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公开(公告)号：US11732750B2
公开(公告)日：2023-08-22
申请号：US17192116
申请日：2021-03-04
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Thomas D. Woodrow , Weize Kang , Praveen Sharma , Ambika Shivamurthy
CPC classification number: F16C19/00 , F01D25/16 , F02C7/06 , F03D13/20 , F03D80/70 , F05B2240/221 , F05B2240/50 , F05D2240/50 , F05D2260/70 , F16C2360/31
Abstract: A bearing system is configured to surround a rotor along a circumferential direction corresponding to the rotor. The rotor is extended along an axial direction co-directional to a centerline axis of the rotor. The bearing system includes a body from which a plurality of first support members is each extended, and wherein the plurality of first support members is spaced apart from one another along the circumferential direction. Each first support member includes a first axial support arm extended along the axial direction and a first radial support arm extended from the first axial support arm along a radial direction. The first radial support arm is configured to position a bearing element in contact with a bearing surface at the rotor.
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公开(公告)号：US11674399B2
公开(公告)日：2023-06-13
申请号：US17368961
申请日：2021-07-07
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Praveen Sharma , Abhijeet Jayshingrao Yadav , Nitesh Jain , Nicholas Joseph Kray
CPC classification number: F01D5/282 , F01D5/147 , F01D5/30 , F05C2251/08 , F05D2240/303 , F05D2240/304 , F05D2240/307 , F05D2300/505
Abstract: An airfoil arrangement for a gas turbine engine may include a support device using a shape memory alloy to support and control the airfoil. The support device may be formed as part of a fan blade. The arrangement may be configured to reduce overall weight and dimensions of the gas turbine engine.
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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：US20220163428A1
公开(公告)日：2022-05-26
申请号：US17101446
申请日：2020-11-23
Applicant: General Electric Company
Inventor： Kanahayya Dudhale , Peeyush Pankaj , Praveen Sharma
IPC: G01M15/14 , G01M13/045 , G06F30/17
Abstract: Systems, methods, and a gas turbine engine that includes features for condition monitoring of a damper thereof are provided. In one aspect, a gas turbine engine includes a rotary component, a bearing operatively coupled with the rotary component, and a damper associated with the bearing. The gas turbine engine also includes sensors and a controller. The controller receives data that includes sensed and/or calculated parameter values. The controller generates a damper severity index based on the parameter values. The damper severity index indicates a health state of the damper. The controller determines whether the damper severity index exceeds a threshold. When the damper severity index exceeds the threshold, a notification indicating the health state of the damper is generated. A computing system can determine a fault type and a remaining useful life of the damper and can update controller logic based on field data received from engines in a fleet.
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公开(公告)号：US11193390B2
公开(公告)日：2021-12-07
申请号：US17062876
申请日：2020-10-05
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Thomas Ory Moniz , Satish Kumar Yadav , Ambika Shivamurthy , Praveen Sharma , Bhujabal Prashant Mahadeo
Abstract: A support assembly for a bearing of a gas turbine engine including a spring finger ring positioned radially exterior to an outer race of the bearing. The spring finger ring includes an outer ring positioned radially exterior to the outer ring, an inner ring positioned radially interior to the outer ring, and a plurality of spring fingers extending between the inner and outer rings. One or more spring fingers configured as two-sided spring fingers including a first ligament coupled to the outer ring and extending at a first circumferential angle to a first radial bumper proximate to the inner ring and a second ligament coupled to the inner ring and extending at a different second circumferential angle to a second radial bumper proximate to the outer ring. The first and second radial bumpers define first and second radial gaps between the bumpers and the inner and outer rings, respectively.
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Patent Agency Ranking
公开(公告)号：US11105223B2
公开(公告)日：2021-08-31
申请号：US16535254
申请日：2019-08-08
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：US20210040865A1
公开(公告)日：2021-02-11
申请号：US16535254
申请日：2019-08-08
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Praveen Sharma , Shivam Mittal , Bhujabal Prashant Mahadeo , Weize Kang , Richard Schmidt
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：US20210040864A1
公开(公告)日：2021-02-11
申请号：US16535231
申请日：2019-08-08
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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公开(公告)号：US10823002B2
公开(公告)日：2020-11-03
申请号：US15979982
申请日：2018-05-15
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Praveen Sharma , Shuvajyoti Ghosh , Amit Zutshi , Raghavendra Muralidhar , Rangasai Madoor Comandore
IPC: F01D25/16
Abstract: A turbine engine including a first static structure comprising a first material defining a first thermal expansion coefficient and a second static structure comprising a second material defining a second thermal expansion coefficient different from the first thermal expansion coefficient. The first static structure and the second static structure are together disposed in adjacent arrangement along a load direction. The first static structure and the second static structure together selectively define a gap therebetween along the load direction based at least on a load difference between the first static structure and the second static structure.
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40.发明授权公开(公告)号：US10760498B2
公开(公告)日：2020-09-01
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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