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公开(公告)号：US10739087B2
公开(公告)日：2020-08-11
申请号：US14847409
申请日：2015-09-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Benjamin Paul Lacy , Sandip Dutta , David Edward Schick
Abstract: An article and method of forming an article are provided. The 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 and the outer region, and a baffle extending along at least a portion of an inner surface of the article, the baffle dividing the inner region into a plurality of sub-regions. The method of forming an 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 at least one baffle extending along at least a portion of an inner surface of the body portion, the at least one baffle dividing the inner region into a plurality of sub-regions. Also provided is a component including a cooling article disposed therein.
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公开(公告)号：US10550721B2
公开(公告)日：2020-02-04
申请号：US15080201
申请日：2016-03-24
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Matthew Troy Hafner , Gary Michael Itzel , John McConnell Delvaux , Sandip Dutta
Abstract: An apparatus is disclosed including a first and second article, a first interface volume disposed between and enclosed by the first article and second article, a cooling fluid supply, and at least one cooling fluid channel in fluid communication with the cooling fluid supply and the first interface volume. The first article includes a first material composition. The second article includes a second material composition. The at least one cooling fluid channel includes a heat exchange portion disposed in at least one of the first and second article downstream of the cooling fluid supply and upstream of the first interface volume. A turbine shroud is disclosed wherein the first and second articles are an outer and inner shroud. A turbine nozzle is disclosed wherein the first and second articles are an endwall and fairing.
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公开(公告)号：US10385727B2
公开(公告)日：2019-08-20
申请号：US14880580
申请日：2015-10-12
Applicant: General Electric Company
Inventor： Sandip Dutta , Benjamin Paul Lacy , Gary Michael Itzel , James William Vehr
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 inner and outer flow boundaries of the turbine nozzle. At least one of the inner band and the outer band define a first set of cooling channels and a second set of cooling channels formed beneath a gas side surface of the corresponding inner band or outer band. The inner band or the outer band further define a coolant distribution plenum that is in fluid communication with the first and second sets of cooling channels. The coolant distribution plenum provides a stream of coolant to at least one of the first set of cooling channels and the second set of cooling channels.
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公开(公告)号：US20180334910A1
公开(公告)日：2018-11-22
申请号：US15599912
申请日：2017-05-19
Applicant: General Electric Company
Inventor： Sandip Dutta , Scott Francis Johnson , Joseph Anthony Weber
CPC classification number: F01D5/189 , F01D5/147 , F01D5/187 , F01D5/188 , F05D2250/184 , F05D2260/20 , F05D2260/201 , F05D2260/202 , F05D2260/2214 , F05D2260/38
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：US09995172B2
公开(公告)日：2018-06-12
申请号：US14880575
申请日：2015-10-12
Applicant: General Electric Company
Inventor： Sandip Dutta , Benjamin Paul Lacy , Gary Michael Itzel , Stephen Paul Wassynger
CPC classification number: F01D25/12 , F01D9/041 , F05D2220/32 , F05D2240/128 , F05D2240/81 , F05D2260/202 , F05D2260/204 , 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 inner and outer flow boundaries of the turbine nozzle. At least one of the inner band and the outer band defines a plurality of cooling channels formed and a coolant discharge plenum beneath a gas side surface of the corresponding inner or outer band that is in fluid communication with the cooling channels. The coolant discharge plenum is formed within the inner band or the outer band downstream from the cooling channels and upstream from a plurality of coolant discharge ports.
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Patent Agency Ranking
公开(公告)号：US20170356341A1
公开(公告)日：2017-12-14
申请号：US15176208
申请日：2016-06-08
Applicant: General Electric Company
Inventor： Sandip Dutta
CPC classification number: F01D9/065 , F01D5/189 , F01D25/12 , F02C3/04 , F02C7/18 , F05D2240/126 , F05D2250/141 , F05D2250/231 , F05D2260/201 , F05D2260/22141
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：US20160298545A1
公开(公告)日：2016-10-13
申请号：US14684908
申请日：2015-04-13
Applicant: General Electric Company
Inventor： Xiuzhang James Zhang , Sandip Dutta , Gary Michael Itzel
CPC classification number: F02C7/185 , F01D5/02 , F01D5/187 , F02C3/06 , F05D2220/3212 , F05D2230/11 , F05D2240/24 , F05D2240/306 , F05D2240/307 , F05D2240/35 , F05D2260/20
Abstract: A turbine airfoil includes a leading edge, a trailing edge, a root and a tip. Also included is a pressure side wall extending between the leading edge and the trailing edge and between the root and the tip. Further included is a suction side wall extending between the leading edge and the trailing edge and between the root and the tip. Yet further included is a non-circular cooling channel defined by the turbine airfoil and extending radially from the root to the tip, the non-circular cooling channel routing a cooling air to an outlet hole formed in the tip. Also included is an exhaust hole defined by the turbine airfoil and extending from the non-circular cooling channel to the suction side wall, the exhaust hole radially located between the root and the tip.
Abstract translation: 涡轮机翼片包括前缘，后缘，根部和尖端。 还包括在前缘和后缘之间以及根部和尖端之间延伸的压力侧壁。 还包括在前缘和后缘之间以及根部与尖端之间延伸的吸力侧壁。 还包括由涡轮机翼型件限定并从根部到顶端径向延伸的非圆形冷却通道，非圆形冷却通道将冷却空气引导到形成在尖端中的出口孔。 还包括由涡轮机翼型件限定并从非圆形冷却通道延伸到吸入侧壁的排气孔，排气孔位于根部和尖端之间。
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公开(公告)号：US11519281B2
公开(公告)日：2022-12-06
申请号：US17118792
申请日：2020-12-11
Applicant: General Electric Company
Inventor： Sandip Dutta , Benjamin Paul Lacy , Gary Michael Itzel , Zachary John Snider
Abstract: The present disclosure is directed to a turbomachine 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：US20210270141A1
公开(公告)日：2021-09-02
申请号：US17118792
申请日：2020-12-11
Applicant: General Electric Company
Inventor： Sandip Dutta , Benjamin Paul Lacy , Gary Michael Itzel , Zachary John Snider
Abstract: The present disclosure is directed to a turbomachine 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：US10208614B2
公开(公告)日：2019-02-19
申请号：US15054346
申请日：2016-02-26
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Matthew Troy Hafner , Gary Michael Itzel , Sandip Dutta
Abstract: Apparatuses are disclosed including a first article, a second article, a sewing member and a thermal break. The second article includes a second material composition having a second thermal tolerance greater than a first thermal tolerance of a first material composition of the first article. The sealing member is disposed between and contacts the first article and the second article, and includes a third material composition having a third thermal tolerance less than the second thermal tolerance and less than an operating temperature of the second article. The thermal break is defined by the second article, and is proximate to the sealing member and partitioned from the sealing member by a portion of the second article. The thermal break interrupts a thermal conduction path from the second article to the sealing member. The first article and the second article compress the sealing member, forming a thermal gradient-tolerant seal.
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