Patents by Inventor Mahendran Manoharan

Mahendran Manoharan 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: 11933193
    Abstract: A gas turbine engine comprising a set of circumferentially adjacent airfoils, the airfoils having an outer wall defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a stream-wise direction, and between a root and a tip to define a span-wise direction, and a set of dimples provide on the outer wall of at least one of the airfoils, the set of dimples spaced in at least one of the stream-wise or span-wise directions.
    Type: Grant
    Filed: November 18, 2021
    Date of Patent: March 19, 2024
    Assignees: GE Avio S.r.l., General Electric Company
    Inventors: Pratish Patil, Amit Goyal, Mahendran Manoharan, Francesco Bertini, Jaikumar Loganathan
  • Publication number: 20230296024
    Abstract: 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: Application
    Filed: September 23, 2022
    Publication date: September 21, 2023
    Inventors: Francesco Bertini, Davide Torzo, Pratish Patil, John Joseph, Mahendran Manoharan, Ganesh Seshadri
  • Publication number: 20220220854
    Abstract: A gas turbine engine comprising a set of circumferentially adjacent airfoils, the airfoils having an outer wall defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a stream-wise direction, and between a root and a tip to define a span-wise direction, and a set of dimples provide on the outer wall of at least one of the airfoils, the set of dimples spaced in at least one of the stream-wise or span-wise directions.
    Type: Application
    Filed: November 18, 2021
    Publication date: July 14, 2022
    Inventors: Pratish Patil, Amit Goyal, Mahendran Manoharan, Francesco Bertini, Jaikumar Loganathan
  • Patent number: 10982554
    Abstract: 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: Grant
    Filed: October 27, 2017
    Date of Patent: April 20, 2021
    Assignee: General Electric Company
    Inventors: Ganesh Seshadri, Pranav Kamat, Mahendran Manoharan, Dhananjaya Gottapu, Ravikanth Avancha
  • Publication number: 20210079795
    Abstract: 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: Application
    Filed: October 27, 2017
    Publication date: March 18, 2021
    Inventors: Ganesh SESHADRI, Pranav KAMAT, Mahendran MANOHARAN, Dhananjaya GOTTAPU, Ravikanth AVANCHA
  • Patent number: 10815811
    Abstract: 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: Grant
    Filed: November 28, 2017
    Date of Patent: October 27, 2020
    Assignee: General Electric Company
    Inventors: Ganesh Seshadri, Mahendran Manoharan
  • Patent number: 10815824
    Abstract: 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: Grant
    Filed: April 4, 2017
    Date of Patent: October 27, 2020
    Assignee: General Electric
    Inventors: Sanjeev Sai Kumar Manepalli, Monty Lee Shelton, Ganesh Seshadri, Mahendran Manoharan
  • Publication number: 20200049014
    Abstract: 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: Application
    Filed: March 6, 2018
    Publication date: February 13, 2020
    Inventors: Jeffrey Donald Clements, Paul Hadley Vitt, Francesco Bertini, Aspi Rustom Wadia, Ganesh Seshadri, Mahendran Manoharan, Ravikanth Avancha
  • Publication number: 20190284946
    Abstract: An inter-stage seal assembly includes annular seal land mounted inwardly of and to seal support ring and pre-swirlers in purge duct extending through land. Purge duct may be bounded by spaced apart duct walls and pre-swirlers include turning vanes in outer exhaust section. Purge duct may include plurality of enclosed purge passages circumferentially disposed around engine centerline and pre-swirlers include curved section in passages. Seal land may be bifurcated having forward and aft seal land sections and purge duct may include purge duct inlet located therebetween. Seal support ring may include flange attached to or integrally and monolithically formed with inner platform attached to nozzle vanes extending across turbine flowpath and exhaust section may be flush with platform. Labyrinth seal teeth mounted to turbine rotor may engage land, purge duct may extend between annular inlets and outlets, inlet may be between adjacent couple of seal teeth.
    Type: Application
    Filed: March 6, 2019
    Publication date: September 19, 2019
    Inventors: Tomasz Edward Berdowski, Artur Miroslaw Malek, Marcin Piotr Rykala, Adam Kiciak, Mahendran Manoharan, Zbigniew Michal Schabowski, Marcin Kawalkowski
  • Publication number: 20190162074
    Abstract: 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: Application
    Filed: November 28, 2017
    Publication date: May 30, 2019
    Inventors: Ganesh Seshadri, Mahendran Manoharan
  • Publication number: 20180347403
    Abstract: 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: Application
    Filed: May 31, 2017
    Publication date: December 6, 2018
    Inventors: Mahendran Manoharan, Ganesh Seshadri, Robert J. Beacock, Lyle Douglas Dailey, Ravikanth Avancha
  • Publication number: 20180283203
    Abstract: 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: Application
    Filed: April 4, 2017
    Publication date: October 4, 2018
    Inventors: Sanjeev Sai Kumar Manepalli, Monty Lee Shelton, Ganesh Seshadri, Mahendran Manoharan
  • Publication number: 20180156124
    Abstract: 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: Application
    Filed: December 1, 2016
    Publication date: June 7, 2018
    Inventors: Jeffrey Donald Clements, Ganesh Seshadri, Mahendran Manoharan, Ravikanth Avancha, Aspi Rustom Wadia