Patents by Inventor Perumallu Vukanti
Perumallu Vukanti 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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Publication number: 20220364510Abstract: A turbofan gas turbine engine configured to reduce hotspots within combustors. The engine includes an axis and a combustor that is circumferentially disposed about the axis. The combustor includes an annular combustor liner that includes a front portion and a rear portion. The annular combustor liner is joined to an annular combustor dome via front portion and defines a chamber and a nozzle is mounted within the annular combustor dome and is configured to inject fuel into a plurality of swirlers. At least one or more dilution openings is circumferentially distributed around the liner such that a region is fluidly connected through the annular combustor liner to the chamber. Each one of the pluralities of dilution openings includes an opening and a radial support wall that is positioned aft of the opening such that the radial support wall extends into the chamber.Type: ApplicationFiled: May 11, 2021Publication date: November 17, 2022Inventors: Gurunath Gandikota, Varun Lakshmanan, Perumallu Vukanti, Allen M. Danis, Michael A. Benjamin
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Patent number: 11415321Abstract: A method for regulating jet wakes in a combustor including: directing compressed fluid into a passageway between a casing and a combustor liner; directing a combustion gas along a combustion zone; discharging a first portion of compressed fluid from the passageway into the combustion zone via a first through-hole which is disposed on a section of a combustor panel in a first circumferential row; and discharging a second portion of the compressed fluid from the passageway into the combustion zone via second through-holes, wherein the second through-holes are disposed on a section of the panel, spaced apart axially and circumferentially, and adjacent to the first through-hole, wherein the second through-holes include a first set of through-holes and a second set of through-holes, the first set of through-holes in a second row and the second set of through-holes in a third row, wherein the second and third rows extend circumferentially.Type: GrantFiled: September 23, 2020Date of Patent: August 16, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Mayank Krisna Amble, Perumallu Vukanti, Steven Clayton Vise, Michael Anthony Benjamin
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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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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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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: 10890327Abstract: A gas turbine engine combustor includes a liner defining at least in part a combustion chamber, a first side exposed to the combustion chamber, a second side opposite the first side, and a dilution hole extending from the second side to the first side. The liner includes an airflow feature on the first side of the liner adjacent to the dilution hole and extending into the combustion chamber to increase a cooling of the liner.Type: GrantFiled: February 14, 2018Date of Patent: January 12, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Gurunath Gandikota, Hiranya Kumar Nath, Arvind Kumar Rao, Steven Clayton Vise, Perumallu Vukanti, Mayank Krisna Amble, Clayton Stuart Cooper
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Publication number: 20210003281Abstract: A method for regulating jet wakes in a combustor including: directing compressed fluid into a passageway between a casing and a combustor liner; directing a combustion gas along a combustion zone; discharging a first portion of compressed fluid from the passageway into the combustion zone via a first through-hole which is disposed on a section of a combustor panel in a first circumferential row; and discharging a second portion of the compressed fluid from the passageway into the combustion zone via second through-holes, wherein the second through-holes are disposed on a section of the panel, spaced apart axially and circumferentially, and adjacent to the first through-hole, wherein the second through-holes include a first set of through-holes and a second set of through-holes, the first set of through-holes in a second row and the second set of through-holes in a third row, wherein the second and third rows extend circumferentially.Type: ApplicationFiled: September 23, 2020Publication date: January 7, 2021Inventors: Mayank Krisna Amble, Perumallu Vukanti, Steven Clayton Vise, Michael Anthony Benjamin
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Patent number: 10816202Abstract: A combustor liner, a gas turbine engine including a combustor having the combustor liner, and a method for regulating jet wakes in the combustor are disclosed. The combustor liner includes a panel, at least one first through-hole, and a plurality of second through-holes including first and second set of through-holes. The at least one first through-hole is disposed on a section of the panel in a first row. The plurality of second through-holes is disposed on the section along axial and circumferential directions and arranged adjacent to the at least one first through-hole. The first set and the second set of through-holes are arranged in a second row and a third row respectively. The first, second, and third rows extend along the circumferential direction. The at least one first through-hole and the plurality of second through-holes collectively cover circumferential plane of the section along the first, second, and third rows.Type: GrantFiled: November 28, 2017Date of Patent: October 27, 2020Assignee: General Electric CompanyInventors: Mayank Krisna Amble, Perumallu Vukanti, Steven Clayton Vise, Michael Anthony Benjamin
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Patent number: 10801726Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes a deflector wall, an annular axial wall, and an annular shroud. The deflector wall is extended at least partially along a radial direction and a circumferential direction relative to an axial centerline and adjacent to a combustion chamber. A fuel nozzle opening is defined through the deflector wall, and a nozzle centerline is extended through the fuel nozzle opening along a lengthwise direction. The annular axial wall is coupled to the deflector wall and extended through the fuel nozzle opening. The axial wall is defined around the nozzle centerline. The annular shroud is defined around the nozzle centerline and extended co-directional to the axial wall. The axial wall and the annular shroud are each coupled to a radial wall defined upstream of the deflector wall. The annular shroud, the axial wall, and the radial wall together define a cooling plenum therebetween.Type: GrantFiled: September 21, 2017Date of Patent: October 13, 2020Assignee: General Electric CompanyInventors: Eric John Stevens, Allen Michael Danis, Ravi Chandra, Jayanth Sekar, Perumallu Vukanti
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Publication number: 20200248903Abstract: 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: ApplicationFiled: February 1, 2019Publication date: August 6, 2020Inventors: Karthikeyan Sampath, Saket Singh, Gurunath Gandikota, Perumallu Vukanti, Pradeep Naik, Steven Clayton Vise
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Publication number: 20200049349Abstract: 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: ApplicationFiled: August 7, 2018Publication date: February 13, 2020Inventors: Mayank Krisna Amble, Gurunath Gandikota, Perumallu Vukanti, Ravi Chandra, Karthikeyan Sampath
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Publication number: 20200041127Abstract: 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. The liner includes a walled chute disposed at least partially within the opening. The walled chute defines an inner surface at least partially defining a jet destabilizer.Type: ApplicationFiled: August 1, 2018Publication date: February 6, 2020Inventors: Perumallu Vukanti, Hiranya Kumar Nath, Jayanth Sekar, Arthur Wesley Johnson, Gurunath Gandikota, Mayank Krisna Amble, Clayton Stuart Cooper
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Publication number: 20190249874Abstract: A gas turbine engine combustor includes a liner defining at least in part a combustion chamber, a first side exposed to the combustion chamber, a second side opposite the first side, and a dilution hole extending from the second side to the first side. The liner includes an airflow feature on the first side of the liner adjacent to the dilution hole and extending into the combustion chamber to increase a cooling of the liner.Type: ApplicationFiled: February 14, 2018Publication date: August 15, 2019Inventors: Gurunath Gandikota, Hiranya Kumar Nath, Arvind Kumar Rao, Steven Clayton Vise, Perumallu Vukanti, Mayank Krisna Amble, Clayton Stuart Cooper
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Publication number: 20190162413Abstract: A combustor liner, a gas turbine engine including a combustor having the combustor liner, and a method for regulating jet wakes in the combustor are disclosed. The combustor liner includes a panel, at least one first through-hole, and a plurality of second through-holes including first and second set of through-holes. The at least one first through-hole is disposed on a section of the panel in a first row. The plurality of second through-holes is disposed on the section along axial and circumferential directions and arranged adjacent to the at least one first through-hole. The first set and the second set of through-holes are arranged in a second row and a third row respectively. The first, second, and third rows extend along the circumferential direction. The at least one first through-hole and the plurality of second through-holes collectively cover circumferential plane of the section along the first, second, and third rows.Type: ApplicationFiled: November 28, 2017Publication date: May 30, 2019Inventors: Mayank Krisna Amble, Perumallu Vukanti, Steven Clayton Vise, Michael Anthony Benjamin
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Publication number: 20190085767Abstract: 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: ApplicationFiled: September 15, 2017Publication date: March 21, 2019Inventors: Steven Clayton Vise, Allen Michael Danis, Jayanth Sekar, Pradeep Naik, Perumallu Vukanti, Arthur Wesley Johnson, Clayton Stuart Cooper, Karthikeyan Sampath
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Publication number: 20190086088Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes a deflector wall, an annular axial wall, and an annular shroud. The deflector wall is extended at least partially along a radial direction and a circumferential direction relative to an axial centerline and adjacent to a combustion chamber. A fuel nozzle opening is defined through the deflector wall, and a nozzle centerline is extended through the fuel nozzle opening along a lengthwise direction. The annular axial wall is coupled to the deflector wall and extended through the fuel nozzle opening. The axial wall is defined around the nozzle centerline. The annular shroud is defined around the nozzle centerline and extended co-directional to the axial wall. The axial wall and the annular shroud are each coupled to a radial wall defined upstream of the deflector wall. The annular shroud, the axial wall, and the radial wall together define a cooling plenum therebetween.Type: ApplicationFiled: September 21, 2017Publication date: March 21, 2019Inventors: Eric John Stevens, Allen Michael Danis, Ravi Chandra, Jayanth Sekar, Perumallu Vukanti
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Publication number: 20190024895Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes an inner liner and an outer liner together defining a combustion chamber therebetween and a pressure plenum surrounding the inner liner and the outer liner. One or more of the inner liner and the outer liner defines one or more openings. The one or more liners includes a walled chute disposed at least partially within the opening. A structural member extends from the one or more liners to the walled chute.Type: ApplicationFiled: July 18, 2017Publication date: January 24, 2019Inventors: Richard Wade Stickles, Clayton Stuart Cooper, Perumallu Vukanti, Mayank Krisna Amble