Patents by Inventor Vidyashankar Ramasastry BURAVALLA
Vidyashankar Ramasastry BURAVALLA 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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Patent number: 11931986Abstract: A laminate assembly includes a matrix layer and elongated, continuous strips of a conductive alloy. The matrix layer has opposite first and second sides connected by opposite first and second edges. Each of the first and second edges extends from the first side of the matrix layer to the opposite second side of the matrix layer. The elongated, continuous strips of the conductive alloy are disposed in the matrix layer between the first and second sides of the matrix layer. The elongated continuous strips continuously extend through the matrix layer from the first edge to the opposite second edge.Type: GrantFiled: January 31, 2023Date of Patent: March 19, 2024Assignee: General Electric CompanyInventor: Vidyashankar Ramasastry Buravalla
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Publication number: 20240076989Abstract: An airfoil assembly extends along a radial direction between a root and a tip, the airfoil assembly comprising: a first blade segment positioned proximate the root of the airfoil assembly; a second blade segment positioned adjacent the first blade segment along the radial direction; and a tensioning assembly comprising a plurality of tensioning strings that extend between and mechanically couple the first blade segment and the second blade segment.Type: ApplicationFiled: December 14, 2022Publication date: March 7, 2024Inventors: David Raju Yamarthi, Ravindra Shankar Ganiger, Vasanth Kumar Balaramudu, Vishnu Vardhan Venkata Tatiparthi, Nitesh Jain, Vidyashankar Ramasastry Buravalla
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Publication number: 20230399979Abstract: A method for cooling a compressor section of a gas turbine engine includes sensing, via at least one first temperature sensor, a first temperature at the first location on a stationary assembly of the compressor section. The method also includes sensing, via at least one second temperature sensor, a second temperature at a second location on the stationary assembly of the compressor section. The second location is spaced apart from the first location. The method also includes determining, via a controller, a delta between the first temperature and the second temperature. Further, the method includes operating, via the controller, at least one cooling element when the delta exceeds a predetermined threshold, the at least one cooling element provided at the first location of the stationary assembly of the compressor section.Type: ApplicationFiled: December 14, 2022Publication date: December 14, 2023Inventors: Pankaj Dhaka, Kudum Shinde, Paul Mathew, Gautam Naik, Vidyashankar Ramasastry Buravalla
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Publication number: 20230383730Abstract: A method for detecting a failure condition in one or more components of a wind turbine is provided. The method includes actuating, via a controller, an impact device to generate a vibration having a vibration frequency and a vibration magnitude in the one or more components. The method further includes receiving data indicative of the vibration frequency and the vibration magnitude from a sensor communicatively coupled to the controller. The method further includes determining, via the controller, whether the data indicative of the vibration frequency and/or the vibration magnitude is outside of a predetermined vibration range for the one or more components.Type: ApplicationFiled: May 24, 2022Publication date: November 30, 2023Inventors: Dhanesh Chandrashekar Pathuvoth, Vidyashankar Ramasastry Buravalla
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Patent number: 11828235Abstract: An epicyclic gearbox is configured to transfer rotational motion between a first rotating component and a second rotating component of the gas turbine engine. The gearbox includes a centrally located sun gear, two or more planet gears circumscribing the sun gear, and a ring gear circumscribing the plurality of planet gears. The gearbox is configured such that the sun gear is drivingly coupled to the first rotating component, such that rotation of the sun gear causes rotation of each planet gear, and such that the ring gear rotates relative to the plurality of planet gears. The gearbox includes one or more shape memory alloy dampers provided in association with the sun gear, the ring gear, and/or the plurality of planet gears. The shape memory alloy damper(s) is configured in order to reduce vibrations transferred through the epicyclic gearbox to the frame, the first rotating component, and/or the second rotating component.Type: GrantFiled: September 13, 2021Date of Patent: November 28, 2023Assignee: General Electric CompanyInventors: Peeyush Pankaj, Narayanan Payyoor, Shashank Suresh Puranik, Arvind Kumar Rao, Praveen Sharma, Chirayu Pradip Inamdar, Vidyashankar Ramasastry Buravalla, Sankarapandian Palaniappan, Sampath Karthikeyan
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Publication number: 20230173790Abstract: A laminate assembly includes a matrix layer and elongated, continuous strips of a conductive alloy. The matrix layer has opposite first and second sides connected by opposite first and second edges. Each of the first and second edges extends from the first side of the matrix layer to the opposite second side of the matrix layer. The elongated, continuous strips of the conductive alloy are disposed in the matrix layer between the first and second sides of the matrix layer. The elongated continuous strips continuously extend through the matrix layer from the first edge to the opposite second edge.Type: ApplicationFiled: January 31, 2023Publication date: June 8, 2023Inventor: VIDYASHANKAR RAMASASTRY BURAVALLA
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Patent number: 11565505Abstract: A laminate assembly includes a matrix layer and elongated, continuous strips of a conductive alloy. The matrix layer has opposite first and second sides connected by opposite first and second edges. Each of the first and second edges extends from the first side of the matrix layer to the opposite second side of the matrix layer. The elongated, continuous strips of the conductive alloy are disposed in the matrix layer between the first and second sides of the matrix layer. The elongated continuous strips continuously extend through the matrix layer from the first edge to the opposite second edge.Type: GrantFiled: September 10, 2020Date of Patent: January 31, 2023Assignee: General Electric CompanyInventor: Vidyashankar Ramasastry Buravalla
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Patent number: 11486349Abstract: A method for manufacturing a blade structure includes providing the blade structure comprising an outer surface having an aerodynamic profile. The method also includes applying one or more shape memory alloys to the outer surface of the blade structure so as to form an outer protection layer on at least a portion of the blade structure. Moreover, the method includes securing the one or more shape memory alloys to the blade structure.Type: GrantFiled: January 10, 2020Date of Patent: November 1, 2022Assignee: General Electric CompanyInventors: Vidyashankar Ramasastry Buravalla, Paul Mathew, Sriram Krishnamurthy
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Patent number: 11421551Abstract: A gas turbine engine includes a compressor section and a turbine section arranged in serial flow order. A shaft is provided rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. A bearing is also provided supporting rotation of the shaft, with a support element in turn supporting the bearing. The gas turbine engine also includes a superelastic member formed of a shape memory alloy supporting at least one of the support element or the bearing. The superelastic member is installed in a pre-stressed condition to enhance a dampening function of the superelastic member.Type: GrantFiled: May 23, 2017Date of Patent: August 23, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Akash Joshi, Ravindra Shankar Ganiger, Vidyashankar Ramasastry Buravalla, Shuvajyoti Ghosh, Shivaram A C
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Publication number: 20220178310Abstract: An epicyclic gearbox is configured to transfer rotational motion between a first rotating component and a second rotating component of the gas turbine engine. The gearbox includes a centrally located sun gear, two or more planet gears circumscribing the sun gear, and a ring gear circumscribing the plurality of planet gears. The gearbox is configured such that the sun gear is drivingly coupled to the first rotating component, such that rotation of the sun gear causes rotation of each planet gear, and such that the ring gear rotates relative to the plurality of planet gears. The gearbox includes one or more shape memory alloy dampers provided in association with the sun gear, the ring gear, and/or the plurality of planet gears. The shape memory alloy damper(s) is configured in order to reduce vibrations transferred through the epicyclic gearbox to the frame, the first rotating component, and/or the second rotating component.Type: ApplicationFiled: September 13, 2021Publication date: June 9, 2022Inventors: Peeyush Pankaj, Narayanan Payyoor, Shashank Suresh Puranik, Arvind Kumar Rao, Praveen Sharma, Chirayu Pradip Inamdar, Vidyashankar Ramasastry Buravalla, Sankarapandian Palaniappan, Sampath Karthikeyan
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Publication number: 20210215132Abstract: A method for manufacturing a blade structure includes providing the blade structure comprising an outer surface having an aerodynamic profile. The method also includes applying one or more shape memory alloys to the outer surface of the blade structure so as to form an outer protection layer on at least a portion of the blade structure. Moreover, the method includes securing the one or more shape memory alloys to the blade structure.Type: ApplicationFiled: January 10, 2020Publication date: July 15, 2021Inventors: Vidyashankar Ramasastry Buravalla, Paul Mathew, Sriram Krishnamurthy
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Publication number: 20210070015Abstract: A laminate assembly includes a matrix layer and elongated, continuous strips of a conductive alloy. The matrix layer has opposite first and second sides connected by opposite first and second edges. Each of the first and second edges extends from the first side of the matrix layer to the opposite second side of the matrix layer. The elongated, continuous strips of the conductive alloy are disposed in the matrix layer between the first and second sides of the matrix layer. The elongated continuous strips continuously extend through the matrix layer from the first edge to the opposite second edge.Type: ApplicationFiled: September 10, 2020Publication date: March 11, 2021Inventor: VIDYASHANKAR RAMASASTRY BURAVALLA
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Patent number: 10724400Abstract: A support assembly for a load-bearing unit, a gas turbine engine including the support assembly, and a method of operation of the support assembly are provided. The support assembly includes a support element, a damper, and a variable stiffness member. The support element supports the load-bearing unit. The damper supports the support element and is configured to provide dampening of the load-bearing unit. The variable stiffness member is positioned between the damper and the load-bearing unit. The variable stiffness member is configured to provide a serial dampening of the load-bearing unit with the damper. The variable stiffness member includes a shape memory alloy.Type: GrantFiled: April 10, 2018Date of Patent: July 28, 2020Assignee: General Electric CompanyInventors: Shivaram Ac, Vidyashankar Ramasastry Buravalla, Ravindra Shankar Ganiger, Shuvajyoti Ghosh, Akash Joshi
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Patent number: 10626846Abstract: A wind turbine blade includes a first blade segment and a second blade segment extending in opposite directions from a chord-wise joint. Each of the blade segments having a pressure side shell member, a suction side shell member. The blade further including a coupling component extending spanwise and structurally connecting the first blade segment and the second blade segment. A thermal actuation component is coupled to the coupling component and passively actuated in response to a change in thermal conditions so as to provide for aeroelastic tailoring and pitch control to the wind turbine blade.Type: GrantFiled: November 17, 2016Date of Patent: April 21, 2020Assignee: General Electric CompanyInventors: Andreas Herrig, Dominic Alexander von Terzi, Shivaram Ac, Vidyashankar Ramasastry Buravalla, Norman Arnold Turnquist
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Publication number: 20190178104Abstract: A gas turbine engine includes a compressor section and a turbine section arranged in serial flow order. A shaft is provided rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. A bearing is also provided supporting rotation of the shaft, with a support element in turn supporting the bearing. The gas turbine engine also includes a superelastic member formed of a shape memory alloy supporting at least one of the support element or the bearing. The superelastic member is installed in a pre-stressed condition to enhance a dampening function of the superelastic member.Type: ApplicationFiled: May 23, 2017Publication date: June 13, 2019Inventors: Akash Joshi, Ravindra Shankar Ganiger, Vidyashankar Ramasastry Buravalla, Shuvajyoti Ghosh, Shivaram AC
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Patent number: 10196934Abstract: A rotor support system for a gas turbine engine may generally include a bearing assembly and a load reduction member configured to be coupled between the bearing assembly and a support frame of the engine. The load reduction member may include a fuse portion configured to fail when a load transmitted through the load reduction member exceeds a predetermined load threshold. The system may also include a load recoupling member provided between the bearing assembly and the support frame. The load recoupling member may be formed from a super-elastic shape memory alloy that allows the load recoupling member to undergo recoverable deformation without failing when the fuse portion fails such that the load recoupling member maintains a mechanical connection between the bearing assembly and the support frame.Type: GrantFiled: February 11, 2016Date of Patent: February 5, 2019Assignee: General Electric CompanyInventors: Esuff Khan, Shivaram Ac, Vidyashankar Ramasastry Buravalla, Shuvajyoti Ghosh, Akash Joshi
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Publication number: 20180298822Abstract: A support assembly for a load-bearing unit, a gas turbine engine including the support assembly, and a method of operation of the support assembly are provided. The support assembly includes a support element, a damper, and a variable stiffness member. The support element supports the load-bearing unit. The damper supports the support element and is configured to provide dampening of the load-bearing unit. The variable stiffness member is positioned between the damper and the load-bearing unit. The variable stiffness member is configured to provide a serial dampening of the load-bearing unit with the damper. The variable stiffness member includes a shape memory alloy.Type: ApplicationFiled: April 10, 2018Publication date: October 18, 2018Inventors: Shivaram AC, Vidyashankar Ramasastry BURAVALLA, Ravindra Shankar GANIGER, Shuvajyoti GHOSH, Akash JOSHI
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Publication number: 20180135596Abstract: A wind turbine blade includes a first blade segment and a second blade segment extending in opposite directions from a chord-wise joint. Each of the blade segments having a pressure side shell member, a suction side shell member. The blade further including a coupling component extending spanwise and structurally connecting the first blade segment and the second blade segment. A thermal actuation component is coupled to the coupling component and passively actuated in response to a change in thermal conditions so as to provide for aeroelastic tailoring and pitch control to the wind turbine blade.Type: ApplicationFiled: November 17, 2016Publication date: May 17, 2018Inventors: Andreas Herrig, Dominic Alexander von Terzi, Shivaram AC, Vidyashankar Ramasastry Buravalla, Norman Arnold Turnquist
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Patent number: 9803617Abstract: A wind blade includes a self-supporting structural framework, having a span-wise member, a plurality of chord-wise members, a fabric skin, and at least one of a stiffener and a mechanical element. The plurality of chord-wise members is coupled to the span-wise member and each chord-wise member and the span-wise member maintains an aerodynamic contour of the wind blade. Further, the fabric skin is disposed over the self-supporting structural framework. The stiffener and/or the mechanical element are coupled to the self-supporting structural framework, and are operable to provide a relative movement to the self-supporting structural framework for adjusting the aerodynamic contour and provide pretension to the fabric skin.Type: GrantFiled: June 18, 2014Date of Patent: October 31, 2017Assignee: General Electric CompanyInventors: Thomas Merzhaeuser, Vidyashankar Ramasastry Buravalla, Sriram Krishnamurthy, Wendy Wen-Ling Lin
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Publication number: 20170234157Abstract: A rotor support system for a gas turbine engine may generally include a bearing assembly and a load reduction member configured to be coupled between the bearing assembly and a support frame of the engine. The load reduction member may include a fuse portion configured to fail when a load transmitted through the load reduction member exceeds a predetermined load threshold. The system may also include a load recoupling member provided between the bearing assembly and the support frame. The load recoupling member may be formed from a super-elastic shape memory alloy that allows the load recoupling member to undergo recoverable deformation without failing when the fuse portion fails such that the load recoupling member maintains a mechanical connection between the bearing assembly and the support frame.Type: ApplicationFiled: February 11, 2016Publication date: August 17, 2017Inventors: Esuff Khan, Shivaram Ac, Vidyashankar Ramasastry Buravalla, Shuvajyoti Ghosh, Akash Joshi