-
公开(公告)号：US20170284214A1
公开(公告)日：2017-10-05
申请号：US15087352
申请日：2016-03-31
Applicant: General Electric Company
Inventor： Jason Edward Albert , Bodhayan Dev , Neelesh Nandkumar Sarawate , Michael John Brown
Abstract: Various embodiments include gas turbine seals and methods of forming such seals. In some cases, a turbine includes: a first arcuate component adjacent to a second arcuate component, each arcuate component including one or more slots located in an end face, each of the one or more slots having a plurality of axial surfaces and radially facing surfaces extending from opposite ends of the axial surfaces and a seal assembly disposed in the slot. The seal assembly including a backup intersegment seal disposed in the slot on a high-pressure side of the slot and a shim seal disposed in the slot over the backup intersegment seal and covering the backup intersegment seal on a low-pressure side of the slot. The shim seal including one or more shim seal segments and having a gap formed between each of the one or more shim seal segments.
-
公开(公告)号：US20170159480A1
公开(公告)日：2017-06-08
申请号：US14963034
申请日：2015-12-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Bodhayan Dev , Neelesh Nandkumar Sarawate , Jason Edward Albert , Christopher Edward Wolfe
CPC classification number: F01D11/006 , F01D5/02 , F01D9/02 , F01D11/003 , F01D11/005 , F05D2220/32 , F05D2230/23 , F05D2230/60 , F05D2240/11 , F05D2240/55 , F05D2300/177 , F05D2300/20 , F16J15/08
Abstract: The present disclosure relates to a turbomachine that includes a first component and a second component coupled to another and a seal assembly between the two components. The seal assembly may include a first intersegment seal, a second intersegment seal, and a rope seal that are configured to block a flow of gas between the two components.
-
公开(公告)号：US20170159478A1
公开(公告)日：2017-06-08
申请号：US14962979
申请日：2015-12-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Bodhayan Dev , Neelesh Nandkumar Sarawate , Jason Edward Albert
CPC classification number: F01D11/006 , F01D5/02 , F01D5/12 , F01D9/041 , F04D29/083 , F05D2220/32 , F16J15/0887
Abstract: The present disclosure relates to a turbomachine that includes a first component and a second component coupled to another and a seal assembly disposed between the two components. The seal assembly may include an upstream corner shim, a downstream corner shim, and/or one or more intersegment seals that are configured to block a flow of fluid between the two components.
-
公开(公告)号：US20170089215A1
公开(公告)日：2017-03-30
申请号：US14869538
申请日：2015-09-29
Applicant: General Electric Company
Inventor： Xiaoqing Zheng , Michael Dennis Mack , Neelesh Nandkumar Sarawate , Deepak Trivedi
CPC classification number: F01D11/127 , F01D5/02 , F01D11/001 , F01D11/025 , F05D2220/30 , F05D2220/31 , F05D2230/60 , F05D2240/56 , F05D2260/30 , F16J15/164 , F16J15/3288
Abstract: A seal for a rotary machine includes a flexible element extending circumferentially about a rotor and extending generally radially from a first end to a free second end. The flexible element is coupled proximate the first end for rotation with the rotor. The flexible element extends at substantially a first angle between at least an intermediate portion of the flexible element and the free second end when the rotor is operating at less than a critical speed, such that a clearance gap is defined between the free second end and a stationary portion. The seal also includes a retaining plate having a stop that orients the flexible element at a second angle proximate the free second end when the rotor is operating at equal to or greater than the critical speed, such that the flexible element forms a dynamic seal between the rotor and the stationary portion.
-
35.发明申请SHIM SEAL ASSEMBLIES AND ASSEMBLY METHODS FOR STATIONARY COMPONENTS OF ROTARY MACHINES 审中-公开旋转机械静态组件的SHIM密封组件和组装方法公开(公告)号：US20160215643A1
公开(公告)日：2016-07-28
申请号：US15089706
申请日：2016-04-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Neelesh Nandkumar Sarawate , Victor John Morgan , David Wayne Weber
CPC classification number: F01D11/005 , F05D2220/32 , F05D2240/11 , F05D2240/55 , F05D2250/12 , F05D2250/75 , F16J15/0812 , F16J15/0893 , F16J15/128
Abstract: A seal assembly for a rotary machine is provided. The seal assembly includes a shim seal including multiple seal plates forming a box shaped shim seal. The box shaped seal includes a plurality of cuts at two opposing sides or corners for allowing high pressure fluid to occupy the cavity of the box-shaped shim seal. The seal may be inserted within one or more slots between adjacent stator components of the rotary machine.
Abstract translation: 提供了一种用于旋转机器的密封组件。 密封组件包括垫片密封件，该密封件包括形成盒形垫片密封件的多个密封板。 箱形密封件包括在两个相对的侧面或拐角处的多个切口，用于允许高压流体占据箱形垫片密封件的空腔。 密封件可以插入在旋转机器的相邻定子部件之间的一个或多个槽内。
-
Patent Agency Ranking
公开(公告)号：US20140348642A1
公开(公告)日：2014-11-27
申请号：US13875370
申请日：2013-05-02
Applicant: General Electric Company
Inventor： David Wayne Weber , Victor John Morgan , Neelesh Nandkumar Sarawate
CPC classification number: F01D11/005 , F05D2240/11 , F05D2240/59 , F05D2250/75
Abstract: A device including a conjoined laminate interface seal shaped for reducing inter-seal gap (e.g., an angled gap, an ‘L’-shaped gap, etc.) leakage in gas turbines is disclosed. In one embodiment, a seal device for a gas turbine includes: a first flange shaped to be disposed within a first slot of a first arcuate component and a first adjacent slot of a second arcuate component; a conjoined layer connected to a first surface of the first flange, the first surface configured to face a working fluid flow of the gas turbine; and a second flange shaped to be disposed within a second slot of the first arcuate component and a second adjacent slot of the second arcuate component, the second flange including a second surface connected to the conjoined layer.
Abstract translation: 公开了一种包括用于减少燃气涡轮机中的间隙间隙（例如，成角度间隙，“L'形间隙等”）泄漏的结合层压体界面密封件的装置。 在一个实施例中，一种用于燃气涡轮机的密封装置包括：第一凸缘，其被成形为设置在第一弓形部件的第一槽内和第二弧形部件的第一相邻狭槽内; 连接到所述第一凸缘的第一表面的连接层，所述第一表面被配置为面对所述燃气轮机的工作流体流; 以及第二凸缘，其被成形为设置在所述第一弓形部件的第二狭槽内以及所述第二弓形部件的第二相邻狭槽中，所述第二凸缘包括连接到所述连结层的第二表面。
-
公开(公告)号：US20230060175A1
公开(公告)日：2023-03-02
申请号：US17461142
申请日：2021-08-30
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Neelesh Nandkumar Sarawate
IPC: F01D11/12
Abstract: An abradable insert for a gas turbine engine, the abradable insert including: a base layer; a lattice layer connected to the base layer, wherein the lattice layer comprises a series of walls that define a plurality of cells; and a sheet layer connected to the lattice layer on an opposite side on the lattice layer from the base layer, wherein the sheet layer is curved and includes a direction of concavity that points away from the base layer, wherein the lattice layer and the sheet layer are integrally formed together and are a monolithic piece of material.
-
公开(公告)号：US11248705B2
公开(公告)日：2022-02-15
申请号：US16256322
申请日：2019-01-24
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate , Christopher Walter Falcone
Abstract: A flexible seal is used to seal between two adjacent gas turbine components. The flexible seal includes at least one metal ply having a forward end, an aft end axially separated from the forward end, and an intermediate portion between the forward end and the aft end. The intermediate portion defines a continuous curve in the circumferential direction, such that the aft end is circumferentially, and optionally radially, offset from the forward end. A plurality of relief cuts is defined through the at least one metal ply between the forward end and the aft end to increase flexibility and improve sealing in seal slots that are radially offset from one another.
-
公开(公告)号：US20210324754A1
公开(公告)日：2021-10-21
申请号：US17358691
申请日：2021-06-25
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate , Jonathan Dwight Berry , Russell Pierson DeForest , Kevin Weston McMahan , Victor John Morgan , Ibrahim Klara Sezer , Deepak Trivedi
Abstract: A flexible seal for sealing between two adjacent gas turbine components includes a forward end, an aft end axially separated from the forward end, and an intermediate portion between the forward end and the aft end. The intermediate portion defines a continuous curve in the circumferential direction, such that the aft end is circumferentially offset from the forward end. In other cases, the forward and aft ends are axially, radially, and circumferentially offset from one another. A method of sealing using the flexible seal includes inserting, in an axial direction, the aft end of the flexible seal into a recess defined by respective seal slots of two adjacent gas turbine components; and pushing the flexible seal in an axial direction through the recess until the forward end is disposed within the recess.
-
公开(公告)号：US20190203606A1
公开(公告)日：2019-07-04
申请号：US15862520
申请日：2018-01-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Neelesh Nandkumar Sarawate , Christopher Edward Wolfe , Victor John Morgan , Jason Ray Gregg
CPC classification number: F01D11/005 , F01D9/041 , F05D2220/32 , F05D2230/60 , F05D2240/55
Abstract: An assembly for a turbomachine and a method for assembling a plurality of flow path components are presented. The assembly includes a plurality of flow path components disposed adjacent to one another, each flow path component having a forward surface, an aft surface, a pressure side surface, and a suction side surface. A seal channel is defined by the pressure side surface and the suction side surface of adjacent flow path components. The seal channel has an open forward end proximate to the forward surfaces and at least two rear ends proximate to the aft surfaces. The assembly includes a plurality of seal layers disposed within the seal channel such that one or more seal layers extend from the open forward end to a rear end and one or more other seal layers extend from the open forward end to another rear end.
-
-
-
-
-
-
-
-
-
Search Results
68
records
(took 0.038 seconds)
