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公开(公告)号：US20210039799A1
公开(公告)日：2021-02-11
申请号：US16535315
申请日：2019-08-08
Applicant: General Electric Company
Inventor： Praveen Sharma , Vinod Shashikant Chaudhari , Sivakumar Mahesh , Bhujabal Prashant Mahadeo , Mohan Kannaiah Raju , Ravindra Shankar Ganiger , Jagadisha Pai Nagarmat , Shivam Mittal
Abstract: A vibration isolation system for a gas turbine engine. The vibration isolation system includes a first fixed structure and a second fixed structure separate from the first fixed structure. The vibration isolation system further includes a connector coupling the first fixed structure to the second fixed structure. Additionally, the vibration isolation system includes an isolator, including a shape memory alloy material, associated with the connector. The isolator is arranged between the first fixed structure and the second fixed structure such that the isolator reduces vibrations transferred between the first fixed structure and the second fixed structure.
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公开(公告)号：US10584751B2
公开(公告)日：2020-03-10
申请号：US16226211
申请日：2018-12-19
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Shuvajyoti Ghosh , Akash Joshi , Shivaram AC , Ravindra Shankar Ganiger , Praveen Sharma
IPC: F16C39/02 , F01D21/08 , F01D25/16 , F16C29/12 , F16C35/077 , F16C35/067 , F04D29/056
Abstract: A load reduction assembly includes an annular bearing cone configured to extend between a bearing assembly and a frame assembly and form a first load path therebetween. The load reduction assembly further includes an annular recoupler member configured to extend between the bearing assembly and the frame assembly and form a second load path therebetween. The second load path is parallel to the first load path. The recoupler member includes a shape memory alloy configured to change stiffness in response to a change in a stress condition, thereby regulating an imbalance condition of a rotor shaft coupled to the bearing assembly.
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公开(公告)号：US20190249602A1
公开(公告)日：2019-08-15
申请号：US15893800
申请日：2018-02-12
Applicant: General Electric Company
Inventor： Manoj Nayani , Praveen Sharma , Narayanan Payyoor , Shuvajyoti Ghosh
CPC classification number: F02C7/06 , F02K3/06 , F05D2220/32 , F05D2260/606 , F16N7/40 , F16N39/02 , F16N2210/02 , F16N2230/02 , F16N2270/56
Abstract: A gas turbine engine including a lubricant system defining a lubricant circuit through which a lubricant flows in fluid communication with a bearing assembly of the engine. The lubricant system selectively bypasses thermal communication of the lubricant and a heat sink based at least on a temperature of the lubricant within the lubricant circuit.
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公开(公告)号：US20190203646A1
公开(公告)日：2019-07-04
申请号：US15861780
申请日：2018-01-04
Applicant: General Electric Company
Inventor： Andrew Bryan Cannella , Charles Stanley Orkiszewski , Milind Chandrakant Dhabade , Praveen Sharma , Brian Drummond , Shivam Mittal
Abstract: The present disclosure is directed to a gas turbine engine structure and method for reducing or mitigating bowed rotor. The method includes coupling a rotor assembly to a mechanical energy storage device via a clutch mechanism when the rotor assembly is at or below a speed limit below an idle speed condition; storing mechanical energy at the mechanical energy storage device via rotation of the rotor assembly at or below the speed limit; releasing mechanical energy from the mechanical energy storage device to rotate the rotor assembly following shutdown of the gas turbine engine; and rotating the rotor assembly via the mechanical energy from the mechanical energy storage device.
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公开(公告)号：US10197102B2
公开(公告)日：2019-02-05
申请号：US15331158
申请日：2016-10-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Shuvajyoti Ghosh , Akash Joshi , Shivaram Ac , Ravindra Shankar Ganiger , Praveen Sharma
Abstract: A load reduction assembly includes an annular bearing cone configured to extend between a bearing assembly and a frame assembly and form a first load path therebetween. The load reduction assembly further includes an annular recoupler member configured to extend between the bearing assembly and the frame assembly and form a second load path therebetween. The second load path is parallel to the first load path. The recoupler member includes a shape memory alloy configured to change stiffness in response to a change in a stress condition, thereby regulating an imbalance condition of a rotor shaft coupled to the bearing assembly.
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Patent Agency Ranking
16.发明授权公开(公告)号：US12247516B2
公开(公告)日：2025-03-11
申请号：US17955713
申请日：2022-09-29
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Ranganayakulu Alapati , Peeyush Pankaj , Sanjeev Sai Kumar Manepalli , Bhaskar Nanda Mondal , Thomas Moniz , N V Sai Krishna Emani , Shishir Paresh Shah , Anil Soni , Praveen Sharma , Randy T. Antelo , Antonio Giuseppe D'Ettole
Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, and a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with the fan and with a low pressure turbine of the turbine section. The low pressure turbine includes a rotating drum to which a first airfoil structure is connected and extends radially inward toward the rotary member. A torque frame connects the rotating drum to the rotary member and transfers torque from the first airfoil structure mounted to the rotating drum to the rotary member. The torque frame includes an inner disk mounted to the rotary member, an outer ring and a second airfoil structure formed separately from the outer ring and connected thereto by a releasable connecting structure. The second airfoil structure extends radially inward from the outer ring toward the inner disk.
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公开(公告)号：US11591932B2
公开(公告)日：2023-02-28
申请号：US17387002
申请日：2021-07-28
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Praveen Sharma , Shivam Mittal , Bhujabal Prashant Mahadeo , Weize Kang , Richard Schmidt
IPC: F01D25/16 , F02C7/36 , F01D25/18 , F03G7/06 , F02C7/06 , F16C27/04 , F16C35/077 , F16C19/26 , F16C19/06
Abstract: A casing for a bearing of a gas turbine engine includes a shaft extending along an axial direction. The casing includes an attachment feature at a radially outermost portion of the casing. The attachment feature is configured to be coupled to a static frame of the gas turbine engine. The casing further includes a plurality of support arms extend from the attachment feature to a radially innermost portion of the casing. At least one support arm of the plurality of support arms defines an internal cavity. Further, the radially innermost portion of the casing is configured to be coupled to an outer race of the bearing. The casing additionally includes a reinforcing member housed at least partially within the internal cavity of at least one support arm. Moreover, the reinforcing member includes a shape memory alloy material.
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公开(公告)号：US11420755B2
公开(公告)日：2022-08-23
申请号：US16535315
申请日：2019-08-08
Applicant: General Electric Company
Inventor： Praveen Sharma , Vinod Shashikant Chaudhari , Sivakumar Mahesh , Bhujabal Prashant Mahadeo , Mohan Kannaiah Raju , Ravindra Shankar Ganiger , Jagadisha Pai Nagarmat , Shivam Mittal
Abstract: A vibration isolation system for a gas turbine engine. The vibration isolation system includes a first fixed structure and a second fixed structure separate from the first fixed structure. The vibration isolation system further includes a connector coupling the first fixed structure to the second fixed structure. Additionally, the vibration isolation system includes an isolator, including a shape memory alloy material, associated with the connector. The isolator is arranged between the first fixed structure and the second fixed structure such that the isolator reduces vibrations transferred between the first fixed structure and the second fixed structure.
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公开(公告)号：US11162419B2
公开(公告)日：2021-11-02
申请号：US15893800
申请日：2018-02-12
Applicant: General Electric Company
Inventor： Manoj Nayani , Praveen Sharma , Narayanan Payyoor , Shuvajyoti Ghosh
Abstract: A gas turbine engine including a lubricant system defining a lubricant circuit through which a lubricant flows in fluid communication with a bearing assembly of the engine. The lubricant system selectively bypasses thermal communication of the lubricant and a heat sink based at least on a temperature of the lubricant within the lubricant circuit.
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公开(公告)号：US20210277800A1
公开(公告)日：2021-09-09
申请号：US17329220
申请日：2021-05-25
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Praveen Sharma , Bhujabal Prashant Mahadeo , Shivam Mittal
Abstract: A support assembly for a bearing of a gas turbine engine includes a shaft extending along an axial direction. The support assembly includes an outer race positioned radially exterior to the bearing such that the outer race supports the bearing. Additionally, the support assembly includes a shape memory alloy damper positioned radially exterior to the outer race and at least partially supporting the outer race. Moreover, the shape memory alloy damper includes a plurality of sleeves. One or more sleeves of the plurality of sleeves include a shape memory alloy material.
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