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1.发明公开公开(公告)号：US20230399979A1
公开(公告)日：2023-12-14
申请号：US18081217
申请日：2022-12-14
Applicant: General Electric Company
Inventor： Pankaj Dhaka , Kudum Shinde , Paul Mathew , Gautam Naik , Vidyashankar Ramasastry Buravalla
IPC: F02C7/18
CPC classification number: F02C7/18 , F05D2260/232
Abstract: 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.
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公开(公告)号：US10724400B2
公开(公告)日：2020-07-28
申请号：US15949427
申请日：2018-04-10
Applicant: General Electric Company
Inventor： Shivaram Ac , Vidyashankar Ramasastry Buravalla , Ravindra Shankar Ganiger , Shuvajyoti Ghosh , Akash Joshi
IPC: F01D25/16 , F02C7/20 , F16F15/02 , F16C19/54 , F16F15/023 , F02C7/06 , F16C19/26 , F16C27/04 , F16C27/06 , F16F1/22
Abstract: 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.
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公开(公告)号：US12018586B2
公开(公告)日：2024-06-25
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：US20190178104A1
公开(公告)日：2019-06-13
申请号：US16099775
申请日：2017-05-23
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Akash Joshi , Ravindra Shankar Ganiger , Vidyashankar Ramasastry Buravalla , Shuvajyoti Ghosh , Shivaram AC
IPC: F01D25/16
Abstract: 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.
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公开(公告)号：US20150369210A1
公开(公告)日：2015-12-24
申请号：US14307666
申请日：2014-06-18
Applicant: General Electric Company
Inventor： Thomas Merzhaeuser , Vidyashankar Ramasastry Buravalla , Sriram Krishnamurthy , Wendy Wen-Ling Lin
CPC classification number: F03D1/0675 , Y02E10/721 , Y10T29/49339
Abstract: 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.
Abstract translation: 风叶片包括自支撑结构框架，其具有跨度构件，多个弦构件，织物表皮以及加强件和机械元件中的至少一个。 多个弦向构件联接到跨度构件，并且每个弦向构件和跨度构件保持风叶片的空气动力学轮廓。 此外，织物皮肤设置在自支撑结构框架上。 加强件和/或机械元件联接到自支撑结构框架，并且可操作以向自支撑结构框架提供相对运动，用于调节空气动力学轮廓并向织物皮肤提供预张力。
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Patent Agency Ranking
公开(公告)号：US20240301801A1
公开(公告)日：2024-09-12
申请号：US18180449
申请日：2023-03-08
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Vidyashankar Ramasastry Buravalla , David Raju Yamarthi , Rajesh Kumar , Jeffrey Douglas Rambo
CPC classification number: F01D11/08 , F03G7/0614 , F05D2220/30 , F05D2240/55
Abstract: A turbine engine is provided. The turbine engine includes: a rotor; a stator having a carrier; a seal support assembly coupled to the carrier; and a seal assembly disposed between the rotor and the stator and supported by the seal support assembly, the seal assembly defining a high pressure side and a low pressure side and including a plurality of seal segments, the plurality of seal segments having a first seal segment, the first seal segment having a seal face configured to form a fluid bearing with the rotor, a lip assembly, and a body, the lip assembly positioned on the high pressure side, the lip assembly including a seal lip having a high pressure surface defining a first angle with an axial direction and a low pressure surface defining a second angle with the axial direction, the second angle being greater than the first angle.
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公开(公告)号：US12078105B2
公开(公告)日：2024-09-03
申请号：US18081217
申请日：2022-12-14
Applicant: General Electric Company
Inventor： Pankaj Dhaka , Kudum Shinde , Paul Mathew , Gautam Naik , Vidyashankar Ramasastry Buravalla
IPC: F02C7/18
CPC classification number: F02C7/18 , F05D2260/232
Abstract: 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.
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公开(公告)号：US11421551B2
公开(公告)日：2022-08-23
申请号：US16099775
申请日：2017-05-23
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Akash Joshi , Ravindra Shankar Ganiger , Vidyashankar Ramasastry Buravalla , Shuvajyoti Ghosh , Shivaram A C
IPC: F01D25/16
Abstract: 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.
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公开(公告)号：US20180135596A1
公开(公告)日：2018-05-17
申请号：US15354169
申请日：2016-11-17
Applicant: General Electric Company
Inventor： Andreas Herrig , Dominic Alexander von Terzi , Shivaram AC , Vidyashankar Ramasastry Buravalla , Norman Arnold Turnquist
CPC classification number: F03D1/0675 , F03D7/0228 , F05B2220/706 , F05B2240/31 , F05B2240/50 , F05B2260/507 , F05B2260/79 , F05B2280/5002 , F05B2280/5006 , Y02E10/721 , Y02E10/723
Abstract: 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.
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公开(公告)号：US09803617B2
公开(公告)日：2017-10-31
申请号：US14307666
申请日：2014-06-18
Applicant: General Electric Company
Inventor： Thomas Merzhaeuser , Vidyashankar Ramasastry Buravalla , Sriram Krishnamurthy , Wendy Wen-Ling Lin
IPC: F03D1/06
CPC classification number: F03D1/0675 , Y02E10/721 , Y10T29/49339
Abstract: 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.
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