Patents by Inventor Mayank Krisna Amble
Mayank Krisna Amble 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).
-
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
-
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
-
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
-
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
-
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
-
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
-
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
-
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
-
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
-
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
-
Patent number: 10323571Abstract: A method of heating a hollow structure and a heating system are provided. The system includes a plurality of hollow structures spaced circumferentially about an annular flow path. The hollow structures include a heating fluid inlet port, a first plurality of film heating apertures, and a second plurality of film heating apertures. The hollow structures also include a first internal passage extending between the heating fluid inlet port and the first plurality of film heating apertures. The first internal passage includes an impingement leg configured to channel a first flow of heating fluid to a leading edge of the hollow structure. A second internal passage extends between the heating fluid inlet port and the second plurality of film heating apertures through a path along an inner surface of the hollow structure before being channeled to the second plurality of film heating apertures.Type: GrantFiled: December 16, 2015Date of Patent: June 18, 2019Assignee: GENERAL ELECTRIC COMPANYInventors: Sesha Subramanian, Bhaskar Nanda Mondal, Sushilkumar Gulabrao Shevakari, Mayank Krisna Amble
-
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
-
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
-
Publication number: 20170175628Abstract: A method of heating a hollow structure and a heating system are provided. The system includes a plurality of hollow structures spaced circumferentially about an annular flow path. The hollow structures include a heating fluid inlet port, a first plurality of film heating apertures, and a second plurality of film heating apertures. The hollow structures also include a first internal passage extending between the heating fluid inlet port and the first plurality of film heating apertures. The first internal passage includes an impingement leg configured to channel a first flow of heating fluid to a leading edge of the hollow structure. A second internal passage extends between the heating fluid inlet port and the second plurality of film heating apertures through a path along an inner surface of the hollow structure before being channeled to the second plurality of film heating apertures.Type: ApplicationFiled: December 16, 2015Publication date: June 22, 2017Inventors: Sesha Subramanian, Bhaskar Nanda Mondal, Sushilkumar Gulabrao Shevakari, Mayank Krisna Amble