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公开(公告)号：US11312502B2
公开(公告)日：2022-04-26
申请号：US16542834
申请日：2019-08-16
Applicant: General Electric Company
Inventor： Jeffrey Anthony Hamel , Kurt David Murrow
Abstract: In one aspect the present subject matter is directed to a gas-electric propulsion system for an aircraft. The system may include a turbofan jet engine, an electric powered boundary layer ingestion fan that is coupled to a fuselage portion of the aircraft aft of the turbofan jet engine, and an electric generator that is electronically coupled to the turbofan jet engine and to the boundary layer ingestion fan. The electric generator converts rotational energy from the turbofan jet engine to electrical energy and provides at least a portion of the electrical energy to the boundary layer ingestion fan. In another aspect of the present subject matter, a method for propelling an aircraft via the gas-electric propulsion system is disclosed.
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公开(公告)号：US20220073199A1
公开(公告)日：2022-03-10
申请号：US17329312
申请日：2021-05-25
Applicant: General Electric Company
Inventor： Randy M. Vondrell , Matthew Ryan Polakowski , Kurt David Murrow , Glenn Crabtree , Darek Tomasz Zatorski
IPC: B64C29/00 , B64C27/28 , H02J50/10 , A61L9/12 , H02J7/00 , B64C21/06 , B64D27/14 , B64D27/24 , H02P9/04
Abstract: A propulsion system of an aircraft has at least one unducted fan and at least one ducted fan, the at least one unducted fan and the at least one ducted fan being powered by an electric power source and rotatable between a vertical thrust position and a forward thrust position, and a controller configured to distribute electrical power between the at least one unducted fan and the at least one ducted fan. During a first mode when the at least one unducted fan and the at least one ducted fan are in the vertical thrust position, the controller is configured to distribute the electrical power between the plurality of unducted fans and the plurality of ducted fans such that the at least one unducted fan is a primary source of thrust.
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公开(公告)号：US11225319B2
公开(公告)日：2022-01-18
申请号：US16801976
申请日：2020-02-26
Applicant: The Boeing Company
Inventor： Miranda Peterson , Kevin R. Tsai
Abstract: A wing stall compensation mechanism employs an upper door having forward upper hinge end pivotally coupled to an upper wing structure for rotation about an upper axis and a free aft upper end. A lower door has a free aft lower end and a forward lower hinge end pivotally coupled to a lower wing structure for rotation about a lower axis and a 2-bar coupler linkage is disposed between and pivotally coupled to the upper door and lower door. Downward rotation of the upper door in response to wing surface airflow separation causes contraction of the coupler linkage inducing upward rotation of the lower door from a closed position that inhibits airflow through a flap slot to an open position that enables airflow through the flap slot, to thereby restore wing surface airflow effectiveness.
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公开(公告)号：US11142330B2
公开(公告)日：2021-10-12
申请号：US16117305
申请日：2018-08-30
Applicant: Aurora Flight Sciences Corporation
Inventor： Gary Richard Papas , Neil Titchener , Brian M. Yutko , Clint Church , Jian Long Tian
IPC: B64D35/00 , B64D27/14 , B64C21/00 , B64D33/04 , F16H1/22 , F16H37/06 , B64C1/16 , B64C21/06 , F02K3/062
Abstract: An aircraft with an integrated boundary layer ingesting propulsion having a mechanically-distributed propulsion system. The mechanically-distributed propulsion system may include an engine to generate a mechanical drive power, a drive shaft, a direction-reversing transmission, and a propulsor fan. The drive shaft may be operatively coupled to the engine to receive the mechanical drive power. The direction-reversing transmission may have a first rotating shaft and a second rotating shaft, the first rotating shaft operatively coupled to the drive shaft to receive the mechanical drive power, which is configured to redirect the mechanical drive power received at the first rotating shaft from a first direction to face a second direction at the second rotating shaft. The propulsor fan may be coupled to the second rotating shaft to convert the mechanical drive power into thrust.
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公开(公告)号：US11105340B2
公开(公告)日：2021-08-31
申请号：US15241137
申请日：2016-08-19
Applicant: General Electric Company
Inventor： Lawrence Chih-hui Cheung , Nikolai N. Pastouchenko , Kishore Ramakrishnan , Brandon Wayne Miller
IPC: F04D29/58 , B64D27/24 , B64D33/08 , B64C21/06 , F04D25/06 , H02K7/18 , H02K9/19 , H02K7/14 , F04D25/02 , B64D33/10 , B64D27/20 , B64D29/04 , B64D33/02 , B64D27/02
Abstract: A propulsion system for an aircraft includes an electric propulsion engine configured to be mounted at an aft end of the aircraft. The electric propulsion engine includes an electric motor and a fan rotatable about a central axis, the fan driven by the electric motor. The electric propulsion system additionally includes a cooling system operable with an airflow over the aft end the aircraft when the electric propulsion system is mounted to the aircraft. The cooling system is configured to cool the electric motor during operation of the electric propulsion engine.
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Patent Agency Ranking
公开(公告)号：US20210261238A1
公开(公告)日：2021-08-26
申请号：US16801976
申请日：2020-02-26
Applicant: The Boeing Company
Inventor： Miranda Peterson , Kevin R. Tsai
Abstract: A wing stall compensation mechanism employs an upper door having forward upper hinge end pivotally coupled to an upper wing structure for rotation about an upper axis and a free aft upper end. A lower door has a free aft lower end and a forward lower hinge end pivotally coupled to a lower wing structure for rotation about a lower axis and a 2-bar coupler linkage is disposed between and pivotally coupled to the upper door and lower door. Downward rotation of the upper door in response to wing surface airflow separation causes contraction of the coupler linkage inducing upward rotation of the lower door from a closed position that inhibits airflow through a flap slot to an open position that enables airflow through the flap slot, to thereby restore wing surface airflow effectiveness.
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公开(公告)号：US11097850B2
公开(公告)日：2021-08-24
申请号：US16503943
申请日：2019-07-05
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：US11046428B2
公开(公告)日：2021-06-29
申请号：US16502913
申请日：2019-07-03
Applicant: General Electric Company
Inventor： Randy M. Vondrell , Matthew Ryan Polakowski , Kurt David Murrow , Glenn Crabtree , Darek Tomasz Zatorski
IPC: B64C29/00 , B64C27/28 , H02J50/10 , A61L9/12 , H02J7/00 , H02J7/02 , B64C21/06 , B64D27/14 , B64D27/24 , H02P9/04 , B64C3/38 , B64D27/02
Abstract: A method for operating a propulsion system of an aircraft includes moving a plurality of forward and aft propulsors to a vertical thrust position. While in the vertical thrust positions, the method also includes providing a first forward to aft ratio of electric power to the plurality of forward and aft propulsors. The method also includes moving the plurality of forward and aft propulsors to a forward thrust position. While in the forward thrust positions, the method also includes providing a second forward to aft ratio of electric power to the plurality of forward and aft propulsors. The first forward to aft ratio of electric power is different than the second forward to aft ratio of electric power to provide certain efficiencies for the aircraft.
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公开(公告)号：US10882636B2
公开(公告)日：2021-01-05
申请号：US16133119
申请日：2018-09-17
Applicant: Airbus Operations SAS
Inventor： Mathias Farouz-Fouquet
IPC: B64D47/00 , B64C21/04 , H05H1/24 , B08B7/00 , B64C21/06 , B64C21/02 , F04D29/68 , B64D15/02 , B64D33/02
Abstract: A wing comprising a leading edge forming a caisson delimited by a wall and an electrically conductive skin forming a lower surface and an upper surface and pierced with holes. A pump is provided to suck the air present in the caisson and/or to inject air into the caisson. The wing includes a voltage generator. Each hole is equipped with an anti-clogging system which comprises an electrically conductive electrode, an electrically insulating body having a stem which lodges in the hole and which has a central orifice in which the electrode lodges. The outer face of the stem has at least one tooth, where each tooth protrudes from the outer face of the stem and extends over the height of the stem. The at least one tooth is distributed around the stem so as to create at least one channel.
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公开(公告)号：US20200369376A1
公开(公告)日：2020-11-26
申请号：US16966353
申请日：2019-01-23
Applicant: AIRBUS OPERATIONS GMBH
Inventor： Thomas HEUER , Volker PIEZUNKA
Abstract: An airfoil for flow control is disclosed having an outer skin in contact with an ambient air flow, wherein the outer skin extends between a leading edge and a trailing edge with two opposite lateral sides, and surrounds an interior space. The outer skin comprises a porous section in the area of the leading edge, a pressure chamber arranged in the interior space and fluidly connected to the porous section, an air inlet fluidly connected to the pressure chamber, and an air outlet fluidly connected to the pressure chamber.
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