Patents by Inventor Giridhar Jothiprasad

Giridhar Jothiprasad 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: 10823194
    Abstract: A compressor is provided including a casing, a hub, a flow path, a plurality of blades, and an end-wall treatment formed in at least one of the casing and the hub, and facing a tip of each blade. The flow path is formed between the casing and the hub, and the plurality of blades is positioned in the flow path. The tip of each blade and the end-wall treatment are configured to move relative to each other. Such end-wall treatment includes a first recess portion extending along a first axis to maintain a fluid flow substantially straight through the first recess portion. The end-wall treatment further includes a plurality of second recess portions spaced apart from each other and extending from the first recess portion along a second axis different than the first axis to maintain the fluid flow substantially straight through the plurality of second recess portions.
    Type: Grant
    Filed: December 1, 2014
    Date of Patent: November 3, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Giridhar Jothiprasad, Ramakrishna Venkata Mallina, John David Stampfli, Rudolf Konrad Selmeier, Davide Giacché
  • Publication number: 20190122401
    Abstract: A system and method for estimating vascular flow using CT imaging include a computer readable storage medium having stored thereon a computer program comprising instructions, which, when executed by a computer, cause the computer to acquire a first set of data comprising anatomical information of an imaging subject, the anatomical information comprises information of at least one vessel. The instructions further cause the computer to process the anatomical information to generate an image volume comprising the at least one vessel, generate hemodynamic information based on the image volume, and acquire a second set of data of the imaging subject. The computer is also caused to generate an image comprising the hemodynamic information in combination with a visualization based on the second set of data.
    Type: Application
    Filed: December 17, 2018
    Publication date: April 25, 2019
    Inventors: Robert F. Senzig, Ravikanth Avancha, Bijan Dorri, Sandeep Dutta, Steven J. Gray, Jiang Hsieh, John Irvin Jackson, Giridhar Jothiprasad, Paul Edgar Licato, Darin Robert Okerlund, Toshihiro Rifu, Saad Ahmed Sirohey, Basel Taha, Peter Michael Edic, Jerome Knoplioch, Rahul Bhotika
  • Patent number: 10227930
    Abstract: A compressor assembly for a turbomachine includes a compressor wall including circumferentially spaced stator vanes defining at least one row of stator vanes. The at least one row of stator vanes defines at least one stator passage therein. Each stator vane includes a leading edge, an opposite trailing edge defining an axial chord distance, and a pressure side. The compressor assembly also includes, at least one bleed opening defined within the compressor wall and disposed adjacent the pressure side in the at least one stator passage within a range from approximately 20% the axial chord distance upstream of the leading edge to approximately 20% the axial chord distance downstream of the trailing edge. The compressor assembly further includes at least one bleed arm extending from the at least one bleed opening with at least a portion of compressor airflow extractable through the at least one bleed arm.
    Type: Grant
    Filed: March 28, 2016
    Date of Patent: March 12, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Swati Saxena, Ajay Keshava Rao, Rudolf Konrad Selmeier, Grover Andrew Bennett, Giridhar Jothiprasad, Corey Bourassa, Byron Andrew Pritchard
  • Patent number: 10196982
    Abstract: The invention relates to a gas turbine engine comprising a casing having a compressor section, combustion section and turbine section, axially arranged in a flow direction about a rotational axis of the engine. The engine includes a rotor located within the casing and rotatable about the rotational axis, including multiple sets of circumferentially arranged blades, with at least one set corresponding to the compressor section and another set corresponding to the turbine section. The engine also includes a set of vanes circumferentially arranged about the rotational axis and at a location upstream of the combustion section, with the vanes having a pressure side and a suction side. The engine further includes a cooling conduit extending from upstream of the combustion section to downstream of the combustion section, with an inlet located on the suction side of at least one of the vanes which allows cooling air to enter the inlet and is directed through the cooling conduit for cooling.
    Type: Grant
    Filed: November 4, 2015
    Date of Patent: February 5, 2019
    Assignee: General Electric Company
    Inventors: Mehmet Muhittin Dede, Satoshi Atsuchi, Byron Andrew Pritchard, Erich Alois Krammer, Giridhar Jothiprasad, Shourya Prakash Otta, Corey Bourassa
  • Patent number: 10186056
    Abstract: A system and method for estimating vascular flow using CT imaging include a computer readable storage medium having stored thereon a computer program comprising instructions, which, when executed by a computer, cause the computer to acquire a first set of data comprising anatomical information of an imaging subject, the anatomical information comprises information of at least one vessel. The instructions further cause the computer to process the anatomical information to generate an image volume comprising the at least one vessel, generate hemodynamic information based on the image volume, and acquire a second set of data of the imaging subject. The computer is also caused to generate an image comprising the hemodynamic information in combination with a visualization based on the second set of data.
    Type: Grant
    Filed: March 21, 2012
    Date of Patent: January 22, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Robert F. Senzig, Ravikanth Avancha, Bijan Dorri, Sandeep Dutta, Steven J. Gray, Jiang Hsieh, John Irvin Jackson, Giridhar Jothiprasad, Paul Edgar Licato, Darin Robert Okerlund, Toshihiro Rifu, Saad Ahmed Sirohey, Basel Taha, Peter Michael Edic, Jerome Knoplioch, Rahul Bhotika
  • Patent number: 10047620
    Abstract: A compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow and circumferential flow non-uniformities in the compressor. The compressor includes a casing, a hub, a flow path formed between the casing and the hub, a plurality of blades positioned in the flow path, and one or more circumferentially varying end-wall treatments formed in an interior surface of at least one of the casing or the hub. Each of the one or more circumferentially varying endwall treatments circumferentially varying based on their relative position to an immediately adjacent upstream bladerow. Each of the one or more endwall treatments is circumferentially varied in at least one of placement relative to the immediately adjacent upstream bladerow or in geometric parameters defining each of the plurality of circumferentially varying endwall treatments. Additionally disclosed is an engine including the compressor.
    Type: Grant
    Filed: December 16, 2014
    Date of Patent: August 14, 2018
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Davide Giacché, John David Stampfli, Ramakrishna Venkata Mallina, Vittorio Michelassi, Giridhar Jothiprasad, Ajay Keshava Rao, Rudolf Konrad Selmeier, Sungho Yoon, Ivan Malcevic
  • Publication number: 20170276141
    Abstract: A compressor assembly for a turbomachine includes a compressor wall including circumferentially spaced stator vanes defining at least one row of stator vanes. The at least one row of stator vanes defines at least one stator passage therein. Each stator vane includes a leading edge, an opposite trailing edge defining an axial chord distance, and a pressure side. The compressor assembly also includes, at least one bleed opening defined within the compressor wall and disposed adjacent the pressure side in the at least one stator passage within a range from approximately 20% the axial chord distance upstream of the leading edge to approximately 20% the axial chord distance downstream of the trailing edge. The compressor assembly further includes at least one bleed arm extending from the at least one bleed opening with at least a portion of compressor airflow extractable through the at least one bleed arm.
    Type: Application
    Filed: March 28, 2016
    Publication date: September 28, 2017
    Inventors: Swati Saxena, Ajay Keshava Rao, Rudolf Konrad Selmeier, Grover Andrew Bennett, Giridhar Jothiprasad, Corey Bourassa, Byron Andrew Pritchard
  • Publication number: 20170122209
    Abstract: The invention relates to a gas turbine engine comprising a casing having a compressor section, combustion section and turbine section, axially arranged in a flow direction about a rotational axis of the engine. The engine includes a rotor located within the casing and rotatable about the rotational axis, including multiple sets of circumferentially arranged blades, with at least one set corresponding to the compressor section and another set corresponding to the turbine section. The engine also includes a set of vanes circumferentially arranged about the rotational axis and at a location upstream of the combustion section, with the vanes having a pressure side and a suction side. The engine further includes a cooling conduit extending from upstream of the combustion section to downstream of the combustion section, with an inlet located on the suction side of at least one of the vanes which allows cooling air to enter the inlet and is directed through the cooling conduit for cooling.
    Type: Application
    Filed: November 4, 2015
    Publication date: May 4, 2017
    Inventors: Mehmet Muhittin Dede, Satoshi Atsuchi, Byron Andrew Pritchard, Erich Alois Krammer, Giridhar Jothiprasad, Shourya Prakash Otta, Corey Bourassa
  • Publication number: 20160169017
    Abstract: A compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow and circumferential flow non-uniformities in the compressor. The compressor includes a casing, a hub, a flow path formed between the casing and the hub, a plurality of blades positioned in the flow path, and one or more circumferentially varying end-wall treatments formed in an interior surface of at least one of the casing or the hub. Each of the one or more circumferentially varying endwall treatments circumferentially varying based on their relative position to an immediately adjacent upstream bladerow. Each of the one or more endwall treatments is circumferentially varied in at least one of placement relative to the immediately adjacent upstream bladerow or in geometric parameters defining each of the plurality of circumferentially varying endwall treatments. Additionally disclosed is an engine including the compressor.
    Type: Application
    Filed: December 16, 2014
    Publication date: June 16, 2016
    Inventors: Davide Giacché, John David Stampfli, Ramakrishna Venkata Mallina, Vittorio Michelassi, Giridhar Jothiprasad, Ajay Keshava Rao, Rudolf Konrad Selmeier, Sungho Yoon, Ivan Malcevic
  • Publication number: 20160153360
    Abstract: A compressor is provided including a casing, a hub, a flow path, a plurality of blades, and an end-wall treatment formed in at least one of the casing and the hub, and facing a tip of each blade. The flow path is formed between the casing and the hub, and the plurality of blades is positioned in the flow path. The tip of each blade and the end-wall treatment are configured to move relative to each other. Such end-wall treatment includes a first recess portion extending along a first axis to maintain a fluid flow substantially straight through the first recess portion. The end-wall treatment further includes a plurality of second recess portions spaced apart from each other and extending from the first recess portion along a second axis different than the first axis to maintain the fluid flow substantially straight through the plurality of second recess portions.
    Type: Application
    Filed: December 1, 2014
    Publication date: June 2, 2016
    Inventors: Giridhar Jothiprasad, Ramakrishna Venkata Mallina, John David Stampfli, Rudolf Konrad Selmeier, Davide Giacché
  • Publication number: 20160153465
    Abstract: An axial compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow in the compressor. The one or more endwall treatments having a height formed in an interior surface of a compressor casing or a compressor hub and configured to return a flow adjacent a plurality of rotor blade tips or a plurality of stator blade tips to a cylindrical flow passage upstream of a point of removal of the flow. Each of the endwall treatments defining a front wall, a rear wall, an outer wall extending between the front wall and the rear wall, an axial overhang, an axial overlap, an axial lean angle and a tangential lean angle. The axial overhang extending upstream to overhang at least one of the at least one set of rotor blades or the at least one set of stator blades. The axial overlap extending downstream to overlap at least one of the at least one set of rotor blades or the at least one set of stator blades.
    Type: Application
    Filed: December 1, 2014
    Publication date: June 2, 2016
    Inventors: Sungho Yoon, John David Stampfli, Ramakrishna Venkata Mallina, Vittorio Michelassi, Giridhar Jothiprasad, Ajay Keshava Rao, Rudolf Konrad Selmeier, Davide Giacché, Ivan Malcevic
  • Publication number: 20120243761
    Abstract: A system and method for estimating vascular flow using CT imaging include a computer readable storage medium having stored thereon a computer program comprising instructions, which, when executed by a computer, cause the computer to acquire a first set of data comprising anatomical information of an imaging subject, the anatomical information comprises information of at least one vessel. The instructions further cause the computer to process the anatomical information to generate an image volume comprising the at least one vessel, generate hemodynamic information based on the image volume, and acquire a second set of data of the imaging subject. The computer is also caused to generate an image comprising the hemodynamic information in combination with a visualization based on the second set of data.
    Type: Application
    Filed: March 21, 2012
    Publication date: September 27, 2012
    Inventors: Robert F. Senzig, Ravikanth Avancha, Bijan Dorri, Sandeep Dutta, Steven J. Gray, Jiang Hsieh, John Irvin Jackson, Giridhar Jothiprasad, Paul Edgar Licato, Darin Robert Okerlund, Toshihiro Rifu, Saad Ahmed Sirohey, Basel Taha, Peter Michael Edic, Jerome Knoplioch, Rahul Bhotika
  • Publication number: 20120195736
    Abstract: The present application provides a plasma actuation system for a turbo-machinery device. The plasma actuation system may include an end wall, a number of end wall actuators positioned about the end wall, and a blade positioned adjacent to the end wall. The end wall actuators are oriented to produce a swirling flow between the end wall and the blade.
    Type: Application
    Filed: January 28, 2011
    Publication date: August 2, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Giridhar Jothiprasad, Seyed Gholamali Saddoughi, Grover Bennett, Robert Murray, Aspi Wadia, Katherine Essenhigh
  • Publication number: 20120144832
    Abstract: A gas turbine combustion system passive air-fuel mixing prechamber includes one or more fuel passages. Each fuel passage includes at least one downstream fuel injection orifice. One or more fluid conduits connect an upstream portion of at least one fuel passage with one or more air passages such that pressure drops across each fuel injection orifice substantially self-equalize in a passive manner with corresponding air passage pressure drops over a broad range of fuel lower heating value (LHV) from about 150 Btu/scf to about 900 Btu/scf of fuel passing through the fuel passage while mixing with air passing through one or more connected fluid conduits. The effective area of each fluid conduit relative to the corresponding fuel and air passages is dependent upon the desired fuel LHV operating range.
    Type: Application
    Filed: December 10, 2010
    Publication date: June 14, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: John Thomas Herbon, Matthew Patrick Boespflug, Grover Andrew Bennett, Fengfeng Tao, Giridhar Jothiprasad