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1. 发明申请

WO2011097121A2 COOLING OF TURBINE COMPONENTS USING COMBUSTOR SHELL AIR 审中-公开
标题翻译：使用COMBUSTOR SHELL空气冷却涡轮机组件
公开(公告)号：WO2011097121A2
公开(公告)日：2011-08-11
申请号：PCT/US2011/022819
申请日：2011-01-28
申请人： SIEMENS ENERGY, INC. , FOUST, Adam, M. , NORDLUND, Raymond, S. , CHHABRA, Nitin , LITTLE, David, A.
发明人： FOUST, Adam, M. , NORDLUND, Raymond, S. , CHHABRA, Nitin , LITTLE, David, A.
IPC分类号： F02C9/18
CPC分类号： F01D9/023 , F02C3/13 , F02C6/08 , F02C7/12 , F02C7/185 , F02C9/18 , F05D2260/20 , F05D2270/08
摘要： A turbine engine assembly for a generator including a turbine engine having a compressor section, a combustor section and a turbine section. An air bleed line is in communication with the combustor section for receiving combustor shell air from the combustor section and conveying the combustor shell air as bleed air to a plurality of stages of the turbine section. Bleed air is controlled to flow through the air bleed line when an operating load of the turbine engine assembly is less than a base load of the engine to bypass air exiting the compressor section around a combustor in the combustor section and effect a flow of high pressure combustor shell air to the stages of the turbine section.
摘要翻译：一种用于发电机的涡轮发动机组件，其包括具有压缩机部分，燃烧器部分和涡轮部分的涡轮发动机。排气管路与燃烧器部分连通，用于从燃烧器部分接收燃烧器壳体空气，并将燃烧器壳体空气作为排气输送到涡轮部分的多个级。当涡轮发动机组件的操作负载小于发动机的基本负载以排出围绕燃烧器部分中的燃烧器排出的压缩机部分的空气时，排出的空气被控制流过排气管，并且产生高压燃烧器壳体空气到涡轮部分的阶段。

2. 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。

3. 发明申请

WO2011097121A3 COOLING OF TURBINE COMPONENTS USING COMBUSTOR SHELL AIR 审中-公开
标题翻译：使用COMBUSTOR SHELL空气冷却涡轮机组件
公开(公告)号：WO2011097121A3
公开(公告)日：2011-10-27
申请号：PCT/US2011022819
申请日：2011-01-28
申请人： SIEMENS ENERGY INC , FOUST ADAM M , NORDLUND RAYMOND S , CHHABRA NITIN , LITTLE DAVID A
发明人： FOUST ADAM M , NORDLUND RAYMOND S , CHHABRA NITIN , LITTLE DAVID A
IPC分类号： F02C9/18 , F01D9/02 , F02C3/13 , F02C6/08 , F02C7/12 , F02C7/18
CPC分类号： F01D9/023 , F02C3/13 , F02C6/08 , F02C7/12 , F02C7/185 , F02C9/18 , F05D2260/20 , F05D2270/08
摘要： A turbine engine assembly for a generator including a turbine engine having a compressor section (12), a combustor section (30) and a turbine section (14). An air bleed line is in communication with the combustor section for receiving combustor shell air from the combustor section and conveying the combustor shell air as bleed air to a plurality of stages of the turbine section. Bleed air is controlled to flow through the air bleed line when an operating load of the turbine engine assembly is less than a base load of the engine to bypass air exiting the compressor section around a combustor in the combustor section and effect a flow of high pressure combustor shell air to the stages of the turbine section.
摘要翻译：一种用于发电机的涡轮发动机组件，包括具有压缩机部分（12），燃烧器部分（30）和涡轮部分（14）的涡轮发动机。排气管路与燃烧器部分连通，用于从燃烧器部分接收燃烧器壳体空气，并将燃烧器壳体空气作为排气输送到涡轮部分的多个级。当涡轮发动机组件的操作负载小于发动机的基本负载以排出围绕燃烧器部分中的燃烧器排出的压缩机部分的空气时，排出的空气被控制流过排气管，并且产生高压燃烧器壳体空气到涡轮部分的阶段。

4. 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。

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