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公开(公告)号：US12196502B2
公开(公告)日：2025-01-14
申请号：US18136594
申请日：2023-04-19
Applicant: General Electric Company
Inventor： Ramon Martinez , Raymond Floyd Martell , Donald Lee Gardner
Abstract: A heat exchanger for a gas turbine engine includes a heat exchanger body having a first surface and a second surface oriented at least partially at an oblique angle relative to the first surface. The heat exchanger body defines a plenum extending between the first and second surfaces. Furthermore, the heat exchanger body defines a fluid passage extending through the second surface such that the fluid passage is in fluid communication with the plenum. The fluid passage, in turn, includes first and second portions. The first portion intersects the plenum at an intersection and defines a line of projection extending normal to the second surface. The second portion defines a line of projection extending normal to the first surface. The fluid passage further includes a curved portion extending from the first portion to the second portion.
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Patent Agency Ranking
公开(公告)号：US20230258407A1
公开(公告)日：2023-08-17
申请号：US18136594
申请日：2023-04-19
Applicant: General Electric Company
Inventor： Ramon Martinez , Raymond Floyd Martell , Donald Lee Gardner
IPC: F28D7/00
CPC classification number: F28D7/0016 , F28F2210/10 , F28F2009/0287
Abstract: A heat exchanger for a gas turbine engine includes a heat exchanger body having a first surface and a second surface oriented at least partially at an oblique angle relative to the first surface. The heat exchanger body defines a plenum extending between the first and second surfaces. Furthermore, the heat exchanger body defines a fluid passage extending through the second surface such that the fluid passage is in fluid communication with the plenum. The fluid passage, in turn, includes first and second portions. The first portion intersects the plenum at an intersection and defines a line of projection extending normal to the second surface. The second portion defines a line of projection extending normal to the first surface. The fluid passage further includes a curved portion extending from the first portion to the second portion.
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公开(公告)号：US11022037B2
公开(公告)日：2021-06-01
申请号：US15861802
申请日：2018-01-04
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Brandon Wayne Miller , Raymond Floyd Martell , Jeffrey Douglas Rambo , Ryan James Matthys , Joel Francis Kirk
IPC: F02C7/143 , F01D5/14 , F02C7/18 , F01D25/12 , F02C7/12 , F01D5/08 , F02C3/06 , F23R3/28 , F01D9/06
Abstract: A gas turbine engine includes a turbomachine including a compressor section, a combustion section, a turbine section, and an exhaust section arranged in serial flow order and together defining at least in part a core air flowpath. The gas turbine engine also includes a thermal management system including a flowpath heat exchanger coupled to, or integrated into, one or more components of the compressor section, the combustion section, the turbine section, or the exhaust section such that the flowpath heat exchanger is directly thermally coupled to an airflow through the core air flowpath.
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公开(公告)号：US20190249570A1
公开(公告)日：2019-08-15
申请号：US15892735
申请日：2018-02-09
Applicant: General Electric Company
Inventor： Ananda Barua , Joshua Tyler Mook , Raymond Floyd Martell , Changjie Sun , Gautam Naik , Jordan Paule Tesorero , Aigbedion Akwara
Abstract: Turbine center frames are provided. For example, a turbine center frame comprises an annular outer case and an annular hub. The hub is defined radially inward of the outer case such that the outer case circumferentially surrounds the hub. The turbine center frame further comprises an annular fairing extending between the outer case and the hub, a ligament extending from the fairing to the outer case to connect the fairing to the outer case, a plurality of struts extending from the hub to the outer case, and a boss structure defined on an outer surface of the outer case. The outer case, hub, fairing, ligament, plurality of struts, and boss structure are integrally formed as a single monolithic component. For instance, the turbine center frame is additively manufactured as an integral structure, and methods for manufacturing turbine center frames also are provided.
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公开(公告)号：US20190017438A1
公开(公告)日：2019-01-17
申请号：US15647380
申请日：2017-07-12
Applicant: General Electric Company
CPC classification number: F02C6/18 , F01D15/10 , F01D25/36 , F02C3/04 , F02C7/32 , F02C7/36 , F05D2260/4031 , H01L35/30
Abstract: A turbine engine has a core with a compressor, combustor, and turbine sections in axial flow arrangement and with corresponding rotating elements mounted to a shaft defining engine rotor elements. The turbine engine has a rotary driver operably coupled to the engine rotor elements. The turbine engine has at least one thermoelectric generator in thermal communication with the core and in electrical communication with the rotary driver to provide power to the rotary driver to turn the engine rotor elements.
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公开(公告)号：US20180163845A1
公开(公告)日：2018-06-14
申请号：US15375348
申请日：2016-12-12
Applicant: General Electric Company
Inventor： Gert Johannes van der Merwe , Raymond Floyd Martell
CPC classification number: F16H57/0417 , B64D33/08 , F01D25/12 , F02C7/14 , F02C7/224 , F02C7/32 , F05D2230/30 , F05D2260/213 , F16H57/02 , F16H57/0415 , F28D7/0041 , F28D7/005 , F28F2255/00 , F28F2255/18 , Y02T50/675
Abstract: A gearbox and a method for additively manufacturing the gearbox are provided. The gearbox includes a housing having an integral heat exchanger additively manufactured within the housing. The heat exchanger includes a plurality of heat exchange passageways for transferring heat between two or more fluids. The heat exchanger is defined at any suitable location or locations within the housing, for example, within voids defined between the walls of the housing and components housed within housing, such as driveshafts, gears, bearings, etc.
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