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公开(公告)号：US20230265767A1
公开(公告)日：2023-08-24
申请号：US17676929
申请日：2022-02-22
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Neelesh Nandkumar Sarawate
CPC classification number: F01D25/04 , F01D5/02 , F01D9/02 , F01D11/001 , F01D11/127 , F05D2240/56 , F05D2260/96
Abstract: A seal for a rotor is provided. The rotor defines an axial direction, a circumferential direction, and a radial direction. The seal includes a first flexible element coupled to the rotor. The first flexible element extends in a first direction that is within forty five degrees of the axial direction.
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公开(公告)号：US11674405B2
公开(公告)日：2023-06-13
申请号：US17461142
申请日：2021-08-30
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Neelesh Nandkumar Sarawate
IPC: F01D11/12
CPC classification number: F01D11/125 , F05D2220/32 , F05D2230/31 , F05D2240/55
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.
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公开(公告)号：US11486263B1
公开(公告)日：2022-11-01
申请号：US17359820
申请日：2021-06-28
Applicant: General Electric Company
Inventor： Surinder Singh Pabla , Martin James Jasper , Neelesh Nandkumar Sarawate , Bradley Taylor Boyer , Srikanth Chandrudu Kottilingam
Abstract: A system for a turbine blade tip to address wear during rubbing with a shroud, and also tip rail cooling, is provided. The turbine blade tip includes a tip rail and cooling passage(s) extending through a radially outer end surface thereof, providing direct cooling to the tip. The tip rail may include tip rail cooling inserts. The radial outer end surface of the tip rail includes a first portion radially inward of a second portion thereof. An abrasive layer extends along the first portion adjacent the cooling passage(s), and may include a matrix alloy having a plurality of cubic boron nitride (cBN) particles and a plurality of ceramic particles embedded therein. The abrasive layer extends radially outward of the second portion of the radial outer end surface. The system also may include a shroud including an abradable coating thereon.
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公开(公告)号：US11215063B2
公开(公告)日：2022-01-04
申请号：US16598003
申请日：2019-10-10
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate , Christopher Walter Falcone
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 a slot including one or more slot segments located in an end face and a seal assembly disposed in the slot. The seal assembly including a plurality of seal segments forming at least one T-junction where a first seal segment intersects a second seal segment and at least one shim seal. The plurality of seal segments define at least one chute gap. The at least one shim seal disposed in a slot proximate the at least one T-junction of the plurality of seal segments. The at least one shim seal positioned on a sidewall of the second seal segment and extending a partial length of the sidewall. The at least one shim seal seals the at least one chute gap to prevent a flow therethrough of a gas turbine hot gas path flow.
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公开(公告)号：US20210108528A1
公开(公告)日：2021-04-15
申请号：US16598003
申请日：2019-10-10
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate , Christopher Walter Falcone
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 a slot including one or more slot segments located in an end face and a seal assembly disposed in the slot. The seal assembly including a plurality of seal segments forming at least one T-junction where a first seal segment intersects a second seal segment and at least one shim seal. The plurality of seal segments define at least one chute gap. The at least one shim seal disposed in a slot proximate the at least one T-junction of the plurality of seal segments. The at least one shim seal positioned on a sidewall of the second seal segment and extending a partial length of the sidewall. The at least one shim seal seals the at least one chute gap to prevent a flow therethrough of a gas turbine hot gas path flow.
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Patent Agency Ranking
公开(公告)号：US10689994B2
公开(公告)日：2020-06-23
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.
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公开(公告)号：US20190383488A1
公开(公告)日：2019-12-19
申请号：US16012412
申请日：2018-06-19
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes , Russell Pierson DeForest , Kevin Weston McMahan , Victor John Morgan , Ibrahim Sezer , Neelesh Nandkumar Sarawate , Deepak Trivedi
Abstract: An integrated combustor nozzle includes an inner liner segment; an outer liner segment; and a panel extending radially between the inner and outer liner segments. The panel includes a forward end, an aft end, and a side walls extending axially from the forward end to the aft end. The aft end defines a turbine nozzle having a trailing edge circumferentially offset from the forward end. The inner liner segment has a pair of sealing surfaces, each of which defines a first continuous curve in the circumferential direction. The outer liner segment has a pair of sealing surfaces, each of which defines a second continuous curve in the circumferential direction. In some instances, the curves are monotonic in the circumferential direction. A segmented annular combustor including an array of such integrated combustor nozzles is also provided.
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公开(公告)号：US10436041B2
公开(公告)日：2019-10-08
申请号：US15481674
申请日：2017-04-07
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate
Abstract: A shroud assembly of a turbine system is presented. The shroud assembly includes a plurality of outer shroud segments disposed annularly and defining a first gap between a pair of outer shroud segments of the plurality of outer shroud segments; a plurality of inner shroud segments disposed annularly and radially inward of the plurality of outer shroud segments, and defining a second gap between a pair of inner shroud segments of the plurality of inner shroud segments, wherein the plurality of inner shroud segments is same in number to the plurality of outer shroud segments, and wherein the first gap and the second gap are offset; and an impingement plate coupled to an outer shroud segment of the pair of outer shroud segments and interposed between the outer shroud segment and the pair of inner shroud segments.
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公开(公告)号：US10100656B2
公开(公告)日：2018-10-16
申请号：US14834866
申请日：2015-08-25
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Stephen Francis Bancheri , Venkat Subramaniam Venkataramani , Glen Harold Kirby , Neelesh Nandkumar Sarawate , Nicholas Edward Antolino , Edip Sevincer , Anthony Christopher Marin
Abstract: A coated seal slot system for turbomachinery includes a first turbine component comprising a first groove having at least one first coating attached to at least a portion of the first groove of the first turbine component, a second turbine component comprising a second groove having at least one second coating attached to at least a portion of the second groove of the second turbine component. The first and the second turbine components are disposable adjacent to each other with the first groove having the first coating and the second groove having the second coating together forming a coated seal slot extending across a gap between the first turbine component and the second turbine component. A seal is disposable in the coated seal slot and extendable across the gap between the first and the second turbine components and engageable with the first coating and the second coating to inhibit leakage of gas through the gap.
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公开(公告)号：US09869194B2
公开(公告)日：2018-01-16
申请号：US15087394
申请日：2016-03-31
Applicant: General Electric Company
Inventor： Bodhayan Dev , Robert Carl Meyer , Neelesh Nandkumar Sarawate , Jason Edward Albert , Gary Michael Itzel
IPC: F01D11/00
CPC classification number: F01D11/005 , F05D2220/32 , F05D2240/11 , F05D2240/57 , F05D2240/59 , F16J15/442
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 an intersegment seal including a plurality of seal segments defining one or more corner regions. The intersegment seal disposed in a slot defining a high-pressure slot side and a low-pressure slot side, wherein the slot includes a plurality of slot segments. Each of the plurality of seal segments including at least one extended portion to either seal the one or more corner regions on a low-pressure slot side, form a recess in the intersegment seal, or both.
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