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公开(公告)号：US20180163555A1
公开(公告)日：2018-06-14
申请号：US15372642
申请日：2016-12-08
Applicant: General Electric Company
Inventor： Zachary John Snider , Sandip Dutta , Kassy Moy Hart
CPC classification number: F01D11/003 , B22F3/1055 , F01D5/18 , F01D5/189 , F01D9/02 , F01D25/12 , F05D2220/32 , F05D2230/22 , F05D2230/234 , F05D2240/55 , F05D2250/75 , F05D2260/201 , F05D2260/30 , F16J15/0887 , F16J15/0893 , Y02T50/676
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：US20180149028A1
公开(公告)日：2018-05-31
申请号：US15364710
申请日：2016-11-30
Applicant: General Electric Company
Inventor： Sandip Dutta , Benjamin Paul Lacy , Gary Michael Itzel , Zachary John Snider
CPC classification number: F01D9/065 , F01D5/189 , F01D11/08 , F01D25/14 , F05D2220/30 , F05D2260/201 , F05D2260/22141 , F05D2260/30
Abstract: The present disclosure is directed to a gas turbine engine that includes a hot gas path component having an inner surface and defining a hot gas path component cavity. An impingement insert is positioned within the hot gas path component cavity. The impingement insert includes an inner surface and an outer surface and defines an impingement insert cavity and a plurality of impingement apertures fluidly coupling the impingement insert cavity and the hot gas path component cavity. A plurality of pins extends from the outer surface of the impingement insert to the inner surface of the hot gas path component.
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公开(公告)号：US20170356299A1
公开(公告)日：2017-12-14
申请号：US15177370
申请日：2016-06-09
Applicant: General Electric Company
Inventor： Sandip Dutta , Kassy Moy Hart
CPC classification number: F01D5/189 , F01D9/065 , F01D11/24 , F05D2240/11 , F05D2250/232 , F05D2250/323 , F05D2250/324 , F05D2260/201
Abstract: The present disclosure is directed to an impingement insert for a gas turbine engine. The impingement insert includes an insert wall having an inner surface and an outer surface spaced apart from the inner surface. A nozzle extends outwardly from the outer surface of the insert wall. The nozzle includes an outer surface and a circumferential surface. The insert wall and the nozzle collectively define a cooling passage extending from the inner surface of the insert wall to the outer surface of the nozzle. The cooling passage includes an inlet portion, a throat portion, a converging portion extending from the inlet portion to the throat portion, an outlet portion, and a diverging portion extending from the throat portion to the outlet portion. The cooling passage further includes a cross-sectional shape having a semicircular portion and a non-circular portion.
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公开(公告)号：US20170101890A1
公开(公告)日：2017-04-13
申请号：US14880565
申请日：2015-10-12
Applicant: General Electric Company
Inventor： Sandip Dutta , Benjamin Paul Lacy , Joseph Anthony Weber , Peter Galen Stevens
CPC classification number: F01D25/12 , F01D9/041 , F02C3/04 , F02C7/12 , F05D2220/32 , F05D2240/128 , F05D2240/35 , F05D2240/81 , F05D2260/204 , F05D2260/221 , Y02T50/676
Abstract: A turbine nozzle includes an airfoil that extends in span from an inner band to an outer band where the inner band and the outer band define outer flow boundaries of the turbine nozzle. The inner band includes a gas side surface that is at least partially covered by one or more inner plates. The inner band also includes a plurality of cooling channels formed within the gas side surface beneath the one or more inner plates. The outer band includes a gas side surface that is at least partially covered by one or more outer plates. The outer band comprises a plurality of cooling channels formed within the gas side surface beneath the one or more outer plates.
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公开(公告)号：US10655477B2
公开(公告)日：2020-05-19
申请号：US15219804
申请日：2016-07-26
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sandip Dutta , Benjamin Paul Lacy , Gary Michael Itzel , Joseph Anthony Weber , David Edward Schick
Abstract: Turbine components are disclosed including a component wall defining a constrained portion, a manifold having an impingement wall, and a post-impingement cavity disposed between the manifold and the component wall. The impingement wall includes a wall thickness and defines a plenum and a tapered portion. The tapered portion tapers toward the constrained portion and includes a plurality of impingement apertures and a wall inflection. The wall inflection is disposed proximal to the constrained portion, and the tapered portion is integrally formed as a single, continuous object. The wall inflection may include an inflection radius of less than about 3 times the wall thickness of the impingement wall, or the tapered portion may include a consolidated portion with the impingement wall extending across the plenum. A method for forming the turbine component is also disclosed, including forming the tapered portion as a single, continuous tapered portion by an additive manufacturing technique.
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Patent Agency Ranking
公开(公告)号：US10590776B2
公开(公告)日：2020-03-17
申请号：US15174332
申请日：2016-06-06
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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公开(公告)号：US10450875B2
公开(公告)日：2019-10-22
申请号：US15334585
申请日：2016-10-26
Applicant: General Electric Company
Inventor： David Wayne Weber , Sandip Dutta , Brendon James Leary
IPC: F01D5/18
Abstract: Various geometries for a trailing edge cooling system for a turbine blade. The trailing edge cooling system may include a plurality of cooling circuits extending at least partially along a radial length of a trailing edge of the turbine blade. Each cooling circuit may include an outward leg extending axially toward the trailing edge, and a plurality of turn legs in fluid communication with the outward leg. The plurality of turn legs may be positioned adjacent the trailing edge. Each cooling circuit may also include a return leg positioned adjacent the outward leg and extending axially from the trailing edge. The return leg may include a first portion and a second portion. The first portion may have a first width, and a second may have a second width that is greater than the first width of the first portion.
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公开(公告)号：US10287894B2
公开(公告)日：2019-05-14
申请号：US15174182
申请日：2016-06-06
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sandip Dutta , James Zhang , Gary Michael Itzel , John McConnell Delvaux , Matthew Troy Hafner
IPC: F01D5/18 , B33Y10/00 , B33Y80/00 , B23K26/342 , B23K26/70 , B22F3/105 , B22F3/24 , B23K15/00 , B23K26/00 , C23C28/04 , F01D9/02 , F01D25/12 , F01D5/14 , F01D5/28 , B23K101/00 , B23K103/08
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 nested cooling channels in the trailing edge portion of the airfoil permit passage of a cooling fluid from an interior of the turbine component 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 leading edge, a trailing edge portion extending to a trailing edge, and a plurality of nested cooling channels in the trailing edge portion. Each nested cooling channel fluidly connects an interior of the turbine component with 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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公开(公告)号：US10184343B2
公开(公告)日：2019-01-22
申请号：US15016498
申请日：2016-02-05
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy , David Edward Schick , Sandip Dutta
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：US20190017392A1
公开(公告)日：2019-01-17
申请号：US15648683
申请日：2017-07-13
Applicant: General Electric Company
Inventor： Sandip Dutta , Kassy Moy Hart , Joseph Anthony Weber , Sean Patrick Gunning
Abstract: The present disclosure is directed to an impingement insert for a turbomachine. The impingement insert includes an insert body having an inner surface, an outer surface spaced apart from the inner surface, and a thickness extending from the inner surface to the outer surface. The insert body defines a first depression extending from one of the inner surface or the outer surface into the insert body. The first depression has a diameter. The insert body further defines an impingement aperture extending from the first depression through the insert body. The impingement aperture has a length and a diameter. The thickness of the insert body is greater than the length of the impingement aperture and the diameter of the first depression is greater than the diameter of the impingement aperture.
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