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公开(公告)号：US09970302B2
公开(公告)日：2018-05-15
申请号：US14739944
申请日：2015-06-15
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy , Srikanth Chandrudu Kottilingam , Carlos Miguel Miranda , Gary Michael Itzel
CPC classification number: F01D5/187 , F01D5/147 , F01D5/186 , F01D5/288 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/122 , F05D2240/304 , F05D2240/305 , F05D2240/306 , F05D2260/202 , F05D2260/204 , Y02T50/672 , Y02T50/676
Abstract: A hot gas path component includes a substrate having an outer surface and an inner surface. The inner surface defines an interior space. The outer surface defines a pressure side surface and a suction side surface. The pressure and suction side surfaces are joined together at a leading edge and at a trailing edge. A first cooling passage is formed in the suction side surface of the substrate. It is coupled in flow communication to the interior space. A second cooling passage, separate from the first cooling passage, is formed in the pressure side surface. The second cooling passage is coupled in flow communication to the interior space. A cover is disposed over at least a portion of the first and second cooling passages. The interior space channels a cooling fluid to the first and second cooling passages, which channel the cooling fluid therethrough to remove heat from the component.
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公开(公告)号：US20180119570A1
公开(公告)日：2018-05-03
申请号：US15342185
申请日：2016-11-03
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy , Christopher Donald Porter , David Edward Schick , Lyndsay Marie Kibler
CPC classification number: F01D25/12 , F01D5/187 , F01D11/08 , F02C3/04 , F05D2230/22 , F05D2230/50 , F05D2240/11 , F05D2240/128 , F05D2240/30 , F05D2240/81 , F05D2250/71 , F05D2260/204 , F05D2260/2214
Abstract: A cooled structure of a gas turbine engine has a main body with a leading edge, a trailing edge, a first side portion, a second side portion, and a cavity. A first set of cooling air micro-channels extends from the cavity and is arranged along the first side portion. A second set of cooling air micro-channels extends from the cavity and is arranged along the second side portion. The first and second set of cooling air micro-channels have turning portions positioned adjacent each other and interwoven exhaust ends originating from each opposing side micro-channel. Each interwoven exhaust end extends around the opposing turning portion and is configured to exhaust cooling air from a plurality of exhaust ports positioned generally radially outward from the turning portions.
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公开(公告)号：US09897006B2
公开(公告)日：2018-02-20
申请号：US14739727
申请日：2015-06-15
Applicant: General Electric Company
Inventor： Carlos Miguel Miranda , Benjamin Paul Lacy
CPC classification number: F02C7/18 , F01D5/187 , F01D5/188 , F02C3/04 , F02C7/052 , F05D2240/81 , F05D2260/202 , F05D2260/204 , F05D2260/607 , Y02T50/672 , Y02T50/676
Abstract: A cooling system for a hot gas path component includes a substrate having an outer surface and an inner surface. The inner surface defines at least one interior space. A passage is formed in the substrate between the outer surface and the inner surface. An access passage is formed in the substrate and extends from the outer surface to the inner space. The access passage is formed at a first acute angle to the passage and includes a particle collection chamber. The access passage is configured to channel a cooling fluid to the passage. Furthermore, the passage is configured to channel the cooling fluid therethrough to cool the substrate.
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公开(公告)号：US20170334188A1
公开(公告)日：2017-11-23
申请号：US15661126
申请日：2017-07-27
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy , Srikanth Chandrudu Kottilingam , Christopher Donald Porter , David Edward Schick
CPC classification number: B33Y80/00 , B22F3/1055 , B22F5/009 , B22F7/062 , B22F2999/00 , B33Y10/00 , F01D5/225 , F01D11/24 , F01D25/12 , F05D2230/31 , F05D2230/51 , F05D2240/11 , F05D2240/81 , F05D2260/202 , Y02P10/295 , B22F2203/05
Abstract: Various embodiments of the disclosure include a turbomachine component. and methods of forming such a component. Some embodiments include a turbomachine component including: a first portion including at least one of a stainless steel or an alloy steel; and a second portion joined with the first portion, the second portion including a nickel alloy including an arced cooling feature extending therethrough, the second portion having a thermal expansion coefficient substantially similar to a thermal expansion coefficient of the first portion, wherein the arced cooling feature is located within the second portion to direct a portion of a coolant to a leakage area of the turbomachine component.
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公开(公告)号：US09796048B2
公开(公告)日：2017-10-24
申请号：US14472483
申请日：2014-08-29
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Benjamin Paul Lacy , Ariel Caesar Prepena Jacala , Srikanth Chandrudu Kottilingam , David Edward Schick
IPC: B23K26/342 , B28B1/00 , F28F13/06 , B33Y80/00 , F28F3/02 , F28F3/04 , F28F13/08 , F01D5/18 , F01D9/06 , B22F3/105 , B22F7/00 , C22C1/04 , C22C33/02 , B23K101/00
CPC classification number: B23K26/342 , B22F3/1055 , B22F7/004 , B22F2999/00 , B23K2101/001 , B28B1/001 , B33Y80/00 , C22C1/0433 , C22C33/0285 , F01D5/187 , F01D9/065 , F05D2240/80 , F05D2260/2212 , F28F3/022 , F28F3/04 , F28F13/06 , F28F13/08 , Y02P10/295 , B22F3/1115
Abstract: An article and a process of producing an article are provided. The article includes a base material, a cooling feature arrangement positioned on the base material, the cooling feature arrangement including an additive-structured material, and a cover material. The cooling feature arrangement is between the base material and the cover material. The process of producing the article includes manufacturing a cooling feature arrangement by an additive manufacturing technique, and then positioning the cooling feature arrangement between a base material and a cover material.
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Patent Agency Ranking
46.发明申请公开(公告)号：US20170260873A1
公开(公告)日：2017-09-14
申请号：US15066794
申请日：2016-03-10
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy , Marc Lionel Benjamin , San Jason Nguyen
CPC classification number: F01D25/12 , F01D11/005 , F01D11/04 , F01D11/08 , F01D11/24 , F01D25/246 , F05D2220/32 , F05D2230/10 , F05D2240/11 , F05D2240/81 , F05D2250/12 , F05D2250/185 , F05D2260/201 , F05D2260/202 , F05D2260/204 , Y02T50/676
Abstract: A host gas flow path component includes a body including a leading edge, a trailing edge, a first side edge, a second side edge, and a pair of opposed lateral sides. A first lateral side is configured to interface with a cavity having a cooling fluid. The hot gas flow path component includes a supply channel disposed within the body and extending from the cavity to adjacent the leading edge or the trailing edge. The hot gas flow path component includes a channel disposed within the body adjacent the trailing edge or the leading edge. The channel extends across the body in a direction from the first side edge toward the second side edge. The channel is configured to receive the cooling fluid from the cavity to cool the trailing edge or the leading edge via an intermediate channel extending between the supply channel and the channel.
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公开(公告)号：US20170176012A1
公开(公告)日：2017-06-22
申请号：US14977979
申请日：2015-12-22
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy
CPC classification number: F01D25/12 , F01D5/185 , F01D9/023 , F01D9/041 , F01D9/065 , F02C3/04 , F02C3/14 , F02C7/222 , F02C7/224 , F05D2220/32 , F05D2240/123 , F05D2240/124 , F05D2240/35 , F05D2260/202 , F05D2260/232 , F05D2260/601 , F23R3/20 , F23R3/34
Abstract: A gas turbine that includes a row of circumferentially spaced stator blades in a turbine. Each of the stator blades may include an airfoil defined between a concave pressure side face and a laterally opposed convex suction side face. At least one of the stator blades within the row may include a fuel injector that includes: a transverse nozzle extending through the airfoil between an inlet formed through the pressure side face and an outlet formed through the suction side face of the airfoil; and a fuel channel formed through the airfoil of the stator blade, the fuel channel having an upstream end, at which an inlet port fluidly connects the fuel channel to a fuel supply, and a downstream end, at which an outlet port fluidly connects the fuel channel to the transverse nozzle.
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48.发明申请公开(公告)号：US20170175576A1
公开(公告)日：2017-06-22
申请号：US14971724
申请日：2015-12-16
Applicant: General Electric Company
Inventor： Marc Lionel Benjamin , Gregory Thomas Foster , Benjamin Paul Lacy , Thomas James Brunt , San Jason Nguyen
CPC classification number: F01D25/12 , F01D9/04 , F01D11/12 , F01D11/24 , F01D25/14 , F01D25/246 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2230/12 , F05D2230/237 , F05D2240/11 , F05D2240/35 , F05D2250/14 , F05D2260/204 , Y02T50/676
Abstract: A shroud segment for use in gas turbines, includes a body, leading edge, trailing edge, a first and second side edge, and a pair of opposed lateral sides between the leading and trailing edges and the first and second side edges. A first lateral side of the lateral sides interface with a cavity having a cooling fluid. A second lateral side interfaces with a hot gas flow path. A first channel disposed within the body includes a first and second end portion. A second channel is disposed within the body includes a third and fourth end portion. The first and second channels receive the cooling fluid from the cavity to cool the body. The first and fourth end portion have portions with free ends having a width greater than an adjacent portion coupled to the free end.
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公开(公告)号：US20170175575A1
公开(公告)日：2017-06-22
申请号：US14971674
申请日：2015-12-16
Applicant: General Electric Company
CPC classification number: F01D25/12 , F01D9/04 , F01D11/24 , F01D25/14 , F01D25/24 , F01D25/246 , F02C3/04 , F02C7/12 , F02C7/18 , F04D29/522 , F04D29/584 , F05D2220/32 , F05D2230/12 , F05D2230/237 , F05D2240/11 , F05D2240/24 , F05D2240/35 , F05D2260/204 , Y02T50/676
Abstract: A system includes a shroud segment for use in a turbine and includes a body having a leading and trailing edge, first and second side edge, and a pair of opposed lateral sides between the leading and trailing edges and the first and second side edges. A first lateral side interfaces with a cavity having a cooling fluid. A first channel includes a first and second end portion. A second channel includes a third end portion and a fourth end portion. The first and second channels receive the cooling fluid from the cavity to cool the body. The second end portion includes a first segmented channel with first metering feature and the third end portion includes a second segmented channel with second exit feature. The first and second exit features meter a flow of the cooling fluid within the first and second channels.
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公开(公告)号：US20170101891A1
公开(公告)日：2017-04-13
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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