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1. 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

2. 发明申请

WO2015089048A1 SWIRLING MIDFRAME FLOW FOR GAS TURBINE ENGINE HAVING ADVANCED TRANSITIONS 审中-公开
标题翻译：用于具有高级过渡的气体涡轮发动机的涡流中流量
公开(公告)号：WO2015089048A1
公开(公告)日：2015-06-18
申请号：PCT/US2014/069309
申请日：2014-12-09
申请人： SIEMENS ENERGY, INC.
发明人： MONTGOMERY, Matthew D. , CHARRON, Richard C. , RODRIGUEZ, Jose L. , KÜSTERS, Bernhard W. , MORRISON, Jay A. , BEECK, Alexander R.
IPC分类号： F23R3/04 , F23R3/42 , F23R3/46
CPC分类号： F23R3/46 , F04D29/542 , F04D29/545 , F04D29/547 , F23R3/02 , F23R3/04 , F23R3/425
摘要： A gas turbine engine can-annular combustion arrangement (10), including: an axial compressor (82) operable to rotate in a rotation direction (60); a diffuser (100, 110) configured to receive compressed air (16) from the axial compressor; a plenum (22) configured to receive the compressed air from the diffuser; a plurality of combustor cans (12) each having a combustor inlet (38) in fluid communication with the plenum, wherein each combustor can is tangentially oriented so that a respective combustor inlet is circumferentially offset from a respective combustor outlet in a direction opposite the rotation direction; and an airflow guiding arrangement (80) configured to impart circumferential motion to the compressed air in the plenum in the direction opposite the rotation direction.
摘要翻译：一种燃气涡轮发动机罐环式燃烧装置（10），包括：可操作以沿旋转方向（60）旋转的轴向压缩机（82）; 构造成从所述轴向压缩机接收压缩空气（16）的扩散器（100,110）配置成从扩散器接收压缩空气的增压室（22）多个燃烧器罐（12）各自具有与所述气室流体连通的燃烧器入口（38），其中每个燃烧室可以切向地定向，使得相应的燃烧器入口在与旋转相反的方向上与相应的燃烧室出口周向地偏移方向; 以及气流引导装置（80），其构造成沿着与旋转方向相反的方向对压缩空气施加周向运动。

3. 发明申请

WO2011136879A1 PLASMA ACTUATOR CONTROLLED FILM COOLING 审中-公开
标题翻译：等离子体执行器控制膜冷却
公开(公告)号：WO2011136879A1
公开(公告)日：2011-11-03
申请号：PCT/US2011/028922
申请日：2011-03-18
申请人： SIEMENS ENERGY, INC. , MONTGOMERY, Matthew D. , PRAKASH, Chander
发明人： MONTGOMERY, Matthew D. , PRAKASH, Chander
IPC分类号： F01D5/18 , F15D1/12
CPC分类号： F01D5/186 , F05D2260/202 , F05D2270/172
摘要： A film cooling apparatus with a cooling hole (46) in a component wall (40). A first surface (42) of the wall is subject to a hot gas flow (48). A second surface (44) receives a coolant gas (50). The coolant flows through the hole, then downstream over the first surface (42). One or more pairs of cooperating electrodes (60- 61, 62-63, 80-81) generates and accelerates a plasma (70) that creates a body force acceleration (71, 82) in the coolant flow that urges the coolant flow to turn around the entry edge (57) and/or the exit edge (58) of the cooling hole without separating from the adjacent surface (47, 42). The electrodes may have a geometry that spreads the coolant into a fan shape over the hot surface (42) of the component wall (40).
摘要翻译：一种在组件壁（40）中具有冷却孔（46）的薄膜冷却装置。壁的第一表面（42）经受热气流（48）。第二表面（44）接收冷却剂气体（50）。冷却剂流过孔，然后流过第一表面（42）的下游。一对或多对配合电极（60-61,62-63,80-81）产生并加速等离子体（70），其产生在促使冷却剂流转向的冷却剂流中的体力加速度（71,82）围绕冷却孔的入口边缘（57）和/或出口边缘（58），而不与相邻表面（47,42）分离。电极可以具有将冷却剂扩散到组件壁（40）的热表面（42）上的扇形形状的几何形状。

4. 发明申请

WO2017023330A1 A DUCTING ARRANGEMENT FOR DIRECTING COMBUSTION GAS 审中-公开
标题翻译：用于指导燃烧气体的排水装置
公开(公告)号：WO2017023330A1
公开(公告)日：2017-02-09
申请号：PCT/US2015/043974
申请日：2015-08-06
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： MORRISON, Jay A. , CHARRON, Richard C. , KUMAR, Manish , MONTGOMERY, Matthew D.
IPC分类号： F01D9/02
CPC分类号： F01D9/023 , F05D2250/38
摘要： A ducting arrangement (10), including: an annular duct (38) having a plurality of discrete IEPs (18) secured together to form the annular duct that defines an annular chamber (14) configured to deliver an annular flow of combustion gases directly onto turbine blades without a turning vane, wherein the annular duct defines a chamber mid-annulus (98); an IEP intermediate portion (34) for each IEP, each IEP intermediate portion defining a respective intermediate flow path (48) in fluid communication with the annular chamber and defining an intermediate flow path axis (192); and a cone (16) for each IEP intermediate portion, each cone defining a cone flow path (46), the cone flow path defining a cone flow path axis (190). When viewed from upstream toward downstream along a longitudinal axis (134) of the gas turbine engine each cone flow path axis intersects a respective intermediate flow path axis (192).
摘要翻译：一种管道装置（10），包括：环形管道（38），其具有固定在一起以形成环形管道的多个离散IEP（18），该环形管道限定环形室（14），其被配置成将环形气流直接传递到不具有转动叶片的涡轮机叶片，其中所述环形管道限定腔室中间环（98）; 每个IEP中间部分限定与环形室流体连通并且限定中间流路轴线（192）的相应的中间流路（48）; 以及用于每个IEP中间部分的锥体（16），每个锥体限定锥形流动路径（46），锥形流动路径限定锥形流动路径轴线（190）。当从燃气涡轮发动机的纵向轴线（134）的上游向下游观察时，每个锥形流路轴线与相应的中间流路轴线（192）相交。

5. 发明申请

WO2016118129A1 TRANSITION DUCT SYSTEM 审中-公开
标题翻译：过渡式排水系统
公开(公告)号：WO2016118129A1
公开(公告)日：2016-07-28
申请号：PCT/US2015/012347
申请日：2015-01-22
申请人： SIEMENS ENERGY, INC.
发明人： MONTGOMERY, Matthew D. , BEECK, Alexander Ralph , KUMAR, Manish , WIEBE, David J.
IPC分类号： F01D9/02
CPC分类号： F01D9/023 , F05D2240/127 , F05D2250/611 , F05D2250/711
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), characterized in that the transition duct system (100) includes one or more irregularities positioned at or adjacent the converging flow joint (196), is disclosed. The transition duct system (100) may include a converging flow joint (196) formed by the intersection of a first side wall (172) of a first transition duct body (126) with a second side wall (194) of a second transition duct body (128). Furthermore, one or more irregularities may be positioned at or adjacent the converging flow joint (196). The one or more irregularities may increase the mixing of gas routed by the first transition duct body (126) and the second transition duct body (128), reducing the tendency for gas flow induced vibration of the turbine blade (142) and/or the penalty associated with unsteady turbine blade (142) loading, in particular embodiments.
摘要翻译：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），其特征在于，所述过渡管道系统（100 ）包括位于会聚流动接头（196）处或邻近会聚流动接头（196）的一个或多个不规则件。过渡管道系统（100）可以包括由第一过渡管体（126）的第一侧壁（172）与第二过渡管道（126）的第二侧壁（194）的相交形成的会聚流动接头（196）身体（128）。此外，一个或多个凹凸可以位于会聚流动接头（196）处或其附近。一个或多个不规则部分可以增加由第一过渡管体（126）和第二过渡管体（128）引导的气体的混合，从而减少涡轮叶片（142）和/或在特定实施例中，与不稳定的涡轮叶片（142）装载有关的惩罚。

6. 发明申请

WO2016033465A1 GAS TURBINE BLADE TIP SHROUD FLOW GUIDING FEATURES 审中-公开
标题翻译：气体涡轮叶片喷嘴水流指导功能
公开(公告)号：WO2016033465A1
公开(公告)日：2016-03-03
申请号：PCT/US2015/047436
申请日：2015-08-28
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： MONTGOMERY, Matthew D. , PALMER, Timothy , MALANDRA, Anthony J.
IPC分类号： F01D11/08 , F01D5/22
CPC分类号： F01D11/08 , F01D5/225 , F05D2240/55
摘要： A turbine blade (10) includes an airfoil (12) extending span-wise along a radial direction, and a shroud (26) positioned along a tip (22) of the airfoil (12) extending generally along a circumferential direction, scalloped, across a pressure side (18) and a suction side (20) of the airfoil (12), the shroud (26) includes an upstream edge (28) and a downstream edge (30) spaced apart axially. The shroud (26) further includes a radially inner surface (32) adjoining the tip (22) of the airfoil (12) and a radially outer surface (34) opposite to the radially inner surface (32). A shroud ridge (42) extends across the shroud (26) along a portion of the radially outer surface (34). A plurality of bladelets (44) is attached across a span of the shroud ridge (42) in a row. The plurality of bladelets (44) produces a plurality of passages (46) with each passage (46) in between each bladelet (44). Half-width passages (50) lie along each of an extreme edge of the plurality of bladelets (44). An intershroud bridge (48) that extends along a portion of the shroud ridge (46) closes at least one half-width passage (50) along at least one end of the shroud ridge (46) at an extreme end (52) of the plurality of bladelets (44). The shroud also include a seal (38) extends radially outward from the radially outer surface (34) of the shroud (26).
摘要翻译：涡轮叶片（10）包括沿着径向方向跨越方向延伸的翼型件（12），以及沿着翼型件（12）的顶端（22）定位的护罩（26），所述护翼（26）大致沿圆周方向延伸，扇形跨越所述翼型件（12）的压力侧（18）和吸力侧（20），所述护罩（26）包括沿轴向间隔开的上游边缘（28）和下游边缘（30）。护罩（26）还包括邻近翼型件（12）的尖端（22）的径向内表面（32）和与径向内表面（32）相对的径向外表面（34）。护罩脊（42）沿着径向外表面（34）的一部分延伸穿过护罩（26）。多个叶片（44）以一排的方式跨过护罩脊（42）的跨度安装。多个叶片（44）产生多个通道（46），每个通道（46）在每个叶片（44）之间。半宽度通道（50）位于多个叶片（44）的每个极限边缘上。沿着护罩脊（46）的一部分延伸的跨带桥（48）沿着护罩脊（46）的至少一端在至少一个半宽度通道（52）的端部（52）处封闭多个叶片（44）。护罩还包括从护罩（26）的径向外表面（34）径向向外延伸的密封件（38）。

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. 发明公开

EP3108124A1 GAS FLOW PATH FOR A GAS TURBINE ENGINE 审中-公开
标题翻译： GASSTRÖMUNGSPFADFÜREINEN GASTURBINENMOTOR
公开(公告)号：EP3108124A1
公开(公告)日：2016-12-28
申请号：EP15703854.8
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用于将气体从多个燃烧器输送到环形室的气体输送结构，所述环形室周向延伸并且与燃气涡轮发动机纵向轴线同心地定向，用于将气流输送到第一排叶片A气体流动路径由相应的燃烧器和用于将气体从每个燃烧器输送到第一排涡轮叶片的环形室之间的管道布置形成。管道装置包括至少一个具有与燃烧器的中心线不对准的中心线的直线段。

9. 发明公开

EP2893152A1 GAS TURBINE ENGINE WITH RADIAL DIFFUSER AND SHORTENED MID SECTION 审中-公开
标题翻译：径向扩散器的燃气涡轮发动机缩短中段
公开(公告)号：EP2893152A1
公开(公告)日：2015-07-15
申请号：EP13753977.1
申请日：2013-08-20
申请人： Siemens Energy, Inc.
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

10. 发明授权

EP2564027B1 Plasma actuator controlled film cooling apparatus 有权
标题翻译：关于等离子体致动器控制膜冷却器
公开(公告)号：EP2564027B1
公开(公告)日：2014-03-05
申请号：EP11714877.5
申请日：2011-03-18
申请人： Siemens Energy, Inc.
发明人： MONTGOMERY, Matthew D. , PRAKASH, Chander
IPC分类号： F01D5/18 , F15D1/12
CPC分类号： F01D5/186 , F05D2260/202 , F05D2270/172

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