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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
Applicant: General Electric Company
Inventor： Kurt David Murrow , Darek Tomasz Zatorksi , Andrew Breeze-Stringfellow , Randy M. Vondrell , Dominic Barone
Abstract: 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：US20190023389A1
公开(公告)日：2019-01-24
申请号：US15699315
申请日：2017-09-08
Applicant: General Electric Company
Abstract: An aircraft includes a fuselage; a wing coupled to, and extending from, the fuselage; and a propulsion system. The propulsion system includes a plurality of electric fans integrated into the wing and oriented to generate thrust along a vertical direction, the plurality of electric fans arranged along a length of the wing and including an outer-most electric fan along a transverse direction relative to the fuselage. The outer-most electric fan is at least one of a variable pitch fan or a variable speed fan to provide increased stability to the aircraft.
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公开(公告)号：US10017270B2
公开(公告)日：2018-07-10
申请号：US14879217
申请日：2015-10-09
Applicant: General Electric Company
IPC: B64D33/02 , B64D27/18 , B64D27/24 , B64D27/26 , F01D15/10 , F02C7/32 , F02K3/062 , F04D29/32 , F04D29/36 , F04D29/52 , F04D29/54 , B64C1/16 , B64C21/06 , B64D27/20 , B64D29/04 , B64D27/02
CPC classification number: B64D33/02 , B64C1/16 , B64C21/06 , B64D27/18 , B64D27/20 , B64D27/24 , B64D27/26 , B64D29/04 , B64D2027/026 , B64D2033/0226 , F01D15/10 , F02C7/32 , F02K3/062 , F04D29/325 , F04D29/36 , F04D29/522 , F04D29/542 , F05D2220/323 , Y02T50/166
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 attached to a fan shaft. The aft engine also includes a nacelle encircling the plurality of fan blades and a structural support system for mounting the aft engine to the aircraft. The structural support system extends from the fuselage of the aircraft, through the fan shaft, and to the nacelle 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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公开(公告)号：US20170184020A1
公开(公告)日：2017-06-29
申请号：US14982793
申请日：2015-12-29
Applicant: General Electric Company
Abstract: A gas turbine engine system and method of operating gas turbine engines are provided. The gas turbine engine assembly includes a gas turbine engine includes a power shaft configured to rotate about an axis of rotation. The gas turbine engine assembly also includes a first fan and a second fan coupled to the power shaft coaxially with the gas turbine engine. The gas turbine engine assembly also includes a first fan duct configured to direct a first stream of air to the first fan. The gas turbine engine assembly also includes a second fan duct configured to direct a second stream of air to the second fan. The gas turbine engine assembly also includes an exhaust duct configured to direct a stream of exhaust gases of the gas turbine engine in a direction of the axis of rotation.
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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：US20160146115A1
公开(公告)日：2016-05-26
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
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.
Abstract translation: 提供了一种涡轮风扇燃气涡轮发动机系统的方法和系统。 燃气涡轮发动机系统包括耦合到第一可旋转轴的变桨距风扇（VPF）组件和耦合到第二可旋转轴的低压压缩机LPC。 LPC包括多个可变桨距定子叶片，其与LPC的转子的叶片行相互指向。 燃气涡轮发动机系统还包括联接到所述第一可旋转轴和所述第二可旋转轴的减速装置。 燃气涡轮发动机系统还包括位于所述LPC的出口和旁路管道之间的调节压力释放阀，以及被配置为响应于操作来调度所述多个变桨距定子叶片和所述调节压力释放阀的位置的控制器 所述涡轮风扇燃气涡轮发动机系统的状态和与所述LPC相关联的温度。
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公开(公告)号：US12006031B2
公开(公告)日：2024-06-11
申请号：US17366749
申请日：2021-07-02
Applicant: General Electric Company
IPC: B64C29/00 , B64C3/10 , B64C3/32 , B64C3/38 , B64D27/24 , B64D29/04 , B64D31/06 , B64D33/04 , B64D35/02 , B64D27/02 , B64D27/40 , H02K7/18
CPC classification number: B64C29/0025 , B64C3/10 , B64C3/32 , B64C3/38 , B64C29/00 , B64D27/24 , B64D29/04 , B64D31/06 , B64D33/04 , B64D35/02 , B64D27/02 , B64D27/026 , B64D27/40 , F05D2220/76 , F05D2270/093 , H02K7/1823
Abstract: An aircraft defines a vertical direction and includes a fuselage and a propulsion system comprising a power source and a plurality of vertical thrust electric fans driven by the power source. A wing extends from the fuselage. The plurality of vertical thrust electric fans are arranged along a length of the wing along a lengthwise direction of the wing. The wing comprises a diffusion assembly along the lengthwise direction of the wing and includes a first diffusion member positioned downstream of at least one of the plurality of vertical thrust electric fans. The first diffusion member defines a curved shape relative to a longitudinal direction of the aircraft. The longitudinal direction is generally perpendicular to the lengthwise direction of the wing.
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58.发明公开公开(公告)号：US20240132226A1
公开(公告)日：2024-04-25
申请号：US18351745
申请日：2023-07-12
Applicant: General Electric Company
Inventor： Darek Tomasz Zatorski , Kurt David Murrow , Paul Robert Gemin , Philip M. Cioffi , John Russell Yagielski
Abstract: A propulsion assembly includes a first torque source coupled with a first shaft and a second torque source coupled with a second shaft. A coupler selectively couples the first and second torque sources. When the first and second torque sources are coupled via the coupler, in response to a command to decouple the first torque source, an unloading operation is performed to decrease the torque output provided by the first torque source to a threshold, and when reached, the first shaft is decoupled from the coupler. When the first torque source is coupled with the coupler but the second torque source is not, in response to a command to couple the second torque source, a speed matching operation is performed to increase the speed of the second shaft to match a speed of the first shaft, and when the speeds are matched, the second shaft is coupled to the coupler.
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59.发明公开公开(公告)号：US20240025555A1
公开(公告)日：2024-01-25
申请号：US18351725
申请日：2023-07-13
Applicant: General Electric Company
Inventor： Darek Tomasz Zatorski , Kurt David Murrow , Paul Robert Gemin , Philip M. Cioffi , John Russell Yagielski
CPC classification number: B64D35/08 , B64D27/10 , B64D27/24 , F02C7/36 , B64D2027/026
Abstract: A propulsion assembly includes a first torque source coupled with a first shaft and a second torque source coupled with a second shaft. A coupler selectively couples the first and second torque sources. When the first and second torque sources are coupled via the coupler, in response to a command to decouple the first torque source, an unloading operation is performed to decrease the torque output provided by the first torque source to a threshold, and when reached, the first shaft is decoupled from the coupler. When the first torque source is coupled with the coupler but the second torque source is not, in response to a command to couple the second torque source, a speed matching operation is performed to increase the speed of the second shaft to match a speed of the first shaft, and when the speeds are matched, the second shaft is coupled to the coupler.
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公开(公告)号：US11673661B2
公开(公告)日：2023-06-13
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 , A61L9/12 , H02J7/00 , H02J50/10 , B64C21/06 , B64D27/14 , B64D27/24 , H02P9/04 , B64C3/38 , B64D27/02
CPC classification number: B64C29/0033 , A61L9/122 , B64C21/06 , B64C27/28 , B64C29/00 , B64D27/14 , B64D27/24 , H02J7/0042 , H02J50/10 , H02P9/04 , A61L2209/133 , B64C3/385 , B64C29/0008 , B64D2027/026 , B64D2221/00 , Y02T50/60
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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