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1. 发明申请

WO2013130148A1 FULL HOOP CASING FOR MIDFRAME OF INDUSTRIAL GAS TURBINE ENGINE 审中-公开
标题翻译：全工业用于工业燃气轮机发动机
公开(公告)号：WO2013130148A1
公开(公告)日：2013-09-06
申请号：PCT/US2012/067583
申请日：2012-12-03
申请人： SIEMENS ENERGY, INC. , MYERS, Gerald A. , CHARRON, Richard C.
发明人： MYERS, Gerald A. , CHARRON, Richard C.
IPC分类号： F01D25/24 , F02C3/14 , F23R3/02
CPC分类号： F02C3/14 , F01D25/24 , F01D25/243 , F01D25/285 , F05D2230/70 , F05D2230/72 , F23R3/46
摘要： A can annular industrial gas turbine engine, including: a single-piece rotor shaft spanning a compressor section (82), a combustion section (84), a turbine section (86); and a combustion section casing (10) having a section (28) configured as a full hoop. When the combustion section casing is detached from the engine and moved to a maintenance position to allow access to an interior of the engine, a positioning jig (98) is used to support the compressor section casing (83) and turbine section casing (87).
摘要翻译：一种罐式环形工业燃气涡轮发动机，包括：跨过压缩机部分（82），燃烧部分（84），涡轮部分（86）的单件转子轴; 和具有构成为完全箍的部分（28）的燃烧部分壳体（10）。当燃烧部分壳体与发动机分离并移动到维修位置以允许进入发动机内部时，定位夹具（98）用于支撑压缩机部分壳体（83）和涡轮部分壳体（87）。

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

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

WO2014039247A1 GAS TURBINE ENGINE WITH RADIAL DIFFUSER AND SHORTENED MID SECTION 审中-公开
标题翻译：燃气涡轮发动机带有径向发生器和中空部分
公开(公告)号：WO2014039247A1
公开(公告)日：2014-03-13
申请号：PCT/US2013/055792
申请日：2013-08-20
申请人： SIEMENS ENERGY, INC. , CHARRON, Richard C. , MONTGOMERY, Matthew D.
发明人： CHARRON, Richard C. , MONTGOMERY, Matthew D.
IPC分类号： F01D9/02 , F02C3/14
CPC分类号： F01D9/023 , F01D9/02 , F01D9/04 , F02C3/14 , F23R3/46 , Y02T50/671
摘要： An industrial gas turbine engine (10), including: a can annular combustion assembly (80), having a plurality of discrete flow ducts configured to receive combustion gas from respective combustors (82) and deliver the combustion gas along a straight flow path at a speed and orientation appropriate for delivery directly onto the first row (56) of turbine blades (62); and a compressor diffuser (32) having a redirecting surface (130, 140) configured to receive an axial flow of compressed air and redirect the axial flow of compressed air radially outward
摘要翻译：一种工业燃气涡轮发动机（10），包括：罐式环形燃烧组件（80），其具有多个分立的流动管道，其构造成从相应燃烧器（82）接收燃烧气体，并沿着直线流动路径适于直接输送到涡轮叶片（62）的第一排（56）上的速度和方位; 和压缩机扩散器（32），其具有被重新定向的表面（130,140），所述重定向表面被构造成接收压缩空气的轴向流动并且将径向向外的压缩空气的轴向流动

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