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公开(公告)号：US20240229648A9
公开(公告)日：2024-07-11
申请号：US17973198
申请日：2022-10-25
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Ananda Barua , Changjie Sun , Christopher Edward Wolfe , John Matthew Sassatelli
CPC classification number: F01D5/005 , B23P6/007 , F05D2230/10 , F05D2230/22
Abstract: A method of manufacturing an erosion-shielded turbine blade includes providing a turbine blade for use with a rotary machine. The turbine blade includes an airfoil extending between a root and a tip. The airfoil includes a pressure side and an opposite suction side, and each of the pressure and suction sides extends between a leading edge and a trailing edge. The method also includes printing a green body part by an additive manufacturing process by selectively depositing a binder solution across a particulate erosion-resistant material, and sintering the green body part to produce a post-sintering erosion shield that includes densified erosion-resistant material. The method also includes coupling the erosion shield to the leading edge of the turbine blade.
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公开(公告)号：US20230228219A1
公开(公告)日：2023-07-20
申请号：US17578062
申请日：2022-01-18
Applicant: General Electric Company
Inventor： Li Zheng , Nicholas J. Kray , Changjie Sun , Thomas Malkus , Giridhar Jothiprasad , Mitchell J. Headley
CPC classification number: F02C9/18 , F01D17/105 , F02C6/08 , F02K3/075 , F16K1/2007 , F16K1/2021 , F05D2220/32 , F05D2270/62 , F05D2270/64 , F05D2270/65
Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed for a variable bleed valve assembly. An example variable bleed valve assembly a variable bleed valve (VBV) door corresponding to a bleed port and a first unison ring, the VBV door coupled to the first unison ring, the first unison ring to move in a circumferential direction between a first position and a second position causing the VBV door to move between the first position and the second position.
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公开(公告)号：US20230184117A1
公开(公告)日：2023-06-15
申请号：US17550791
申请日：2021-12-14
Applicant: General Electric Company
Inventor： Li Zheng , Nicholas J. Kray , Changjie Sun
IPC: F01D5/16 , F16F15/173
CPC classification number: F01D5/16 , F16F15/173 , F16F2232/02 , F16F2236/106 , F16F2222/08 , F16F2224/041 , F05D2220/36
Abstract: Airfoil vibration damping apparatus are disclosed. An example apparatus includes a metallic airfoil including a cavity, and a dilatant material disposed in the cavity to dampen vibrations of the metallic airfoil.
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公开(公告)号：US20230175416A1
公开(公告)日：2023-06-08
申请号：US17542228
申请日：2021-12-03
Applicant: General Electric Company
Inventor： Li Zheng , Nicholas J. Kray , Changjie Sun
CPC classification number: F01D25/02 , F01D11/006 , F05D2240/55 , F05D2260/30 , F05D2260/606
Abstract: Methods, apparatus, systems, and articles of manufacture for deicing fan blades are disclosed. An example apparatus to de-ice a fan blade includes a fan cone including a cavity to hold pressurized hot air, the fan cone including a fan disk in the cavity, the fan disk coupled to the fan blade, and a dovetail seal coupled to the fan disk, the dovetail seal including at least one first hole, wherein the at least one first hole corresponds to at least one second hole in a root of the fan blade.
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公开(公告)号：US11655828B2
公开(公告)日：2023-05-23
申请号：US17511850
申请日：2021-10-27
Applicant: General Electric Company
Inventor： Li Zheng , Nicholas Joseph Kray , Changjie Sun
CPC classification number: F04D29/584 , F01D25/02 , F02C3/00 , F05D2220/323
Abstract: An airfoil for a fan section of a turbine engine may include a fan blade or an outlet guide vane, and an edge guard attached thereto. The edge guard may include a heating conduit disposed within at least a portion of the edge guard. An anti-icing system for a plurality of fan blades or outlet guide vanes may include a fluid supply pathway configured to supply heating fluid to respective ones of a plurality of heating conduits within the edge guards attached to respective ones of a plurality of fan blades and/or to a plurality of outlet guide vanes. The heating fluid may include bleed air from a core air flowpath. A method of inhibiting icing on an airfoil may include flowing a heating fluid into a heating conduit disposed within an edge guard attached to the airfoil and heating the edge guard with the heating fluid.
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Patent Agency Ranking
公开(公告)号：US11314231B2
公开(公告)日：2022-04-26
申请号：US15702040
申请日：2017-09-12
Applicant: General Electric Company
Inventor： Ananda Barua , Sathyanarayanan Raghavan , Arun Karthi Subramaniyan , Changjie Sun , Arvind Rangarajan
IPC: B33Y50/02 , B29C64/40 , G05B19/4099 , B23K26/342 , B29C64/393 , G06F30/20 , B33Y10/00 , B33Y30/00 , G06F119/08 , G06F119/02
Abstract: An industrial asset item definition data store may contain at least one electronic record defining the industrial asset item. An automated support structure creation platform may include a support structure optimization computer processor. The automated support structure optimization computer processor may be adapted to automatically create support structure geometry data associated with an additive printing process for the industrial asset item. The creation may be performed via an iterative loop between a build process simulation engine and a topology optimization engine.
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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：US10832753B2
公开(公告)日：2020-11-10
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
IPC: G11C11/22 , G11C11/41 , H01L27/02 , H01M8/04 , H05K1/02 , B29C64/20 , B29C64/153 , B33Y80/00 , B33Y10/00 , B33Y30/00 , B22F3/105 , B29C64/00 , B22F5/10
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：US10458254B2
公开(公告)日：2019-10-29
申请号：US15353101
申请日：2016-11-16
Applicant: General Electric Company
Inventor： Sathyanarayanan Raghavan , Neelesh Nandkumar Sarawate , Kenneth Martin Lewis , Larry Steven Rosenzweig , Changjie Sun , Ananda Barua
Abstract: Coating systems for components of a gas turbine engine, such as a compressor blade tip, are provided. The coating system can include an abradable material disposed along the compressor blade tip and may be used with a bare compressor casing. The abradable coating is softer than the compressor casing and can reduce the overall rub ratio thereby increasing the lifetime of the compressor blade and casing. Methods are also provided for applying the coating system onto a compressor blade.
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公开(公告)号：US10385865B2
公开(公告)日：2019-08-20
申请号：US15063089
申请日：2016-03-07
Applicant: General Electric Company
Inventor： Sathyanarayanan Raghavan , Neelesh Nandkumar Sarawate , Kenneth Martin Lewis , Changjie Sun , Ananda Barua
Abstract: An airfoil for use in a turbomachine includes a pressure sidewall and a suction sidewall coupled to the pressure sidewall. The suction sidewall and the pressure sidewall define a leading edge and an opposite trailing edge. The leading edge and the trailing edge define a chord distance. The airfoil further includes a root portion, and a tip portion. The tip portion extends between the pressure sidewall and the suction sidewall such that the tip portion is substantially perpendicular to each sidewall. The tip portion includes at least one planar section and at least one oblique section that forms a recess within the tip portion. The at least one oblique section extends from the at least one planar section towards the root portion along the chord distance. The tip portion is configured to reduce airfoil wear during contact with a surrounding casing.
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