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公开(公告)号：US11221610B1
公开(公告)日：2022-01-11
申请号：US16587991
申请日：2019-09-30
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Ananda Barua , Changjie Sun , Sathyanarayanan Raghavan
IPC: G05B19/4099 , B33Y50/02 , B29C64/393
Abstract: A method and system to receive a specification defining a model of a part to be produced by an additive manufacturing (AM) process; define a design space to enclose the part and a support structure for the part, the support structure to support the part and printed with the part during the AM process; execute an iterative topology optimization(TO) based at least in part on the specification for the part and the defined design space, to generate a TO support structure that counteracts predicted gravity-based distortions during the AM process; save a record of the generated TO support structure; and transmit the record of the TO support structure to an AM controller, the AM controller to control an AM system to generate an instance of the part and the TO support structure based on the record.
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公开(公告)号：US10822972B2
公开(公告)日：2020-11-03
申请号：US14962364
申请日：2015-12-08
Applicant: General Electric Company
Inventor： Yu Mukherjee , Ananda Barua , Changjie Sun , Wenfeng Lu
Abstract: The present disclosure is directed to a shroud assembly for a gas turbine. The shroud assembly includes a casing and a shroud. The shroud includes a radially outer wall engaged with the casing. A radially inner wall integrally couples to the radially outer wall. The radially inner wall and the radially outer wall collectively define a pair of axially opposed cavities. The radially inner wall moves radially outward toward the casing when one or more gas turbine blades contact the radially inner wall.
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公开(公告)号：US10508731B2
公开(公告)日：2019-12-17
申请号：US15399291
申请日：2017-01-05
Applicant: General Electric Company
Inventor： Darren Lee Hallman , Donald Albert Bradley , Changjie Sun , Bugra Han Ertas
Abstract: A planet gear includes a pin and an annular planet gear rim. The pin has a pin radius. The pin includes a pin outer surface. The annular planet gear rim has an inner radius and an outer radius. The annular planet gear rim includes an inner surface and an outer surface. The inner surface and the pin outer surface define a clearance therebetween. The clearance is greater than 0 when a radial force is applied to the planet gear.
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公开(公告)号：US20190311758A1
公开(公告)日：2019-10-10
申请号：US15663288
申请日：2017-07-31
Applicant: General Electric Company
Inventor： Ananda Barua , Arun Karthi Subramaniyan , Changjie Sun , Daniel Jason Erno , Darren Lee Hallman
Abstract: A unit cell structure is provided. The unit cell structure includes a first section and a second section. The first section defines a first load path and includes a first plurality of first unit cells joined together. The second section defines a second load path separate from the first load path and includes a second plurality of second unit cells joined together, each second unit cell of the second plurality of second unit cells nested within and spaced apart from each first unit cell of the first plurality of first unit cells of the first section.
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公开(公告)号：US10087772B2
公开(公告)日：2018-10-02
申请号：US14977098
申请日：2015-12-21
Applicant: General Electric Company
Inventor： Changjie Sun , Yu Xie Mukherjee , Bhaskar Nanda Mondal , Atanu Saha , Marcia Boyle Johnson , Wenfeng Lu
Abstract: The turbomachine includes a rotatable member defining an axis of rotation and an inner annular casing extending circumferentially over at least a portion of the rotatable member. The inner annular casing includes a radially outer surface. The turbomachine further includes an outer annular casing extending over at least a portion of the inner annular casing. The inner annular casing and the outer annular casing define a plurality of cavities therebetween. The clearance control system includes a manifold system including a plurality of conduits extending circumferentially about the inner annular casing and disposed within the cavities. The clearance control system also includes an impingement system extending circumferentially about the inner annular casing and disposed within the cavities. The conduits are configured to channel a flow of cooling fluid to the impingement system which is configured to channel the cooling fluid to the radially outer surface of the inner annular casing.
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Patent Agency Ranking
公开(公告)号：US20180087515A1
公开(公告)日：2018-03-29
申请号：US15278860
申请日：2016-09-28
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate , Larry Steven Rosenzweig , Sathyanarayanan Raghavan , Changjie Sun , Ananda Barua , Jinjie Shi
CPC classification number: F04D29/023 , C23C4/11 , C23C4/134 , C23C30/00 , F01D5/284 , F01D5/288 , F02C3/06 , F04D29/324 , F05D2230/312 , F05D2230/90 , F05D2240/303 , F05D2240/307 , F05D2300/2118 , F05D2300/501 , F05D2300/506 , F05D2300/611 , Y02T50/672
Abstract: Coating systems for components of a gas turbine engine, such as a compressor blade tip, are provided. The coating system can include a ceramic material disposed along the compressor blade tip and may be used with a bare compressor casing. The ceramic coating is harder than the bare compressor casing and can reduce the rub ratio thereby increasing the lifetime of the compressor blades. Methods are also provided for applying the coating system onto a compressor blade.
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公开(公告)号：US20240240571A1
公开(公告)日：2024-07-18
申请号：US18155118
申请日：2023-01-17
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Kishore Ramakrishnan , William Dwight Gerstler , Changjie Sun , Lana Maria Osusky
CPC classification number: F01D25/12 , F01D9/041 , F01D25/04 , F05D2220/32 , F05D2240/12 , F05D2260/202 , F05D2260/96
Abstract: Airfoil include a body extending along a spanwise direction between a root end and a tip end, the body comprising a plurality of acoustic cavities each having an inlet on the airfoil; and at least one cooling channel having an inlet section an outlet section and a middle section within the airfoil extending between the inlet section and the outlet section; and at least one porous face sheet positioned on at least one inlet of the plurality of acoustic cavities.
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公开(公告)号：US11988103B2
公开(公告)日：2024-05-21
申请号：US17511866
申请日：2021-10-27
Applicant: General Electric Company
Inventor： Li Zheng , Nicholas Joseph Kray , Changjie Sun
CPC classification number: F01D25/005 , F01D5/14 , F01D5/28 , F05D2220/32 , F05D2230/60
Abstract: An airfoil for a fan section of a turbine engine may include a fan blade or an outlet guide vane formed of a first material, and an edge guard disposed about an edge of the fan blade. The edge guard may include a matrix composite that has a toughness that is greater than a toughness of the first material. The airfoil may include a fan blade or an outlet guide vane. The first material of the airfoil may include a metal alloy and/or a matrix composite. A method of manufacturing an airfoil for a fan section of a turbine engine may include manufacturing an edge guard, attaching the edge guard to the airfoil.
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公开(公告)号：US20230260687A1
公开(公告)日：2023-08-17
申请号：US17670836
申请日：2022-02-14
Applicant: General Electric Company
Inventor： Wanming Zhang , Ananda Barua , Shenyan Huang , Changjie Sun , Vandana Prabhakar Rallabandi , Anthony Joseph Vinciquerra , Min Zou
CPC classification number: H01F1/24 , C22C19/00 , H01F1/1475 , C22C2202/02
Abstract: Methods for manufacturing dual phase soft magnetic components include combining a plurality of soft ferromagnetic particles with a plurality of paramagnetic particles to form a component structure, wherein the plurality of soft ferromagnetic particles each comprise an electrically insulative coating, and, heat treating the component structure to consolidate the plurality of soft ferromagnetic particles with the plurality of paramagnetic particles.
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公开(公告)号：US11639685B1
公开(公告)日：2023-05-02
申请号：US17537223
申请日：2021-11-29
Applicant: General Electric Company
Inventor： Li Zheng , Nicholas J. Kray , Changjie Sun
Abstract: Blades including integrated damping structures are disclosed herein. An airfoil to be disposed within a flow path of a gas turbine engine, the gas turbine engine defining an axial axis, a radial axis and a circumferential axis comprising an airfoil body including a first face, a second face and a recessed portion formed in the second face, and an airfoil cap having a first surface, the airfoil cap disposed within the recessed portion, the first surface substantially flush with the second face.
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