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公开(公告)号：US20180230835A1
公开(公告)日：2018-08-16
申请号：US15509987
申请日：2014-10-07
申请人： Siemens Energy, Inc.
发明人： David A. Little
CPC分类号： F01D9/023 , F02C7/12 , F02C7/125 , F05D2240/12 , F05D2250/25 , F05D2260/201 , F05D2260/202 , F23R3/42 , F23R3/425 , F23R3/46 , F23R2900/03044
摘要： An arrangement (10) for delivering gases from combustors (15) to a first row of blades. The arrangement (10) includes at least an upstream flow path (60) including an aft first side wall (64) and a downstream flow path (62) including a forward second side wall (66). A convergence junction trailing edge (40) is defined at a downstream terminal edge (41) of the first side wall (64), and the second side wall (66) converges toward the first side wall (64) in the direction of the convergence junction trailing edge (40). An impingement sheet structure (78) is located between and provides impingement cooling air to the first and second side walls (64, 66). Openings (88) provide a cooling air passage between the first and second side walls (64, 66) and provide a flow of post impingement air into the gas path at the convergence junction trailing edge (40).
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2.发明申请公开(公告)号：US20180187563A1
公开(公告)日：2018-07-05
申请号：US15739819
申请日：2015-07-24
摘要： An improved combustion system having a reduced combustion residence time in a combustion turbine engine is provided. The combustor system may include a flow-accelerating structure (16, 51) having an inlet (26) and an outlet (28). The inlet 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 and the outlet of the flow-accelerating structure. The flow-accelerating structure causes an increasing speed to the flow of combustion gases, and, as a result, the flow of combustion gases in the flow-accelerating structure 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.
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公开(公告)号：US20180016922A1
公开(公告)日：2018-01-18
申请号：US15208219
申请日：2016-07-12
申请人： Siemens Energy, Inc.
发明人： Anthony L. Schiavo
CPC分类号： F01D9/023 , F23R3/425 , F23R3/48 , F23R3/60 , F23R2900/00005 , F23R2900/00017
摘要： A gas turbine engine has a crown locking device and a seal portion. The crown locking device and seal portion connect a transition duct to an inlet extension piece. The crown locking device and seal portion is located between a metallic integrated exit piece and a transition duct that is made of ceramic matrix composites.
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4.发明申请公开(公告)号：US20180016921A1
公开(公告)日：2018-01-18
申请号：US15207716
申请日：2016-07-12
申请人： Siemens Energy, Inc.
发明人： Anthony L. Schiavo
CPC分类号： F01D9/023 , F05D2240/40 , F05D2250/141 , F05D2300/175 , F05D2300/20 , F05D2300/6033 , F23R3/007 , F23R3/425 , F23R3/60 , F23R2900/00005
摘要： A ducting arrangement (12) for a combustion turbine engine is provided. The arrangement includes a ceramic liner (22) defining a hot gas path throughout a length of the ducting arrangement. A cooling sleeve (24) is disposed circumferentially outwardly onto the ceramic liner along the length. A metallic support frame (26) is disposed circumferentially outwardly onto the cooling sleeve along the length. The cooling sleeve may be structured with structural features along the length for biasing against the ceramic liner and the metallic support frame to resiliently accept mechanical and thermal growth induced loading that develops between the ceramic liner and the metallic support frame during operating conditions of the combustion turbine engine.
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公开(公告)号：US20170211811A1
公开(公告)日：2017-07-27
申请号：US15002437
申请日：2016-01-21
申请人： Siemens Energy, Inc.
发明人： David J. Wiebe
CPC分类号： F23R3/425 , F01D9/023 , F05D2260/232 , F05D2300/20 , F05D2300/6033 , F23R3/002 , F23R3/005 , F23R3/007 , F23R3/46 , F23R3/50 , F23R3/60 , F23R2900/00017 , F23R2900/03044
摘要： A transition duct system (10) for delivering hot-temperature gases from a plurality of combustors in a combustion turbine engine is provided. The system includes an exit piece (16) for each combustor. The exit piece may include an arcuate connecting segment (36). An arcuate ceramic liner (60) may be inwardly disposed onto a metal outer shell (38) along the arcuate connecting segment of the exit piece. Structural arrangements are provided to securely attach the ceramic liner in the presence of substantial flow path pressurization. Cost-effective serviceability of the transition duct systems is realizable since the liner can be readily removed and replaced as needed.
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公开(公告)号：US08978388B2
公开(公告)日：2015-03-17
申请号：US13152638
申请日：2011-06-03
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。
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7.发明申请MID-SECTION OF A CAN-ANNULAR GAS TURBINE ENGINE WITH AN IMPROVED ROTATION OF AIR FLOW FROM THE COMPRESSOR TO THE TURBINE 有权CAN-ANNULAR气体涡轮发动机的中间部分，从压缩机到涡轮机的空气流改进公开(公告)号：US20130219853A1
公开(公告)日：2013-08-29
申请号：US13408287
申请日：2012-02-29
IPC分类号： F02G1/00
摘要： A midframe portion (313) of a gas turbine engine (310) is presented and includes a compressor section with a last stage blade to orient an air flow (311) at a first angle (372). The midframe portion (313) further includes a turbine section with a first stage blade to receive the air flow (311) oriented at a second angle (374). The midframe portion (313) further includes a manifold (314) to directly couple the air flow (311) from the compressor section to a combustor head (318) upstream of the turbine section. The combustor head (318) introduces an offset angle in the air flow (311) from the first angle (372) to the second angle (374) to discharge the air flow (311) from the combustor head (318) at the second angle (374). While introducing the offset angle, the combustor head (318) at least maintains or augments the first angle (372).
摘要翻译： 呈现燃气涡轮发动机（310）的中架部分（313）并且包括具有最后级叶片的压缩机部分，以使空气流（311）以第一角度（372）定向。 中间部分（313）还包括具有第一级叶片的涡轮机部分，以接收以第二角度（374）定向的空气流（311）。 中间部分（313）还包括歧管（314），用于将空气流（311）从压缩机部分直接耦合到涡轮部分上游的燃烧器头部（318）。 燃烧器头部（318）将空气流（311）中的偏移角从第一角度（372）引入第二角度（374），以使空气流（311）以第二角度从燃烧器头部（318）排出 （374）。 在引入偏移角的同时，燃烧器头（318）至少保持或增加第一角度（372）。
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公开(公告)号：US20120304653A1
公开(公告)日：2012-12-06
申请号：US13152638
申请日：2011-06-03
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。
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9.发明申请Pulse Detonation Turbine Engine Using Turbine Shaft Speed for Monitoring Combustor Tube Operation 审中-公开脉冲爆震涡轮发动机使用涡轮轴转速监测燃烧管运行公开(公告)号：US20120192630A1
公开(公告)日：2012-08-02
申请号：US13015619
申请日：2011-01-28
IPC分类号： G01M15/14
CPC分类号： F23R7/00 , F02C5/00 , F02C9/00 , F02K7/02 , F05D2260/80 , F05D2270/304 , F23N1/08 , F23N5/00 , F23R3/425
摘要： The present application provides a shaft speed monitoring system for a pulse detonation combustor with a number of combustion tubes and positioned about a shaft of a pulse detonation turbine engine. The shaft speed monitoring system may include one or more shaft sensors positioned about the shaft and a control in communication with the shaft sensors to determine a number of shaft speed fluctuations related to each of the combustion tubes.
摘要翻译： 本申请提供了一种用于具有多个燃烧管并且围绕脉冲爆震涡轮发动机的轴定位的脉冲爆震燃烧器的轴速度监测系统。 轴速度监测系统可以包括围绕轴定位的一个或多个轴传感器和与轴传感器连通的控制器，以确定与每个燃烧管相关的轴速度波动的数量。
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公开(公告)号：US08230688B2
公开(公告)日：2012-07-31
申请号：US12420149
申请日：2009-04-08
IPC分类号： F02C3/00
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： 用于将罐体环形燃气轮机内燃机的燃烧器的气体输送到包括第一排涡轮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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