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公开(公告)号：US11384649B1
公开(公告)日：2022-07-12
申请号：US17173388
申请日：2021-02-11
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo
Abstract: A propulsion system is provided including a first vane extended along the radial direction. The first vane is configured to rotate relative to a vane axis extended along the radial direction. A second vane is extended along the radial direction. The second vane is positioned aft along the axial direction of the first vane. The second vane forms an inlet opening proximate to a second vane leading edge, and the second vane forms an outlet opening proximate to a second vane trailing edge. The inlet opening and the outlet opening together allow a flow of fluid through the second vane. A heat exchanger is positioned within the second vane. The inlet opening and the outlet opening allow the flow of fluid in fluid communication with the heat exchanger.
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公开(公告)号：US20220213802A1
公开(公告)日：2022-07-07
申请号：US17142357
申请日：2021-01-06
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Julius John Montgomery , Brandon Wayne Miller , Robert Proctor , Bradley W. Fintel , Jeffrey Douglas Rambo
Abstract: A system for controlling blade clearances within a gas turbine engine includes a rotor disk and a rotor blade coupled to the rotor disk. Additionally, the system includes an outer turbine component positioned outward of the rotor blade such that a clearance is defined between the rotor blade and the outer turbine component. Furthermore, the system includes a heat exchanger configured to receive a flow of cooling air bled from the gas turbine engine and transfer heat from the received flow of the cooling air to a flow of coolant to generate cooled cooling air. Moreover, the system includes a valve configured to control the flow of the coolant to the heat exchanger. In this respect, the cooled cooling air is supplied to at least one of the rotor disk or the rotor blade to adjust the clearance between the rotor blade and the outer turbine component.
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公开(公告)号：US20220111968A1
公开(公告)日：2022-04-14
申请号：US17069034
申请日：2020-10-13
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo
Abstract: A system for cooling aircraft components includes a compressor configured to receive air bled from a gas turbine engine and compress the received air. Additionally, the system includes a water separator configured to receive the compressed air from the compressor and remove moisture from the compressed air to dry the compressed air. Furthermore, the system includes a turbine configured to receive the dried air from the heat exchanger, with the dried air expanding as the dried air flows through the turbine. Moreover, the system includes a defroster configured to receive the expanded air from the turbine, with the defroster further configured to capture frozen particulate matter from the expanded air. As such, the moisture removed from the compressed air by the water separator is routed to the defroster to melt the captured frozen particulate matter.
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公开(公告)号：US11174789B2
公开(公告)日：2021-11-16
申请号：US15986943
申请日：2018-05-23
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo , Gregory Michael Petrasko
Abstract: A gas turbine engine assembly includes a turbomachine including a compressor section, a combustion section, and a turbine section in serial flow order; a fuel delivery system operable with the combustion section of the turbomachine for providing fuel to the combustion section of the turbomachine; and an air cycle assembly including an air cycle machine and a heat exchanger, the air cycle machine in airflow communication with the compressor section of the turbomachine and the heat exchanger in airflow communication with the air cycle machine. The gas turbine engine assembly also includes a thermal transfer bus thermally coupling the heat exchanger of the air cycle assembly to the fuel delivery system for transferring heat from the air cycle machine to the fuel delivery system.
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公开(公告)号：US20210246849A1
公开(公告)日：2021-08-12
申请号：US16788384
申请日：2020-02-12
Applicant: General Electric Company
Inventor： Arvind Namadevan , Hari Shanker Thakur , Jeffrey Douglas Rambo , Arnab Sen , Siddhartha Pal
Abstract: An ejector assembly includes a primary nozzle in fluid communication with a primary fluid inlet, a secondary nozzle in fluid communication with a secondary fluid inlet, the primary nozzle being oriented concentrically within the secondary nozzle and the secondary nozzle having a venturi downstream of the primary nozzle, and the primary nozzle having a variable cross-sectional area. A gas turbine engine includes a source of high pressure air, a region of low pressure air, and an ejector assembly, the ejector assembly includes a primary nozzle in fluid communication with a primary fluid inlet, the primary fluid inlet in fluid communication with the source of high pressure air, a secondary nozzle in fluid communication with a secondary fluid inlet, the secondary fluid inlet in fluid communication with the region of low pressure air, the primary nozzle being oriented concentrically within the secondary nozzle and the secondary nozzle having a venturi downstream of the primary nozzle, and the primary nozzle having a variable cross-sectional area.
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Patent Agency Ranking
公开(公告)号：US09835380B2
公开(公告)日：2017-12-05
申请号：US14656789
申请日：2015-03-13
Applicant: General Electric Company
Inventor： Thomas Kupiszewski , Jeffrey Douglas Rambo , James F. Bonar , Jared Wolfe
CPC classification number: F28D1/0233 , F01D25/12 , F28D1/05375 , F28D7/163 , F28D2021/0021 , F28F1/006 , F28F2009/226 , F28F2225/02 , Y02T50/672 , Y02T50/675
Abstract: A heat exchanger that includes an input cavity defined by inlet cavity walls; a heat exchanger portion in fluid communication with the input cavity and defined between a first side and a second side, and wherein a plurality of baffles are positioned within the heat exchanger portion; and an outlet cavity in fluid communication with the heat exchanger portion and defined by outlet cavity walls. The heat exchanger portion comprises: a plurality of first fluid paths defined between the baffles and extending from the input cavity to the outlet cavity, and a plurality of tubes extending through the heat exchanger portion from the first side to the second side. Each tube extends through the baffles so as to define a second fluid path through the heat exchanger portion. Heat exchanger systems are also generally provided, along with methods for cooling a hot fluid input with a heat exchanger.
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公开(公告)号：US20250043720A1
公开(公告)日：2025-02-06
申请号：US18434047
申请日：2024-02-06
Applicant: General Electric Company
Inventor： Scott Alan Schimmels , Jeffrey Douglas Rambo , Timothy Richard DePuy , Steven B. Morris , Eric Barre , Brandon Wayne Miller , Leonardo Aguilar Willys , Victor Moreno Patan
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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公开(公告)号：US20250035038A1
公开(公告)日：2025-01-30
申请号：US18434128
申请日：2024-02-06
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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公开(公告)号：US20250027448A1
公开(公告)日：2025-01-23
申请号：US18436275
申请日：2024-02-08
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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公开(公告)号：US12196136B2
公开(公告)日：2025-01-14
申请号：US17128704
申请日：2020-12-21
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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