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Giridhar Jothiprasad

from Clifton Park, NY
Age ~46
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Also known as:
Giridha Jothiprasad, Jothiprasad Giridhar, Giridhar O, Charles Sokol
Phone and address:
25 Lincoln Ave, Clifton Park Center, NY 12065
Connected to:
Ivanka L Jotic, 64Pitiporn Jotikapukkana, 47Amy Jotkowitz, 52Tirtza Jotkowitz, 77Arun Jotshi, 44Pritam Jotsinghani, 85Ashish Jotwani, 71Kishore R Jotwani, 57Marc D Jotzat, 58Alice H Jou, 32

Giridhar Jothiprasad Phones & Addresses

  • 25 Lincoln Ave, Clifton Park, NY 12065
  • Niskayuna, NY
  • 29 Parsalin Ct, Latham, NY 12110 (518) 785-0580
  • 210 Lake St, Ithaca, NY 14850
  • 301 Maple Ave, Ithaca, NY 14850 (607) 277-2106
  • Woodland Hls, CA

Education

Degree: High school graduate or higher

Emails

g***[email protected]

Resumes

Resumes

Giridhar Jothiprasad Photo 1

Researcher, Turbomachinery Aero @ Ge-Research

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Position:
Mechanical Engineer at GE Global Research
Location:
Albany, New York Area
Industry:
Research
Work:
GE Global Research - Albany, New York Area since 2005
Mechanical Engineer
Giridhar Jothiprasad Photo 2

Giridhar Jothiprasad

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Publications

Us Patents

Plasma Actuation Systems To Produce Swirling Flows

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US Patent:
20120195736, Aug 2, 2012
Filed:
Jan 28, 2011
Appl. No.:
13/015786
Inventors:
Giridhar Jothiprasad - Niskayuna NY, US
Seyed Gholamali Saddoughi - Clifton Park NY, US
Grover Bennett - Schenectady NY, US
Robert Murray - Rotterdam NY, US
Aspi Wadia - Loveland OH, US
Katherine Essenhigh - Niskayuna NY, US
Assignee:
GENERAL ELECTRIC COMPANY - Schnectady NY
International Classification:
F04D 27/02
F04D 29/56
US Classification:
415 1, 415148
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.

System And Method For Estimating Vascular Flow Using Ct Imaging

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US Patent:
20120243761, Sep 27, 2012
Filed:
Mar 21, 2012
Appl. No.:
13/425724
Inventors:
Robert F. Senzig - Germantown WI, US
Ravikanth Avancha - Niskayuna NY, US
Bijan Dorri - Hartland WI, US
Sandeep Dutta - Waukesha WI, US
Steven J. Gray - Elm Grove WI, US
Jiang Hsieh - Brookfield WI, US
John Irvin Jackson - Brookfield WI, US
Giridhar Jothiprasad - Clifton Park NY, US
Paul Edgar Licato - Wauwatosa WI, US
Darin Robert Okerlund - Muskego WI, US
Toshihiro Rifu - Milwaukee WI, US
Saad Ahmed Sirohey - Pewaukee WI, US
Basel Taha - Madison WI, US
Peter Michael Edic - Albany NY, US
Jerome Knoplioch - Neuilly Sur Seine, FR
Rahul Bhotika - Albany NY, US
International Classification:
G06K 9/00
A61B 6/03
US Classification:
382131, 378 19, 382134
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.

Passive Air-Fuel Mixing Prechamber

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US Patent:
20120144832, Jun 14, 2012
Filed:
Dec 10, 2010
Appl. No.:
12/964836
Inventors:
John Thomas Herbon - Rexford NY, US
Matthew Patrick Boespflug - Clifton Park NY, US
Grover Andrew Bennett - Schenectady NY, US
Fengfeng Tao - Clifton Park NY, US
Giridhar Jothiprasad - Clifton Park NY, US
Assignee:
GENERAL ELECTRIC COMPANY - Schenectady NY
International Classification:
F02C 3/14
US Classification:
60737
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.

Compressor Bleed Systems In Turbomachines And Methods Of Extracting Compressor Airflow

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US Patent:
20170276141, Sep 28, 2017
Filed:
Mar 28, 2016
Appl. No.:
15/082524
Inventors:
- Schenectady NY, US
Ajay Keshava Rao - Bangalore, IN
Rudolf Konrad Selmeier - Fahrenzhausen, DE
Grover Andrew Bennett - Esperance NY, US
Giridhar Jothiprasad - Clifton Park NY, US
Corey Bourassa - Mechanicville NY, US
Byron Andrew Pritchard - Loveland OH, US
International Classification:
F04D 27/00
F04D 29/52
F02C 9/18
F04D 29/54
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.

Gas Turbine Engine Having A Flow Control Surface With A Cooling Conduit

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US Patent:
20170122209, May 4, 2017
Filed:
Nov 4, 2015
Appl. No.:
14/932162
Inventors:
- Schenectady NY, US
Satoshi Atsuchi - Rexford NY, US
Byron Andrew Pritchard - Loveland OH, US
Erich Alois Krammer - West Chester OH, US
Giridhar Jothiprasad - Clifton Park NY, US
Shourya Prakash Otta - Clifton Park NY, US
Corey Bourassa - Mechanicville NY, US
International Classification:
F02C 7/18
F02C 7/052
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.

Circumferentially Varying Axial Compressor Endwall Treatment For Controlling Leakage Flow Therein

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US Patent:
20160169017, Jun 16, 2016
Filed:
Dec 16, 2014
Appl. No.:
14/572119
Inventors:
- Schenectady NY, US
John David Stampfli - Greer SC, US
Ramakrishna Venkata Mallina - Clifton Park NY, US
Vittorio Michelassi - Munich, DE
Giridhar Jothiprasad - Clifton Park NY, US
Ajay Keshava Rao - Bangalore, IN
Rudolf Konrad Selmeier - Fahrenzhausen, DE
Sungho Yoon - Munich, DE
Ivan Malcevic - Schenectady NY, US
International Classification:
F01D 11/00
F02C 3/04
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.

Axial Compressor Endwall Treatment For Controlling Leakage Flow Therein

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US Patent:
20160153465, Jun 2, 2016
Filed:
Dec 1, 2014
Appl. No.:
14/556452
Inventors:
- Schenectady NY, US
John David Stampfli - Greer SC, US
Ramakrishna Venkata Mallina - Clifton Park NY, US
Vittorio Michelassi - Munich, DE
Giridhar Jothiprasad - Clifton Park NY, US
Ajay Keshava Rao - Bangalore, IN
Rudolf Konrad Selmeier - Fahrenzhausen, DE
Davide Giacché - Munich, DE
Ivan Malcevic - Schenectady NY, US
International Classification:
F04D 29/52
F02C 3/04
F01D 11/08
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.
Control profile
Giridhar Jothiprasad from Clifton Park, NY, age ~46 Get Report