Patents by Inventor Karthikeyan Sampath
Karthikeyan Sampath 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).
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Patent number: 11692708Abstract: A combustor liner for a gas turbine includes a liner that at least partially defines a combustion chamber, and that a plurality of dilution openings therethrough. Each dilution opening includes an outer wall defining an outer perimeter of the dilution opening and defining a dilution opening centerline axis through the dilution opening. A plurality of swirl vanes extend from the outer wall into a dilution airflow passage that extends through the dilution opening. Each of the plurality of swirl vanes extends from the outer wall into the dilution airflow passage at a respective swirl vane angle with respect to the outer wall. The plurality of swirl vanes are arranged in a successive arrangement about the outer wall, and successive respective ones of the plurality of swirl vanes extend from the outer wall at a different swirl vane angle.Type: GrantFiled: June 28, 2022Date of Patent: July 4, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Karthikeyan Sampath, Perumallu Vukanti, Ajoy Patra, Pradeep Naik, Hiranya Nath
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Patent number: 11635209Abstract: A swirler assembly includes a swirler having a primary swirler and a secondary swirler, and a flare connected the secondary swirler, and a dome disposed radially outward of the flare. A flare oxidizer flow passage is defined by a flare outer surface and a dome inner surface, and the flare oxidizer flow passage includes a swirl inducing member therewithin that induces a swirled flow of an oxidizer passing through the flare oxidizer flow passage into a combustion chamber.Type: GrantFiled: January 27, 2022Date of Patent: April 25, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Perumallu Vukanti, Pradeep Naik, Sripathi Mohan, Karthikeyan Sampath, Steven C. Vise, Shai Birmaher, Saket Singh
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Publication number: 20230053389Abstract: A swirler assembly includes a swirler having a primary swirler and a secondary swirler, and a flare connected the secondary swirler, and a dome disposed radially outward of the flare. A flare oxidizer flow passage is defined by a flare outer surface and a dome inner surface, and the flare oxidizer flow passage includes a swirl inducing member therewithin that induces a swirled flow of an oxidizer passing through the flare oxidizer flow passage into a combustion chamber.Type: ApplicationFiled: January 27, 2022Publication date: February 23, 2023Inventors: Perumallu Vukanti, Pradeep Naik, Sripathi Mohan, Karthikeyan Sampath, Steven C. Vise, Shai Birmaher, Saket Singh
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Publication number: 20230042970Abstract: A dome assembly for a combustor includes: at least one swirler assembly including: at least one swirler including a plurality of swirl vanes arrayed about an axis, the plurality of swirl vanes oriented so as to impart a tangential velocity to air passing through the swirler parallel to the axis; each of the plurality of swirl vanes having a thickness and including a plurality of edges which collectively define a peripheral boundary of the respective swirl vane; wherein at least a selected one of the plurality of swirl vanes includes at least one void passing through the thickness of the selected swirl vane, the void disposed within the peripheral boundary of the selected swirl vane.Type: ApplicationFiled: August 5, 2021Publication date: February 9, 2023Inventors: Gurunath Gandikota, Karthikeyan Sampath, Perumallu Vukanti, Allen M. Danis, Scott M. Bush, Steven Clayton Vise, Hari Ravi Chandra, Rimple Rangrej, Saket Singh, Pradeep Naik, Neeraj Kumar Mishra, Arvind Kumar Rao, Balasubramaniam Venkatanarayanan, Ranjeet Kumar Mishra
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Publication number: 20220412550Abstract: A swirler-ferrule assembly includes a radial swirler, a ferrule, a fuel nozzle, and a surface feature. The radial swirler includes a primary swirler vane having a primary air passage and a secondary swirler vane having a secondary air passage. The ferrule may be connected to the radial swirler. The surface feature may be located on the primary swirler vane and/or the ferrule. The surface feature may be configured to direct an air flow through the primary air passage away from a recirculation zone located upstream of the primary swirler vane. The surface feature has a trailing end and a distal end, and the fuel nozzle is axially aligned with the trailing end of the surface feature or is located axially downstream of the trailing end of the surface feature. The surface feature may have a plurality of grooves.Type: ApplicationFiled: August 6, 2021Publication date: December 29, 2022Inventors: Steven C. Vise, Clayton S. Cooper, Michael A. Benjamin, Pradeep Naik, Kwanwoo Kim, Shai Birmaher, Perumallu Vukanti, Saket Singh, Karthikeyan Sampath
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Publication number: 20220390111Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber, the liner further defining a gap; and an intermediate member disposed at least partially within the gap of the liner and in fluid communication with the combustion chamber, wherein the intermediate member is retained at a relatively fixed position with respect to the liner by a support extending between the intermediate member and a case of the gas turbine engine.Type: ApplicationFiled: June 7, 2021Publication date: December 8, 2022Inventors: Ravindra Shankar Ganiger, Hiranya Kumar Nath, Daniel J. Kirtley, Shai Birmaher, Veeraraju Vanapalli, Karthikeyan Sampath, Deepak Ghiya, Perumallu Vukanti, Rajendra Mahadeorao Wankhade, Pradeep Naik
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Publication number: 20220390115Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.Type: ApplicationFiled: June 7, 2021Publication date: December 8, 2022Inventors: Karthikeyan Sampath, Pradeep Naik, Veeraraju Vanapalli, Perumallu Vukanti, Shai Birmaher, Daniel J. Kirtley, Deepak Ghiya, Rimple Rakeshkumar Rangrej, Saket Singh, Ravindra Shankar Ganiger, Hiranya Kumar Nath, Michael Anthony Benjamin, Rajendra Mahadeorao Wankhade
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Publication number: 20220390112Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber, the liner including a dilution slot in fluid communication with the combustion chamber; and one or more guides configured to redirect cooling medium into the dilution slot.Type: ApplicationFiled: June 7, 2021Publication date: December 8, 2022Inventors: Ravindra Shankar Ganiger, Hiranya Kumar Nath, Perumallu Vukanti, Daniel J. Kirtley, Karthikeyan Sampath, Shai Birmaher, Pradeep Naik, Rajendra Mahadeorao Wankhade, Michael Anthony Benjamin, Veeraraju Vanapalli, Deepak Ghiya
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Publication number: 20220390114Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; and an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber, wherein the forward and aft liner segments are coupled together at a moveable interface.Type: ApplicationFiled: June 7, 2021Publication date: December 8, 2022Inventors: Ravindra Shankar Ganiger, Hiranya Kumar Nath, Daniel J. Kirtley, Shai Birmaher, Veeraraju Vanapalli, Karthikeyan Sampath, Deepak Ghiya, Perumallu Vukanti, Rajendra Mahadeorao Wankhade, Pradeep Naik, Rimple Rakeshkumar Rangrej, Saket Singh
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Patent number: 11384937Abstract: A swirler with integrated damper may include a primary swirler vane having a primary air passage, a secondary swirler vane having a secondary air passage, and a damper within the primary swirler vane, the secondary swirler vane, or both the primary swirler vane and the secondary swirler vane. The damper may include a series of cavities. The damper is configured to absorb one or more frequencies present in an air flow through the primary air passage, the secondary air passage, or both the primary air passage and the secondary air passage.Type: GrantFiled: May 12, 2021Date of Patent: July 12, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Karthikeyan Sampath, Ugandhar K. Reddy, Steven C. Vise, Allen M. Danis, Kwanwoo Kim, Ranganatha Narasimha Chiranthan
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Patent number: 11280495Abstract: A flow device for a combustor assembly defining a longitudinal axis around which the flow device is positioned is provided. The flow device includes a body extended around the longitudinal axis. The body includes a first wall and a second wall separated longitudinally from one another along the longitudinal axis. A fuel injector passage is defined through the body coaxial to the longitudinal axis. A plurality of vane walls is extended radially between the first wall and the second wall relative to the longitudinal axis. A radial flow passage is extended between the plurality of vane walls and the fuel injector passage.Type: GrantFiled: March 4, 2020Date of Patent: March 22, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Gurunath Gandikota, Steven Clayton Vise, Perumallu Vukanti, Mayank Krisna Amble, Clayton Stuart Cooper, Nicholas Ryan Overman, Karthikeyan Sampath, Allen Michael Danis, Craig Douglas Young
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Patent number: 11268438Abstract: An apparatus and method for a combustor, the combustor including combustor liner having a plurality of dilution openings. The combustor receives a flow of fuel that is ignited and mixed with dilution air to form a flow of combustion gases. The flow of combustion gases travels through the combustor to a turbine section of an engine.Type: GrantFiled: September 15, 2017Date of Patent: March 8, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Steven Clayton Vise, Allen Michael Danis, Jayanth Sekar, Pradeep Naik, Perumallu Vukanti, Arthur Wesley Johnson, Clayton Stuart Cooper, Karthikeyan Sampath
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Patent number: 11255543Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes a liner defining a combustion chamber therewithin and a pressure plenum surrounding the liner. The liner defines an opening and includes a walled chute disposed at least partially through the opening. A plurality of flow openings is defined through the walled chute.Type: GrantFiled: August 7, 2018Date of Patent: February 22, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Mayank Krisna Amble, Gurunath Gandikota, Perumallu Vukanti, Ravi Chandra, Karthikeyan Sampath
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Publication number: 20220026068Abstract: A method and structure for operating a combustion system of a gas turbine engine to mitigate low frequency combustion acoustics is generally provided. The method includes flowing an oxidizer through a fuel nozzle passage defining an inner wall and an outer wall, in which each of the inner wall and the outer wall are contoured from a first radius to a second radius smaller than the first radius; flowing the oxidizer at a higher axial velocity at the inner wall relative to the outer wall upstream of a fuel injection port; flowing a fuel through the fuel injection port to the fuel nozzle passage to mix with the flow of oxidizer to produce a fuel-oxidizer mixture; and igniting the fuel-oxidizer mixture downstream of the fuel injection port.Type: ApplicationFiled: October 8, 2021Publication date: January 27, 2022Inventors: Michael Anthony Benjamin, Girish Venkata Satya Sesha Goda, Habeeb Kunnummal Manat, Karthikeyan Sampath
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Patent number: 11226101Abstract: A gas turbine engine swirler that includes a tubular body having a forward face, an aft end, and a throat. A plurality of primary swirl vanes that is positioned between the aft end and the forward face. A plurality of secondary swirl vanes that is positioned between the primary swirl vanes and the aft end. The plurality of primary swirl vanes and the plurality of secondary swirl vanes are configured such that the throat is fluidly connected to a plenum that is positioned outside of the tubular body. A tubular ferrule is positioned such that it joins the body at the forward face thereof. Each of the primary swirl vanes extend radially inwardly to a vane lip. The secondary swirl vanes extend radially inwardly for swirling air therefrom. The body also includes a tubular Venturi that extends aft from between the primary swirler vanes and the secondary swirler vanes for radially separating air swirled therefrom.Type: GrantFiled: February 1, 2019Date of Patent: January 18, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Karthikeyan Sampath, Saket Singh, Gurunath Gandikota, Perumallu Vukanti, Pradeep Naik, Steven Clayton Vise
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Patent number: 11193720Abstract: A gas turbine engine having a heat absorption device and an associated method are disclosed. The gas turbine engine includes a compressor having a compressor discharge nozzle, a combustor coupled to the compressor, a turbine coupled to the combustor and the compressor, a fluid flow passage fluidly coupling the compressor and the turbine and bypassing the combustor, and a heat absorption device disposed fluidly along the fluid flow passage at a first predefined location. The heat absorption device includes a casing having an inlet and an outlet, a flow path within the casing and extending between the inlet and the outlet, wherein the flow path directs an input bleed flow diverted from a fluid stream discharged from the compressor, and a phase change material hermetically sealed within the casing. The phase change material is separated from the flow path.Type: GrantFiled: March 24, 2020Date of Patent: December 7, 2021Assignee: General Electric CompanyInventors: Karthikeyan Sampath, Atanu Saha, Bhaskar Nanda Mondal, Sanjeev Sai Kumar Manepalli
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Patent number: 11175045Abstract: A method and structure for operating a combustion system of a gas turbine engine to mitigate low frequency combustion acoustics is generally provided. The method includes flowing an oxidizer through a fuel nozzle passage defining an inner wall and an outer wall, in which each of the inner wall and the outer wall are contoured from a first radius to a second radius smaller than the first radius; flowing the oxidizer at a higher axial velocity at the inner wall relative to the outer wall upstream of a fuel injection port; flowing a fuel through the fuel injection port to the fuel nozzle passage to mix with the flow of oxidizer to produce a fuel-oxidizer mixture; and igniting the fuel-oxidizer mixture downstream of the fuel injection port.Type: GrantFiled: January 4, 2018Date of Patent: November 16, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Michael Anthony Benjamin, Girish Venkata Satya Sesha Goda, Habeeb Kunnummal Manat, Karthikeyan Sampath
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Publication number: 20210278085Abstract: A flow device for a combustor assembly defining a longitudinal axis around which the flow device is positioned is provided. The flow device includes a body extended around the longitudinal axis. The body includes a first wall and a second wall separated longitudinally from one another along the longitudinal axis. A fuel injector passage is defined through the body coaxial to the longitudinal axis. A plurality of vane walls is extended radially between the first wall and the second wall relative to the longitudinal axis. A radial flow passage is extended between the plurality of vane walls and the fuel injector passage.Type: ApplicationFiled: March 4, 2020Publication date: September 9, 2021Inventors: Gurunath Gandikota, Steven Clayton Vise, Perumallu Vukanti, Mayank Krisna Amble, Clayton Stuart Cooper, Nicholas Ryan Overman, Karthikeyan Sampath, Allen Michael Danis, Craig Douglas Young
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Patent number: 11029029Abstract: A fuel injector heat exchanger assembly is provided, in which the fuel injector assembly includes a body defining an outer surface and an inner surface. The body includes a plurality of walls in concentric arrangement. The plurality of walls defines a plurality of passages including a first passage surrounded by a second passage, and a third passage surrounding the second passage. Each passage is fluidly segregated from one another by the plurality of walls. A first conduit wall is defined through the body from the outer surface. The first conduit wall defines a first conduit in fluid communication with the second passage. The first conduit wall fluidly segregates the first conduit from the third passage. The first conduit is configured to admit a flow of fluid from outside the fuel injector into the second passage.Type: GrantFiled: January 3, 2019Date of Patent: June 8, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Varun Swaminathan Lakshmanan, Michael Anthony Benjamin, Veeraraju Vanapalli, Karthikeyan Sampath
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Patent number: 10989411Abstract: A turbo machine including a heat exchanger flowpath is generally provided. The turbo machine includes an outer casing extended along an axial direction, a prediffuser defining an inlet passage into a combustion section of the turbo machine, an inner casing extended from the prediffuser, in which a diffuser cavity is defined between the outer casing and the inner casing, a first plenum wall extended outward along a radial direction from the prediffuser, and a second plenum wall extended outward along a radial direction from the prediffuser. The second plenum wall is separated along the axial direction from the first plenum wall. A plenum is defined between the first plenum wall and the second plenum wall. The turbo machine includes a heat exchanger including a first conduit in fluid communication with the diffuser cavity. The first conduit is in fluid communication with a passage, and a second conduit in fluid communication with the passage and the plenum.Type: GrantFiled: January 3, 2019Date of Patent: April 27, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Karthikeyan Sampath, Varun Swaminathan Lakshmanan, Michael Anthony Benjamin, Veeraraju Vanapalli