Patents by Inventor Sheo Narain Giri
Sheo Narain Giri 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: 20210262363Abstract: An exhaust plume control structure includes a mounting member configured to mount to an exhaust flow source. At least one divider member operatively couples to the mounting member and is positioned in fluid communication with the exhaust flow source. A diverter member operatively couples to the divider member(s) to radially direct an initial exhaust flow from the exhaust plume towards the divider member(s). Each divider member separates the initial exhaust flow into a plurality of exhaust flows. A number of peripherally spaced, radially extending vanes may also separate the exhaust flows into additional exhaust flows. Each of the additional exhaust flows has a slower velocity than the initial exhaust flow. The structure reduces exhaust flow velocity and may provide back pressure to the initial exhaust flow. A power generating plant including the structure is also disclosed.Type: ApplicationFiled: February 24, 2020Publication date: August 26, 2021Inventors: Laxmikant Merchant, Sheo Narain Giri
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Patent number: 10584597Abstract: A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes an elongated body having a center portion that is disposed between a first end portion and a second end portion. The first end portion, center portion and second end portion at least partially define a generally arcuate top portion of the elongated body. At least a portion of the top portion may be configured to contact with a groove that is defined between the adjacent turbine blades. The first end portion and the second end portion have substantially semi-cylindrical cross sectional shapes and the center portion has a cylindrical cross sectional shape. A bottom portion of the elongated body diverges radially outwardly from the first end portion to the center portion and from the second end portion to the center portion.Type: GrantFiled: September 3, 2015Date of Patent: March 10, 2020Assignee: General Electric CompanyInventors: Spencer A. Kareff, Sheo Narain Giri
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Patent number: 10465531Abstract: A turbine bucket adapted to be supported on a turbine or rotor wheel includes an airfoil portion extending radially relative to a longitudinal axis of the rotor wheel and having a leading edge, a trailing edge, a pressure side and a suction side. At least one tip shroud extends in opposite circumferential directions, the shroud having a first hard face adapted to engage a mating second hard face on a shroud extending circumferentially from an adjacent bucket. The first hard face defined by a surface portion that varies circumferentially with an increasing radius as measured from the longitudinal axis of the rotor wheel.Type: GrantFiled: February 21, 2013Date of Patent: November 5, 2019Assignee: General Electric CompanyInventors: Gayathri Puram, Sheo Narain Giri, Harish Bommanakatte
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Publication number: 20170191366Abstract: A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes an elongated body having a center portion disposed between a first end portion and a second end portion. The first end portion, center portion and second end portion define an outer surface of the elongated body. The outer surface is configured to contact with a groove defined between the adjacent turbine blades. The elongated body defines a slot that extends radially inwardly through the outer surface and axially through the elongated body.Type: ApplicationFiled: January 5, 2016Publication date: July 6, 2017Inventors: Spencer A. Kareff, Sheo Narain Giri, Kevin Lee Worley, Harish Bommanakatte
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Publication number: 20170067351Abstract: A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes an elongated body having a center portion that is disposed between a first end portion and a second end portion. The first end portion, center portion and second end portion at least partially define a generally arcuate top portion of the elongated body. At least a portion of the top portion may be configured to contact with a groove that is defined between the adjacent turbine blades. The first end portion and the second end portion have substantially semi-cylindrical cross sectional shapes and the center portion has a cylindrical cross sectional shape. A bottom portion of the elongated body diverges radially outwardly from the first end portion to the center portion and from the second end portion to the center portion.Type: ApplicationFiled: September 3, 2015Publication date: March 9, 2017Inventors: Spencer A. Kareff, Sheo Narain Giri
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Publication number: 20160273377Abstract: A cooling arrangement for a gas turbine engine includes a discharge channel for airflow from a compressor, a first cooling channel, and at least one aperture providing communication between the flow of air through the discharge channel and the first cooling channel. A restrictor device in the aperture regulates the flow of air between the discharge channel and the first cooling channel. The restrictor device deforms to vary air flowing through the aperture in response to a physical condition of the engine. This physical condition of the engine may be that of the temperature of air flowing through the discharge channel or the power output of the gas turbine engine. The restrictor device may be a boreplug, which may be a two-way shape memory alloy.Type: ApplicationFiled: March 18, 2016Publication date: September 22, 2016Inventors: Sheo Narain GIRI, Sanjeev Kumar JHA, Bhaskar PEMMI, Harish BOMMANAKATTE, Santhosh DONKADA, Krishna Kishore GUMPINA, Indrajit MAZUMDER, Rajarshi SAHA
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Patent number: 9297310Abstract: A cooling arrangement for a gas turbine engine. The cooling arrangement comprises a discharge channel for air flow from a compressor, a first cooling channel and at least one aperture providing communication between the flow of air through the discharge channel and the first cooling channel. A restrictor device in the aperture regulates the flow of air between the discharge channel and the first cooling channel. The restrictor device deforms to vary air flowing through the aperture in response to a physical condition of the engine. This physical condition of the engine may be that of the temperature of air flowing through the discharge channel, the restrictor device responding to regulate the flow of air based on that temperature. The restrictor device may be a two-way shape memory alloy.Type: GrantFiled: October 18, 2012Date of Patent: March 29, 2016Assignee: General Electric CompanyInventors: Sheo Narain Giri, Sanjeev Kumar Jha, Bhaskar Pemmi, Harish Bommanakatte, Santhosh Donkada, Krishna Kishore Gumpina, Indrajit Mazumder, Rajarshi Saha
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Patent number: 9188010Abstract: Embodiments of the present application include a gas turbine system. The system may include a rotor wheel and one or more impeller vanes radially disposed on the rotor wheel. The system may also include one or more fluid passages defined by adjacent impeller vanes. The one or more fluid passages may be radially disposed across the rotor wheel. Moreover, the system may include one or more shape memory alloy valves disposed within each of the fluid passages. The one or more shape memory alloy valves may be configured to change shape to control a flow of fluid through the fluid passages.Type: GrantFiled: June 25, 2012Date of Patent: November 17, 2015Assignee: General Electric CompanyInventors: Sanjeev Kumar Jha, Sheo Narain Giri, Bhaskar Pemmi, Harish Bommanakatte, Rajesh Achudhan
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Patent number: 9051845Abstract: A turbomachine system includes a turbomachine that includes a rotor that includes a rotational axis, a first rotating segment having a first mating axial mount coupled to a first axial mount of the rotor in a first installed position and a first pin configured to insert into a first inserted position in both a first slot in the rotor and a first mating slot in the first rotating segment. The first pin in the first inserted position is configured to block axial movement of the first mating axial mount relative to the first axial mount. The turbomachine also includes a second rotating segment having a second mating axial mount coupled to a second axial mount of the rotor in a second installed position. The second rotating segment in the second installed position is configured to block removal of the first pin.Type: GrantFiled: January 5, 2012Date of Patent: June 9, 2015Assignee: GENERAL ELECTRIC COMPANYInventors: Harish Bommanakatte, Sheo Narain Giri, David Randolph Spracher, Zachary James Taylor, Ryan Zane Ziegler
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Patent number: 9033669Abstract: A rotating airfoil component of a turbomachine, in which the component has an airfoil aligned in a spanwise direction of the component, a shank, and a platform therebetween oriented transverse to the spanwise direction. The platform has an outer radial surface adjacent the airfoil, and at least one recessed region defined in its outer radial surface. The recessed region extends opposite the spanwise direction from a platform plane that contains portions of the outer radial surface that are upstream and downstream from the recessed region. The recessed region is contiguous with an end wall of the platform and extends therefrom toward the airfoil. The recessed region defines a surface shape whose boundary is contained by the platform plane, and has a profile shape that extends from the end wall toward the airfoil. The recessed region is sized and shaped to increase the stiffness of the platform.Type: GrantFiled: June 15, 2012Date of Patent: May 19, 2015Assignee: General Electric CompanyInventors: Sheo Narain Giri, Harish Bommanakatte, Mohankumar Banakar, John David Ward, Jr., Jonathan Matthew Lomas
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Publication number: 20140234110Abstract: A turbine bucket adapted to be supported on a turbine or rotor wheel includes an airfoil portion extending radially relative to a longitudinal axis of the rotor wheel and having a leading edge, a trailing edge, a pressure side and a suction side. At least one tip shroud extends in opposite circumferential directions, the shroud having a first hard face adapted to engage a mating second hard face on a shroud extending circumferentially from an adjacent bucket. The first hard face defined by a surface portion that varies circumferentially with an increasing radius as measured from the longitudinal axis of the rotor wheel.Type: ApplicationFiled: February 21, 2013Publication date: August 21, 2014Applicant: General Electric CompanyInventors: Gayathri PURAM, Sheo Narain Giri, Harish Bommanakatte
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Publication number: 20140140807Abstract: A turbine shroud arrangement for a turbine system includes a first region of a tip shroud, the first region disposed in close proximity to an adjacent tip shroud. Also included is a second region of the tip shroud, the second region disposed in close proximity to the adjacent tip shroud, the second region comprising a temperature sensitive material configured to engage the second region and the adjacent tip shroud in contact over a first operating condition of the turbine system and configured to provide a second region gap over a second operating condition of the turbine system.Type: ApplicationFiled: November 19, 2012Publication date: May 22, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Krishna Kishore Gumpina, Harish Bommanakatte, Sheo Narain Giri, Sanjeev Kumar Jha
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Publication number: 20140140841Abstract: A turbine bucket shroud arrangement for a turbine system includes a contact region of a tip shroud, wherein the contact region is in close proximity to an adjacent tip shroud. Also included is a negative thermal expansion material disposed proximate the contact region, the contact region comprising a first volume during a startup condition and a shutdown condition of the turbine system and a second volume during a steady state condition of the turbine system, wherein the second volume is less than the first volume.Type: ApplicationFiled: November 19, 2012Publication date: May 22, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Krishna Kishore Gumpina, Sheo Narain Giri, Sanjeev Kumar Jha, Mahesh Pasupuleti
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Patent number: 8714911Abstract: An impingement plate adapted to reduce thermally-induced strains and stresses that may damage the plate or its attachment to a second component. The plate includes an interior region having cooling holes, a peripheral wall surrounding the interior region and projecting out of the plane of the interior region, a peripheral flange surrounding the peripheral wall and lying in a plane spaced apart from the plane of the interior region, and one or more through-thickness rib. One such rib may be disposed in the interior region, project away from and out of the plane of the interior region, and linearly extend across the interior region. Alternatively or in addition, one such rib may be disposed between the peripheral wall and flange and project out of the plane of the flange.Type: GrantFiled: January 6, 2011Date of Patent: May 6, 2014Assignee: General Electric CompanyInventors: Sheo Narain Giri, Siddaraja Mallikarjuna Devangada, Brad Wilson VanTassel, Debdulal Das
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Publication number: 20140119879Abstract: Various embodiments include a turbomachine with a plasma seal system. The turbomachine can include: a diaphragm section having: an axially facing diaphragm wall; and a discourager seal protruding axially from the axially facing diaphragm wall; a rotor section having: a bucket having an axially facing bucket wall opposing the axially facing diaphragm wall; and a seal member extending from the axially facing bucket wall, wherein the seal member axially overlaps a portion of the discourager seal of the diaphragm section leaving a radial gap between the seal member and the discourager seal; and a plasma generator coupled to the diaphragm section for generating a plasma which reduces the radial gap between the seal member and the discourager seal.Type: ApplicationFiled: October 29, 2012Publication date: May 1, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Sanjeev Kumar Jha, Sheo Narain Giri
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Publication number: 20140109580Abstract: A cooling arrangement for a gas turbine engine. The cooling arrangement comprises a discharge channel for air flow from a compressor, a first cooling channel and at least one aperture providing communication between the flow of air through the discharge channel and the first cooling channel. A restrictor device in the aperture regulates the flow of air between the discharge channel and the first cooling channel. The restrictor device deforms to vary air flowing through the aperture in response to a physical condition of the engine. This physical condition of the engine may be that of the temperature of air flowing through the discharge channel, the restrictor device responding to regulate the flow of air based on that temperature. The restrictor device may be a two-way shape memory alloy.Type: ApplicationFiled: October 18, 2012Publication date: April 24, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Sheo Narain GIRI, Sanjeev Kumar JHA, Bhaskar PEMMI, Harish BOOMANAKATTE, Santhosh DONKADA, Krishna Kishore GUMPINA, Indrajit MAZUMDER, Rajarshi SAHA
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Publication number: 20140023517Abstract: A nozzle for a turbine system is disclosed. The nozzle includes an airfoil, an inner sidewall, and an outer sidewall. The airfoil includes exterior surface defining a pressure side and a suction side extending between a leading edge and a trailing edge. The airfoil further defines a tip and a root. The inner sidewall is connected to the airfoil at the tip. The outer sidewall is connected to the airfoil at the root. The inner sidewall and outer sidewall each includes a peripheral edge defining a pressure side slash face, a suction side slash face, a leading edge face, and a trailing edge face. At least one of the inner sidewall pressure side slash face, the inner sidewall suction side slash face, the outer sidewall pressure side slash face, or the outer sidewall suction side slash face has a generally curvilinear profile.Type: ApplicationFiled: July 23, 2012Publication date: January 23, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Shruti Kulkarni, Joseph Vincent Pawlowski, Sheo Narain Giri
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Publication number: 20130343868Abstract: Embodiments of the present application include a gas turbine system. The system may include a rotor wheel and one or more impeller vanes radially disposed on the rotor wheel. The system may also include one or more fluid passages defined by adjacent impeller vanes. The one or more fluid passages may be radially disposed across the rotor wheel. Moreover, the system may include one or more shape memory alloy valves disposed within each of the fluid passages. The one or more shape memory alloy valves may be configured to change shape to control a flow of fluid through the fluid passages.Type: ApplicationFiled: June 25, 2012Publication date: December 26, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Sanjeev Kumar Jha, Sheo Narain Giri, Bhaskar Pemmi, Harish Bommanakatte, Rajesh Achudhan
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Publication number: 20130336801Abstract: A rotating airfoil component of a turbomachine, in which the component has an airfoil aligned in a spanwise direction of the component, a shank, and a platform therebetween oriented transverse to the spanwise direction. The platform has an outer radial surface adjacent the airfoil, and at least one recessed region defined in its outer radial surface. The recessed region extends opposite the spanwise direction from a platform plane that contains portions of the outer radial surface that are upstream and downstream from the recessed region. The recessed region is contiguous with an end wall of the platform and extends therefrom toward the airfoil. The recessed region defines a surface shape whose boundary is contained by the platform plane, and has a profile shape that extends from the end wall toward the airfoil. The recessed region is sized and shaped to increase the stiffness of the platform.Type: ApplicationFiled: June 15, 2012Publication date: December 19, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Sheo Narain Giri, Harish Bommanakatte, Mohankumar Banakar, John David Ward, JR., Jonathan Matthew Lomas
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Patent number: 8544852Abstract: A torsion seal is provided and includes a first section, a second section and a torsion section connected at opposite end portions thereof to the first and second sections and having a central portion extending between the opposite end portions to absorb differential thermal growth of vessels to which the first and second sections are coupled.Type: GrantFiled: June 3, 2011Date of Patent: October 1, 2013Assignee: General Electric CompanyInventor: Sheo Narain Giri