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公开(公告)号：US20230407759A1
公开(公告)日：2023-12-21
申请号：US18046651
申请日：2022-10-14
Applicant: General Electric Company
Inventor： Illya Emmanuel Arcos Perez , Ashish Rajput , Amarnath Kakarla , Narayanan Payyoor , Abhijeet Yadav , Abhishek Goverdhan , Balaraju Suresh , Ricardo Hernandez Pandeli , Suryarghya Chakrabarti , Nicholas M. Daggett , Gary W. Bryant
CPC classification number: F01D15/12 , B64D35/04 , F01D7/00 , F05D2260/70 , F05D2220/36
Abstract: An engine for an aircraft. The engine includes a rotating airfoil assembly, at least one actuator, a torque producing system, and a controller. The rotating airfoil assembly includes a rotation axis and a plurality of rotating airfoils configured to rotate about the rotation axis in a plane of rotation. The at least one actuator is operable to change the plane of rotation of the plurality of rotating airfoils. The torque producing system is coupled to the rotating airfoil assembly and configured to rotate the rotating airfoil assembly about the rotation axis of the rotating airfoil assembly. The controller is configured to determine that the aircraft has an angle of attack and to operate the at least one actuator to change the plane of rotation of the plurality of rotating airfoils based on the angle of attack.
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公开(公告)号：US11384641B2
公开(公告)日：2022-07-12
申请号：US17297041
申请日：2018-12-11
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Suryarghya Chakrabarti , Bugra Han Ertas
Abstract: A turbine blade includes an internal vibration damping system having a plurality of unit cells. Each unit cell includes: an impacting structure; and a cavity encapsulating the impacting structure. The cavity, which includes a first hemisphere and a second hemisphere, is disposed within a substrate, which forms an outer casing of the cavity. At least one fluid is disposed in each of the first and second hemispheres between the impacting structure and the outer casing.
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公开(公告)号：US11339665B2
公开(公告)日：2022-05-24
申请号：US16816568
申请日：2020-03-12
Applicant: General Electric Company
Inventor： Andrew Clifford Hart , Jing Li , Suryarghya Chakrabarti , James Tyson Balkcum, III , Markus Feigl
Abstract: The present embodiments set forth a blade including an airfoil, the airfoil including a tip cap, a pressure sidewall and a suction sidewall extending axially between corresponding leading and trailing edges and radially between the base and the tip cap. The blade, including the airfoil and base, being formed in at least two airfoil parts, each of the two airfoil parts including contacting edges engaging each other respective contacting edges, the contacting edges defining a joint for preloading each of the at least two parts with each other and with the base. The at least two airfoil parts forming the airfoil being retained to each other by an interference fit at the joint. The interference fit providing frictional damping of vibrations in the blade during blade operation.
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公开(公告)号：US12281582B2
公开(公告)日：2025-04-22
申请号：US18046651
申请日：2022-10-14
Applicant: General Electric Company
Inventor： Illya Emmanuel Arcos Perez , Ashish Rajput , Amarnath Kakarla , Narayanan Payyoor , Abhijeet Yadav , Abhishek Goverdhan , Balaraju Suresh , Ricardo Hernandez Pandeli , Suryarghya Chakrabarti , Nicholas M. Daggett , Gary W. Bryant
Abstract: An engine for an aircraft. The engine includes a rotating airfoil assembly, at least one actuator, a torque producing system, and a controller. The rotating airfoil assembly includes a rotation axis and a plurality of rotating airfoils configured to rotate about the rotation axis in a plane of rotation. The at least one actuator is operable to change the plane of rotation of the plurality of rotating airfoils. The torque producing system is coupled to the rotating airfoil assembly and configured to rotate the rotating airfoil assembly about the rotation axis of the rotating airfoil assembly. The controller is configured to determine that the aircraft has an angle of attack and to operate the at least one actuator to change the plane of rotation of the plurality of rotating airfoils based on the angle of attack.
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公开(公告)号：US11739645B2
公开(公告)日：2023-08-29
申请号：US17038540
申请日：2020-09-30
Applicant: General Electric Company
Inventor： Suryarghya Chakrabarti , Bugra Han Ertas
IPC: F01D5/16 , F02C3/04 , F16F15/173
CPC classification number: F01D5/16 , F02C3/04 , F16F15/173 , F05D2240/30 , F05D2240/35 , F05D2260/96 , F16F2222/08 , F16F2232/02 , F16F2234/02
Abstract: A vibrational dampening element is attached to a component and configured to adjust the amplitude of oscillations of the component. The vibrational dampening element includes a mass. The mass includes a main body and a member extending from the main body. A casing that encapsulates the mass. A fluidic chamber defined between the mass and the casing. A first fluidic portion is disposed between a first side of the mass and the casing. The first fluidic portion includes a first accumulator portion directly neighboring the member. A second fluidic portion is disposed between a second side of the mass and the casing. The second fluidic portion includes a second accumulator portion directly neighboring the member. The first accumulator portion is in fluid communication with the second accumulator portion. The vibrational dampening element further includes a primary passage that extends between the first fluidic portion and the second fluidic portion.
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Patent Agency Ranking
公开(公告)号：US11371358B2
公开(公告)日：2022-06-28
申请号：US16794732
申请日：2020-02-19
Applicant: General Electric Company
Inventor： Suryarghya Chakrabarti , Jing Li
IPC: F01D5/16
Abstract: A turbine damper may be provided that may include an elongated body sized to fit inside a turbine blade, the elongated body elongated along a radial direction of the turbine blade relative to a rotation axis of the turbine blade, and plural dampening masses coupled with the elongated body and disposed at different locations along the radial direction. The plural dampening masses may be one or more of sized to dampen different vibration modes of the turbine blade, or moveable relative to and along the elongated body in the radial direction.
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公开(公告)号：US20210285330A1
公开(公告)日：2021-09-16
申请号：US16816568
申请日：2020-03-12
Applicant: General Electric Company
Inventor： Andrew Clifford Hart , Jing Li , Suryarghya Chakrabarti , James Tyson Balkcum, III , Markus Feigl
Abstract: The present embodiments set forth a blade including an airfoil, the airfoil including a tip cap, a pressure sidewall and a suction sidewall extending axially between corresponding leading and trailing edges and radially between the base and the tip cap. The blade, including the airfoil and base, being formed in at least two airfoil parts, each of the two airfoil parts including contacting edges engaging each other respective contacting edges, the contacting edges defining a joint for preloading each of the at least two parts with each other and with the base. The at least two airfoil parts forming the airfoil being retained to each other by an interference fit at the joint. The interference fit providing frictional damping of vibrations in the blade during blade operation.
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公开(公告)号：US11085303B1
公开(公告)日：2021-08-10
申请号：US16902343
申请日：2020-06-16
Applicant: General Electric Company
Inventor： John McConnell Delvaux , Claire Fridtjof Lang , Suryarghya Chakrabarti
Abstract: A blade vibration damping system impacts a pressurized damping fluid on a surface of at least one of a plurality of blades of a turbine in opposition to a vibratory movement thereof to cause damping of vibration of the blade(s) during operation of the turbine. The system includes a fluid injection nozzle in a stationary component adjacent the plurality of blades. A valve selectively admits the pressurized damping fluid to the fluid injection nozzle from a source of pressurized damping fluid, and a control system controls the valve to operate the fluid injection nozzle in response to an operational parameter exceeding a threshold during operation of the turbine. A related turbine casing and method are also provided.
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公开(公告)号：US20210232109A1
公开(公告)日：2021-07-29
申请号：US16750190
申请日：2020-01-23
Applicant: General Electric Company
Inventor： Suryarghya Chakrabarti , Youngwon Shin , John Joseph Mihok , Waad Hussain Subber
IPC: G05B19/042
Abstract: A system and method are provided for operating and maintaining a wind turbine. Accordingly, a plurality of data inputs are received. The plurality of data inputs represent a plurality of monitored attributes of a component of the wind turbine. A consolidated risk index for the component is determined using the plurality of monitored attributes, and a range of potential risk indices is forecasted. A remaining-useful-life distribution is determined based on the damage potential and an end-of-life damage threshold. The wind turbine is shut down or idled if the remaining-useful-life distribution is below a shutdown threshold.
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公开(公告)号：US20240375763A1
公开(公告)日：2024-11-14
申请号：US18777961
申请日：2024-07-19
Applicant: General Electric Company
Inventor： Suryarghya Chakrabarti , Drew M. Capps , Nicholas M. Daggett , Gary W. Bryant
Abstract: A rotating airfoil including a body and a vibration absorber located within the body. The body has a root end and a tip. The rotating airfoil has a natural frequency, and the vibration absorber has a natural frequency. The natural frequency of the vibration absorber is different than the natural frequency of the rotating airfoil.
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