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公开(公告)号：US20170138306A1
公开(公告)日：2017-05-18
申请号：US14943055
申请日：2015-11-17
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Daniel Alan Niergarth , Darek Tomasz Zatorski
CPC classification number: F02K3/06 , F01D7/00 , F01D25/16 , F02C3/04 , F02C7/04 , F02C7/06 , F02C7/36 , F04D29/059 , F04D29/323 , F05B2220/302 , F05B2240/52 , F05D2240/52 , F05D2260/40311 , F05D2260/70 , Y02T50/673
Abstract: A gas turbine engine includes a core turbine engine and a fan mechanically coupled to the core turbine engine. The fan includes a plurality of fan blades, each fan blade defining a base and an inner end along a radial direction of the gas turbine engine. The fan also includes a hub covering the base of each of the plurality of fan blades. Further, the fan includes one or more bearings for supporting rotation of the plurality of fan blades. The one or more bearings define a fan bearing radius along a radial direction of the gas turbine engine. Similarly, the hub defines a hub radius along the radial direction of the gas turbine engine. The ratio of the hub radius to the fan bearing radius is less than about three, providing for desired packaging of the various components within the fan of the gas turbine engine.
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公开(公告)号：US20170138207A1
公开(公告)日：2017-05-18
申请号：US14943059
申请日：2015-11-17
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Darek Tomasz Zatorski , Brandon Wayne Miller
CPC classification number: F01D7/00 , B64C11/32 , B64C11/325 , F01D7/02 , F01D17/12 , F02C3/10 , F02C7/04 , F02C7/32 , F02C9/58 , F02K3/06 , F05B2220/302 , F05B2260/70 , F05B2260/74 , F05D2220/36 , F05D2260/70 , F05D2260/74 , F05D2260/75 , F05D2260/76 , Y02T50/673
Abstract: A gas turbine engine including a core having in serial flow order a compressor, a combustor, and a turbine—the compressor, combustor, and turbine together defining a core air flowpath. The gas turbine engine additionally includes a fan section mechanically coupled to the core, the fan section including a plurality of fan blades, and each of the plurality fan blades defining a pitch axis. An actuation device is operable with the plurality fan blades for rotating the plurality fan blades about their respective pitch axes, the actuation device including an actuator located outward of the core air flowpath to, e.g., simplify the gas turbine engine.
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公开(公告)号：US20170130606A1
公开(公告)日：2017-05-11
申请号：US14937266
申请日：2015-11-10
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Brandon Wayne Miller , Kyle Robert Snow , Christopher James Kroger
Abstract: A self-contained lubrication fluid circulation system for use with a gas turbine engine defining a core air flowpath includes a sump configured to collect lubrication fluid and a heat source coupled in fluid communication with the sump and configured to transfer heat to the lubrication fluid. The system also includes a heat sink positioned within the sump and coupled in fluid communication with the heat source. A lubrication fluid conduit of the system is configured to channel the lubrication fluid between the heat source and the heat sink, wherein the lubrication fluid conduit is positioned entirely within the sump.
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公开(公告)号：US20170113805A1
公开(公告)日：2017-04-27
申请号：US14923062
申请日：2015-10-26
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Ian Francis Prentice
CPC classification number: B64D27/02 , B64C11/48 , B64D27/12 , B64D2027/005 , Y02T50/66
Abstract: A propulsion system for an aircraft includes at least two propulsion engines. Each propulsion engine rotates about a longitudinal rotational axis, and a propulsive fan associated with each propulsion engine rotates in a plane perpendicular to the longitudinal rotational axis. Each plane is at least one of spaced axially along a fuselage of the aircraft and canted such that each plane does not intersect any other plane associated with another propulsion engine and propulsive fan.
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公开(公告)号：US20170081035A1
公开(公告)日：2017-03-23
申请号：US14859514
申请日：2015-09-21
Applicant: General Electric Company
CPC classification number: B64D27/14 , B64C21/06 , B64C2230/00 , B64D27/20 , B64D29/00 , B64D29/04 , B64D2027/264 , B64D2033/0226
Abstract: A propulsion system for an aircraft is provided having an aft engine configured to be mounted to the aircraft at an aft end of the aircraft. The aft engine includes a fan rotatable about a central axis of the aft engine having a plurality of fan blades. The aft engine also includes a nacelle encircling the plurality of fan blades with one or more structural members extending between the nacelle and the mean line of the aircraft at a location forward of the plurality of fan blades when the aft engine is mounted to the aircraft. The aft engine may increase a net thrust of the aircraft when mounted to the aircraft.
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Patent Agency Ranking
公开(公告)号：US20250146453A1
公开(公告)日：2025-05-08
申请号：US19016281
申请日：2025-01-10
Inventor： Darek Tomasz Zatorski , David Marion Ostdiek , Mohamed Osama , William Joseph Solomon , Brandon Wayne Miller , Randy M. Vondrell , Craig William Higgins , Alexander Kimberley Simpson
Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct; a primary fan driven by the turbomachine; and a secondary fan located downstream of the primary fan within the inlet duct. The gas turbine engine defines a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10, wherein the thrust to power airflow ratio is a ratio of an airflow through a bypass passage over the turbomachine plus an airflow through the fan duct to an airflow through the core duct, and wherein the core bypass ratio is a ratio of the airflow through the fan duct to the airflow through the core duct.
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公开(公告)号：US20250084799A1
公开(公告)日：2025-03-13
申请号：US18671084
申请日：2024-05-22
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Brandon Wayne Miller , Andrew Hudecki , Kevin Richard Graziano , Arthur William Sibbach , Inenhe Mohammed Khalid , Andrea Piazza , Stefan Joseph Cafaro
Abstract: A gas turbine engine includes a fan section having a fan rotatable with a fan shaft, a turbomachinery section having a turbine and a turbomachine shaft rotatable with the turbine, a power gearbox mechanically coupled to the fan shaft and the turbomachine shaft such that the fan shaft is rotatable by the turbomachine shaft across the power gearbox, a grounded structure coupled to and supporting the power gearbox, and a torque monitoring system. The torque monitoring system includes a gearbox sensor. The gearbox sensor is coupled to the grounded structure and the torque monitoring system configured to determine a torque across the power gearbox using the gearbox sensor.
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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：US20250003375A1
公开(公告)日：2025-01-02
申请号：US18740613
申请日：2024-06-12
Applicant: General Electric Company
Inventor： Joseph George Rose , Thomas Ory Moniz , Tsuguji Nakano , Jeffrey S. Spruill , Brandon Wayne Miller , Randy M. Vondrell , David Marion Ostdiek , Craig William Higgins , Alexander Kimberley Simpson
Abstract: A gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct, a primary fan driven by the turbomachine, a secondary fan located downstream of the primary fan within the inlet duct, a heat exchanger disposed in the fan duct, and a booster upstream of the heat exchanger, the booster including a booster cowl extending into the fan duct, the booster cowl separating an upstream portion of the fan duct into an upper fan duct having an upper fan duct inlet and a lower fan duct having a lower fan duct inlet, the upper fan duct inlet and lower fan duct inlet collectively forming the fan duct inlet.
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公开(公告)号：US20240291008A1
公开(公告)日：2024-08-29
申请号：US18404083
申请日：2024-01-04
Applicant: General Electric Company
Inventor： Honggang Wang , Brandon Wayne Miller , Michael Anthony Benjamin , Richard L. Hart , Randy M. Vondrell , Ryan St. Pierre
IPC: H01M8/0612 , F02C7/22
CPC classification number: H01M8/0618 , F02C7/22 , H01M8/0625 , H01M2250/20
Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a compressor section, a combustor, and a turbine section arranged in serial flow order, the turbomachine further including an outer casing; a fuel cell assembly positioned within the outer casing of the turbomachine, the fuel cell assembly including a fuel cell and an output products line in fluid communication with an outlet of the fuel cell for receiving output products from the fuel cell; a fuel delivery assembly including a fuel line; and a reformer in communication with the fuel line and the output products from the fuel cell during operation of the gas turbine engine to convert a fuel flow through the fuel line to a hydrogen rich gas.
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