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公开(公告)号：US20240352866A1
公开(公告)日：2024-10-24
申请号：US18354021
申请日：2023-07-18
发明人： Randy M. Vondrell , Kevin William Caldwell , John Carl Glessner , Javier Barba Fuentes , Dorota Kopkowicz
CPC分类号： F01D11/20 , F05D2260/213
摘要： A gas turbine engine includes a fan section, an engine inlet, and a fan duct splitter in serial flow order. The fan duct splitter splits an airflow entering the engine inlet from the fan section into a fan duct and a core duct. The core duct includes a compressor section, a combustion section, and a turbine section in serial flow order. A duct assembly is coupled to the fan duct to extract a portion of a fan duct airflow passing through the fan duct and deliver the portion of the fan duct airflow to an active clearance control mechanism of the turbine section.
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公开(公告)号：US11685542B2
公开(公告)日：2023-06-27
申请号：US16891337
申请日：2020-06-03
发明人： Daniel Alan Niergarth , Randy M. Vondrell , Brandon Wayne Miller , Patrick Michael Marrinan , Lawrence Chih-Hui Cheung , Nikolai N. Pastouchenko
IPC分类号： B64D27/10 , B64D27/24 , B64D33/08 , F02K5/00 , F02C7/14 , F02C6/20 , B64C11/00 , B64C21/06 , F01D15/10 , F01D15/12 , F02K3/062 , F04D29/056 , F04D29/063 , F04D29/32 , F04D29/58 , B64D27/02
CPC分类号： B64D33/08 , B64C11/001 , B64C21/06 , B64D27/10 , B64D27/24 , F01D15/10 , F01D15/12 , F02C6/206 , F02C7/14 , F02K3/062 , F02K5/00 , F04D29/056 , F04D29/063 , F04D29/325 , F04D29/582 , B64D2027/026 , F05D2220/323 , F05D2260/213 , F05D2260/98 , Y02T50/60
摘要： A propulsion system for an aircraft having an aft end is provided herein. The propulsion system can include an electric propulsion engine defining a central axis. The electric propulsion engine can include an electric motor, a fan rotatable about the central axis of the electric propulsion engine by the electric motor, a bearing supporting rotation of the fan, and a thermal management system. The thermal management system can include a lubrication oil circulation assembly for providing the bearing with lubrication oil. The lubrication oil circulation assembly can be driven independently of a shaft of the electric propulsion engine.
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公开(公告)号：US20220289394A1
公开(公告)日：2022-09-15
申请号：US17571752
申请日：2022-01-10
IPC分类号： B64D27/24 , F01D15/10 , F01D25/18 , F02K5/00 , F04D25/06 , F02C7/32 , B64D27/12 , F02C7/24 , F02K3/06 , F04D19/02 , H02K1/27 , H02K7/18
摘要： 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. A cavity wall defines at least in part a buffer cavity surrounding at least a portion of the electric machine to thermally insulate the electric machine, e.g., from the relatively high temperatures within the core air flowpath.
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公开(公告)号：US11156128B2
公开(公告)日：2021-10-26
申请号：US16108732
申请日：2018-08-22
摘要： 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：US20190023408A1
公开(公告)日：2019-01-24
申请号：US15699349
申请日：2017-09-08
发明人： Kurt David Murrow , Darek Tomasz Zatorksi , Andrew Breeze-Stringfellow , Randy M. Vondrell , Dominic Barone
摘要： An aircraft includes a fuselage; a wing coupled to, and extending from, the fuselage; and a hybrid-electric propulsion system. The hybrid-electric propulsion system includes a power source including a combustion engine and an electric generator; a plurality of vertical thrust electric fans integrated into the wing and oriented to generate thrust along the vertical direction, the plurality of vertical thrust electric fans arranged along a length of the wing and driven by the power source; and a forward thrust propulsor. The forward thrust propulsor it is selectively or permanently mechanically coupled to the combustion engine.
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公开(公告)号：US20180304753A1
公开(公告)日：2018-10-25
申请号：US15493544
申请日：2017-04-21
摘要： 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：US10093428B2
公开(公告)日：2018-10-09
申请号：US15242844
申请日：2016-08-22
摘要： A propulsion system includes an electric propulsor and a gas turbine engine. The propulsion system also includes an electric machine coupled to a rotary component of the gas turbine engine generating a voltage at a baseline voltage magnitude during operation of the gas turbine engine. An electric communication bus is provided electrically connecting the electric machine to the electric propulsor. The propulsion system additionally includes a means for providing a differential voltage to the electric propulsor equal to about twice the baseline voltage magnitude.
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公开(公告)号：US20180216575A1
公开(公告)日：2018-08-02
申请号：US15417745
申请日：2017-01-27
发明人： Brandon Wayne Miller , Matthew Ryan Polakowski , Patrick Michael Marrinan , Joel Francis Kirk , Randy M. Vondrell , Jeffrey Donald Clements
CPC分类号： F02K3/06 , F01D25/26 , F02C3/04 , F02C7/18 , F02C7/36 , F05D2220/36 , F05D2300/20 , Y02T50/672
摘要： A turbofan engine is provided including a fan having a plurality of rotatable fan blades and defining a fan pressure ratio during operation of the turbofan engine. The turbofan engine also includes a turbomachine operably coupled to the fan for driving the fan, the turbomachine including a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath. The turbofan also includes an outer nacelle at least partially surrounding the fan and the turbomachine, the outer nacelle defining a bypass passage with the turbomachine. A bypass ratio of an amount of airflow through the bypass passage to an amount of airflow through the core air flowpath during operation of the turbofan is less than or equal to about 11 and wherein the fan pressure ratio is less than or equal to about 1.5.
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公开(公告)号：US20180050810A1
公开(公告)日：2018-02-22
申请号：US15241157
申请日：2016-08-19
发明人： Daniel Alan Niergarth , Randy M. Vondrell , Brandon Wayne Miller , Patrick Michael Marrinan , Lawrence Chih-hui Cheung , Nikolai N. Pastouchenko
IPC分类号： B64D33/08 , B64C21/06 , B64D27/10 , B64D27/24 , F01D15/10 , F01D15/12 , F02K3/062 , F04D29/32 , F04D29/056 , F04D29/063 , F04D29/58
摘要： 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：US20170291693A1
公开(公告)日：2017-10-12
申请号：US15095262
申请日：2016-04-11
CPC分类号： B64C21/06 , B64C2230/04 , B64D27/24 , B64D33/02 , B64D2027/026 , B64D2033/0226 , F02K5/00 , Y02T50/166 , Y02T50/62
摘要： 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 fan rotatable about a central axis of the electric propulsion engine. The fan includes a fan shaft mechanically coupled to a power gearbox. The electric propulsion engine also includes an electric motor having a driveshaft, with the electric motor coupled to the power gearbox through the drive shaft. The electric motor rotates the fan through the power gearbox. The driveshaft includes a flexible element for accommodating a misalignment of the electric motor and the power gearbox.
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