涡轮发动机纵向轴线同心地定向，以将气流输送到第一排叶片。气体流路由相应的燃烧器和环形室之间的管道装置形成，用于将气体从每个燃烧器输送到第一排涡轮叶片。管道装置包括具有与燃烧器的中心线不对准的中心线的至少一个直线部分。

8. 发明申请

WO2015069450A1 GAS TURBINE ENGINE DUCTING ARRANGMENT HAVING DISCRETE INSERT 审中-公开
标题翻译：具有离散插件的气体涡轮发动机排气装置
公开(公告)号：WO2015069450A1
公开(公告)日：2015-05-14
申请号：PCT/US2014/061544
申请日：2014-10-21
申请人： SIEMENS ENERGY, INC.
发明人： MARRA, John J. , MORRISON, Jay A. , CAMPBELL, Ernie B.
IPC分类号： F01D9/02 , F23R3/42
CPC分类号： F01D9/023 , F05D2260/941 , F05D2270/114 , F23R3/425 , F23R3/46
摘要： A ducting arrangement (10), including: a plurality of discrete ducts (18), each defining a flow path and configured to receive a flow of combustion gases from a respective combustor can, where the plurality of discrete ducts merge to form a common duct structure; and a throat insert (50) configured to define at least part of a junction of one of the discrete ducts and the common duct structure.
摘要翻译：一种管道装置（10），包括：多个分立的管道（18），每个管道限定流路并被构造成从相应的燃烧器罐接收燃烧气体流，其中所述多个离散管道合并形成公共管道结构体; 以及喉部插入件（50），其构造成限定所述离散管道和所述公共管道结构中的一个的至少部分接合部。

9. 发明申请

WO2013028169A1 CAN-ANNULAR COMBUSTOR WITH PREMIXED TANGENTIAL FUEL-AIR NOZZLES FOR USE ON GAS TURBINE ENGINES 审中-公开
标题翻译：具有预先使用在燃气涡轮发动机上的先进燃油喷嘴的CAN-ANNULAR COMBUSTOR
公开(公告)号：WO2013028169A1
公开(公告)日：2013-02-28
申请号：PCT/US2011048622
申请日：2011-08-22
申请人： TOQAN MAJED , GREGORY BRENT ALLAN , REGELE JONATHAN DAVID , YAMANE RYAN SADAO
发明人： TOQAN MAJED , GREGORY BRENT ALLAN , REGELE JONATHAN DAVID , YAMANE RYAN SADAO
IPC分类号： F02C3/00
CPC分类号： F23R3/346 , F23R3/425 , F23R3/58
摘要： A combustion device used in gas turbine engines to produce propulsion or rotate a shaft for power generation includes a can-annular combustor with a system of fuel and air inlet passages and nozzles that results in an optimal combustion environment of premixed fuel and air. The fuel-air inlets are placed at various longitudinal locations and circumferentially distributed, and direct the flow tangentially or nearly tangent to the can liner. The combustion device provides effective mixing of fuel and air, creates an environment for combustion that reduces pollutant emissions, reduces the need for costly pollution control devices, enhances ignition and flame stability, reduces piloting issues, and improves vibration reduction.
摘要翻译：用于燃气涡轮发动机以产生推进或旋转轴用于发电的燃烧装置包括具有燃料和空气入口通道和喷嘴系统的罐环式燃烧器，其导致预混燃料和空气的最佳燃烧环境。燃料空气入口被放置在各种纵向位置并且周向分布，并且使流动与罐衬里切向或几乎相切。燃烧装置提供燃料和空气的有效混合，产生燃烧环境，减少污染物排放，减少对昂贵的污染控制装置的需要，增强点燃和火焰稳定性，减少驾驶问题，并改善振动减少。

10. 发明申请

WO2010036426A2 MODULAR TRANSVANE ASSEMBLY 审中-公开
标题翻译：模块化变电站组件
公开(公告)号：WO2010036426A2
公开(公告)日：2010-04-01
申请号：PCT/US2009/047213
申请日：2009-08-27
申请人： SIEMENS ENERGY, INC. , WILSON, Jody W. , NORDLUND, Raymond S. , CHARRON, Richard C.
发明人： WILSON, Jody W. , NORDLUND, Raymond S. , CHARRON, Richard C.
IPC分类号： F23R3/46 , F01D9/04
CPC分类号： F01D9/023 , F05D2240/40 , F05D2250/121 , F05D2250/141 , F05D2250/322 , F05D2250/323 , F05D2250/324 , F23R3/425 , F23R3/46
摘要： An arrangement for delivering gasses from can combustors of a can annular gas turbine combustion engine to a turbine first stage section including a first row of turbine blades, the arrangement including a flow-directing structure for each combustor, wherein each flow-directing structure includes a straight path and an annular chamber end, wherein the annular chamber ends together define an annular chamber for delivering the gas flow to the turbine first stage section, wherein gasses flow from respective combustors, through respective straight paths, and into the annular chamber as respective straight gas flows, and wherein the annular chamber is configured to unite the respective straight gas flows along respective shear planes to form a singular annular gas flow, and wherein the annular chamber is configured to impart circumferential motion to the singular annular gas flow before the singular annular gas flow exits the annular chamber to the first row of blades.
摘要翻译：一种用于将罐状罐式燃气轮机燃烧器的气体输送到包括第一排涡轮机叶片的涡轮机第一级部分的装置，该装置包括用于每个燃烧器的流动导向结构，其中每个流动导向结构包括直线路径和环形室端部，其中环形室端部一起限定了用于将气流输送到涡轮机第一级段的环形室，其中气体通过相应的直线路径从相应的燃烧器流动，并且作为相应的直线气体流动，并且其中所述环形室被构造成沿着相应的剪切平面联合相应的直的气体流以形成奇异的环形气流，并且其中所述环形室被构造成在所述单个环形气流气流离开环形室到第一排叶片。

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