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公开(公告)号：US12110125B2
公开(公告)日：2024-10-08
申请号：US18543254
申请日：2023-12-18
发明人： Michael Mark , Paul C. Imel , Leonid Guerchkovitch
CPC分类号： B64D31/06 , B64D27/02 , B64D27/24 , B64D31/14 , B64D45/00 , B64D27/026 , B64D2045/0085
摘要： A hybrid electric propulsion (HEP) system can include a heat engine torque sensor connected between a heat engine and a combining gear box to sense a heat motor input torque input to the combining gear box, an electric motor torque sensor connected between an electric motor and the combining gear box to sense an electric motor input torque input to the combining gear box, and a combining gear box torque sensor connected to an output of the combining gearbox. The system can include a HEP controller operatively connected to each of the heat engine torque sensor, the electric motor torque sensor, and the combining gear box torque sensor to receive one or more torque signals therefrom. The controller can be configured to output one or more output signals as a function of the signals from each of the heat engine torque sensor, the electric motor torque sensor, and the combining gear box torque sensor.
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公开(公告)号：US12103698B1
公开(公告)日：2024-10-01
申请号：US18307837
申请日：2023-04-27
申请人： Lowental Hybrid Ltd.
发明人： Itay Lowental
IPC分类号： B64D35/08 , B60L53/24 , B64C39/02 , B64D27/02 , B64D27/24 , B64D35/02 , B64U50/11 , B64U50/19 , H02K7/10 , H02K7/116 , H02K11/00
CPC分类号： B64D35/08 , B60L53/24 , B64C39/024 , B64D27/24 , B64D35/02 , H02K7/1004 , H02K7/116 , H02K11/0094 , B64D27/026 , B64U50/11 , B64U50/19
摘要： The disclosure is directed to drive assemblies for unmanned aerial vehicles (UAVs). Specifically, the disclosure is directed to hybrid drive assembly and control system for UAVs, utilizing indexed belt tension modulation to couple and decouple an electric motor and an internal combustion engine.
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公开(公告)号：US12092038B2
公开(公告)日：2024-09-17
申请号：US16991275
申请日：2020-08-12
申请人： RTX Corporation
CPC分类号： F02C7/36 , B64D27/02 , B64D27/026 , F05D2220/323 , F05D2270/023 , F05D2270/053 , F05D2270/304
摘要： Hybrid electric propulsion systems are described. The systems include a gas turbine engine having low and high speed spools, each spool having a respective compressor and turbine. A mechanical power transmission is configured to at least one of extract power from and supply power to at least one of the low speed spool and the high speed spool, an electric machine is configured to augment rotational power of at least one of the spools, and a controller is operable to determine a rotational speed of the low speed spool, determine a rotational speed of the high speed spool, determine if a predetermined operational zone of operation based on the determined rotational speeds is present, and when a predetermined operational zone is determined, control a power augmentation of at least one spool to limit dwell operation of the gas turbine engine within the predetermined operational zone.
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公开(公告)号：US20240287931A1
公开(公告)日：2024-08-29
申请号：US18655808
申请日：2024-05-06
申请人： RTX Corporation
IPC分类号： F02C6/00 , B64D27/02 , B64D27/10 , B64D27/24 , B64D33/08 , F02C7/12 , F02C9/26 , H01M8/04007
CPC分类号： F02C6/00 , B64D27/10 , B64D27/24 , B64D33/08 , F02C7/12 , F02C9/26 , H01M8/04059 , B64D27/026 , H01M2250/20
摘要： Turbine engine systems include a core assembly having a compressor section, a burner section, and a turbine section arranged along a shaft, with a core flow path through the turbine engine such that exhaust from the burner section passes through the turbine section and exits through a nozzle. A core condenser is arranged downstream of the turbine section and upstream of the nozzle and configured to condense water from the core flow path. A fuel cell is operably connected to the core assembly. A fuel source is configured to supply a fuel to each of the burner section for combustion and the fuel cell for reaction to generate electricity. At least one electric motor is operably coupled to the core assembly and configured to impart power to a portion of the core assembly and the fuel cell is configured to supply electrical power to the at least one electric motor.
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公开(公告)号：US12071234B2
公开(公告)日：2024-08-27
申请号：US18244785
申请日：2023-09-11
发明人： Pranay Sinha , Damon Vander Lind
IPC分类号： B64C29/00 , B60L50/64 , B60L53/00 , B64C13/48 , B64C27/82 , B64C39/12 , B64D27/02 , B64D27/24 , B64D27/40 , B64D31/06 , G05D1/00
CPC分类号： B64C29/0033 , B60L50/64 , B60L53/00 , B64C13/48 , B64C27/82 , B64C39/12 , B64D27/02 , B64D27/24 , B64D27/40 , B64D31/06 , G05D1/101 , B60L2200/10 , B64C2027/8209 , B64D27/026 , B64D27/402
摘要： During a cruise mode, a cruise-only propeller provides thrust using power from a first power source. During a hovering mode and a transitional mode, the propeller provides no thrust. The first power source includes an internal combustion engine; a second power source includes a high discharge rate battery and a high energy battery. The propeller is electrically connected to the first power source and is electrically disconnected from the second power source. During the hovering mode and the transitional mode, a hover-and-transition-only tiltrotor provides thrust using power from the second power source. During a vertical landing, the tiltrotor switches power sources from the high energy battery to the high discharge rate battery, independent of current draw. The tiltrotor is electrically disconnected from the first power source and is electrically connected to the second power source. During the cruise mode, the tiltrotor provides no thrust.
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6.发明授权公开(公告)号：US12054268B2
公开(公告)日：2024-08-06
申请号：US17969451
申请日：2022-10-19
申请人： Duxion Motors, Inc.
CPC分类号： B64D27/24 , B64D27/10 , F01D15/10 , B64D27/026 , F05D2220/76
摘要： A system includes a first electric motor that when in operation imparts rotation to a fan stage of an engine. The system also includes a combustion section of the engine comprising a combustor that when in operation generates combustion gas through ignition of fuel and compressed air. The system further includes a turbine of the engine coupled to a shaft of the engine, wherein the turbine when in operation receives the combustion gas from the combustion section and imparts rotation to the shaft using the combustion gas.
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公开(公告)号：US12043405B2
公开(公告)日：2024-07-23
申请号：US18202736
申请日：2023-05-26
发明人： Paul R. Hanrahan
CPC分类号： B64D35/02 , F02C7/36 , B64D27/026 , F05D2260/40311
摘要： An assembly is provided for an aircraft. The aircraft assembly includes a rotating structure, a geartrain, a propulsor rotor and an electric machine. The rotating structure includes a turbine rotor. The geartrain includes a sun gear, a ring gear, a plurality of intermediate gears and a carrier. The sun gear is rotatably driven by the rotating structure. Each of the intermediate gears is between and meshed with the sun gear and the ring gear. Each of the intermediate gears is rotatably mounted to the carrier. The propulsor rotor is rotatably driven by the carrier. The electric machine is coupled to the ring gear.
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公开(公告)号：US12043374B2
公开(公告)日：2024-07-23
申请号：US17796238
申请日：2021-01-26
申请人： KOPTER GROUP AG
摘要： A hybrid propulsion system with controllers and a drive shaft of a helicopter with a main rotor connected to a gearbox which can keep a flight attitude set by a pilot stable. It includes a pilot controller, a combustion engine and an electric motor, both of which act directly on the drive shaft. The VM is connected to a VM controller, and the EM is connected to an EM controller. One torque sensor and one tachometer are each arranged on the drive shaft, wherein during operation both the VM controller and the EM controller are able to receive values for the current speed and the current torque. Specified values for speed and torque, in which the VM can attain its optimum efficiency, are stored in memory and can be retrieved by the EM controller, wherein the first value can also be retrieved by the VM controller.
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公开(公告)号：US12024302B2
公开(公告)日：2024-07-02
申请号：US16171896
申请日：2018-10-26
CPC分类号： B64D27/12 , F01D15/10 , F02C7/36 , B64D2027/026 , F05D2220/323 , F05D2220/76
摘要： An example hybrid propulsion system is described that includes a plurality of propulsors, a first drive shaft, a second drive shaft, a gas turbine engine, a motor-generator, and a clutch. The gas turbine engine includes a first turbine stage operatively coupled to the first drive shaft and a second turbine stage operatively coupled to the second drive shaft. The motor-generator is operatively coupled to the second drive shaft and is configured to generate electrical power to drive at least one propulsor of the plurality of propulsors and selectively drive the second shaft. The clutch is configured to operatively couple the second drive shaft to the first drive shaft.
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公开(公告)号：US12018617B2
公开(公告)日：2024-06-25
申请号：US17779094
申请日：2020-11-24
CPC分类号： F02C7/32 , B64D27/16 , B64D27/24 , B64D27/026 , B64D2221/00 , F05D2220/323 , F05D2220/76
摘要： An aircraft turbine engine includes a gas generator having a longitudinal axis (A), a fan located at an upstream end of the gas generator and configured to turn about said axis, and an electric machine of generally annular shape. The electric machine is coaxially mounted downstream of the fan and has a rotor coupled to rotate with the fan. The electric machine further includes a stator connected to an electronic power circuit by at least one rigid electrically-conductive bar.
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