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公开(公告)号：US20170284215A1
公开(公告)日：2017-10-05
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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公开(公告)号：US11988096B2
公开(公告)日：2024-05-21
申请号：US17841847
申请日：2022-06-16
Inventor： Ravindra Shankar Ganiger , Neelesh Nandkumar Sarawate , Rahul Anil Bidkar , Narendra Anand Hardikar , Kevin Randall McManus , Steven Douglas Johnson , Prateek Jalan , Antonio Guijarro Valencia , Julius John Montgomery , Rodrigo Rodriguez Erdmenger , Jose Maria Rey Villazon
CPC classification number: F01D11/003 , F01D11/001 , F01D11/02 , F05D2220/323 , F05D2240/56
Abstract: A seal assembly for a rotary machine, such as a turbine engine, may include a seal rotor comprising a rotor face, a seal slider comprising a slider face, a seal stator, wherein the seal slider is slidably coupled to the seal stator, and wherein the slider face and the rotor face define a primary seal. The seal slider may be configured to slidably engage and retract the slider face with respect to the rotor face. The seal assembly may further include a secondary seal disposed between the seal slider and the seal stator. The secondary seal may be configured to compress and rebound and/or to expand and rebound, over at least a portion of a range of motion of the seal slider.
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公开(公告)号：US20230312935A1
公开(公告)日：2023-10-05
申请号：US17841861
申请日：2022-06-16
Applicant: General Electric Company
Inventor： Atanu Saha , Bernard Patrick Bewlay , Neelesh Nandkumar Sarawate
IPC: C09D1/00 , C04B35/63 , C04B35/488 , C04B35/505
CPC classification number: C09D1/00 , C04B35/6316 , C04B35/488 , C04B35/505 , C04B2235/3246 , C04B2235/3225 , C04B2235/5436
Abstract: Coated components, along with methods of their formation, are provided. The coating may include a component having a surface and a coating over the surface of the component. The coating may include a first plurality of coarse micrograins having an coarse median grain size of greater than 10 μm to 20 μm, a second plurality of medium micrograins having a medium median grain size of 4 μm to 10 μm, a third plurality of fine micrograins having a fine median grain size of 0.001 μm to less than 4 μm. Each of the coarse micrograins, medium micrograins, and fine micrograins may include, independently, a yttria-stabilized zirconia (YSZ) constituent having a chemical formula of (ZrO2)(1−x)(Y2O3)x with x is from greater than 0 to less than 1.
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公开(公告)号：US11773739B2
公开(公告)日：2023-10-03
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
CPC classification number: F01D11/005 , F16J15/0887 , F23R3/46 , F05D2240/35 , F05D2240/55 , F23R2900/00012
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.
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公开(公告)号：US20230279781A1
公开(公告)日：2023-09-07
申请号：US17841847
申请日：2022-06-16
Inventor： Ravindra Shankar Ganiger , Neelesh Nandkumar Sarawate , Rahul Anil Bidkar , Narendra Anand Hardikar , Kevin Randall McManus , Steven Douglas Johnson , Prateek Jalan , Antonio Guijarro Valencia , Julius John Montgomery , Rodrigo Rodriguez Erdmenger , Jose Maria Rey Villazon
CPC classification number: F01D11/003 , F01D11/02 , F01D11/001 , F05D2240/56 , F05D2220/323
Abstract: A seal assembly for a rotary machine, such as a turbine engine, may include a seal rotor comprising a rotor face, a seal slider comprising a slider face, a seal stator, wherein the seal slider is slidably coupled to the seal stator, and wherein the slider face and the rotor face define a primary seal. The seal slider may be configured to slidably engage and retract the slider face with respect to the rotor face. The seal assembly may further include a secondary seal disposed between the seal slider and the seal stator. The secondary seal may be configured to compress and rebound and/or to expand and rebound, over at least a portion of a range of motion of the seal slider.
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Patent Agency Ranking
公开(公告)号：US11231175B2
公开(公告)日：2022-01-25
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：US11047248B2
公开(公告)日：2021-06-29
申请号：US16012380
申请日：2018-06-19
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate , Jonathan Dwight Berry , Russell Pierson DeForest , Kevin Weston McMahan , Victor John Morgan , Ibrahim 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.
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公开(公告)号：US10774665B2
公开(公告)日：2020-09-15
申请号：US16050008
申请日：2018-07-31
Applicant: General Electric Company
Inventor： John Ellington Greene , Neelesh Nandkumar Sarawate
Abstract: A seal system for a gas turbine vane includes a first seal layer and an optional second seal layer. Each first seal layer includes multiple seal segments, each of which includes a first leg, a second leg, and an intermediate portion between the first leg and the second leg. Each adjacent pair of seal segments of the first seal is separated by a gap. The seal segments define a substantially complete perimeter of a seal slot in which the first seal is installed. The second seal, which is also segmented, may or may not define the substantially complete perimeter of the seal slot. If present, the second seal segments are circumferentially offset from the first seal segments to block the gaps between the first seal segments. A turbine vane including the present seal system is also disclosed.
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公开(公告)号：US10683769B2
公开(公告)日：2020-06-16
申请号：US15248161
申请日：2016-08-26
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate , Deepak Trivedi , Xiaoqing Zheng
IPC: F01D11/08 , F01D11/00 , F01D11/02 , F16J15/3292 , F16J15/3288 , F16J15/16 , F01D5/02 , F01D9/02
Abstract: A seal for a rotary machine includes a flexible element extending circumferentially about a rotating component 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 rotating component. The seal also includes a retaining plate having a stop face that orients the flexible element at a first angle when the rotating component is operating at less than a critical speed and under the including of pressure loading, such that a clearance gap is defined between the free second end and a stationary component. The flexible element extends at substantially a second angle when the rotating component is operating at a speed greater than the critical speed, such that the flexible element forms a dynamic seal between the rotating component and the stationary component.
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公开(公告)号：US20190383393A1
公开(公告)日：2019-12-19
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.
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