专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明公开

EP3216982A1 TURBINE AIRFOIL HAVING NEAR-WALL COOLING INSERT 审中-公开
标题翻译：涡轮机翼具有近壁冷却插入
公开(公告)号：EP3216982A1
公开(公告)日：2017-09-13
申请号：EP17157690.3
申请日：2017-02-23
申请人： Siemens Energy, Inc.
发明人： MARTIN, Nicholas F., Jr. , WIEBE, David J.
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D9/02 , F01D25/12 , F05D2220/32 , F05D2230/642 , F05D2230/80 , F05D2250/183 , F05D2260/20 , F05D2260/221 , F05D2300/10 , F05D2300/20 , F05D2300/50212 , F05D2300/6033
摘要： A turbine airfoil (10) is provided with at least one insert (30) positioned in a cavity (24) in an airfoil interior. The insert (30) extends along a span-wise extent of the turbine airfoil (10) and includes first (32) and second (34) opposite faces. A first near-wall cooling channel (82) is defined between the first face (32) and a pressure sidewall (14) of an airfoil outer wall (12). A second near-wall cooling channel (84) is defined between the second face (34) and a suction sidewall (16) of the airfoil outer wall (12). A locating feature (40) engages the insert (30) with the outer wall (12) for supporting the insert (30) in position. The locating feature (30) is configured to control flow of the coolant through the first (82) or second (84) near-wall cooling channel.
摘要翻译：涡轮翼型件（10）设置有至少一个位于翼型内部的空腔（24）中的插入件（30）。插入件（30）沿着涡轮机翼型（10）的翼展范围延伸并且包括第一（32）和第二（34）相对的面。第一近壁冷却通道（82）限定在翼型件外壁（12）的第一面（32）和压力侧壁（14）之间。第二近壁冷却通道（84）限定在翼型件外壁（12）的第二面（34）和吸入侧壁（16）之间。定位特征（40）将插入件（30）与外壁（12）接合，以将插入件（30）支撑在位。定位特征（30）构造成控制冷却剂通过第一（82）或第二（84）近壁冷却通道的流动。

2. 发明公开

EP2764214A1 CASING FOR A GAS TURBINE ENGINE 审中-公开
标题翻译：住房燃气涡轮发动机
公开(公告)号：EP2764214A1
公开(公告)日：2014-08-13
申请号：EP12772861.6
申请日：2012-10-02
申请人： Siemens Energy, Inc.
发明人： WIEBE, David J. , LITTLE, David A. , CHARRON, Richard C.
IPC分类号： F01D9/02 , F02C3/14 , F23R3/46
CPC分类号： F02C3/14 , F01D9/023 , F23R3/02 , F23R3/46
摘要： A casing for a can annular gas turbine engine, including: a compressed air section (40) spanning between a last row of compressor blades (26) and a first row of turbine blades (28), the compressed air section (40) having a plurality of openings (50) there through, wherein a single combustor/advanced duct assembly (64) extends through each opening (50); and one top hat (68) associated with each opening (50) configured to enclose the associated combustor/advanced duct assembly (64) and seal the opening (50). A volume enclosed by the compressed air section (40) is not greater than a volume of a frustum (54) defined at an upstream end (56) by an inner diameter of the casing at the last row of compressor blades (26) and at a downstream end (60) by an inner diameter of the casing at the first row of turbine blades (28).

3. 发明授权

EP2764214B1 CASING FOR A GAS TURBINE ENGINE 有权
公开(公告)号：EP2764214B1
公开(公告)日：2018-08-22
申请号：EP12772861.6
申请日：2012-10-02
申请人： Siemens Energy, Inc.
发明人： WIEBE, David J. , LITTLE, David A. , CHARRON, Richard C.
IPC分类号： F01D9/02 , F02C3/14 , F23R3/46
CPC分类号： F02C3/14 , F01D9/023 , F23R3/02 , F23R3/46
摘要： A casing for a can annular gas turbine engine, including: a compressed air section (40) spanning between a last row of compressor blades (26) and a first row of turbine blades (28), the compressed air section (40) having a plurality of openings (50) there through, wherein a single combustor/advanced duct assembly (64) extends through each opening (50); and one top hat (68) associated with each opening (50) configured to enclose the associated combustor/advanced duct assembly (64) and seal the opening (50). A volume enclosed by the compressed air section (40) is not greater than a volume of a frustum (54) defined at an upstream end (56) by an inner diameter of the casing at the last row of compressor blades (26) and at a downstream end (60) by an inner diameter of the casing at the first row of turbine blades (28).

4. 发明公开

EP2948638A2 PURGE AND COOLING AIR FOR AN EXHAUST SECTION OF A GAS TURBINE ASSEMBLY 有权
标题翻译：空气净化和冷却气体的火车燃气涡轮机系统
公开(公告)号：EP2948638A2
公开(公告)日：2015-12-02
申请号：EP14702423.6
申请日：2014-01-22
申请人： Siemens Energy, Inc.
发明人： PATAT, Harry , SCHOPF, Cheryl A. , KATY, Jerome H. , WALLACE, Adam , WIEBE, David J.
IPC分类号： F01D9/06 , F01D25/12 , F01D25/30
摘要： A turbine exhaust casing having an outer casing, an inner casing, an annular exhaust gas path defined between outer and inner flow path walls, and a turbine exhaust casing cavity located radially outward and radially inward from the gas path. A plurality of structural struts support the inner casing to the outer casing, and a fairing surrounds each of the struts in an area extending between the outer and inner flow path walls. A first purge air path extends through at least one of the struts for conducting purge cooling air radially inward to the inner casing, and a second purge air path extends through the strut for further conducting the purge cooling air radially outward to provide a flow of purge air to a location of the exhaust casing cavity radially outward from the outer flow path wall.

5. 发明授权

EP2791489B1 RADIAL INFLOW GAS TURBINE ENGINE WITH ADVANCED TRANSITION DUCT 有权
公开(公告)号：EP2791489B1
公开(公告)日：2020-02-05
申请号：EP12861047.4
申请日：2012-12-07
申请人： Siemens Energy, Inc.
发明人： WIEBE, David J.
IPC分类号： F02C3/14 , F01D9/02

6. 发明公开

EP3060762A1 STRUCTURAL MOUNTING ARRANGEMENT FOR GAS TURBINE ENGINE COMBUSTION GAS DUCT 审中-公开
标题翻译：结构上安装安排燃气涡轮发动机的内部的气体管线
公开(公告)号：EP3060762A1
公开(公告)日：2016-08-31
申请号：EP14783714.0
申请日：2014-09-22
申请人： Siemens Energy, Inc.
发明人： WIEBE, David J. , CHARRON, Richard C. , MORRISON, Jay A.
IPC分类号： F01D9/02
CPC分类号： F23R3/60 , F01D9/023 , F05D2260/30 , F23R3/46
摘要： A gas turbine engine ducting arrangement (10), including: an annular chamber (14) configured to receive a plurality of discrete flows of combustion gases originating in respective can combustors and to deliver the discrete flows to a turbine inlet annulus, wherein the annular chamber includes an inner diameter (52) and an outer diameter (60); an outer diameter mounting arrangement (34) configured to permit relative radial movement and to prevent relative axial and circumferential movement between the outer diameter and a turbine vane carrier (20); and an inner diameter mounting arrangement (36) including a bracket (64) secured to the turbine vane carrier, wherein the bracket is configured to permit the inner diameter to move radially with the outer diameter and prevent axial deflection of the inner diameter with respect to the outer diameter.

7. 发明公开

EP3036406A1 BELLY BAND SEAL WITH CIRCUMFERENTIAL SPACER 审中-公开
标题翻译：贝利带密封圈与CIRCUMENTIAL间隔
公开(公告)号：EP3036406A1
公开(公告)日：2016-06-29
申请号：EP14753422.6
申请日：2014-08-07
申请人： Siemens Energy, Inc.
发明人： WIEBE, David J.
IPC分类号： F01D11/00 , F01D5/06 , F02C7/28
CPC分类号： F01D11/08 , F01D5/06 , F01D5/066 , F01D11/003 , F01D11/005 , F01D11/008 , F02C7/28
摘要： A circumferentially extending sealing band is located within sealing band receiving slots formed in adjacent turbine engine disks. The sealing band includes a plurality of seal strips forming overlap joints defined by overlapping end portions, each formed by a tongue portion extending from a seal face of one seal strip past a seal face of the adjacent seal strip, along a radially inward facing side of the adjacent seal strip. A joint gap is defined within at least one overlap joint between the seal face of the one seal strip and the seal face of the adjacent strip, and a spacer is affixed to the one seal strip and is located at a position within the joint gap between the seal faces to limit circumferential movement of the seal faces toward each other.
摘要翻译：周向延伸的密封带位于形成在相邻涡轮发动机盘中的密封带接收槽内。所述密封带包括多个密封条，所述多个密封条形成由重叠的端部限定的交叠接头，每个密封条由从一个密封条的密封面延伸经过相邻密封条的密封面的舌状部分形成，沿着径向内侧相邻的密封条。在一个密封条的密封面和相邻条的密封面之间的至少一个重叠接合处内限定有接合间隙，并且间隔件被固定到该密封条并且位于接合间隙密封件面对以限制密封面朝向彼此的周向运动。

8. 发明授权

EP2948638B1 PURGE AND COOLING AIR FOR AN EXHAUST SECTION OF A GAS TURBINE ASSEMBLY 有权
公开(公告)号：EP2948638B1
公开(公告)日：2020-10-28
申请号：EP14702423.6
申请日：2014-01-22
申请人： Siemens Energy, Inc.
发明人： PATAT, Harry , SCHOPF, Cheryl A. , KATY, Jerome H. , WALLACE, Adam , WIEBE, David J.
IPC分类号： F01D9/06 , F01D25/12 , F01D25/30

9. 发明公开

EP3169878A1 TURBINE ASSEMBLY WITH DETACHABLE STRUTS 审中-公开
标题翻译：带可拆卸杆的涡轮总成
公开(公告)号：EP3169878A1
公开(公告)日：2017-05-24
申请号：EP14753351.7
申请日：2014-07-18
申请人： Siemens Energy, Inc.
发明人： WIEBE, David J. , KATY, Jerome H. , SELESKI, Richard , HETTINGER, Benjamin G. , WALLACE, Adam
IPC分类号： F01D25/16 , F01D25/28 , F01D9/06
CPC分类号： F01D25/28 , F01D9/065 , F01D25/162 , F05D2240/14 , F05D2260/30 , F05D2260/31
摘要： A turbine assembly having an outer casing (36), an inner structural ring (38), and an annular gas path (42) defined between outer and inner flow path walls (44, 46) for conducting a gas flow through the turbine assembly. A plurality of structural struts (52) are spaced apart in a circumferential direction, each strut (52) including a strut body (52a) extending in a radial direction for supporting the inner structural ring (38) to the outer casing (36). A first strut end (64) at a radially outer end of the strut body (52a) is detachably attached to the outer casing (36) with a first fastener structure (68) engaging the outer casing (36), and a second strut end (66) at a radially inner end of the strut body (52a) is detachably attached to the inner structural ring (38) with a second fastener structure (70) engaging the inner structural ring (38).
摘要翻译：一种具有外壳（36），内部结构环（38）和限定在外部和内部流动路径壁（44,46）之间的环形气体路径（42）的涡轮机组件，用于引导气体流过涡轮机组件。多个结构支柱（52）在周向上间隔开，每个支柱（52）包括径向延伸的支柱主体（52a），用于将内部结构环（38）支撑到外壳（36）。利用与外壳（36）接合的第一紧固件结构（68），支柱主体（52a）的径向外端处的第一支柱端部（64）可拆卸地附接到外壳（36），并且第二支柱端部通过与内部结构环（38）接合的第二紧固件结构（70），在支柱主体（52a）的径向内端处的内部结构环（66）可拆卸地附接到内部结构环（38）。

10. 发明公开

EP3161266A1 CONVERGING FLOW JOINT INSERT SYSTEM AT AN INTERSECTION BETWEEN ADJACENT TRANSITION DUCT BODLJS 审中-公开
标题翻译：在相邻过渡管道之间的交叉处汇合流动接头插入系统
公开(公告)号：EP3161266A1
公开(公告)日：2017-05-03
申请号：EP14741483.3
申请日：2014-06-26
申请人： Siemens Energy, Inc.
发明人： WIEBE, David J. , CARLSON, Andrew , STOKER, Kyle C.
IPC分类号： F01D9/02 , F02C3/14 , F23R3/42
CPC分类号： F01D9/023 , F01D5/02 , F01D9/00 , F01D9/02 , F01D9/047 , F01D9/065 , F01D25/28 , F02C3/14 , F02C7/20 , F05D2220/32 , F05D2240/10 , F05D2250/25 , F05D2260/20 , F05D2260/94 , F05D2260/941 , F23R3/002 , F23R3/425 , F23R3/46 , F23R3/60 , F23R2900/00005
摘要： A transition duct system for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine, wherein the transition duct system includes one or more converging flow joint inserts forming a trailing edge at an intersection between adjacent transition ducts is disclosed. The transition duct system may include a transition duct having an internal passage extending between an inlet to an outlet and may expel gases into the first stage turbine with a tangential component. The converging flow joint insert may be contained within a converging flow joint insert receiver and disconnected from the transition duct bodies by which the converging flow joint insert is positioned. Being disconnected eliminates stress formation within the converging flow joint insert, thereby enhancing the life of the insert. The converging flow joint insert may be removable such that the insert can be replaced once worn beyond design limits.
摘要翻译：一种过渡管道系统，用于将来自燃烧器的气流引导至燃气涡轮发动机中的涡轮部段的第一级，其中所述过渡管道系统包括一个或多个会聚流接头插入件，所述一个或多个会聚流接头插入件在相邻过渡管道被披露。过渡管道系统可以包括过渡管道，该过渡管道具有在入口到出口之间延伸的内部通道并且可以用切向分量将气体排出到第一级涡轮机中。会聚流接头插入件可以包含在会聚流接头插入件接收器内并且与会聚流接头插入件所位于的过渡导管本体断开。断开连接消除了会聚流接头插入物内的应力形成，从而延长了插入物的使用寿命。会聚流接头插入件可以是可移除的，使得插入件一旦磨损超过设计极限就可以更换。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式