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1. 发明授权

US11821320B2 Turbine engine with a rotor seal assembly 有权
公开(公告)号：US11821320B2
公开(公告)日：2023-11-21
申请号：US17338807
申请日：2021-06-04
申请人： GENERAL ELECTRIC COMPANY
发明人： Steven Douglas Johnson , Kevin Randall McManus , Rahul Anil Bidkar
IPC分类号： F01D11/22 , F01D11/00 , F01D11/02
CPC分类号： F01D11/001 , F01D11/025 , F01D11/22 , F05D2220/323 , F05D2240/11 , F05D2240/80 , F05D2260/38
摘要： A turbine engine comprising an engine core having at least a compressor section, a combustor section, and a turbine section in axial flow arrangement defining an axial direction and an engine centerline. The turbine engine further having a rotor and a stator, a carriage assembly carried by the stator, and a seal assembly biased toward the rotor.

2. 发明授权

US10989058B2 Segmented piston seal system 有权
公开(公告)号：US10989058B2
公开(公告)日：2021-04-27
申请号：US15957415
申请日：2018-04-19
申请人： General Electric Company
发明人： Deepak Trivedi , Rahul Anil Bidkar , Xiaoqing Zheng , Christopher Edward Wolfe
IPC分类号： F01D11/00 , F01D5/02 , F01D25/18 , F16J15/34
摘要： The subject matter described herein relate to a segmented piston seal system. The segmented piston seal includes a first semi-circular section (FSCS) that includes a first locking structure at opposite ends of the FSCS. The segmented piston seal includes a second semi-circular section (SSCS) that includes a second locking structure at opposite ends of the SSCS. The first and second locking structures are configured to lock the FSCS and the SSCS together to form a piston seal.

3. 发明授权

US10626743B2 Segmented face seal assembly and an associated method thereof 有权
公开(公告)号：US10626743B2
公开(公告)日：2020-04-21
申请号：US15397278
申请日：2017-01-03
申请人： General Electric Company
发明人： Rahul Anil Bidkar , Azam Mihir Thatte , Jifeng Wang , Xiaoqing Zheng , Edip Sevincer
IPC分类号： F01D11/00 , F16J15/34 , F01D5/02 , F01D9/04 , F01D25/16 , F16J15/44
CPC分类号： F01D11/003 , F01D5/02 , F01D9/041 , F01D25/16 , F16J15/3488 , F16J15/442 , F05D2220/32 , F05D2230/60 , F05D2240/55
摘要： A turbomachine and a method of operating the turbomachine are disclosed. The turbomachine includes a stator, a rotor including a rotor bearing face, and a face seal assembly including a first segmented seal ring and a second segmented seal ring. The first segmented seal ring includes a plurality of joints and a first flat-contact surface and the second segmented seal ring includes a plurality of segment ends and a second flat-contact surface. One of the first and second segmented seal rings includes a seal bearing face. The second segmented seal ring is coupled to the first segmented seal ring such that the second flat-contact surface is in contact with the first flat-contact surface. The plurality of segment ends is circumferentially offset from the plurality of joints. The first segmented seal ring is slidably coupled to the stator and defines a face seal clearance between the rotor and seal bearing faces.

4. 发明授权

US10415707B2 Face seal assembly and an associated method thereof 有权
公开(公告)号：US10415707B2
公开(公告)日：2019-09-17
申请号：US15397317
申请日：2017-01-03
申请人： General Electric Company
发明人： Rahul Anil Bidkar , Azam Mihir Thatte , Jifeng Wang , Xiaoqing Zheng , Edip Sevincer
IPC分类号： F16J15/40 , F01D25/22 , F16J15/34
摘要： A turbomachine and a method of operating the turbomachine are disclosed. The turbomachine includes a stator, a rotor including a rotor bearing face, a face seal assembly, a first pressure cavity, and a second pressure cavity. The face seal assembly includes a seal ring including a seal bearing face, a first pressure cavity, and a plurality of isolated hydrostatic ports extending from the first pressure cavity to the seal bearing face. The face seal assembly is slidably coupled to the stator and defines a face seal clearance between the rotor and seal bearing faces. The second and third pressure cavities are defined by the stator, the rotor, and the face seal assembly. The third pressure cavity is disposed downstream of the second pressure cavity with reference to flow of a process fluid along the stator and rotor. The first pressure cavity is isolated from the second and third pressure cavities.

5. 发明申请

US20180372229A1 SEAL ASSEMBLY FOR ROTARY MACHINE 审中-公开
公开(公告)号：US20180372229A1
公开(公告)日：2018-12-27
申请号：US14619246
申请日：2015-02-11
申请人： General Electric Company
发明人： Rahul Anil Bidkar , Christopher Edward Wolfe , Bugra Han Ertas , Adolfo Delgado Marquez , Nathan Evan McCurdy Gibson
IPC分类号： F16J15/447
摘要： A seal assembly for a rotary machine is provided. The seal assembly includes a plurality of seal segments disposed circumferentially intermediate to a stationary housing and a rotor, where each of the plurality of seal segments includes a stator interface element and a shoe plate movably supported by the stator interface element. The shoe plate includes one or more labyrinth teeth, a load-bearing surface, and one or more supply ports for facilitating supply of high pressure fluid toward the rotor. In one embodiment, the shoe plate also includes a radially extending portion that is in contact with a portion of the ring movably supported into the stator interface element. In another embodiment, each of the plurality of seal segments includes a plurality of overlapping spring-loaded leaf seal plates in contact with the stator interface element and the radially extending portion. Method of operating the seal segment is also disclosed.

6. 发明申请

US20180258789A1 SYSTEM AND METHOD FOR TRANSITION PIECE SEAL 审中-公开
公开(公告)号：US20180258789A1
公开(公告)日：2018-09-13
申请号：US15452473
申请日：2017-03-07
申请人： General Electric Company
发明人： Rahul Anil Bidkar , Neelesh Nandkumar Sarawate , Kevin McMahan , Ronald Chila
IPC分类号： F01D25/12 , F01D9/02 , F01D11/00 , F04D29/54
CPC分类号： F01D25/12 , F01D9/023 , F01D11/003 , F01D11/005 , F01D25/08 , F01D25/243 , F01D25/28 , F01D25/30 , F04D29/545 , F05D2220/32 , F05D2240/35 , F05D2240/55 , F05D2260/201 , F23R3/002 , F23R3/005 , F23R3/60 , F23R2900/00012
摘要： A system includes a web plate axially disposed between a transition piece and a turbine nozzle. The web plate includes a radial arm extending in a radial direction between an inner surface and an outer surface of the web plate. The radial arm, the inner surface, and the outer surface are disposed about an axial passage configured to facilitate a flow of combustion products from the transition piece to the turbine nozzle. The transition piece is disposed within a compressor discharge cavity configured to receive an oxidant. The radial arm includes an upstream face in fluid communication with the compressor discharge cavity. The radial arm also includes an arm passage that extends an axial length in an axial direction from the upstream face through at least an axial depth of the radial arm. The arm passage is configured to receive a portion of the oxidant through the upstream face.

7. 发明申请

US20140119912A1 FILM RIDING AERODYNAMIC SEALS FOR ROTARY MACHINES 有权
标题翻译：旋转机械电动滑行气动密封件
公开(公告)号：US20140119912A1
公开(公告)日：2014-05-01
申请号：US13665431
申请日：2012-10-31
申请人： GENERAL ELECTRIC COMPANY
发明人： Rahul Anil Bidkar , Matthew Michael Langenderfer , Hrishikesh Vishvas Deo , Azam Mihir Thatte
IPC分类号： F01D11/02 , F03B11/00 , B23P11/00
CPC分类号： F01D11/02 , F01D11/025 , F05D2240/55 , F16J15/442 , Y10T29/49826
摘要： A seal assembly for a rotary machine is provided. The seal assembly includes multiple sealing device segments disposed circumferentially intermediate to a stationary housing and a rotor. Each of the sealing device segments includes a stator interface element. The sealing device segment also includes a shoe plate having one or more labyrinth teeth facing the rotor and a load-bearing surface region, wherein the shoe plate allows a high pressure fluid to an upstream portion of the forwardmost labyrinth tooth and a low pressure fluid to a downstream portion of the aftmost labyrinth tooth. The sealing device segment further includes a secondary seal in contact with the stator interface element at a radially outer end and in contact with an elevated nose of the shoe plate on a radially inner end; and multiple bellow springs or flexures attached to the shoe plate and to the stator interface element.
摘要翻译：提供了一种用于旋转机器的密封组件。密封组件包括沿周向设置在固定壳体和转子周围的多个密封装置段。每个密封装置段包括定子接口元件。密封装置段还包括具有面向转子的一个或多个迷宫齿和承载表面区域的鞋板，其中，鞋板允许高压流体到达最前面的迷宫齿的上游部分，而低压流体最后迷宫齿的下游部分。密封装置段还包括在径向外端处与定子界面元件接触并在径向内端上与鞋板的升高的鼻部接触的次级密封件; 以及多个波纹管弹簧或挠曲件，其附接到鞋板和定子接口元件。

8. 发明授权

US12123306B2 Seal assemblies for turbine engines and related methods 有权
公开(公告)号：US12123306B2
公开(公告)日：2024-10-22
申请号：US17851672
申请日：2022-06-28
申请人： General Electric Company
发明人： Deepak Trivedi , Rahul Anil Bidkar , Bugra Han Ertas
IPC分类号： F01D11/00 , F01D11/08
CPC分类号： F01D11/08 , F05D2220/323 , F05D2240/55
摘要： A seal assembly for an aeronautical turbine engine includes a passive flow regulator. The passive flow regulator includes a seal body defining an aspiration conduit, and a flow constrictor disposed within and/or adjacently upstream of the aspiration conduit. The aspiration conduit provides fluid communication across the seal body from a relatively higher-pressure fluid volume to a relatively lower-pressure fluid volume. The flow constrictor includes one or more flexure elements that move in one or more degrees of freedom as a result of changes in a pressure differential across the flow constrictor. The movement of the one or more flexure elements changes a hydraulic resistance of fluid flow past the flow constrictor based at least in part on a position of the flow constrictor in relation to the aspiration conduit.

9. 发明公开

US20240133770A1 SEAL MONITORING APPARATUS 审中-公开
公开(公告)号：US20240133770A1
公开(公告)日：2024-04-25
申请号：US17972834
申请日：2022-10-24
申请人： General Electric Company
发明人： Bugra H. Ertas , Deepak Trivedi , Scott Alan Schimmels , Joseph Herbert Fields , Rahul Anil Bidkar , Eric R. Westervelt , Andrew Kevin Winn
IPC分类号： G01M15/14 , F01D11/08 , F02C7/28
CPC分类号： G01M15/14 , F01D11/08 , F02C7/28 , F05D2220/32 , F05D2240/55 , F05D2260/80
摘要： A seal monitoring apparatus is provided. The seal monitoring apparatus includes one or more pressure sensors and a controller in communication with the one or more pressure sensors. The one or more pressure sensors is mounted at a seal of a turbine to measure pressure on a first side of the seal and/or a second side of the seal. The controller is configured to receive pressure data from the one or more pressure sensors and determine a condition of the seal based at least in part on the pressure data. The controller is configured to output a signal upon determining a change in the condition of the seal.

10. 发明公开

US20230417148A1 SEAL ASSEMBLIES FOR TURBINE ENGINES AND RELATED METHODS 审中-公开
公开(公告)号：US20230417148A1
公开(公告)日：2023-12-28
申请号：US17851672
申请日：2022-06-28
申请人： General Electric Company
发明人： Deepak Trivedi , Rahul Anil Bidkar , Bugra Han Ertas
IPC分类号： F01D11/08
CPC分类号： F01D11/08 , F05D2220/323 , F05D2240/55
摘要： A seal assembly for an aeronautical turbine engine includes a passive flow regulator. The passive flow regulator includes a seal body defining an aspiration conduit, and a flow constrictor disposed within and/or adjacently upstream of the aspiration conduit. The aspiration conduit provides fluid communication across the seal body from a relatively higher-pressure fluid volume to a relatively lower-pressure fluid volume. The flow constrictor includes one or more flexure elements that move in one or more degrees of freedom as a result of changes in a pressure differential across the flow constrictor. The movement of the one or more flexure elements changes a hydraulic resistance of fluid flow past the flow constrictor based at least in part on a position of the flow constrictor in relation to the aspiration conduit.

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