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公开(公告)号：US10793281B2
公开(公告)日：2020-10-06
申请号：US15429979
申请日：2017-02-10
Applicant: General Electric Company
Inventor： Randy M. Vondrell , Glenn David Crabtree
Abstract: A propulsion system for an aircraft includes a turbomachine having a first turbine, a primary fan mechanically driven by the first turbine of the turbomachine, and an electric generator mechanically driven by the first turbine of the turbomachine. The propulsion system also includes an electric fan assembly, the electric generator electrically connected to the electric fan assembly for powering the electric fan assembly.
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公开(公告)号：US10703496B2
公开(公告)日：2020-07-07
申请号：US15493544
申请日：2017-04-21
Applicant: General Electric Company
Inventor： Randy M. Vondrell , Anthony Austin Bouvette , Glenn David Crabtree
IPC: B64D27/24 , B60L50/16 , B60L11/14 , B64C21/06 , B64D27/12 , B64D27/18 , F02C6/20 , F02K3/04 , H02G5/10 , H02K7/18 , B64D27/02
Abstract: A propulsion system for an aircraft includes an electric power source and an electric propulsion assembly having an electric motor and a propulsor, the propulsor powered by the electric motor. The propulsion system also includes an electric power bus electrically connecting the electric power source to the electric propulsion assembly. The electric power source is configured to provide electrical power to the electric power bus, and the electric power bus is configured to transfer the electric power to the electric propulsion assembly at a voltage exceeding 800 volts.
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公开(公告)号：US10676205B2
公开(公告)日：2020-06-09
申请号：US15241157
申请日：2016-08-19
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Randy M. Vondrell , Brandon Wayne Miller , Patrick Michael Marrinan , Lawrence Chih-hui Cheung , Nikolai N. Pastouchenko
IPC: B64D33/08 , F02K5/00 , F02C7/14 , F02C6/20 , B64C11/00 , B64C21/06 , B64D27/10 , B64D27/24 , F01D15/10 , F01D15/12 , F02K3/062 , F04D29/056 , F04D29/063 , F04D29/32 , F04D29/58 , B64D27/02
Abstract: A propulsion system for an aircraft includes an electric propulsion engine. The electric propulsion engine includes an electric motor and a fan rotatable about a central axis of the electric propulsion engine by the electric motor. The electric propulsion engine also includes a bearing supporting rotation of the fan and a thermal management system. The thermal management system includes a lubrication oil circulation assembly and a heat exchanger thermally connected to the lubrication oil circulation assembly. The lubrication oil circulation assembly is configured for providing the bearing with lubrication oil. Such an electric propulsion engine may be a relatively self-sufficient engine.
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公开(公告)号：US20200063606A1
公开(公告)日：2020-02-27
申请号：US16108732
申请日：2018-08-22
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Randy M. Vondrell , Darek Tomasz Zatorski , Christopher Charles Glynn
Abstract: A method is provided for maintaining a gas turbine engine installed on an aircraft, the gas turbine engine including an electric machine mounted at least partially inward of a core air flowpath of the gas turbine engine. The method includes removing a rotor mount connecting a rotor of the electric machine to a rotary component of the gas turbine engine; removing a stator mount connecting a stator of the electric machine to a stationary component of the gas turbine engine; and removing in situ the electric machine.
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公开(公告)号：US10392120B2
公开(公告)日：2019-08-27
申请号：US15132298
申请日：2016-04-19
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Randy M. Vondrell , Brandon Wayne Miller , Patrick Michael Marrinan
Abstract: A propulsion system for an aircraft is provided having a propulsion engine configured to be mounted to the aircraft. The propulsion engine includes an electric machine defining an electric machine tip speed during operation. The propulsion system additionally includes a fan rotatable about a central axis of the electric propulsion engine with the electric machine. The fan defines a fan pressure ratio, RFP, and includes a plurality of fan blades, each fan blade defining a fan blade tip speed. The electric propulsion engine defines a ratio of the fan blade tip speed to electric machine tip speed that is within twenty percent of the equation, 1.68×RFP−0.518, such that the propulsion engine may operate at a desired efficiency.
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Patent Agency Ranking
公开(公告)号：US10392119B2
公开(公告)日：2019-08-27
申请号：US15095249
申请日：2016-04-11
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Randy M. Vondrell , Brandon Wayne Miller , Patrick Michael Marrinan
Abstract: A propulsion system for an aircraft includes an electric propulsion engine configured to be mounted to the aircraft at an aft end of the aircraft. The electric propulsion engine includes a power gearbox mechanically coupled to an electric motor. The electric propulsion engine further includes a fan rotatable about a central axis of the electric propulsion engine by the electric motor through the power gearbox. Moreover, the electric propulsion engine includes an attachment assembly for mounting at least one of the electric motor or the power gearbox. The attachment assembly includes a torsional damper for accommodating a torsional vibration of the electric motor or the power gearbox.
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公开(公告)号：US10392106B2
公开(公告)日：2019-08-27
申请号：US15259564
申请日：2016-09-08
Applicant: General Electric Company
Inventor： Randy M. Vondrell , Matthew Ryan Polakowski , Kurt David Murrow , Glenn Crabtree , Darek Tomasz Zatorski
Abstract: An aircraft includes a fuselage, a forward wing assembly, and aft wing assembly, and a propulsion system. The propulsion system includes a port forward propulsor and a starboard forward propulsor, each of which rotatable between a forward thrust position and a vertical thrust position and together defining a maximum forward thrust capability. The propulsion system also includes a port aft propulsor and a starboard aft propulsor, each of which also rotatable between a forward thrust position and a vertical thrust position, and together defining a maximum aft thrust capability. The maximum forward thrust capability is different than the maximum aft thrust capability to achieve certain efficiencies.
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公开(公告)号：US20180334258A1
公开(公告)日：2018-11-22
申请号：US15597571
申请日：2017-05-17
Applicant: General Electric Company
Abstract: A propulsion system for an includes a combustion engine, a propulsor, and an electric machine configured to either be driven by the combustion engine or configured to drive the propulsor. The electric machine defines an axis. The electric machine includes a rotor extending along and rotatable about the axis, and a stator having a plurality of winding assemblies, the plurality of winding assemblies spaced along the axis of the electric machine, each winding assembly operable with the rotor independently of an adjacent winding assembly during operation of the electric machine.
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公开(公告)号：US20180320633A1
公开(公告)日：2018-11-08
申请号：US15439167
申请日：2017-02-22
Applicant: General Electric Company
Inventor： Thomas Ory Moniz , Randy M. Vondrell , Jeffrey Donald Clements , Brandon Wayne Miller
CPC classification number: F02K3/075 , B64D33/04 , F02C3/107 , F02C3/13 , F02C7/36 , F02K3/04 , F02K3/06 , F05D2260/40
Abstract: The present disclosure is directed to a gas turbine engine defining a radial direction, a longitudinal direction, and a circumferential direction, an upstream end and a downstream end along the longitudinal direction, and an axial centerline extended along the longitudinal direction. The gas turbine engine includes a fan assembly including a plurality of fan blades rotatably coupled to a fan rotor in which the fan blades define a maximum fan diameter and a fan pressure ratio. The gas turbine engine further includes a low pressure (LP) turbine defining a core flowpath therethrough generally along the longitudinal direction. The core flowpath defines a maximum outer flowpath diameter relative to the axial centerline. The gas turbine engine defines a fan to turbine diameter ratio of the maximum fan diameter to the maximum outer flowpath diameter. The fan to turbine diameter ratio over the fan pressure ratio is approximately 0.90 or greater.
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公开(公告)号：US20180163558A1
公开(公告)日：2018-06-14
申请号：US15377080
申请日：2016-12-13
Applicant: General Electric Company
Inventor： Randy M. Vondrell , Glenn Crabtree
CPC classification number: F01D15/10 , B64D27/10 , B64D27/24 , B64D35/08 , B64D2027/026 , F02C7/36 , F05D2220/32 , F05D2220/76 , F05D2240/60 , F05D2260/4023 , F16D41/069 , F16D48/06 , F16D2500/10412 , F16D2500/10493 , F16D2500/3065 , Y02T50/64
Abstract: A propulsion system includes a propulsor having a driveshaft, an electric machine coupled to the driveshaft of the propulsor, and a combustion engine having an output shaft. The propulsion system additionally includes a one-way clutch operable with at least one of the driveshaft of the propulsor and the output shaft of the combustion engine. The one-way clutch allows for a differential angular velocity of the driveshaft relative to the output shaft in a first circumferential direction and prevents a differential angular velocity of the driveshaft relative to the output shaft in a second circumferential direction.
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