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公开(公告)号：US20180017342A1
公开(公告)日：2018-01-18
申请号：US15210434
申请日：2016-07-14
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo
CPC classification number: F28F9/22 , F05D2260/213 , F28D7/1623 , F28D2021/0026 , F28F13/06 , F28F13/08 , F28F27/02 , F28F2009/228
Abstract: A heat exchanger apparatus includes: a shell extending over a flow length from an inlet at a upstream end to an outlet at a downstream end, and defining a first flowpath for a first fluid; a structure disposed within the shell defining a second flowpath for a second fluid; at least one secondary inlet in the shell disposed downstream from the upstream end; and a nozzle disposed downstream of the inlet.
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公开(公告)号：US20250116234A1
公开(公告)日：2025-04-10
申请号：US18483620
申请日：2023-10-10
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo , Eric Barre , Brandon Wayne Miller , Leonardo Aguilar Willys , Victor Moreno Patan
Abstract: A thermal management system includes a thermal circuit having a thermal transport bus with a thermal fluid flowing therethrough. The thermal transport bus includes first and second bus segments. First and second thermal loads are on the first and second bus segments, respectively, and have different first and second inlet temperature requirements. The thermal management system includes a plurality of heat exchangers in thermal communication with the first and second thermal loads. The heat exchangers include a first heat exchanger and one or more second heat exchangers. The first heat exchanger is on one of the first or second bus segments for rejecting heat to engine fuel. The thermal fluid is split between each of the first and second bus segments such that only a portion of the thermal fluid flows through the first heat exchanger to accommodate the different first and second inlet temperature requirements.
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公开(公告)号：US12270342B1
公开(公告)日：2025-04-08
申请号：US18483620
申请日：2023-10-10
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo , Eric Barre , Brandon Wayne Miller , Leonardo Aguilar Willys , Victor Moreno Patan
Abstract: A thermal management system includes a thermal circuit having a thermal transport bus with a thermal fluid flowing therethrough. The thermal transport bus includes first and second bus segments. First and second thermal loads are on the first and second bus segments, respectively, and have different first and second inlet temperature requirements. The thermal management system includes a plurality of heat exchangers in thermal communication with the first and second thermal loads. The heat exchangers include a first heat exchanger and one or more second heat exchangers. The first heat exchanger is on one of the first or second bus segments for rejecting heat to engine fuel. The thermal fluid is split between each of the first and second bus segments such that only a portion of the thermal fluid flows through the first heat exchanger to accommodate the different first and second inlet temperature requirements.
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公开(公告)号：US20250101920A1
公开(公告)日：2025-03-27
申请号：US18977350
申请日：2024-12-11
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo
Abstract: Systems and methods for operating systems are provided. For example, a system comprises a heat source for providing a flow of a hot fluid and a fuel flowpath for a flow of a fuel. The fuel flowpath includes a fuel accumulator and a heat exchanger for heat transfer between the hot fluid and fuel. The heat exchanger includes a hot fluid inlet for receipt of the hot fluid at an inlet temperature and a fuel inlet for receipt of the fuel at an inlet temperature. The hot fluid inlet temperature is greater than the fuel inlet temperature such that the fuel is heated through heat transfer with the hot fluid in the heat exchanger. The fuel accumulator accumulates at least a portion of the heated fuel. An exemplary system is selectively operated to heat and circulate the fuel through the fuel flowpath for consumption and/or accumulation in the fuel accumulator.
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公开(公告)号：US20250012236A1
公开(公告)日：2025-01-09
申请号：US18430907
申请日：2024-02-02
Applicant: General Electric Company
Abstract: A heat exchanger positioned within an annular duct of a gas turbine engine is provided. The heat exchanger extends substantially continuously along the circumferential direction and defining a heat exchanger height equal to at least 10% of a duct height. An effective transmission loss (ETL) for the heat exchanger positioned within the annular duct is between 5 decibels and 1 decibels for an operating condition of the gas turbine engine. The heat exchanger includes a heat transfer section defining an acoustic length (Li), and wherein an Operational Acoustic Reduction Ratio (OARR) is greater than or equal to 0.75 to achieve the ETL at the operating condition.
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Patent Agency Ranking
公开(公告)号：US12173654B2
公开(公告)日：2024-12-24
申请号：US18456966
申请日：2023-08-28
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo , Gregory Michael Petrasko
Abstract: A system for energy conversion that includes a propulsion system, a fuel circuit, a combustion device, a turbine, and a load device. The fuel circuit is in fluid communication with a fuel tank and a fuel flow control device that separates a flow of fuel into a first portion and a second portion. The combustion device receives a flow of oxidizer and the second portion of fuel to generate combustion gases. The turbine receives the combustion gases from the combustion device via a fluid circuit. The load device is operably coupled to the turbine via a driveshaft and is configured to receive torque from the driveshaft.
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公开(公告)号：US20240301801A1
公开(公告)日：2024-09-12
申请号：US18180449
申请日：2023-03-08
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Vidyashankar Ramasastry Buravalla , David Raju Yamarthi , Rajesh Kumar , Jeffrey Douglas Rambo
CPC classification number: F01D11/08 , F03G7/0614 , F05D2220/30 , F05D2240/55
Abstract: A turbine engine is provided. The turbine engine includes: a rotor; a stator having a carrier; a seal support assembly coupled to the carrier; and a seal assembly disposed between the rotor and the stator and supported by the seal support assembly, the seal assembly defining a high pressure side and a low pressure side and including a plurality of seal segments, the plurality of seal segments having a first seal segment, the first seal segment having a seal face configured to form a fluid bearing with the rotor, a lip assembly, and a body, the lip assembly positioned on the high pressure side, the lip assembly including a seal lip having a high pressure surface defining a first angle with an axial direction and a low pressure surface defining a second angle with the axial direction, the second angle being greater than the first angle.
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公开(公告)号：US12044182B2
公开(公告)日：2024-07-23
申请号：US17844863
申请日：2022-06-21
Applicant: General Electric Company
Inventor： Arthur William Sibbach , Brandon Wayne Miller , Jeffrey Douglas Rambo
IPC: F02C7/36
CPC classification number: F02C7/36 , F05D2260/4023
Abstract: A shaft power transfer system includes a first mechanical clutch mechanism operably coupling a high-pressure shaft to a low-pressure shaft. The first mechanical clutch mechanism transfers power from the high-pressure shaft to the low-pressure shaft at a predefined first speed transient condition. The system further includes a second mechanical clutch mechanism that operably couples the low-pressure shaft to the high-pressure shaft. The second mechanical clutch mechanism transfers power from the low-pressure shaft to the high-pressure shaft at a predefined second speed transient condition where the predefined first speed transient condition is different than the predefined second speed transient condition.
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公开(公告)号：US12006870B2
公开(公告)日：2024-06-11
申请号：US17117336
申请日：2020-12-10
Applicant: General Electric Company
Inventor： Matthew Ryan Johns , Alex William Ariapad , Nicolas Kristopher Sabo , Jeffrey Douglas Rambo , Ramon Martinez , Jared Wolfe
IPC: F02C7/14
CPC classification number: F02C7/14 , F05D2220/323 , F05D2260/213 , F05D2260/606
Abstract: A heat exchanger for an aircraft includes an inlet plenum housing defining an inlet plenum configured to receive a fluid and an outlet plenum housing defining an outlet plenum configured to discharge the fluid. Furthermore, the heat exchanger includes a core configured to heat or cool a first portion of the fluid, with the core defining a plurality of fluid passages extending from the inlet plenum to the outlet plenum. Moreover, the heat exchanger includes a passive bypass defining a passive bypass flow path fluidly coupled to and extending between the inlet plenum and the outlet plenum. As such, the passive bypass flow path is in parallel with at least a portion of the core such that a second portion of the fluid bypasses at least a portion of the core and flows continuously and unobstructed through the passive bypass flow path to the outlet plenum.
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公开(公告)号：US20240182180A1
公开(公告)日：2024-06-06
申请号：US18437873
申请日：2024-02-09
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo , Scott Gregory Edens
Abstract: A thermal management system for a propulsion system of an aircraft includes a fluid circuit configured to provide a flow of a compressed fluid from a compressor section of the propulsion system to, in serial flow order, a first turbine, a compressor, a second turbine, a thermal load, and an exhaust sink. A heat exchanger is disposed in a fan stream of the propulsion system at a location along the fluid circuit between the compressor and the second turbine. The fluid circuit extends through and is in thermal communication with the heat exchanger.
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