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公开(公告)号：US20250109695A1
公开(公告)日：2025-04-03
申请号：US18883919
申请日：2024-09-12
Applicant: General Electric Company
Inventor： Brandon W. Miller , Arthur W. Sibbach , Andrew Hudecki , Patrick S. Sage , Eric Barre , Stefan Joseph Cafaro , Gerardo Perez Perez , Kevin Graziano
Abstract: An engine includes a gearbox coupled to a first element and a second element. The engine may include a first speed sensor positioned on an input side of the gearbox, the first speed sensor operable to detect a first speed of the first element. The engine may further include a second speed sensor positioned on an output side of the gearbox, the second speed sensor operable to detect a second speed of the second element. The engine includes a controller comprising a processor and a memory coupled to the processor. The processor may be configured to receive data from the first speed sensor and the second speed sensor. The processor is also configured to detect a trigger event based on the data from the first speed sensor and the data from the second speed sensor. Upon detecting the trigger event, the processor communicates a command to an engine operational system.
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公开(公告)号：US20240426250A1
公开(公告)日：2024-12-26
申请号：US18488420
申请日：2023-10-17
Applicant: General Electric Company
Inventor： Eric Barre , Brandon W. Miller , Arthur W. Sibbach
IPC: F02C7/36
Abstract: A turbine engine has a longitudinal centerline axis. The turbine engine includes a fan, a turbo-engine, and a unidirectional brake. The fan includes a plurality of fan blades that rotate in a first direction about the longitudinal centerline axis. The turbo-engine includes a combustor that combusts compressed air and fuel to generate combustion gases and a low-pressure turbine including a low-pressure shaft. The low-pressure turbine receives the combustion gases to rotate the low-pressure turbine. The fan is coupled to the low-pressure shaft such that rotation of the low-pressure shaft causes the fan to rotate in the first direction. A unidirectional brake is coupled to the low-pressure shaft to prevent rotation of the low-pressure shaft and, thus, the fan in a second direction opposite the first direction.
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Patent Agency Ranking
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：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：US20240110518A1
公开(公告)日：2024-04-04
申请号：US18071743
申请日：2022-11-30
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Andrew Hudecki , Eric Barre
CPC classification number: F02C7/185 , F02C6/08 , F05D2220/323 , F05D2260/213
Abstract: A gas turbine engine is provided. The gas turbine engine includes: a fan; a turbomachine drivingly coupled to the fan and defining in part a working gas flowpath, the gas turbine engine defining a bypass passage over the turbomachine, the turbomachine defining an annular cooling passage extending between a CP inlet and a CP outlet, the CP inlet in airflow communication with the working gas flowpath and the CP outlet in airflow communication with the bypass passage; and a variable bleed assembly including a variable bleed duct extending between a VB inlet and a VB outlet, the VB inlet in airflow communication with the working gas flowpath at a location downstream of the CP inlet and the VB outlet in airflow communication with the annular cooling passage for urging an airflow through the cooling passage.
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公开(公告)号：US20240110515A1
公开(公告)日：2024-04-04
申请号：US18071722
申请日：2022-11-30
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Andrew Hudecki , Steven Douglas Johnson , Eric Barre , John Carl Glessner , Efren Souza Chavez
CPC classification number: F02C7/18 , F01D25/12 , F05D2220/323 , F05D2260/232
Abstract: A gas turbine engine including: a fan assembly comprising a fan; and a turbomachine drivingly coupled to the fan and including a compressor section, a combustion section, and a turbine section arranged in serial flow order and defining in part a working gas flowpath, the gas turbine engine defining a bypass passage over the turbomachine; the turbomachine further including a heat exchanger and defining an annular cooling passage extending between an inlet and an outlet, the inlet in airflow communication with the working gas flowpath at a location upstream of the compressor section and the outlet in airflow communication with the bypass passage, the heat exchanger in thermal communication with an airflow through the cooling passage.
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