Patents by Inventor Ganesh Seshadri
Ganesh Seshadri 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: 20230296024Abstract: Aerodynamically mistuned airfoils for unsteady loss reductions are disclosed herein. An example apparatus disclosed herein includes a disk, a first airfoil coupled to the disk, the first airfoil having a first geometry, and a second airfoil coupled to the disk adjacent to the first airfoil, the second airfoil having a second geometry different than the first geometry, the first airfoil and the second airfoil produce non-uniform wake passing times during operation of the disk.Type: ApplicationFiled: September 23, 2022Publication date: September 21, 2023Inventors: Francesco Bertini, Davide Torzo, Pratish Patil, John Joseph, Mahendran Manoharan, Ganesh Seshadri
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Patent number: 11401835Abstract: An apparatus and method for diffusing an airflow in a turbine engine can include a turbine center frame positioned between a high pressure turbine and a low pressure turbine of a turbine section of the engine. The turbine center frame can include two or more diffusion sections for diffusing the airflow. A stabilization section can be provided between the two or more diffusion sections to stabilize the airflow.Type: GrantFiled: June 12, 2017Date of Patent: August 2, 2022Assignee: General Electric CompanyInventors: Chaitanya Venkata Rama Krishna Ongole, John Joseph, Ganesh Seshadri, Ravikanth Avancha
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Patent number: 11274563Abstract: A turbine rear frame for a gas turbine engine comprises a plurality of struts disposed between an outer ring and an inner ring. The struts can be mounted adjacent to one or more mount surfaces defined within the outer ring. The mount surface can comprise a recess in the outer ring having a maximum radial distance upstream of engine mounts inserted therein. The struts can further comprise a pitch angle offset from a centerline of the mount surface and a tangentially curved trailing edge at a tip to improve aerodynamic performance of the turbine rear frame.Type: GrantFiled: January 21, 2016Date of Patent: March 15, 2022Assignee: General Electric CompanyInventors: Mohsin Hasan Khan, Sarasija Sudharsan, Ganesh Seshadri, Ravikanth Avancha, Lyle Douglas Dailey
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Patent number: 10982554Abstract: A turbine engine with a tip shroud and method for shaping the tip shroud where at least one pair of airfoils including a first and second airfoil each having an outer wall bounding an interior. Each airfoil extending between a pressure side and a suction side to define a circumferential direction and extending between a leading edge and a trailing edge to define an axial direction. Each airfoil extending between a root and a tip to define a radial direction. The first and second airfoils are circumferentially spaced to define an inlet between the leading edges and an outlet between the trailing edges where each airfoil is coupled to an inner platform at the root. A tip shroud circumscribing the airfoil operably coupled to the tip extending in the axial direction between axially spaced first and second planes where the tip shroud includes at least one scalloped portion.Type: GrantFiled: October 27, 2017Date of Patent: April 20, 2021Assignee: General Electric CompanyInventors: Ganesh Seshadri, Pranav Kamat, Mahendran Manoharan, Dhananjaya Gottapu, Ravikanth Avancha
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Publication number: 20210079795Abstract: A turbine engine with a tip shroud and method for shaping the tip shroud where at least one pair of airfoils including a first and second airfoil each having an outer wall bounding an interior. Each airfoil extending between a pressure side and a suction side to define a circumferential direction and extending between a leading edge and a trailing edge to define an axial direction. Each airfoil extending between a root and a tip to define a radial direction. The first and second airfoils are circumferentially spaced to define an inlet between the leading edges and an outlet between the trailing edges where each airfoil is coupled to an inner platform at the root. A tip shroud circumscribing the airfoil operably coupled to the tip extending in the axial direction between axially spaced first and second planes where the tip shroud includes at least one scalloped portion.Type: ApplicationFiled: October 27, 2017Publication date: March 18, 2021Inventors: Ganesh SESHADRI, Pranav KAMAT, Mahendran MANOHARAN, Dhananjaya GOTTAPU, Ravikanth AVANCHA
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Patent number: 10815811Abstract: A rotatable component for a turbomachine and a method for regulating a circumferential ingress of a fluid at a trailing edge of the rotatable component are disclosed. The rotatable component includes an airfoil and a mechanical component. The airfoil includes a pressure side and a suction side. The mechanical component is coupled to the airfoil and includes a forward overhanging portion, and an aft overhanging portion. The forward overhanging portion is disposed at a leading edge of the airfoil and extends longitudinally beyond the leading edge. The aft overhanging portion is disposed at a trailing edge of the airfoil and extends longitudinally beyond the trailing edge, where both the forward and aft overhanging portions further extend circumferentially along the pressure side and the suction side of the airfoil. The aft overhanging portion includes a non-axisymmetric profile for regulating the circumferential ingress of the fluid from the pressure to suction sides.Type: GrantFiled: November 28, 2017Date of Patent: October 27, 2020Assignee: General Electric CompanyInventors: Ganesh Seshadri, Mahendran Manoharan
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Patent number: 10815824Abstract: A gas turbine engine, system, and method of severing at least one blade of a row of blades spaced about a rotor during an over speed condition are provided. The gas turbine engine includes a shaft rotatable about an axis of the shaft, a rotor coupled to the shaft and having a radially outer surface, and one or more rows of blades spaced axially along the outer portion. Each row of blades includes a plurality of blades spaced circumferentially around the radially outer surface. A gas turbine engine casing at least partially surrounds the one or more rows of blades. One or more rows of stationary vanes are spaced axially along the casing. Each row of stationary vanes includes a plurality of stationary vanes extending radially between the shaft and the gas turbine engine casing. The stationary vanes are coupled to the gas turbine engine casing using a fuse element.Type: GrantFiled: April 4, 2017Date of Patent: October 27, 2020Assignee: General ElectricInventors: Sanjeev Sai Kumar Manepalli, Monty Lee Shelton, Ganesh Seshadri, Mahendran Manoharan
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Publication number: 20200049014Abstract: A turbomachinery apparatus (10) includes: a turbine (22), including: a turbine component (36) defining at least one arcuate flowpath surface (40); an array of axial-flow turbine airfoils (46) extending from the flowpath surface, the turbine airfoils defining spaces therebetween; and a plurality of splitter airfoils (146) extending from the at least one flowpath surface, in the spaces between the turbine airfoils, each splitter airfoil having opposed pressure and suction sides extending between a leading edge and a trailing edge, wherein the splitter airfoils have a thickness ratio which is less than a thickness ratio of the turbine airfoils.Type: ApplicationFiled: March 6, 2018Publication date: February 13, 2020Inventors: Jeffrey Donald Clements, Paul Hadley Vitt, Francesco Bertini, Aspi Rustom Wadia, Ganesh Seshadri, Mahendran Manoharan, Ravikanth Avancha
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Publication number: 20190162074Abstract: A rotatable component for a turbomachine and a method for regulating a circumferential ingress of a fluid at a trailing edge of the rotatable component are disclosed. The rotatable component includes an airfoil and a mechanical component. The airfoil includes a pressure side and a suction side. The mechanical component is coupled to the airfoil and includes a forward overhanging portion, and an aft overhanging portion. The forward overhanging portion is disposed at a leading edge of the airfoil and extends longitudinally beyond the leading edge. The aft overhanging portion is disposed at a trailing edge of the airfoil and extends longitudinally beyond the trailing edge, where both the forward and aft overhanging portions further extend circumferentially along the pressure side and the suction side of the airfoil. The aft overhanging portion includes a non-axisymmetric profile for regulating the circumferential ingress of the fluid from the pressure to suction sides.Type: ApplicationFiled: November 28, 2017Publication date: May 30, 2019Inventors: Ganesh Seshadri, Mahendran Manoharan
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Publication number: 20180355763Abstract: An apparatus and method for diffusing an airflow in a turbine engine can include a turbine center frame positioned between a high pressure turbine and a low pressure turbine of a turbine section of the engine. The turbine center frame can include two or more diffusion sections for diffusing the airflow. A stabilization section can be provided between the two or more diffusion sections to stabilize the airflow.Type: ApplicationFiled: June 12, 2017Publication date: December 13, 2018Inventors: Chaitanya Venkata Rama Krishna Ongole, John Joseph, Ganesh Seshadri, Ravikanth Avancha
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Publication number: 20180347403Abstract: An apparatus and method for a turbine engine comprising an outer casing having a first surface and defining an axial centerline and an inner casing located within the outer casing and having a second surface spaced. The first and second surfaces are spaced from each other and define an annular channel between where a combustion air flows in a fore to aft direction along a profile.Type: ApplicationFiled: May 31, 2017Publication date: December 6, 2018Inventors: Mahendran Manoharan, Ganesh Seshadri, Robert J. Beacock, Lyle Douglas Dailey, Ravikanth Avancha
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Publication number: 20180283203Abstract: A gas turbine engine, system, and method of severing at least one blade of a row of blades spaced about a rotor during an over speed condition are provided. The gas turbine engine includes a shaft rotatable about an axis of the shaft, a rotor coupled to the shaft and having a radially outer surface, and one or more rows of blades spaced axially along the outer portion. Each row of blades includes a plurality of blades spaced circumferentially around the radially outer surface. A gas turbine engine casing at least partially surrounds the one or more rows of blades. One or more rows of stationary vanes are spaced axially along the casing. Each row of stationary vanes includes a plurality of stationary vanes extending radially between the shaft and the gas turbine engine casing. The stationary vanes are coupled to the gas turbine engine casing using a fuse element.Type: ApplicationFiled: April 4, 2017Publication date: October 4, 2018Inventors: Sanjeev Sai Kumar Manepalli, Monty Lee Shelton, Ganesh Seshadri, Mahendran Manoharan
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Publication number: 20180156124Abstract: A frame apparatus for a turbine engine includes: a turbomachinery stage discharging into a downstream flowpath, the stage including a rotor carrying an array of axial-flow rotor airfoils; and a frame disposed downstream of the turbomachinery stage, the frame including: a support structure comprising at least one of a hub and an annular casing; an annular array of stationary struts carried by the support structure, each strut having an airfoil shape with spaced-apart pressure and suction sides extending between a leading edge and a trailing edge thereof, the stationary struts defining spaces therebetween; and the stationary struts defining spaces therebetween; and a plurality of splitters carried by the support structure, the splitters positioned in the spaces between the stationary struts, wherein at least one of a chord dimension of the splitters and a span dimension of the splitters is less than the corresponding dimension of the stationary struts.Type: ApplicationFiled: December 1, 2016Publication date: June 7, 2018Inventors: Jeffrey Donald Clements, Ganesh Seshadri, Mahendran Manoharan, Ravikanth Avancha, Aspi Rustom Wadia
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Publication number: 20170211399Abstract: A turbine rear frame for a gas turbine engine comprises a plurality of struts disposed between an outer ring and an inner ring. The struts can be mounted adjacent to one or more mount surfaces defined within the outer ring. The mount surface can comprise a recess in the outer ring having a maximum radial distance upstream of engine mounts inserted therein. The struts can further comprise a pitch angle offset from a centerline of the mount surface and a tangentially curved trailing edge at a tip to improve aerodynamic performance of the turbine rear frame.Type: ApplicationFiled: January 21, 2016Publication date: July 27, 2017Inventors: Mohsin Hasan Khan, Sarasija Sudharsan, Ganesh Seshadri, Ravikanth Avancha, Lyle Douglas Dailey