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公开(公告)号：US10260363B2
公开(公告)日：2019-04-16
申请号：US15372642
申请日：2016-12-08
Applicant: General Electric Company
Inventor： Zachary John Snider , Sandip Dutta , Kassy Moy Hart
Abstract: Aspects of the disclosure include a sealing insert, turbine component, and code for manufacturing a sealing insert. A sealing insert includes at least one insert wall for insertion proximate a component wall to define a space between the at least one insert wall and the component wall. At least one compressible seal is provided between the at least one insert wall and the component wall. The compressible seal or seals divide the space into a plurality of compartments.
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公开(公告)号：US10138743B2
公开(公告)日：2018-11-27
申请号：US15176208
申请日：2016-06-08
Applicant: General Electric Company
Inventor： Sandip Dutta
Abstract: The present disclosure is directed to an impingement cooling system for a gas turbine engine having a gas turbine engine component and an insert positioned within the gas turbine engine component. The insert includes an insert body that defines an inner cavity therein, a first impingement aperture, a first heat exchanger inlet aperture, and a first heat exchanger outlet aperture. A first baffle extends outwardly from an outer surface of the insert body. The first baffle, the gas turbine engine component, and the insert body define a first and a second cooling chamber therebetween. The first impingement aperture fluidly couples the inner cavity of the insert body and the first cooling chamber. A first heat exchanger wall couples to an inner surface of the insert body. The first heat exchanger wall and the insert body define a first heat exchanger chamber therebetween.
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公开(公告)号：US09849510B2
公开(公告)日：2017-12-26
申请号：US14688436
申请日：2015-04-16
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: B22F3/1055 , B22F5/009 , B22F5/04 , B22F5/10 , B22F2005/005 , B22F2998/10 , B23K15/0086 , B23K26/34 , B23K26/342 , B23K2101/001 , B33Y10/00 , B33Y80/00 , Y02P10/295 , B22F3/15
Abstract: Provided are an article and a method of forming an article. The method includes providing a metallic powder, heating the metallic powder to a temperature sufficient to joint at least a portion of the metallic powder to form an initial layer, sequentially forming additional layers in a build direction by providing a distributed layer of the metallic powder over the initial layer and heating the distributed layer of the metallic powder, repeating the steps of sequentially forming the additional layers in the build direction to form a portion of the article having a hollow space formed in the build direction, and forming an overhang feature extending into the hollow space. The article includes an article formed by the method described herein.
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公开(公告)号：US20170226892A1
公开(公告)日：2017-08-10
申请号：US15016498
申请日：2016-02-05
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy , David Edward Schick , Sandip Dutta
CPC classification number: F01D5/189 , F01D5/041 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2230/22 , F05D2230/30 , F05D2240/126 , F05D2240/128 , F05D2240/30 , F05D2260/201 , F05D2260/2214 , F05D2300/17 , F05D2300/171 , Y02T50/673 , Y02T50/676
Abstract: A system having an impingement sleeve configured to receive a cooling flow is provided. The impingement sleeve includes a column of ports extending from an outer surface of the impingement sleeve, wherein each port of the column of ports is configured to direct an impingement stream toward a heated structure, and each impingement stream includes a portion of the cooling flow. Further, one or more pins are disposed outside the outer surface relative to the cooling flow, wherein each pin of the one or more pins is coupled between pairs of ports of the column of ports.
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公开(公告)号：US11319816B2
公开(公告)日：2022-05-03
申请号：US16787819
申请日：2020-02-11
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sandip Dutta , James Zhang , Gary Michael Itzel , John McConnell Delvaux , Matthew Troy Hafner
Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. A plurality of axial cooling channels in the trailing edge portion of the airfoil are arranged to permit axial flow of a cooling fluid from an interior of the turbine component at the trailing edge portion to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a trailing edge portion with axial cooling channels. The axial cooling channels are arranged to permit axial flow of a cooling fluid from an interior to an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.
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Patent Agency Ranking
公开(公告)号：US10851663B2
公开(公告)日：2020-12-01
申请号：US15619600
申请日：2017-06-12
Applicant: General Electric Company
Inventor： Sandip Dutta , Joseph Anthony Weber
Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil defining a passage extending from a root to a tip of the airfoil. The passage includes a first passage portion and a second passage portion. The first passage portion has a greater diameter than the second passage portion. The rotor blade also includes a first tube positioned within the first passage portion. The first tube is spaced apart from the airfoil. The rotor blade further includes a second tube positioned within the first passage portion. The second tube is positioned between the airfoil and the first tube. Furthermore, the rotor blade includes a plurality of inserts positioned within the first passage portion. The plurality of inserts is positioned between and in contact with the first and second tubes.
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公开(公告)号：US10392945B2
公开(公告)日：2019-08-27
申请号：US15599912
申请日：2017-05-19
Applicant: General Electric Company
Inventor： Sandip Dutta , Scott Francis Johnson , Joseph Anthony Weber
Abstract: The present disclosure is directed to a cooling system for a turbomachine. The cooling system includes a turbomachine component defining a turbomachine component cavity. The cooling system also includes an insert positioned within the turbomachine component cavity for cooling the turbomachine component. The insert includes an insert body and a spring body. The spring body includes a first portion fixedly coupled to the insert body, a second portion in sliding engagement with the turbomachine component, and a third portion in sliding engagement with the insert body.
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公开(公告)号：US10309227B2
公开(公告)日：2019-06-04
申请号：US15334563
申请日：2016-10-26
Applicant: General Electric Company
Inventor： David Wayne Weber , Sandip Dutta
Abstract: A trailing edge cooling system for a turbine blade is disclosed. The system may include a cooling circuit including an outward leg, and a return leg positioned adjacent the outward leg. The outward and return leg each may extend toward and away, respectively, from a trailing edge of the turbine blade. The cooling circuit may also include a plurality of turn legs. The plurality of turn legs may include a turn leg positioned directly adjacent the trailing edge of the turbine blade, and a distinct turn leg positioned axially adjacent the turn leg, and opposite the trailing edge of the turbine blade. The distinct turn leg may be oriented non-parallel to at least one of the outward leg and the return leg.
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公开(公告)号：US10300530B2
公开(公告)日：2019-05-28
申请号：US15405668
申请日：2017-01-13
Applicant: General Electric Company
Inventor： Kassy Moy Hart , Sandip Dutta , Srikanth Chandrudu Kottilingam , David Edward Schick
IPC: B22F3/105 , B33Y30/00 , B33Y50/02 , B23K26/70 , B29C64/153 , B23K101/00 , B29C64/25 , B29C64/364 , B33Y10/00 , B29C64/245
Abstract: This disclosure provides systems and tooling for cooling components during additive manufacturing. A build plate supports layers of powdered materials as they are positioned and selectively fused to create the component. The build plate defines a build surface and the build surface retracts in a working direction opposite a build direction for the component. At least one vertical cooling structure is provided perpendicular to the build plate and protruding from the build plate as the build surface retracts. The vertical cooling structure cools at least a portion of the component through unfused powdered materials between the vertical cooling structure and the component.
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公开(公告)号：US10253986B2
公开(公告)日：2019-04-09
申请号：US14847347
申请日：2015-09-08
Applicant: GENERAL ELECTRIC COMPANY
IPC: F01D25/12 , F01D5/18 , F23R3/06 , B22F3/105 , B22F5/00 , B33Y10/00 , B33Y80/00 , B22F5/04 , B22F5/10
Abstract: A cooling article and method of forming a cooling article are provided. The cooling article includes a body portion separating an inner region and an outer region, an aperture in the body portion, the aperture fluidly connecting the inner region to the outer region, and a cooling feature extending away from an outer surface of the body portion. The cooling feature disturbs fluid flow in the outer region. The method of forming a cooling article includes forming a body portion defining an inner region and an outer region, forming an aperture in the body portion, the aperture fluidly connecting the inner region to the outer region, and forming a cooling feature extending away from an outer surface of the body portion. The cooling article is arranged and disposed for insertion within a hot gas path component of a turbine engine.
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