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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
IPC分类号： 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分类号： 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
摘要： 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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2.发明授权公开(公告)号：US11981419B2
公开(公告)日：2024-05-14
申请号：US17560544
申请日：2021-12-23
CPC分类号： B64C11/38 , F02K3/06 , F04D29/325 , F04D29/36 , F04D29/362 , Y02T50/60
摘要： The variable pitch propeller assembly includes a hub. The variable pitch propeller assembly also includes a plurality of propeller blade assemblies spaced circumferentially about the hub. Each of the plurality of propeller blade assemblies configured to rotate a respective propeller blade. The variable pitch propeller assembly also includes a hydraulic fluid port assembly integrally formed and including at least three hydraulic fluid ports configured to receive respective flows of hydraulic fluid from a stationary hydraulic fluid transfer sleeve. The variable pitch propeller assembly also includes a pitch actuator assembly coupled in flow communication with at least three hydraulic fluid ports through respective hydraulic fluid transfer tubes. The pitch actuator coupled to the plurality of propeller blade assemblies to selectively control a pitch of the propeller blades. The pitch actuator assembly includes a travel stop configured to limit a rotation of at least one of the pitch actuator assemblies.
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3.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
发明人： Darek Tomasz Zatorski , Kurt David Murrow , Paul Robert Gemin , Philip M. Cioffi , John Russell Yagielski
摘要： 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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4.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
发明人： Darek Tomasz Zatorski , Kurt David Murrow , Paul Robert Gemin , Philip M. Cioffi , John Russell Yagielski
CPC分类号： B64D35/08 , B64D27/10 , B64D27/24 , F02C7/36 , B64D2027/026
摘要： 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
发明人： Randy M. Vondrell , Matthew Ryan Polakowski , Kurt David Murrow , Glenn Crabtree , Darek Tomasz Zatorski
IPC分类号： B64C29/00 , B64C27/28 , A61L9/12 , H02J7/00 , H02J50/10 , B64C21/06 , B64D27/14 , B64D27/24 , H02P9/04 , B64C3/38 , B64D27/02
CPC分类号： 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
摘要： 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：US11606011B2
公开(公告)日：2023-03-14
申请号：US16989141
申请日：2020-08-10
IPC分类号： H02K21/02 , B64D27/02 , B64D27/10 , B64D27/24 , B64D31/00 , F01D15/10 , H02K7/18 , H02K21/22
摘要： An electric machine is provided. The electric machine defines a centerline and includes: a stator assembly; a rotor assembly rotatable relative to the stator assembly about the centerline; and an actuator coupled to the rotor assembly, the stator assembly, or both for moving the rotor assembly, the stator assembly, or both along the centerline between a first position and a second position, the rotor assembly positioned closer to the stator assembly when in the first position than when in the second position.
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公开(公告)号：US20220063825A1
公开(公告)日：2022-03-03
申请号：US17162158
申请日：2021-01-29
摘要： A method for operating a hybrid electric propulsion system of an aircraft, the hybrid electric propulsion system comprising a turbomachine, an electric machine coupled to the turbomachine, and a propulsor coupled to the turbomachine, the method comprising: operating the turbomachine to drive the propulsor; receiving data indicative of a failure condition of the hybrid electric propulsion system; and extracting power from the turbomachine using the electric machine to slow down one or more rotating components of the turbomachine in response to receiving the data indicative of the failure condition.
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公开(公告)号：US11117675B2
公开(公告)日：2021-09-14
申请号：US16042216
申请日：2018-07-23
IPC分类号： B64D27/24 , B64D29/04 , B64C3/10 , B64D27/08 , B64C3/32 , B64C35/02 , B64C3/38 , B64D33/04 , B64D31/06 , B64C29/00 , B64D35/02 , B64D27/02 , B64D27/26 , H02K7/18
摘要： An aircraft includes a fuselage; a propulsion system including a power source and a plurality of vertical thrust electric fans driven by the power source; and a wing extending from the fuselage. The plurality of vertical thrust electric fans are arranged along a length of the wing, the wing including a variable geometry assembly extending along the length of the wing and moveable between a forward thrust position and a vertical thrust position, the variable geometry assembly at least partially covering the plurality of vertical thrust electric fans when in the forward thrust position and at least partially exposing the plurality of vertical thrust electric fans when in the vertical thrust position.
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公开(公告)号：US11105200B2
公开(公告)日：2021-08-31
申请号：US15648867
申请日：2017-07-13
摘要： The present disclosure is directed to a turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction. The turbine engine includes a power turbine including a first turbine rotor assembly interdigitated with a second turbine rotor assembly along the longitudinal direction; a gear assembly coupled to the first turbine rotor assembly and the second turbine rotor assembly, wherein the gear assembly includes a first input interface coupled to the first turbine rotor assembly, a second input interface coupled to the second turbine rotor assembly, and one or more third gears coupled to the first input interface and the second input interface therebetween; and a first output shaft and a second output shaft, wherein each of the first output shaft and the second output shaft are configured to couple to an electrical load device.
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公开(公告)号：US10823001B2
公开(公告)日：2020-11-03
申请号：US15710146
申请日：2017-09-20
发明人： Peeyush Pankaj , Shashank Suresh Puranik , Darek Tomasz Zatorski , Christopher Charles Glynn , Richard Schmidt , Bhaskar Nanda Mondal , Ramana Reddy Kollam
IPC分类号： F01D25/16 , F01D5/30 , F02C3/04 , F02K3/04 , F02C3/067 , F02C7/06 , F02C3/107 , F02C3/113 , F02C7/36
摘要： A turbomachine includes a spool and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The turbomachine also includes a bearing assembly substantially completely supporting rotation of the turbine, the bearing assembly including a total of four bearings, each of the four bearings aligned with, or positioned aft of, the turbine center frame.
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