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公开(公告)号：US20180305036A1
公开(公告)日：2018-10-25
申请号：US15493623
申请日：2017-04-21
Applicant: General Electric Company
Inventor： Randy M. Vondrell , Anthony Austin Bouvette , Robert Charles Hon
IPC: B64D33/08 , B64D27/18 , B64D27/24 , B64C21/06 , B60L11/14 , F02K3/04 , H02G5/10 , H02K9/19 , H02K7/18
CPC classification number: B64D33/08 , B60L50/16 , B60L2200/10 , B64C21/06 , B64D27/18 , B64D27/24 , B64D2027/026 , B64D2221/00 , F02K3/04 , H02G5/10 , H02K7/1823 , H02K9/19 , Y02T50/64
Abstract: A propulsion system for an aircraft includes an electric power source, an electric propulsor assembly having an electric motor and a propulsor configured to generate thrust for the aircraft, and a power bus electrically connecting the electric power source to the electric propulsor assembly such that the electric power source powers the electric propulsor assembly. The power bus includes an electric line and a fluid cooling system, the fluid cooling system extending along at least a portion of a length of the electric line. The fluid cooling system is in thermal communication with the electric line for cooling the electric line during operation and is further in thermal communication with the electric motor of the electric propulsor assembly for cooling the electric motor of the electric propulsor assembly.
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公开(公告)号：US10071811B2
公开(公告)日：2018-09-11
申请号：US15242811
申请日：2016-08-22
Applicant: General Electric Company
Inventor： Thomas Kupiszewski , Brandon Wayne Miller , Randy M. Vondrell , Paul Robert Gemin
CPC classification number: B64D27/12 , B64C21/06 , B64D27/18 , B64D27/24 , B64D29/04 , B64D33/00 , B64D2027/026 , B64D2033/0226 , B64D2221/00 , F01D9/065 , F01D15/10 , F01D25/162 , F02C3/04 , F02C7/16 , F02C7/32 , F02K5/00 , F04D25/06 , F05D2220/32 , F05D2220/76 , F05D2260/20 , F05D2260/98 , Y02T50/676
Abstract: A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. An electric machine is mounted coaxially with the rotary component and positioned at least partially inward of the core air flowpath along a radial direction of the gas turbine engine. An electric communication bus is electrically connected to the electric machine and extends through the core air flowpath to, e.g., electrically connect the electric machine to one or more systems of the gas turbine engine or a propulsion system including the gas turbine engine.
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公开(公告)号：US20180229606A1
公开(公告)日：2018-08-16
申请号：US15429934
申请日：2017-02-10
Applicant: General Electric Company
Inventor： Randy M. Vondrell , Glenn David Crabtree , Dominic Barone
CPC classification number: B60L1/006 , B60L50/10 , B60L2200/10 , B64C29/0033 , B64C39/024 , B64C2201/126 , B64C2201/128 , B64D27/14 , B64D27/24 , B64D2027/026 , H02P9/04
Abstract: An aircraft includes an electric power source having a combustion engine and an electric generator. The electric generator is powered by the combustion engine. The aircraft also includes a propulsion assembly including a propulsor and an electric motor, the electric motor configured for rotating the propulsor. The aircraft also includes an electrical outlet configured for connection with an outside power sink. The electrical outlet and the propulsion assembly are selectively in electrical communication with the electric power source such that the electric power source selectively provides electrical power to one of the electrical outlet or the propulsion assembly.
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公开(公告)号：US20180051702A1
公开(公告)日：2018-02-22
申请号：US15242811
申请日：2016-08-22
Applicant: General Electric Company
Inventor： Thomas Kupiszewski , Brandon Wayne Miller , Randy M. Vondrell , Paul Robert Gemin
CPC classification number: B64D27/12 , B64D27/18 , B64D27/24 , F01D9/065 , F01D15/10 , F01D25/162 , F02C3/04 , F02C7/16 , F02C7/32 , F02K5/00 , F04D25/06 , F05D2220/32 , F05D2220/76 , F05D2260/20 , F05D2260/98
Abstract: A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. An electric machine is mounted coaxially with the rotary component and positioned at least partially inward of the core air flowpath along a radial direction of the gas turbine engine. An electric communication bus is electrically connected to the electric machine and extends through the core air flowpath to, e.g., electrically connect the electric machine to one or more systems of the gas turbine engine or a propulsion system including the gas turbine engine.
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公开(公告)号：US09878501B2
公开(公告)日：2018-01-30
申请号：US14596841
申请日：2015-01-14
Applicant: General Electric Company
Inventor： Darek Tomasz Zatorski , Ian Francis Prentice , Randy M. Vondrell , Andrew Breeze-Stringfellow
CPC classification number: B29C70/34 , B29D99/0025
Abstract: A method of manufacturing a frangible laminate is provided. The method comprises constructing a reinforced polymer matrix, cutting the reinforced polymer matrix into a plurality of laminae, forming a laminate via stacking the plurality of laminae and at least one energy dissipating member, and consolidating the laminate.
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Patent Agency Ranking
公开(公告)号：US20170297727A1
公开(公告)日：2017-10-19
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
CPC classification number: B64D27/24 , B64D27/02 , B64D27/18 , B64D2027/026 , F02C3/04 , F02C7/20 , F02C7/36 , F02K3/04 , F05D2220/76 , Y10S903/905 , Y10S903/906 , Y10S903/907
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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公开(公告)号：US09777642B2
公开(公告)日：2017-10-03
申请号：US14919825
申请日：2015-10-22
Applicant: General Electric Company
Inventor： Kurt David Murrow , Andrew Breeze-Stringfellow , Randy M. Vondrell , Tsuguji Nakano , Jeffrey Anthony Hamel , Darek Tomasz Zatorski
IPC: F02C1/00 , F02C9/20 , F01D7/00 , F01D15/12 , F01D17/08 , F01D17/10 , F01D17/16 , F02K1/66 , F02K3/04 , F02K3/075 , F02C3/13 , F02C7/36 , F02C9/18 , F02C3/04 , F02C7/042
CPC classification number: F02C9/20 , F01D7/00 , F01D15/12 , F01D17/085 , F01D17/105 , F01D17/162 , F02C3/04 , F02C3/13 , F02C7/042 , F02C7/36 , F02C9/18 , F02K1/66 , F02K3/04 , F02K3/075 , F05D2220/36 , F05D2270/101 , F05D2270/303 , F05D2300/30 , Y02T50/672
Abstract: A method and system for a turbofan gas turbine engine system is provided. The gas turbine engine system includes a variable pitch fan (VPF) assembly coupled to a first rotatable shaft and a low pressure compressor LPC coupled to a second rotatable shaft. The LPC including a plurality of variable pitch stator vanes interdigitated with rows of blades of a rotor of the LPC. The gas turbine engine system also includes a speed reduction device coupled to said first rotatable shaft and said second rotatable shaft. The gas turbine engine system further includes a modulating pressure relief valve positioned between an outlet of said LPC and a bypass duct and a controller configured to schedule a position of said plurality of variable pitch stator vanes and said modulating pressure relief valve in response to an operational state of said turbofan gas turbine engine system and a temperature associated with said LPC.
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公开(公告)号：US12240615B2
公开(公告)日：2025-03-04
申请号：US18079072
申请日：2022-12-12
Inventor： David Marion Ostdiek , William Joseph Solomon , Mohamed Osama , Arthur William Sibbach , Randy M. Vondrell
Abstract: An electric propulsor is provided. The electric propulsor includes a core cowl and an outer cowl. A first air flowpath is defined radially outward of the outer cowl and a second air flowpath is defined between the core cowl and the outer cowl. The electric propulsor also includes one or more electric machines, a fan rotatably drivable by at least one electric machine, and a booster having a plurality of airfoils disposed at least in part in the second air flowpath, the booster being rotatably drivable by at least one electric machine for compressing air flowing along the second air flowpath. The electric propulsor further includes a heat exchanger disposed within the second air flowpath downstream of the booster, the heat exchanger being in thermal communication with at least one of the one or more electric machines and/or a gearbox mechanically coupled with the fan.
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公开(公告)号：US20240401491A1
公开(公告)日：2024-12-05
申请号：US18678000
申请日：2024-05-30
Applicant: General Electric Company
Inventor： Syed Khalid , David Marion Ostdiek , Jeffrey S. Spruill , Daniel Lawrence Tweedt , William Joseph Solomon , Brandon Wayne Miller , Randy M. Vondrell , Kevin Edward Hinderliter
Abstract: A gas turbine engine is provided, comprising: a turbomachine having a compressor section, a combustion section, and a turbine section in serial flow order; and a fan section having a fan drivingly coupled to the turbomachine and an airflow surface rotatable with the fan and exposed to a fan airflow provided to and through the fan during operation of the gas turbine engine, the airflow surface defining a plurality of boundary layer openings configured to ingest a boundary layer of the fan airflow over the airflow surface during operation of the gas turbine engine.
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公开(公告)号：US20240287938A1
公开(公告)日：2024-08-29
申请号：US18404322
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: F02C7/232 , H01M8/04014 , H01M8/04089 , H01M8/04111 , H01M8/0612
CPC classification number: F02C7/232 , H01M8/04014 , H01M8/04097 , H01M8/04111 , H01M8/0618 , H01M2250/20
Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a turbomachine having a compressor section, a combustor, and a turbine section arranged in serial flow order, the turbomachine further including an outer casing; and a fuel cell assembly positioned within the outer casing of the turbomachine, the fuel cell assembly including a fuel cell, an inlet line in fluid communication with an inlet of the 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, wherein the inlet line is positioned to be in thermal communication with the output products during operation of the gas turbine engine.
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