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21. 发明授权

US10101577B2 System to prognose gas turbine remaining useful life 有权
公开(公告)号：US10101577B2
公开(公告)日：2018-10-16
申请号：US14684471
申请日：2015-04-13
申请人： Siemens Energy, Inc.
发明人： Arun Meenakshinatha Iyer , Anand A. Kulkarni , Kevin Licata
IPC分类号： H04N5/33 , H04N7/18 , G02B23/24 , G01J5/04 , G01J5/08 , G01J5/00
摘要： A flash thermography device for generating an infrared image of a turbine component located inside a turbine, wherein the turbine includes at least one inspection port. The device includes a flash source that generates a light pulse that heats the turbine component and an infrared sensor for detecting thermal energy radiated by the turbine component. The device also includes a borescope having a sensor end, a viewing end that includes the flash source and an interior hollow that extends between the sensor and viewing ends. The borescope is positioned in the inspection port such that the viewing end is located inside the turbine. Thermal energy radiated from the turbine component is transmitted through the hollow to the infrared sensor to enable generation of the infrared image. The device further includes a reflector located on the viewing end that directs the light pulse toward the turbine component and a flash power supply for energizing the flash source.

22. 发明申请

US20170070686A1 FLASH THERMOGRAPHY BORESCOPE 审中-公开
标题翻译：闪光热成像
公开(公告)号：US20170070686A1
公开(公告)日：2017-03-09
申请号：US15354004
申请日：2016-11-17
申请人： Siemens Energy, Inc.
发明人： Dustin C. Boudin , Clifford Hatcher, JR. , Anand A. Kulkarni
IPC分类号： H04N5/33 , H04N5/225
CPC分类号： H04N5/33 , A61B1/00064 , G02B23/24 , G02B23/2453 , G02B23/2492 , H04N5/2256 , H04N2005/2255
摘要： A flash thermography device for generating an infrared image of each of a plurality of rotating turbine components located inside a turbine. The device includes an infrared sensor for detecting thermal energy radiated by each component. The device also includes a borescope having a viewing end located on a longitudinal axis of the borescope. The borescope is positioned in an inspection port to locate the viewing end inside the turbine such that at least one component is within a field of view of the viewing end. In addition, the device includes a flash source that generates a plurality of light pulses corresponding to the number of components that rotate during a single rotation of the rotor, wherein the light pulses are oriented substantially transverse to the longitudinal. Thermal energy radiated from each component is transmitted through the borescope to the infrared sensor to enable generation infrared images.
摘要翻译：一种用于产生位于涡轮机内的多个旋转涡轮机部件中的每一个的红外图像的闪光热成像装置。该装置包括用于检测由每个部件辐射的热能的红外传感器。该装置还包括具有位于管状镜的纵向轴线上的观察端的管状镜。管道镜定位在检查端口中，以将观察端定位在涡轮机内，使得至少一个部件在观察端的视场内。另外，该装置包括闪光源，其产生对应于在转子的单次旋转期间旋转的分量的数量的多个光脉冲，其中光脉冲基本上横向于纵向取向。从每个组件辐射的热能通过管道镜传输到红外传感器，以便产生红外图像。

23. 发明申请

US20160237827A1 GAS TURBINE BLADE WITH CORRUGATED TIP WALL 审中-公开
标题翻译：气体涡轮叶片与腐蚀性提示墙
公开(公告)号：US20160237827A1
公开(公告)日：2016-08-18
申请号：US15139379
申请日：2016-04-27
申请人： Siemens Energy, Inc.
发明人： Christian Xavier Campbell , Anand A. Kulkarni , Daniel M. Eshak , Allister William James , Phillip Behling , Ahmed Kamel
IPC分类号： F01D5/14 , B22F3/105 , B22F5/04 , B23K26/342
CPC分类号： F01D5/147 , B22D19/10 , B22F3/1055 , B22F5/04 , B22F2003/1058 , B22F2007/068 , B23K26/342 , B23K2101/001 , B23P15/04 , B33Y10/00 , B33Y80/00 , F01D5/005 , F01D5/20 , F05D2220/32 , F05D2230/21 , F05D2230/22 , F05D2240/307 , F05D2250/12 , F05D2250/13 , F05D2250/14 , Y02P10/295
摘要： A gas turbine engine blade (10), including a base portion (12) having a cast wall, and a tip portion (14) attached to the base portion and having a wall (60) formed by an additive manufacturing process. The tip portion wall may be formed to be solid and less than 2 mm in thickness, or it may be corrugated and be greater than 2 mm in thickness. Openings (80) defining the wall corrugations may be semi-circular, rectangular, trapezoidal, or elliptical in cross-sectional shape. The resulting blade has lower tip mass while retaining adequate mechanical properties. The tip portion may be formed to have a directionally solidified grain structure on a base portion having an equiaxed grain structure.
摘要翻译：一种燃气涡轮发动机叶片（10），包括具有铸造壁的基部（12）和附接到基部的顶端部分（14），并具有通过添加剂制造工艺形成的壁（60）。尖端部分壁可以形成为固体并且厚度小于2mm，或者其可以是波纹状，并且厚度大于2mm。限定壁波纹的开口（80）可以是横截面形状的半圆形，矩形，梯形或椭圆形。所得到的刀片具有较低的尖端质量，同时保持足够的机械性能。尖端部分可以形成为在具有等轴晶粒结构的基部上具有定向凝固的晶粒结构。

24. 发明申请

US20160023303A1 METHOD FOR FORMING THREE-DIMENSIONAL ANCHORING STRUCTURES 审中-公开
标题翻译：形成三维锚固结构的方法
公开(公告)号：US20160023303A1
公开(公告)日：2016-01-28
申请号：US14337623
申请日：2014-07-22
申请人： Siemens Energy, Inc.
发明人： Gerald J. Bruck , Ahmed Kamel , Anand A. Kulkarni
IPC分类号： B23K26/00
CPC分类号： B23K26/3584 , B23K10/027 , B23K15/0086 , B23K26/14 , B23K26/354 , B23K26/355
摘要： A method for texturing a surface to form anchoring structures for a coating. The method includes: traversing an energy beam (10) along a path (30) on a solid substrate surface (12) to cause a melt pool (16) to move along the path; controlling power and motion parameters of the energy beam effective to establish a wave front (18) in the melt pool; and terminating the energy beam at an end (34) of the path when the wave front contains sufficient energy to create a protrusion (22) of material above the surface at the end of the path as the melt pool solidifies.
摘要翻译：用于纹理化表面以形成涂层的锚固结构的方法。该方法包括：沿着固体基质表面（12）上的路径（30）穿过能量束（10）以使熔池（16）沿着路径移动; 控制能量束的功率和运动参数，以有效地在熔池中建立波前（18）; 并且当所述波前包含足够的能量以在所述熔池固化时在所述路径的端部处的表面上方形成材料的突起（22），并且在所述路径的端部（34）处终止所述能量束。

25. 发明申请

US20150244344A1 SELF-POWERED SENSING AND TRANSMITTING DEVICE AND METHOD OF FABRICATING THE SAME 有权
标题翻译：自动感测和发送装置及其制造方法
公开(公告)号：US20150244344A1
公开(公告)日：2015-08-27
申请号：US14187359
申请日：2014-02-24
申请人： Siemens Energy, Inc.
发明人： David J. Mitchell , Anand A. Kulkarni
IPC分类号： H03H9/25 , G01M15/14
CPC分类号： H03H9/25 , F01D17/02 , F01D21/003 , F05D2230/90 , G01K1/024 , G01M15/14 , G01N29/2462 , G01N2291/2693 , H04Q9/00
摘要： A self-powered sensing and transmitting circuit (50) including a power element (44) and a sensing element (46) that is powered by the power element for generating a sensor signal responsive to a local operating environment The circuit also includes a transmitting element (48) powered by the power element for transmitting an output signal responsive to the sensor signal to a receiving location (33, 55) remote from the circuit The power element, sensing element and transmitting element of the circuit are arranged in a generally planar and non-integrated circuit configuration formed on a substrate (57) component exposed to operating temperatures at or exceeding 650° C.
摘要翻译：一种自供电感测和发射电路（50），包括功率元件（44）和感测元件（46），该功率元件（44）由功率元件供电，用于响应于本地操作环境产生传感器信号。该电路还包括发射元件（48）由功率元件供电，用于将响应于传感器信号的输出信号发送到远离电路的接收位置（33,55）。电路的功率元件，感测元件和传输元件被布置在大致平面和形成在暴露于或超过650℃的工作温度的基板（57）部件上的非集成电路配置

26. 发明授权

US11939884B2 System and method for repairing high-temperature gas turbine blades 有权
公开(公告)号：US11939884B2
公开(公告)日：2024-03-26
申请号：US17627779
申请日：2019-11-13
申请人： Siemens Energy, Inc.
发明人： Anand A. Kulkarni , Kazim Ozbaysal , Ahmed Kamel , Kyle I. Stoodt
IPC分类号： F01D5/28 , B22F1/10 , B22F3/10 , B22F3/26 , B22F5/04 , B22F10/16 , B22F10/18 , B22F10/38 , B22F10/40 , B22F10/68 , B23K1/00 , B23K35/30 , B23K101/00 , B23P6/00 , C22C19/05 , F01D5/00 , F01D25/00
CPC分类号： F01D5/28 , B22F1/10 , B22F3/1021 , B22F3/26 , B22F5/04 , B22F10/16 , B22F10/18 , B22F10/38 , B23K1/0018 , B23K35/3033 , B23P6/005 , C22C19/058 , F01D5/005 , F01D25/005 , B22F10/40 , B22F10/68 , B22F2301/15 , B23K2101/001 , F05D2230/237 , F05D2230/64 , F05D2230/80 , B22F2998/10 , B22F10/16 , B22F3/1021 , B22F10/64 , C22C1/08 , B22F3/26 , B22F2998/10 , B22F10/16 , B22F3/1021 , B22F10/64 , C22C1/08 , B22F2007/066 , B22F2999/00 , B22F10/16 , C22C1/0458
摘要： A blade for a gas turbine includes a removed portion space, and further includes an airfoil portion defining the removed portion space, the airfoil portion formed from a base material, and a replacement component formed to fill the removed portion space. The replacement component is formed from a material that includes 50%-80% base material, 0%-30% braze material, and 0%-8% aluminum. A braze joint is formed between the airfoil portion and the replacement component to attach the replacement component to the airfoil portion and fill the removed portion space.

27. 发明申请

US20220203448A1 SYSTEM AND METHOD FOR REPAIRING HIGH-TEMPERATURE GAS TURBINE COMPONENTS 有权
公开(公告)号：US20220203448A1
公开(公告)日：2022-06-30
申请号：US17627786
申请日：2019-11-13
申请人： Siemens Energy, Inc.
发明人： Anand A. Kulkarni , Kazim Ozbaysal , Ahmed Kamel , Kyle I. Stoodt
IPC分类号： B22F10/18 , F01D25/00 , F01D5/28 , B22F5/04 , B22F3/10 , B22F1/10
摘要： A method of forming a component includes mixing a powdered base material and a binder to define a mixture, forming the mixture into a desired shape without melting the base material, removing the binder from the desired shape to define a skeleton, the volume of the skeleton being between 80 percent and 95 percent base material, and infiltrating the skeleton with a melting point depressant material to define a finished component, the finished component having less than one percent porosity by volume.

28. 发明授权

US11248473B2 Metal trailing edge for laminated CMC turbine vanes and blades 有权
公开(公告)号：US11248473B2
公开(公告)日：2022-02-15
申请号：US16086324
申请日：2017-04-04
申请人： Siemens Energy, Inc.
发明人： Arindam Dasgupta , Anand A. Kulkarni
IPC分类号： F01D5/18 , F01D5/14 , F01D5/00 , F01D5/28
摘要： A turbine blade includes a platform with an internal cavity formed therein and an airfoil extending radially from the platform. The turbine blade includes a first portion made from ceramic matrix composite materials and a second portion made from superalloy materials. The first and second portions are selectively connected to each other via a spur and include an internal cooling circuit extending across both the first and second portions for circulating coolant therethrough. At least one supply passage extends between the internal cooling circuit and the internal platform cavity and includes an array of pin fins and turbulators for diverting coolant to the internal platform cavity.

29. 发明申请

US20210199052A1 HYBRID MANUFACTURING OF A SUPPORT HOUSING 有权
公开(公告)号：US20210199052A1
公开(公告)日：2021-07-01
申请号：US16755352
申请日：2018-05-01
申请人： Siemens Energy, Inc.
发明人： Anand A. Kulkarni , Charalambos Polyzopoulos
IPC分类号： F02C7/22
摘要： A support housing for use in distributing fuel in a gas turbine engine includes a main body defining an inlet aperture, a plurality of outlet apertures, and a substantially planar mounting surface. A first fuel channel has a wall that defines a first flow space and a support member extends across the first flow space and has a long axis oriented at an oblique angle with respect to the mounting surface.

30. 发明申请

US20190112932A1 METAL TRAILING EDGE FOR LAMINATED CMC TURBINE VANES AND BLADES 审中-公开
公开(公告)号：US20190112932A1
公开(公告)日：2019-04-18
申请号：US16086324
申请日：2017-04-04
申请人： Siemens Energy, Inc.
发明人： Arindam Dasgupta , Anand A. Kulkarni
IPC分类号： F01D5/18 , F01D5/00 , F01D5/14 , F01D5/28
摘要： A turbine blade includes a platform with an internal cavity formed therein and an airfoil extending radially from the platform. The turbine blade includes a first portion made from ceramic matrix composite materials and a second portion made from superalloy materials. The first and second portions are selectively connected to each other via a spur and include an internal cooling circuit extending across both the first and second portions for circulating coolant therethrough. At least one supply passage extends between the internal cooling circuit and the internal platform cavity and includes an array of pin fins and turbulators for diverting coolant to the internal platform cavity.

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