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公开(公告)号：US20190257247A1
公开(公告)日：2019-08-22
申请号：US15899831
申请日：2018-02-20
Applicant: General Electric Company
Inventor： Kishanjit Pal , Arnab Sen , Pranav R. Kamat , Brandon Wayne Miller , Daniel Alan Niergarth
Abstract: A method of operating a thermal management system for a gas turbine engine includes determining the gas turbine engine is in a first operating mode; transferring heat from a first heat source exchanger to a heat sink system in response to determining the gas turbine engine is in the first operation mode, the first heat source exchanger thermally coupled to a first system/component of the gas turbine engine; determining the gas turbine engine is in a second operating mode, the second operating mode being different than the first operating mode; and transferring heat from a second heat source exchanger to the heat sink system in response to determining the gas turbine engine is in the second operation mode, the second heat source exchanger thermally coupled to a second system/component of the gas turbine engine, the second system/component being different than the first system/component.
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公开(公告)号：US20190249599A1
公开(公告)日：2019-08-15
申请号：US15895336
申请日：2018-02-13
Applicant: General Electric Company
Inventor： Arnab Sen , Brandon Wayne Miller , Bhaskar Nanda Mondal , Kishanjit Pal , Daniel Alan Niergarth
CPC classification number: F02C6/18 , F02C3/04 , F02C7/18 , F02K3/02 , F05D2210/20 , F05D2220/323 , F05D2220/62 , F05D2220/76 , F05D2260/213
Abstract: An aeronautical gas turbine engine includes a turbomachine including a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order. The aeronautical gas turbine engine additionally includes a closed cycle heat engine including a compressor configured to compress a working fluid; a primary heat exchanger in thermal communication with the turbomachine and the working fluid, the primary heat exchanger configured to transfer heat from the turbomachine to the working fluid; an expander coupled to the compressor for expanding the working fluid; and an output shaft driven by the expander.
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公开(公告)号：US20190217963A1
公开(公告)日：2019-07-18
申请号：US16366453
申请日：2019-03-27
Applicant: General Electric Company
Inventor： Thomas Kupiszewski , Brandon Wayne Miller , Daniel Alan Niergarth , Randy M. Vondrell
IPC: B64D27/24 , F02C7/32 , F02K3/06 , F04D19/02 , B64D27/12 , H02K1/27 , F04D25/06 , F02K5/00 , F01D25/18 , F01D15/10 , F02C7/24 , H02K7/18
CPC classification number: B64D27/24 , B64D27/12 , B64D2027/026 , F01D15/10 , F01D25/183 , F02C7/24 , F02C7/32 , F02K3/06 , F02K5/00 , F04D19/02 , F04D25/06 , F05D2220/323 , F05D2220/768 , F05D2260/98 , H02K1/27 , H02K7/1823
Abstract: A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. An electric machine is mounted coaxially with the rotary component and positioned at least partially inward of the core air flowpath along a radial direction of the gas turbine engine. A cavity wall defines at least in part a buffer cavity surrounding at least a portion of the electric machine to thermally insulate the electric machine, e.g., from the relatively high temperatures within the core air flowpath.
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公开(公告)号：US10316856B2
公开(公告)日：2019-06-11
申请号：US14955327
申请日：2015-12-01
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Andrew Michael Tompkins , Daniel Alan Niergarth
IPC: F02C7/06 , F01D9/06 , F04D29/063 , F04D25/04 , F04D29/52 , F01D25/18 , F16N31/00 , F02K3/06 , F01M1/12
Abstract: A casing for use in a turbofan engine is provided. The casing includes an inner hub including a first fluid opening defined at bottom dead center of the casing. The casing also includes an intermediate casing positioned radially outward from the inner hub, an outer casing positioned radially outward from the intermediate casing, and struts spaced circumferentially about the inner hub and extending between the inner hub and the outer casing. The struts include a first strut and a second strut positioned on opposing sides of bottom dead center of the casing such that a first fluid sump is defined between the inner hub, the intermediate casing, and the first and second struts. At least one of said first and second struts includes a flow channel extending therethrough such that a fluid flow path is defined from the first fluid opening, through the first fluid sump, and through the flow channel.
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公开(公告)号：US20190153954A1
公开(公告)日：2019-05-23
申请号：US16256629
申请日：2019-01-24
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Duane Howard Anstead , Mohammed El Hacin Sennoun , Ning Fang , Kyle Robert Snow
Abstract: A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500° F. The system additionally includes a fuel system having a deoxygenation unit for deoxygenating fuel in the fuel system, as well as a fuel-oil heat exchanger located downstream of the deoxygenation unit. The fuel-oil heat exchanger is in thermal communication with the oil in the first engine system and the fuel in the fuel system for transferring heat from the oil in the first engine system to the fuel in the fuel system.
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Patent Agency Ranking
公开(公告)号：US10294821B2
公开(公告)日：2019-05-21
申请号：US15485515
申请日：2017-04-12
Applicant: General Electric Company
Inventor： Thomas Ory Moniz , Alan Roy Stuart , Jeffrey Donald Clements , Brandon Wayne Miller , Darek Tomasz Zatorski , Gert Johannes van der Merwe , Joel Francis Kirk , Richard Wesling
Abstract: The present disclosure is directed to a gas turbine engine defining a radial direction, a circumferential direction, an axial centerline along a longitudinal direction, and wherein the gas turbine engine defines an upstream end and a downstream end along the longitudinal direction, and wherein the gas turbine engine defines a core flowpath extended generally along the longitudinal direction. The gas turbine engine includes a turbine frame defined around the axial centerline, the turbine frame comprising a first bearing surface disposed inward along the radial direction. The gas turbine engine further includes a turbine rotor assembly including a bearing assembly coupled to the first bearing surface of the turbine frame and the turbine rotor assembly. The turbine rotor assembly further includes a first turbine rotor disposed upstream of the turbine frame and a second turbine rotor disposed downstream of the turbine frame. The first turbine rotor and the second turbine rotor are rotatable together about the axial centerline.
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公开(公告)号：US10260419B2
公开(公告)日：2019-04-16
申请号：US14814546
申请日：2015-07-31
Applicant: General Electric Company
Inventor： Matthew Robert Cerny , Christopher James Kroger , Brandon Wayne Miller
IPC: F02C7/06 , F02C7/14 , F02C7/18 , F02C7/224 , F02C7/16 , F25B1/00 , F25B41/06 , F28D15/00 , F28F27/02 , F28D21/00
Abstract: A thermal management system for a gas turbine engine and/or an aircraft is provided including a thermal transport bus having a heat exchange fluid flowing therethrough. The thermal management system also includes a plurality of heat source exchangers and at least one heat sink exchanger. The plurality of heat source exchangers and the at least one heat sink exchanger are in thermal communication with the heat exchange fluid in the thermal transport bus. The plurality of heat source exchangers are arranged along the thermal transport bus and configured to transfer heat from one or more accessory systems to the heat exchange fluid, and the at least one heat sink exchanger is located downstream of the plurality of heat source exchangers and configured to remove heat from the heat exchange fluid.
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公开(公告)号：US10221706B2
公开(公告)日：2019-03-05
申请号：US14943059
申请日：2015-11-17
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Darek Tomasz Zatorski , Brandon Wayne Miller
IPC: F01D7/00 , B64C11/32 , F02C7/32 , F01D17/12 , F01D7/02 , F02C9/58 , F02C3/10 , F02C7/04 , F02K3/06
Abstract: A gas turbine engine including a core having in serial flow order a compressor, a combustor, and a turbine—the compressor, combustor, and turbine together defining a core air flowpath. The gas turbine engine additionally includes a fan section mechanically coupled to the core, the fan section including a plurality of fan blades, and each of the plurality fan blades defining a pitch axis. An actuation device is operable with the plurality fan blades for rotating the plurality fan blades about their respective pitch axes, the actuation device including an actuator located outward of the core air flowpath to, e.g., simplify the gas turbine engine.
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公开(公告)号：US10215097B2
公开(公告)日：2019-02-26
申请号：US15041224
申请日：2016-02-11
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Duane Howard Anstead , Mohammed El Hacin Sennoun , Ning Fang , Kyle Robert Snow
Abstract: A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500° F. The system additionally includes a fuel system having a deoxygenation unit for deoxygenating fuel in the fuel system, as well as a fuel-oil heat exchanger located downstream of the deoxygenation unit. The fuel-oil heat exchanger is in thermal communication with the oil in the first engine system and the fuel in the fuel system for transferring heat from the oil in the first engine system to the fuel in the fuel system.
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公开(公告)号：US10208676B2
公开(公告)日：2019-02-19
申请号：US15083392
申请日：2016-03-29
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Brandon Wayne Miller , Craig Alan Gonyou
Abstract: Axially adjacent annular booster bleed aft and forward plenums with annular common wall therebetween extend radially outwardly from transition duct. Variable bleed valve includes bleed valve door in bleed inlet in transition duct, attached to rotatable valve body rotatable about axis of rotation, operable to open and close bleed inlet to aft plenum. Rotatable plenum door clocked or circumferentially spaced apart from variable bleed valve door and attached to rotatable valve body, operable to close and open up and control flow through an inter plenum aperture in common wall. Aft and forward bleed exhaust ducts extend from booster bleed aft and forward plenums to bypass flow path. One or more heat exchanger, such as from thermal management system, may be disposed in the bleed exhaust ducts. Heat exchangers may be used for cooling oil for power gear box and/or engine bearings, air conditioning, or variable frequency generator.
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