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公开(公告)号：US20170234157A1
公开(公告)日：2017-08-17
申请号：US15041136
申请日：2016-02-11
Applicant: General Electric Company
Inventor： Esuff Khan , Shivaram Ac , Vidyashankar Ramasastry Buravalla , Shuvajyoti Ghosh , Akash Joshi
IPC: F01D25/16
CPC classification number: F01D25/164 , F01D21/00 , F01D21/045 , F01D21/08 , F01D25/162 , F05D2220/32 , F05D2240/24 , F05D2240/242 , F05D2240/54 , F05D2240/60 , F05D2240/91 , F05D2260/15 , F05D2300/1723 , F05D2300/173 , F05D2300/174 , F05D2300/505 , Y02T50/671
Abstract: 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.
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公开(公告)号：US12241375B2
公开(公告)日：2025-03-04
申请号：US18189379
申请日：2023-03-24
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , David Raju Yamarthi , Chandrashekhar Kandukuri , Deepak Trivedi , Narendra Anand Hardikar , Vidyashankar Ramasastry Buravalla , Steven Douglas Johnson , Amit Goyal , Grant Robert Portune , Himanshu Gupta , Srinivasan Swaminathan , Shalini Thimmegowda , Guru Venkata Dattu Jonnalagadda , Shalabh Saxena , Prateek Jalan
IPC: F01D11/02
Abstract: A turbine engine is provided. The turbine engine defines an axial direction and a radial direction, and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly defining a high-pressure side and a low-pressure side and comprising a plurality of seal segments, the plurality of seal segments including a seal segment having a seal face forming a fluid bearing with the rotor, a lip, and a body, the lip extending from the body along the axial direction of the turbine engine on the high-pressure side and including an outer pressurization surface along the radial direction of the turbine engine; and a seal support assembly, the seal support assembly comprising a spring arrangement extending between the carrier and the first seal segment to counter a pressure on the outer pressurization surface during operation of the turbine engine.
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公开(公告)号：US11931986B2
公开(公告)日：2024-03-19
申请号：US18103982
申请日：2023-01-31
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Vidyashankar Ramasastry Buravalla
CPC classification number: B32B15/043 , B32B5/26 , B32B27/065 , B32B27/12 , B32B37/18 , B32B2307/202 , B32B2307/56 , B32B2311/005 , B32B2605/18
Abstract: 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.
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公开(公告)号：US20240076989A1
公开(公告)日：2024-03-07
申请号：US18081151
申请日：2022-12-14
Applicant: General Electric Company
Inventor： David Raju Yamarthi , Ravindra Shankar Ganiger , Vasanth Kumar Balaramudu , Vishnu Vardhan Venkata Tatiparthi , Nitesh Jain , Vidyashankar Ramasastry Buravalla
IPC: F01D5/14
CPC classification number: F01D5/147 , F05D2230/60
Abstract: 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.
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公开(公告)号：US11828235B2
公开(公告)日：2023-11-28
申请号：US17473233
申请日：2021-09-13
Applicant: General Electric Company
Inventor： Peeyush Pankaj , Narayanan Payyoor , Shashank Suresh Puranik , Arvind Kumar Rao , Praveen Sharma , Chirayu Pradip Inamdar , Vidyashankar Ramasastry Buravalla , Sankarapandian Palaniappan , Sampath Karthikeyan
CPC classification number: F02C7/36 , F16H57/0006 , F16H57/02 , F05D2220/32 , F05D2260/40311 , F05D2260/96 , F16F2222/02 , F16F2224/0258 , F16H2057/02039 , F16H2057/085
Abstract: 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.
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Patent Agency Ranking
公开(公告)号：US11486349B2
公开(公告)日：2022-11-01
申请号：US16739244
申请日：2020-01-10
Applicant: General Electric Company
Inventor： Vidyashankar Ramasastry Buravalla , Paul Mathew , Sriram Krishnamurthy
IPC: F03D1/06
Abstract: 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.
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公开(公告)号：US20220178310A1
公开(公告)日：2022-06-09
申请号：US17473233
申请日：2021-09-13
Applicant: General Electric Company
Inventor： Peeyush Pankaj , Narayanan Payyoor , Shashank Suresh Puranik , Arvind Kumar Rao , Praveen Sharma , Chirayu Pradip Inamdar , Vidyashankar Ramasastry Buravalla , Sankarapandian Palaniappan , Sampath Karthikeyan
Abstract: 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.
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公开(公告)号：US20240318570A1
公开(公告)日：2024-09-26
申请号：US18189379
申请日：2023-03-24
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , David Raju Yamarthi , Chandrashekhar Kandukuri , Deepak Trivedi , Narendra Anand Hardikar , Vidyashankar Ramasastry Buravalla , Steven Douglas Johnson , Amit Goyal , Grant Robert Portune , Himanshu Gupta , Srinivasan Swaminathan , Shalini Thimmegowda , Guru Venkata Dattu Jonnalagadda , Shalabh Saxena , Prateek Jalan
IPC: F01D11/02
CPC classification number: F01D11/025 , F05D2240/53 , F05D2240/55 , F05D2260/38
Abstract: A turbine engine is provided. The turbine engine defines an axial direction and a radial direction, and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly defining a high-pressure side and a low-pressure side and comprising a plurality of seal segments, the plurality of seal segments including a seal segment having a seal face forming a fluid bearing with the rotor, a lip, and a body, the lip extending from the body along the axial direction of the turbine engine on the high-pressure side and including an outer pressurization surface along the radial direction of the turbine engine; and a seal support assembly, the seal support assembly comprising a spring arrangement extending between the carrier and the first seal segment to counter a pressure on the outer pressurization surface during operation of the turbine engine.
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公开(公告)号：US20240318558A1
公开(公告)日：2024-09-26
申请号：US18312122
申请日：2023-05-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Vidyashankar Ramasastry Buravalla
Abstract: A gas turbine engine includes a fan section, a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine centerline. An airfoil is located in one of the fan section, the compressor section, or the turbine section. The airfoil defines an interior and extends between a leading edge and a trailing edge defining a chord-wise direction, and extending between a root and a tip defining a span-wise direction. At least one stiffener is located within the interior, having a deformation threshold, and including at least one crush initiator formed on the at least one stiffener. The crush initiator determines deformation geometry of the at least one stiffener in response to a force acting on the at least one stiffener exceeding the deformation threshold.
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公开(公告)号：US11565505B2
公开(公告)日：2023-01-31
申请号：US17016621
申请日：2020-09-10
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Vidyashankar Ramasastry Buravalla
Abstract: 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.
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