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公开(公告)号：US20240026791A1
公开(公告)日：2024-01-25
申请号：US18376977
申请日：2023-10-05
Applicant: GE Infrastructure Technology, LLC
Inventor： Caitlin Shea Lucking , Patrick Yerkes , Daniel J. Dorriety , Stanley Frank Simpson , Kyle J. Lewis
CPC classification number: F01D5/18 , F01D25/12 , F05D2220/30 , F05D2240/30 , F05D2260/20 , F05D2260/81
Abstract: A method for redirection of coolant flow is provided. The method includes an identifying step that identifies a hot spot on an exterior surface of a body of a component of a turbine system. A first parameter of the component indicates that a temperature of the exterior surface in the hot spot exceeds a threshold value. Another identifying step identifies a cool spot on the exterior surface. A second parameter of the component indicates that the temperature of the exterior surface in the cool spot is below the threshold value. A reconfiguring step reconfigures a plurality of cooling passages of the component to direct a portion of a coolant from the cool spot to the hot spot.
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公开(公告)号：US11859550B2
公开(公告)日：2024-01-02
申请号：US17219988
申请日：2021-04-01
Applicant: General Electric Company
Inventor： James Daniel Longhurst , Antonio C. Gominho , Jordan Paule Tesorero , Jonathan David Baldiga , Orin J. Hall
CPC classification number: F02C7/18 , F01D25/12 , F05D2220/32 , F05D2230/31 , F05D2260/201
Abstract: Accelerators, methods of manufacturing accelerators, and gas turbine engines are provided. For example, an accelerator for a gas turbine engine defines a radial direction and an axial direction and comprises an annular outer wall, an annular inner wall, an annular channel defined between the outer and inner walls, and a plurality of vanes disposed within the channel. The channel has an inlet for ingress of a cooling fluid and an outlet for egress of the cooling fluid. Each vane extends from the outer wall to the inner wall adjacent the outlet, which is angled such that an exit angle of the cooling fluid is nonzero with respect to both the radial and axial directions. The accelerator may be manufactured using an additive manufacturing method. The accelerator outlet may be disposed immediately upstream of a first turbine rotor blade stage of a gas turbine engine to direct the cooling fluid thereto.
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公开(公告)号：US11834995B2
公开(公告)日：2023-12-05
申请号：US17706814
申请日：2022-03-29
Applicant: General Electric Company
Inventor： Eyitayo James Owoeye , Scott Alan Schimmels
CPC classification number: F02C7/185 , F01D25/125 , F05D2260/213 , F05D2260/2214 , F05D2260/232 , F05D2260/606
Abstract: An air-to-air heat exchanger in flow communication with a gas turbine engine is provided. The air-to-air heat exchanger has an air-to-air heat exchanger potential defined by a product raised to a half power, the product being a heat transfer surface area density associated with the air-to-air heat exchanger multiplied by an airflow conductance factor associated with the gas turbine engine. The air-to-air heat exchanger potential is between about 6.7 and 19.5 for a bypass ratio associated with the gas turbine engine between about 3 and 10 and the heat transfer surface area density being between about 3,000 m2/m3 and 10,000 m2/m3 and is between about 2.9 and 12.2 for a bypass ratio associated with the gas turbine engine between about 10 and 20 and the heat transfer surface area density being between about 1,000 m2/m3 and 10,000 m2/m3.
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公开(公告)号：US11826830B2
公开(公告)日：2023-11-28
申请号：US16916722
申请日：2020-06-30
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sandip Dutta , Zachary Snider , Srikanth Chandrudu Kottilingam , Stephen Wassynger , Joseph Moroso
CPC classification number: B22F5/04 , B22F7/08 , F01D5/147 , F01D9/041 , F01D9/044 , F01D25/12 , B22F10/28 , F04D29/666 , F05D2220/32 , F05D2230/21 , F05D2230/22 , F05D2230/237 , F05D2230/31 , F05D2230/50 , F05D2240/128 , F05D2240/80 , F05D2240/81 , F05D2260/202 , Y02P10/25
Abstract: At least one turbine component for a gas turbine includes a base component formed by casting and an article. The base component includes a platform. The article on the upper surface of the platform is formed by additive manufacturing. The article has a proximal face sized and shaped to cover at least a portion of the upper surface of the platform of the turbine component and a contoured distal face opposite the proximal face. The contoured distal face has a contour surface serving as at least a portion of a hot gas path surface of the turbine component. The contour surface is arranged and disposed to provide a controlled flow pattern of a working fluid across the contour surface based on a clock mounting location of the turbine component in a turbine.
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公开(公告)号：US11815022B2
公开(公告)日：2023-11-14
申请号：US17882114
申请日：2022-08-05
Applicant: Raytheon Technologies Corporation
Inventor： Daniel P. Preuss , Dominic J. Mongillo, Jr. , Timothy J. Jennings
CPC classification number: F02C7/18 , F01D5/18 , F01D25/12 , F02C3/06 , F05D2220/323 , F05D2240/12 , F05D2240/30 , F05D2260/232
Abstract: A gas turbine engine includes a compressor section that provides first and second compressor stages that are configured to respectively provide first and second cooling fluids. The first compressor stage has a higher pressure than the second compressor stage. The gas turbine engine further includes a component that has platform with an internal cooling passage fed by first and second inlets that respectively receive fluid from the first and second cooling sources. The second inlet is downstream from the first inlet.
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Patent Agency Ranking
公开(公告)号：US11814974B2
公开(公告)日：2023-11-14
申请号：US17389005
申请日：2021-07-29
Applicant: Solar Turbines Incorporated
Inventor： Sudhakar Bollapragada , Xiaoqiang Zeng , Michael D. Fox , Branden R. Elam , Daniel Ryan , Karen A. Thole , Thomas M. Corbett
IPC: F01D25/12
CPC classification number: F01D25/12 , F05D2260/20
Abstract: A tip shroud, comprising a plurality of tip shoes encircling a rotor assembly, in a turbine may deform due to thermal gradients experienced during operation of the turbine. Accordingly, a tip shoe is disclosed that utilizes an internal cooling cavity to supply coolant throughout the interior of the tip shoe, as well as to the slash faces of the tip shoe. In addition, features are described that increase the surface area exposed to the coolant, while remaining suitable for additive manufacturing.
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公开(公告)号：US11814967B2
公开(公告)日：2023-11-14
申请号：US17617692
申请日：2020-06-11
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Ulysse Jacques Bernard Danteny , Laurent Cédric Zamai
CPC classification number: F01D11/24 , F01D25/12 , F01D25/14 , F02C3/067 , F02C7/18 , F05D2250/182 , F05D2250/44 , F05D2260/201
Abstract: A turbine for a turbomachine has a first rotor and a second rotor configured to pivot about an axis in two opposite directions of rotation. The first rotor includes a radially outer drum from which blades extend radially inwards. The turbine has cooling means attached relative to the outer drum. The cooling means include a support plate with at least one first orifice and a calibration plate that is attached to the support plate and located radially inside the support plate. The calibration plate has at least one second calibration orifice facing the outer drum to allow the passage of cooling air radially from the outside to the inside through the first and second orifices.
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公开(公告)号：US20230332513A1
公开(公告)日：2023-10-19
申请号：US18330000
申请日：2023-06-06
Applicant: General Electric Company
Inventor： Scott Alan Schimmels , Daniel Alan Niergarth , Arthur William Sibbach , Brandon Wayne Miller
CPC classification number: F01D25/10 , F02C7/12 , F01D25/12 , F05D2260/213 , F05D2220/32 , F05D2260/20
Abstract: A method of regulating pressure in a thermal transport bus of a gas turbine engine, the method including: operating the gas turbine engine with the thermal transport bus having an intermediary heat exchange fluid flowing therethrough, the thermal transport bus including one or more heat source heat exchangers and one or more heat sink heat exchangers in thermal communication through the intermediary heat exchanger fluid; and adjusting a flow volume of the thermal transport bus using a variable volume device in fluid communication with the thermal transport bus in response to a pressure change associated with the thermal transport bus.
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公开(公告)号：US11791524B2
公开(公告)日：2023-10-17
申请号：US17970822
申请日：2022-10-21
Applicant: RTX Corporation
Inventor： Geoffrey T. Blackwell , Richard A. Poisson
CPC classification number: H01P1/30 , F02C7/185 , H04B3/52 , F01D25/12 , F05D2220/32 , F05D2260/232
Abstract: A radio frequency waveguide communication system includes a guided electromagnetic transmission network, and a cooling air source. The guided electromagnetic transmission network includes one or more remote node in fluid communication with one or more waveguides. The cooling air source is in fluid communication with the guided electromagnetic transmission network and is configured to provide pressurized cooling air to the waveguide. The waveguides direct the pressurized cooling air to the remote node.
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公开(公告)号：US11788431B2
公开(公告)日：2023-10-17
申请号：US17556524
申请日：2021-12-20
Inventor： Jack Moody , Kevin P. Holley
CPC classification number: F01D25/12 , F01D9/04 , F01D21/003 , F05D2240/128 , F05D2260/201 , F05D2260/202 , F05D2260/232 , F05D2260/80
Abstract: A cooling system includes a nozzle guide vane endwall. The nozzle guide vane endwall includes a first wall and a second wall. The first wall includes a first opening that extends completely through the first wall into a primary flow path of a high-pressure turbine. The second wall includes a second opening that extends completely through the second wall into an inner passageway of the nozzle guide vane endwall. The inner passageway is configured to direct a cooling fluid to the first opening and/or the second opening. The first and second opening are configured to receive a plug or a probe.
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