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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:US11021961B2
公开(公告)日:2021-06-01
申请号:US16210314
申请日:2018-12-05
Applicant: General Electric Company
Inventor: Jeffrey Douglas Rambo , Kirk Douglas Gallier , Brandon Wayne Miller , Craig Alan Gonyou , Kevin Robert Feldmann , Justin Paul Smith
Abstract: An aspect of the present disclosure is directed to a rotor assembly for a turbine engine. The rotor assembly includes an airfoil assembly and a hub to which the airfoil assembly is attached. A wall assembly defines a first cavity and a second cavity between the airfoil assembly and the hub. The first cavity and the second cavity are at least partially fluidly separated by the wall assembly. The first cavity is in fluid communication with a flow of first cooling fluid and the second cavity is in fluid communication with a flow of second cooling fluid different from the first cooling fluid.
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公开(公告)号:US20210102492A1
公开(公告)日:2021-04-08
申请号:US16592122
申请日:2019-10-03
Applicant: General Electric Company
Inventor: Jeffrey Douglas Rambo , Thomas Kupiszewski
Abstract: Heat exchangers, heat exchanger systems, and hypersonic vehicles are provided. For example, a heat exchanger is provided that comprises a first chamber for receipt of a flow of cool fluid and a second chamber for receipt of a flow of hot fluid. The heat exchanger further comprises a buffer fluid flowpath for circulation of a buffer fluid therethrough. The buffer fluid circulates within the buffer fluid flowpath disposed between the first chamber and the second chamber to transfer heat from the hot fluid to the cool fluid. In certain embodiments, a hypersonic vehicle comprises such a heat exchanger, and the cool fluid is cryogenic or near-cryogenic fuel of the hypersonic vehicle and the hot fluid is engine bleed air from a hypersonic propulsion engine of the vehicle.
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公开(公告)号:US10927761B2
公开(公告)日:2021-02-23
申请号:US16386697
申请日:2019-04-17
Applicant: General Electric Company
Inventor: Jeffrey Douglas Rambo
Abstract: A heat management system for a turbomachine may include a first heat exchanger configured and arranged to receive a first fluid stream from a first duct, a second heat exchanger configured and arranged to receive the first fluid stream after discharging from the first heat exchanger, and a hatch configured to provide fluid communication from a second duct to the first duct so as to introduce a second fluid stream from the second duct to the first duct. A method of cooling fluid streams may include directing a first fluid stream from a first duct across or through a first heat exchanger, directing the first fluid stream across or through a second heat exchanger after discharging from the first heat exchanger, and directing a second fluid stream from a second duct to the first duct, with the second fluid stream flowing through a hatch configured to provide fluid communication from the second duct to the first duct.
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公开(公告)号:US20210031937A1
公开(公告)日:2021-02-04
申请号:US16941730
申请日:2020-07-29
Applicant: General Electric Company
Inventor: Scott Alan Schimmels , Jeffrey Douglas Rambo , Thomas Kupiszewski , Paul Alexander Intemann , Robert Proctor
Abstract: A vehicle is provided including a structure including a skin defining an outside surface exposed to ambient cooling flow and an inside surface. The structure includes a first structural member extending from the inside surface of the skin and a second structural member extending from the inside surface of the skin; and a thermal management system including a heat exchanger assembly positioned adjacent to, and in thermal communication with, the inside surface of the skin, the heat exchanger assembly positioned at least partially between the first and second structural members of the structure.
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公开(公告)号:US10670349B2
公开(公告)日:2020-06-02
申请号:US15652717
申请日:2017-07-18
Applicant: General Electric Company
Abstract: A heat exchanger includes a heat exchanger core, a header defining a header manifold, and a transition portion that provides fluid communication between the heat exchanger core and the header manifold. The transition portion includes a transition tube extending between the header and the heat exchanger core, a header junction where the transition tube joins the header, and a splitting junction that splits the transition tube into the plurality of heat exchange tubes. The header junction may define elliptical inlet apertures, a large filleted joint, and a junction thickness that is greater than a header wall thickness.
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公开(公告)号:US10364750B2
公开(公告)日:2019-07-30
申请号:US15796991
申请日:2017-10-30
Applicant: General Electric Company
Inventor: Jeffrey Douglas Rambo
Abstract: A gas turbine engine includes an outer nacelle; a fan at least partially surrounded by the outer nacelle; and a turbomachine drivingly coupled to the fan and at least partially surrounded by the outer nacelle. The outer nacelle defines a bypass airflow passage with the turbomachine. The turbomachine includes a compressor section defining in part a core air flowpath. The turbomachine also includes a heat sink heat exchanger; and a thermal management duct assembly defining a thermal management duct flowpath extending between an inlet and an outlet and positioned between the core air flowpath and the bypass airflow passage along the radial direction, the outlet selectively in airflow communication with a core compartment of the turbomachine, and the heat sink heat exchanger positioned in thermal communication with the thermal management duct flowpath for transferring heat to an airflow through the thermal management duct flowpath during operation.
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公开(公告)号:US20190203600A1
公开(公告)日:2019-07-04
申请号:US15861811
申请日:2018-01-04
Applicant: General Electric Company
Inventor: Gregory Michael Petrasko , Jeffrey Douglas Rambo
CPC classification number: F01D5/087 , F01D25/12 , F02C3/06 , F02C7/18 , F02C7/28 , F05D2220/3216 , F05D2240/55 , F05D2240/81 , F05D2260/201
Abstract: A gas turbine engine includes a combustion section and a compressor section, the compressor section including a high pressure compressor. The high pressure compressor includes an aft-most compressor stage and an upstream compressor stage, each of the aft-most compressor stage and the upstream compressor stage including a rotor disk. The gas turbine engine also includes a high pressure spool assembly, the high pressure spool assembly including a rotor disk, and an airflow member extending from the rotor disk of the high pressure spool assembly to the rotor disk of the upstream compressor stage of the high pressure compressor to define in part a compressor cooling air passage outward of the airflow member along a radial direction.
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公开(公告)号:US20190024989A1
公开(公告)日:2019-01-24
申请号:US15652717
申请日:2017-07-18
Applicant: General Electric Company
CPC classification number: F28F9/0273 , F02C7/141 , F05D2260/213 , F28D1/0477 , F28D2021/0026 , F28F9/0214 , F28F9/0243 , F28F9/027 , F28F2009/0285 , F28F2009/0297 , F28F2210/02
Abstract: A heat exchanger includes a heat exchanger core, a header defining a header manifold, and a transition portion that provides fluid communication between the heat exchanger core and the header manifold. The transition portion includes a transition tube extending between the header and the heat exchanger core, a header junction where the transition tube joins the header, and a splitting junction that splits the transition tube into the plurality of heat exchange tubes. The header junction may define elliptical inlet apertures, a large filleted joint, and a junction thickness that is greater than a header wall thickness.
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公开(公告)号:US20180230812A1
公开(公告)日:2018-08-16
申请号:US15405648
申请日:2017-01-13
Applicant: General Electric Company
Inventor: Junwoo Lim , Jeffrey Douglas Rambo , Aaron Ezekiel Smith
IPC: F01D5/18
CPC classification number: F01D5/186 , F05D2220/323 , F05D2240/303 , F05D2250/10 , F05D2250/12 , F05D2250/18 , F05D2250/312 , F05D2250/324 , F05D2250/34 , F05D2250/38 , F05D2260/202 , Y02T50/676
Abstract: An apparatus and method for an engine component for a turbine engine including an exterior wall separating a hot fluid flow exterior of the engine component from a cooling fluid flow interior of the engine component. A cooling circuit can be provided within the component having a cooling passage. At least two film holes can extend through the exterior wall for providing a cooling film along the exterior of the wall. The film holes can overlap one another relative to the hot fluid flow.
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