Patents by Inventor Neelesh Nandkumar Sarawate

Neelesh Nandkumar Sarawate has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Publication number: 20230312935
    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 ?m to 20 ?m, a second plurality of medium micrograins having a medium median grain size of 4 ?m to 10 ?m, a third plurality of fine micrograins having a fine median grain size of 0.001 ?m to less than 4 ?m. 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.
    Type: Application
    Filed: June 16, 2022
    Publication date: October 5, 2023
    Inventors: Atanu Saha, Bernard Patrick Bewlay, Neelesh Nandkumar Sarawate
  • Patent number: 11773739
    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.
    Type: Grant
    Filed: June 25, 2021
    Date of Patent: October 3, 2023
    Assignee: General Electric Company
    Inventors: Neelesh Nandkumar Sarawate, Jonathan Dwight Berry, Russell Pierson DeForest, Kevin Weston McMahan, Victor John Morgan, Ibrahim Klara Sezer, Deepak Trivedi
  • Publication number: 20230279781
    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.
    Type: Application
    Filed: June 16, 2022
    Publication date: September 7, 2023
    Inventors: 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
  • Publication number: 20230265767
    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.
    Type: Application
    Filed: February 22, 2022
    Publication date: August 24, 2023
    Inventors: Steven Douglas Johnson, Neelesh Nandkumar Sarawate
  • Patent number: 11674405
    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.
    Type: Grant
    Filed: August 30, 2021
    Date of Patent: June 13, 2023
    Assignee: General Electric Company
    Inventors: Steven Douglas Johnson, Neelesh Nandkumar Sarawate
  • Publication number: 20230060175
    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.
    Type: Application
    Filed: August 30, 2021
    Publication date: March 2, 2023
    Inventors: Steven Douglas Johnson, Neelesh Nandkumar Sarawate
  • Patent number: 11486263
    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.
    Type: Grant
    Filed: June 28, 2021
    Date of Patent: November 1, 2022
    Assignee: General Electric Company
    Inventors: Surinder Singh Pabla, Martin James Jasper, Neelesh Nandkumar Sarawate, Bradley Taylor Boyer, Srikanth Chandrudu Kottilingam
  • Patent number: 11248705
    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.
    Type: Grant
    Filed: January 24, 2019
    Date of Patent: February 15, 2022
    Assignee: General Electric Company
    Inventors: Neelesh Nandkumar Sarawate, Christopher Walter Falcone
  • Patent number: 11231175
    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.
    Type: Grant
    Filed: June 19, 2018
    Date of Patent: January 25, 2022
    Assignee: General Electric Company
    Inventors: Jonathan Dwight Berry, Michael John Hughes, Russell Pierson DeForest, Kevin Weston McMahan, Victor John Morgan, Ibrahim Sezer, Neelesh Nandkumar Sarawate, Deepak Trivedi
  • Patent number: 11215063
    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.
    Type: Grant
    Filed: October 10, 2019
    Date of Patent: January 4, 2022
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Neelesh Nandkumar Sarawate, Christopher Walter Falcone
  • Patent number: 11181002
    Abstract: A turbine system including a sealing component is presented. The sealing component is positioned in a gap between adjacent turbine components of the turbine system. The sealing component includes a metallic shim including a high-temperature-resistant alloy in a single crystal form. A turbine shroud assembly including the sealing component is also presented.
    Type: Grant
    Filed: September 29, 2016
    Date of Patent: November 23, 2021
    Assignee: General Electric Company
    Inventors: Neelesh Nandkumar Sarawate, Venkat Subramaniam Venkataramani, Anthony Christopher Marin, Stephen Francis Bancheri, Larry Steven Rosenzweig, Edip Sevincer
  • Publication number: 20210324754
    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.
    Type: Application
    Filed: June 25, 2021
    Publication date: October 21, 2021
    Inventors: Neelesh Nandkumar Sarawate, Jonathan Dwight Berry, Russell Pierson DeForest, Kevin Weston McMahan, Victor John Morgan, Ibrahim Klara Sezer, Deepak Trivedi
  • Patent number: 11047248
    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.
    Type: Grant
    Filed: June 19, 2018
    Date of Patent: June 29, 2021
    Assignee: General Electric Company
    Inventors: Neelesh Nandkumar Sarawate, Jonathan Dwight Berry, Russell Pierson DeForest, Kevin Weston McMahan, Victor John Morgan, Ibrahim Sezer, Deepak Trivedi
  • Publication number: 20210108528
    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.
    Type: Application
    Filed: October 10, 2019
    Publication date: April 15, 2021
    Inventors: Neelesh Nandkumar Sarawate, Christopher Walter Falcone
  • Patent number: 10934873
    Abstract: A turbine shroud is disposed between stages of stationary turbine nozzles. The turbine shroud includes arcuate shroud segments sealingly engaged with one another. Each shroud segment includes a bottom panel with a radially inner surface and a radially outer surface and opposite ends. Each end includes an end face, an end cutback face spaced from the end face, and an intermediate surface extending between the end face and the end cutback face to define a recess. One or more seals overlap the recess of a circumferentially adjacent pair of shroud segments to produce a sealed joint.
    Type: Grant
    Filed: November 7, 2018
    Date of Patent: March 2, 2021
    Assignee: General Electric Company
    Inventors: Neelesh Nandkumar Sarawate, Christopher Edward Wolfe, John Patrick Pollinger
  • Patent number: 10837299
    Abstract: A system may include a transition piece, coupled to a support of the system, to receive combustion products from a combustion chamber. The system may also include a turbine nozzle, coupled to a support of the system, to receive combustion products from the transition piece. Additionally, a web plate disposed at a radial position about a turbine axis between the transition piece and the turbine nozzle may form a first seal between the web plate and the transition piece and form a second seal between the web plate and the turbine nozzle. In addition, the web plate may extend in a circumferential direction about the turbine axis and couple to a support of the system. Further, the web plate may include an inner surface, an outer surface, and an arm extending in a radial direction between the inner surface and the outer surface.
    Type: Grant
    Filed: March 7, 2017
    Date of Patent: November 17, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Rahul Anil Bidkar, Neelesh Nandkumar Sarawate
  • Patent number: 10774665
    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.
    Type: Grant
    Filed: July 31, 2018
    Date of Patent: September 15, 2020
    Assignee: General Electric Company
    Inventors: John Ellington Greene, Neelesh Nandkumar Sarawate
  • Patent number: 10731494
    Abstract: Various embodiments include gas turbine seals and methods of forming such seals for advanced gas path (AGP) heat transfer designed gas turbine engines. In some cases, a turbine includes: a first arcuate component adjacent to a second arcuate component, each arcuate component formed of a ceramic matrix composite and including a seal slot located in an end face, each seal slot having a plurality of axial surfaces and radially facing surfaces extending from opposite ends of the axial surfaces and an overhanging seal assembly disposed in the seal slot. The overhanging seal assembly including an intersegment seal including a plurality of seal segments defining two vertical seal segments and a plurality of horizontal seal segments and a first overhanging positioner shim seal and a second overhanging positioner shim seal, each including an extended portion. The overhanging seal assembly disposed in the seal slot so as to provide position constrainment of the two vertical seal segments.
    Type: Grant
    Filed: October 20, 2016
    Date of Patent: August 4, 2020
    Assignee: General Electric Company
    Inventors: Bodhayan Dev, Neelesh Nandkumar Sarawate, Matthew Troy Hafner
  • Patent number: 10689994
    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.
    Type: Grant
    Filed: March 31, 2016
    Date of Patent: June 23, 2020
    Assignee: General Electric Company
    Inventors: Jason Edward Albert, Bodhayan Dev, Neelesh Nandkumar Sarawate, Michael John Brown
  • Patent number: 10683769
    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.
    Type: Grant
    Filed: August 26, 2016
    Date of Patent: June 16, 2020
    Assignee: General Electric Company
    Inventors: Neelesh Nandkumar Sarawate, Deepak Trivedi, Xiaoqing Zheng