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公开(公告)号：US20220100919A1
公开(公告)日：2022-03-31
申请号：US17232540
申请日：2021-04-16
Applicant: General Electric Company
Inventor： Suryarghya Chakrabarti , Kevin Turner , Yoon Seok Choi , Douglas L. Washburn , Liping Wang , Andrew J. Blair
Abstract: A method of analyzing a blended airfoil that includes generating a plurality of simulated blended airfoil designs each including one of a plurality of blend geometries, training surrogate models representing the plurality of simulated blended airfoil designs based on natural frequency, modal force, and Goodman scale factors, determining a likelihood of operational failure of each of the plurality of blended airfoil designs in response to one or more vibratory modes, determining which of the plurality of simulated blended airfoil designs violate at least one aeromechanical constraint and generating, a blend design space visualization including a blend design space, where the blend design space includes one or more restricted regions indicating blended airfoil designs where at least one aeromechanical constraint is violates and one or more permitted regions indicating blended airfoil designs where no aeromechanical constraints are violated.
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公开(公告)号：US20220098985A1
公开(公告)日：2022-03-31
申请号：US17038540
申请日：2020-09-30
Applicant: General Electric Company
Inventor： Suryarghya Chakrabarti , Bugra Han Ertas
IPC: F01D5/16 , F16F15/173 , F02C3/04
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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公开(公告)号：US11261738B2
公开(公告)日：2022-03-01
申请号：US17309467
申请日：2018-12-11
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Suryarghya Chakrabarti , Changjie Sun
Abstract: A nested lattice structure for use in a damping system for a turbine blade includes a first lattice structure including: a first outer passage including a hollow interior; a second outer passage including a hollow interior; and an outer node including a hollow interior and forming an intersection of the first outer passage and the second outer passage. The nested lattice structure includes a second lattice structure nested within the hollow interior of the first lattice structure. The second lattice structure includes: a first inner passage; a second inner passage; and an inner node forming an intersection of the first inner passage and the second inner passage. Each of the first inner passage, the second inner passage, and the inner node are nested within the respective first outer passage, the second outer passage, and the outer node.
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公开(公告)号：US10808788B2
公开(公告)日：2020-10-20
申请号：US15481507
申请日：2017-04-07
Applicant: General Electric Company
Inventor： Charles Erklin Seeley , Walter John Smith , Suryarghya Chakrabarti , Andrew Joseph Wickersham
Abstract: Dampers and a fuel delivery systems including such dampers are disclosed. The damper includes a first component and a dampening component. The first component is coupled to a first tubular element and includes a first extended hollow section. The dampening component is coupled to a second tubular element. The dampening component includes a first end portion including a plurality of slits. The first end portion is disposed within the first extended hollow section to frictionally couple the first end portion to the first extended hollow section.
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公开(公告)号：US20180291976A1
公开(公告)日：2018-10-11
申请号：US15481507
申请日：2017-04-07
Applicant: General Electric Company
Inventor： Charles Erklin Seeley , Walter John Smith , Suryarghya Chakrabarti , Andrew Joseph Wickersham
Abstract: Dampers and a fuel delivery systems including such dampers are disclosed. The damper includes a first component and a dampening component. The first component is coupled to a first tubular element and includes a first extended hollow section. The dampening component is coupled to a second tubular element. The dampening component includes a first end portion including a plurality of slits. The first end portion is disposed within the first extended hollow section to frictionally couple the first end portion to the first extended hollow section.
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Patent Agency Ranking
公开(公告)号：US12043368B2
公开(公告)日：2024-07-23
申请号：US17656109
申请日：2022-03-23
Applicant: General Electric Company
Inventor： Suryarghya Chakrabarti , Drew M. Capps , Nicholas M. Daggett , Gary W. Bryant
CPC classification number: B64C11/008 , F04D29/668 , F05D2260/96
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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公开(公告)号：US11858615B2
公开(公告)日：2024-01-02
申请号：US17647561
申请日：2022-01-10
Applicant: General Electric Company
Inventor： Kevin E. Turner , Suryarghya Chakrabarti , Drew M. Capps
CPC classification number: B64C11/24 , B64C21/08 , F01D5/18 , F01D5/182 , F01D5/183 , F02K3/06 , F05D2240/306
Abstract: A rotating airfoil assembly including a rotation axis and a plurality of rotating airfoils configured to rotate about the rotation axis. Each rotating airfoil of the rotating airfoils includes a leading edge, a trailing edge, a suction surface between the leading edge and the trailing edge, and a pressure surface between the leading edge and the trailing edge. The suction surface and the pressure surface are positioned on opposite sides of the rotating airfoil such that, when airflows over the suction surface and the pressure surface of the rotating airfoil as the rotating airfoil rotates about the rotation axis, the rotating airfoil generates lift. At least one opening is located on one of the suction surface or the pressure surface. The at least one opening is configured to eject air or to draw air into the opening.
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公开(公告)号：US11536144B2
公开(公告)日：2022-12-27
申请号：US17038601
申请日：2020-09-30
Applicant: General Electric Company
Inventor： Suryarghya Chakrabarti , Jing Li , John McConnell Delvaux
IPC: F01D5/22
Abstract: A rotor blade assembly includes a first rotor blade and a second rotor blade positioned adjacent to one another. The first rotor blade and the second rotor blade each include a platform and an airfoil extending radially outward from a root coupled to the platform to a tip. The airfoil includes a part-span shroud. The part-span shroud extends from the airfoil and is disposed between the root and the tip. The part-span shroud includes a pressure side portion extending from the pressure side surface and a suction side portion extending from the suction side surface. A damper is in contact with both the part span shroud of the first rotor blade and the part span shroud of the second rotor blade at an interference joint. The damper is movable relative to the part span shroud of both the first rotor blade and the second rotor blade.
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公开(公告)号：US20220098989A1
公开(公告)日：2022-03-31
申请号：US17038601
申请日：2020-09-30
Applicant: General Electric Company
Inventor： Suryarghya Chakrabarti , Jing Li , John McConnell Delvaux
IPC: F01D5/22
Abstract: A rotor blade assembly includes a first rotor blade and a second rotor blade positioned adjacent to one another. The first rotor blade and the second rotor blade each include a platform and an airfoil extending radially outward from a root coupled to the platform to a tip. The airfoil includes a part-span shroud. The part-span shroud extends from the airfoil and is disposed between the root and the tip. The part-span shroud includes a pressure side portion extending from the pressure side surface and a suction side portion extending from the suction side surface. A damper is in contact with both the part span shroud of the first rotor blade and the part span shroud of the second rotor blade at an interference joint. The damper is movable relative to the part span shroud of both the first rotor blade and the second rotor blade.
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公开(公告)号：US20210254478A1
公开(公告)日：2021-08-19
申请号：US16794732
申请日：2020-02-19
Applicant: General Electric Company
Inventor： Suryarghya Chakrabarti , Jing Li
IPC: F01D5/26
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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