公开(公告)号：US12024302B2

公开(公告)日：2024-07-02

申请号：US16171896

申请日：2018-10-26

申请人： Rolls-Royce Corporation

发明人： Claire Elizabeth Stuckey

IPC分类号： F02C7/36 ,  B64D27/12 ,  F01D15/10 ,  B64D27/02

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.

公开(公告)号：US20240166359A1

公开(公告)日：2024-05-23

申请号：US18477729

申请日：2023-09-29

申请人： KOREA AEROSPACE RESEARCH INSTITUTE

发明人： Keun Bae KIM

IPC分类号： B64D27/24 ,  F02B63/04 ,  F16D41/12 ,  H02K7/108 ,  H02K21/22

CPC分类号： B64D27/24 ,  F02B63/042 ,  F16D41/12 ,  H02K7/108 ,  H02K21/22 ,  B64D2027/026

摘要： A power unit includes an engine including a driving shaft, a power generator provided on the driving shaft and configured to supply electric energy to a flight vehicle, and a thrust generator provided on an outer side of the power generator and configured to provide a propulsion force to the flight vehicle. When a temperature of the power generator is greater than or equal to a first temperature, the power generator and the thrust generator are decoupled from each other, and the power generator is driven by an output of the engine and supplies the electric energy to the flight vehicle. When the temperature of the power generator is less than the first temperature, the power generator and the thrust generator are coupled to each other, and the thrust generator is driven by the output of the engine and provides the propulsion force to the flight vehicle.

公开(公告)号：US20240158090A1

公开(公告)日：2024-05-16

申请号：US17984457

申请日：2022-11-10

申请人： Jay BHATT

发明人： Jay BHATT

IPC分类号： B64D27/16 ,  B64C27/12 ,  B64C29/00 ,  B64D27/24

CPC分类号： B64D27/16 ,  B64C27/12 ,  B64C29/0075 ,  B64D27/24 ,  B64D2027/026

摘要： Hybrid powertrains for a fixed wing aircraft, a helicopter, and a V/STOL aircraft. A core of the jet engine rotates an integral generator without gear train, that provides current to charge batteries located in various locations on the aircraft. The batteries are used to power electric motors that provide the sole source of torque to fans, propellers, or rotors that propel the aircraft. These differ from the prior configurations by provisioning integrated architectures.

公开(公告)号：US11958622B2

公开(公告)日：2024-04-16

申请号：US16875095

申请日：2020-05-15

申请人： Pratt & Whitney Canada Corp.

发明人： Richard A. Poisson ,  Paul C. Imel ,  Leonid Guerchkovitch

IPC分类号： B64D31/02 ,  B64D27/02 ,  B64D27/04 ,  B64D27/24

CPC分类号： B64D31/02 ,  B64D27/02 ,  B64D27/04 ,  B64D27/24 ,  B64D2027/026

摘要： A method includes controlling an electric motor of a hybrid-electric powerplant for an aircraft using an EPC (electric powertrain controller) and controlling a heat engine of the hybrid-electric powerplant using an ECU (engine control unit). The method includes performing at least one of the following to protect the hybrid-electric powerplant: using the ECU to power down the electric motor, and/or using the EPC to power down the heat engine.

公开(公告)号：US11945573B2

公开(公告)日：2024-04-02

申请号：US17529556

申请日：2021-11-18

申请人： General Electric Company ,  GE Avio S.r.l.

发明人： Mehdi Milani Baladi ,  Randy M Vondrell

IPC分类号： B64C17/06 ,  B64C29/00 ,  B64D27/02 ,  B64D27/14 ,  B64D27/24 ,  B64D31/02

CPC分类号： B64C17/06 ,  B64C29/0033 ,  B64D27/14 ,  B64D27/24 ,  B64D31/02 ,  B64D2027/026

摘要： A hybrid electric aircraft equipped with gyroscopic stabilization control is provided. In one aspect, a hybrid electric aircraft includes a turbo-generator having a gas turbine engine and an electric generator operatively coupled thereto for generating electrical power. The turbo-generator defines a rotation axis. The aircraft also includes one or more electrically-driven propulsors for producing thrust for the aircraft. In addition, the aircraft includes a pivot mount operatively coupled with the turbo-generator. To provide gyroscopic stabilization control of the aircraft, the pivot mount is controlled to adjust the rotation axis of the turbo-generator relative to a prime stability axis of the aircraft. Additionally or alternatively, a rotational speed of the turbo-generator can be changed to provide gyroscopic stabilization control of the aircraft.

公开(公告)号：US20240067348A1

公开(公告)日：2024-02-29

申请号：US18336177

申请日：2023-06-16

申请人： The Boeing Company

发明人： Steve G. MACKIN ,  Eric B. GILBERT ,  Russell H. HIGGINS

IPC分类号： B64D27/24 ,  B64C13/28 ,  B64C21/08 ,  B64D27/10 ,  B64D41/00 ,  B64D47/00 ,  F02C6/20 ,  F02C7/36

CPC分类号： B64D27/24 ,  B64C13/28 ,  B64C21/08 ,  B64D27/10 ,  B64D41/00 ,  B64D47/00 ,  F02C6/20 ,  F02C7/36 ,  B64D2027/026 ,  B64D2041/005

摘要： A hybrid engine including features to meet aircraft thrust, passenger airflow, and fuel cell requirements. The engine includes a combustor burning the same fuel as the fuel cell. The engine has electric motors to utilize the power output of the fuel cell. The engine shafts have sprags to allow motors to drive the compressors and over run the turbines. The engine has variable flowpath geometry to bypass the combustor.

公开(公告)号：US11912421B2

公开(公告)日：2024-02-27

申请号：US17614458

申请日：2020-05-27

申请人： VOLTAERO

发明人： Jean Botti ,  Didier Esteyne

IPC分类号： B64D27/02 ,  B60L50/60 ,  B64D27/24 ,  B64D31/00 ,  B64C27/12 ,  B64D35/08 ,  B64U50/11 ,  B64U50/19

CPC分类号： B64D27/02 ,  B60L50/60 ,  B64C27/12 ,  B64D27/24 ,  B64D31/00 ,  B64D35/08 ,  B64U50/11 ,  B64U50/19 ,  B60L2200/10 ,  B64D2027/026 ,  Y02T50/60

摘要： The machine, such as an aircraft, is provided with a powertrain which comprises a vaned propulsion system (3), and a thermal drive system (1), including a first thermal engine (1A) and a second thermal engine (1B), which is configured to allow the vaned propulsion system (3) to be driven. The powertrain also includes an electric drive system (2) which allows the vaned propulsion system (3) to be driven, an electrical power supply system (4) including a battery (40) which allows the electric drive system (2) to be supplied with power. A clutch system (10) allows any or each of the thermal engines (1A, 1B) to be engaged in order to drive the vaned propulsion system (3), the clutch system (10) also being configured to allow any or each of the thermal engines (1A, 1B) to be disengaged from the vaned propulsion system (3).

公开(公告)号：US20240059422A1

公开(公告)日：2024-02-22

申请号：US17892761

申请日：2022-08-22

申请人： Pratt & Whitney Canada Corp.

发明人： Pierre Bertrand ,  Jean Thomassin

IPC分类号： B64D35/08 ,  B64D27/24 ,  B64D35/04

CPC分类号： B64D35/08 ,  B64D27/24 ,  B64D35/04 ,  B64D2027/026

摘要： A system is provided for an aircraft. This aircraft system includes a propulsion system, and the propulsion system includes a first thermal engine, a second thermal engine and a first electric machine. The propulsion system is configured to operate the first thermal engine and the second thermal engine, without operating the first electric machine, during a first mode of operation to provide aircraft thrust. The propulsion system is configured to operate the first electric machine and the second thermal engine, without operating the first thermal engine, during a second mode of operation to provide the aircraft thrust.

公开(公告)号：US11891907B2

公开(公告)日：2024-02-06

申请号：US17757529

申请日：2020-12-18

申请人： SAFRAN HELICOPTER ENGINES ,  SAFRAN POWER UNITS

发明人： Camel Serghine ,  Denis Antoine Julien Real

IPC分类号： F01D25/18 ,  F01D15/10 ,  B64D27/10 ,  B64D27/24 ,  B64D27/02

CPC分类号： F01D25/18 ,  B64D27/10 ,  B64D27/24 ,  F01D15/10 ,  B64D2027/026 ,  F05D2220/323 ,  F05D2220/76 ,  F05D2260/609

摘要： A turbogenerator (1) for an aircraft (2) comprising: a turboshaft engine (3); an electric generator (4) comprising a rotor (5) driven mechanically by the turboshaft engine (3) and a stator (6) supported by a housing (7) of the electric generator (4); characterized in that the turbogenerator (1) comprises a static separator (8) for separating an air/oil mixture coming from the turboshaft engine (3), the static separator (8) being positioned around the housing (7) of the electric generator (4).

公开(公告)号：US11869881B2

公开(公告)日：2024-01-09

申请号：US18116455

申请日：2023-03-02

申请人： Rolls-Royce Deutschland Ltd & Co KG

发明人： Uwe Waltrich ,  Stanley Buchert

IPC分类号： H01L25/16 ,  H02M7/217 ,  H01L23/538 ,  B64D35/04 ,  B64D27/24 ,  B60L58/00 ,  H01L23/31 ,  B64C29/00 ,  B64D27/02

CPC分类号： H01L25/16 ,  B60L58/00 ,  B64C29/0008 ,  B64D27/24 ,  B64D35/04 ,  H01L23/3121 ,  H01L23/5383 ,  H01L23/5386 ,  H02M7/217 ,  B60L2200/10 ,  B60L2210/30 ,  B64D2027/026

摘要： A power electronics converter includes a multi-layer planar carrier substrate having a plurality of electrically conductive layers, at least one electrical connection, and a converter commutation cell comprising a power circuit and a gate driver circuit. The power circuit includes at least one power semiconductor switching element and at least one capacitor. Each power semiconductor switching element is included in a power semiconductor prepackage having one or more power semiconductor switching elements embedded in a solid insulating material. The power electronics converter includes a heat sink configured to remove heat from the power semiconductor prepackage. A converter parameter η is greater than or 20 equal to 100 kW/m3K, η being defined as a heat transfer coefficient between the heat removal side of the power semiconductor prepackage and a cooling medium of the heat sink divided by the size of a gap between the power semiconductor prepackage and the heat sink.