公开(公告)号：US12077279B2

公开(公告)日：2024-09-03

申请号：US17241915

申请日：2021-04-27

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Jagoda Krzywon

IPC分类号： B64C11/38 ,  B64C11/30 ,  B64D45/00 ,  F01D7/02 ,  F01D21/00

CPC分类号： B64C11/385 ,  B64C11/301 ,  B64D45/00 ,  F01D7/02 ,  F01D21/003 ,  B64D2045/0085

摘要： There is provided a method and a system for detecting and mitigating a propeller failure condition. An actual value of a rotational speed of the propeller and/or of a pitch angle of blades of the propeller is obtained. In response to determining that the speed is below a reference rotational speed for the propeller and/or determining that the pitch angle is above a pitch angle threshold, an actuator operatively connected to the blades is commanded to decrease the pitch angle to increase the speed towards the reference speed. After commanding of the actuator to decrease the pitch angle, a subsequent value of the speed and/or a subsequent value of the pitch angle is obtained. The actuator is commanded to hold the pitch angle in response to determining that the speed has failed to increase towards the reference speed and/or determining that the pitch angle has failed to decrease.

公开(公告)号：US12043244B2

公开(公告)日：2024-07-23

申请号：US17378389

申请日：2021-07-16

申请人： Ampaire, Inc.

发明人： Jeffrey Spitzer ,  James Lawson

IPC分类号： H02P25/18 ,  B60K6/24 ,  B60K6/26 ,  B60K6/28 ,  B60W20/10 ,  B64C11/30 ,  B64C11/44 ,  B64D27/24 ,  B64D31/02 ,  H02P27/06 ,  B64D27/02

CPC分类号： B60W20/10 ,  B60K6/24 ,  B60K6/26 ,  B60K6/28 ,  B64C11/303 ,  B64C11/44 ,  B64D27/24 ,  B64D31/02 ,  H02P27/06 ,  B60Y2200/50 ,  B60Y2200/92 ,  B64D27/026

摘要： A propulsion system for a hybrid electric vehicle comprises a traction motor having first and second stator windings; a power source having a DC power output coupled to the first windings; a battery having a DC power output coupled to the second windings; and a controller to independently control: (i) a first power level output at the first DC power output, and (ii) a second power level of motive power output by the traction motor; wherein responsive to a signal to set the second power level less than full capacity of the traction motor, the controller provides a power difference between the first and second power levels from the second windings to the battery.

公开(公告)号：US20240186935A1

公开(公告)日：2024-06-06

申请号：US18285667

申请日：2022-04-05

申请人： SAFRAN HELICOPTER ENGINES ,  SAFRAN ELECTRICAL & POWER

发明人： Stéphane Meyer BEDDOK ,  David Bernard Martin LEMAY ,  Julien Marc Nicolas BAMBAUD

IPC分类号： H02P29/10 ,  B64C11/30 ,  B64D27/34

CPC分类号： H02P29/10 ,  B64C11/305 ,  B64D27/34

摘要： The present invention relates to a device (1) for controlling an electric aircraft-propelling assembly, said propelling assembly comprising a propeller (3) and at least one electric motor (4) that is powered by an electric supply voltage and that delivers a torque and a rotation speed to drive the propeller (3). The control device (1) comprises at least a unit (11) for measuring an electric supply voltage, and a control unit (12) suitable for making a signal delivered to the electric motor vary as a function of said electric supply voltage, with a view to making the rotation speed of the propeller vary.

公开(公告)号：US11987369B2

公开(公告)日：2024-05-21

申请号：US17288206

申请日：2019-10-25

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Nicolas Jérôme Jean Tantot ,  Anthony Binder ,  Mario Antoine Lambey

IPC分类号： B64D27/10 ,  B64C11/30 ,  B64C11/48 ,  B64D27/24 ,  F02B61/04 ,  F02C3/067 ,  F02C7/36 ,  B64D27/00 ,  B64D27/02

CPC分类号： B64D27/10 ,  B64C11/306 ,  B64C11/48 ,  B64D27/24 ,  F02B61/04 ,  F02C3/067 ,  F02C7/36 ,  B64D2027/005 ,  B64D2027/026 ,  F05D2220/324 ,  F05D2220/325 ,  F05D2220/76

摘要： A turbomachine of an aircraft comprising an outer casing delimiting with an inner hub, a flow path of a gas stream in which is disposed a low-pressure turbine configured to rotationally drive a low-pressure shaft; said turbomachine comprising, in the direction of flow of the gas stream, a first propeller; and a second propeller downstream of the first propeller, the first propeller being rotationally driven by said low-pressure shaft and the second propeller being rotationally driven by an electric motor, the second propeller being further disposed at a distance between 1.5 and 4 cord lengths from the first propeller defined between the respective axes of shimming of each of the first and second propellers.

公开(公告)号：US11964750B2

公开(公告)日：2024-04-23

申请号：US16295433

申请日：2019-03-07

申请人： General Electric Company

发明人： Jozef Zakucia ,  Vojtech Jirasek ,  Milan Matejka

IPC分类号： B64C11/30 ,  B64C11/40 ,  B64C11/42 ,  B64C11/44

CPC分类号： B64C11/305 ,  B64C11/303 ,  B64C11/40 ,  B64C11/42 ,  B64C11/44

摘要： A control system for an engine operatively coupled with a propeller and methods for controlling an engine operatively coupled with a propeller are provided. In one example aspect, the control system includes a controller and an electric propeller governor. The electric propeller governor includes a motor operatively coupled with a flyweight governor spring. The motor is communicatively coupled with the controller. The controller is operable to receive data indicative of the speed of the propeller, determine if the measured speed exceeds a propeller speed threshold, and if the threshold is exceeded, the controller is configured to change a propeller speed set point. Particularly, the controller can cause the motor to change the preload on the flyweight governor spring, which in turn causes adjustment of the propeller speed set point. In this way, propeller speed overshoot is prevented during fast acceleration of the engine.

公开(公告)号：US11958621B1

公开(公告)日：2024-04-16

申请号：US18531357

申请日：2023-12-06

申请人： Archer Aviation Inc.

发明人： Scott Graves

IPC分类号： B64D27/24 ,  B64C11/30 ,  B64C27/12 ,  B64C27/54 ,  B64C29/00 ,  B64D33/08 ,  B64D35/02 ,  H02K5/20 ,  H02K7/08 ,  H02K7/116 ,  H02K9/19 ,  H02K11/33 ,  H02K7/00

CPC分类号： B64D27/24 ,  B64C27/54 ,  B64C29/0008 ,  B64C29/0033 ,  B64D33/08 ,  B64D35/02 ,  H02K5/203 ,  H02K7/08 ,  H02K7/116 ,  H02K9/19 ,  H02K11/33 ,  H02K7/006

摘要： An electric propulsion system for a vertical take-off and landing (VTOL) aircraft, the electric propulsion system including an electrical motor having a stator and a rotor. The electric propulsion system may include a main shaft possessing at least one shoulder on an outer surface of the main shaft. The electric propulsion system may include a gearbox assembly comprising a sun gear that is concentrically aligned with the main shaft at least one planetary gear that interfaces with the sun gear. The electric propulsion system may include a planetary carrier, wherein a center of the planetary carrier is concentrically aligned with the main shaft. The electric propulsion system may include a propeller flange assembly that travels through the rotor, and an axial buttress positioned in the at least one shoulder located on the main shaft.

公开(公告)号：US11835543B2

公开(公告)日：2023-12-05

申请号：US17748549

申请日：2022-05-19

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Dana Tomescu ,  James Jarvo

IPC分类号： F03D17/00 ,  G01P3/488 ,  B64C11/30 ,  B64D27/10 ,  F01D7/00 ,  F01D17/20 ,  F01D21/00 ,  F01D17/06 ,  G01D5/14 ,  F01D17/02 ,  F04D29/36 ,  B64C27/473 ,  B64C27/57 ,  F02C9/22 ,  F02D29/02 ,  G01D5/12 ,  G01D5/20 ,  G01P3/487 ,  F02C7/32 ,  B63H3/00 ,  B64C11/06 ,  F02D41/28

CPC分类号： G01P3/488 ,  B64C11/301 ,  B64C27/473 ,  B64C27/57 ,  B64D27/10 ,  F01D7/00 ,  F01D17/02 ,  F01D17/06 ,  F01D17/20 ,  F01D21/003 ,  F02C9/22 ,  F02D29/02 ,  F04D29/362 ,  G01D5/125 ,  G01D5/145 ,  G01D5/2013 ,  G01P3/487 ,  B63H2003/006 ,  B64C11/06 ,  B64C2027/4733 ,  F02C7/32 ,  F02D2041/281 ,  F02D2041/288 ,  F05B2270/328 ,  F05D2220/323 ,  F05D2260/70 ,  F05D2270/02 ,  F05D2270/80 ,  F05D2270/821 ,  F05D2300/507

摘要： There is provided a blade angle feedback system for an aircraft-bladed rotor rotatable about a longitudinal axis and having an adjustable blade pitch angle. A feedback device is coupled to rotate with the rotor and to move along the axis with adjustment of the blade pitch angle. The feedback device comprises a body having position marker(s) embedded therein, the body made of a first material having a first magnetic permeability and the position marker(s) comprising a second material having a second magnetic permeability greater than the first. Sensor(s) are positioned adjacent the feedback device and configured for producing, as the feedback device rotates about the axis, sensor signal(s) in response to detecting passage of the position marker(s). A control unit is communicatively coupled to the sensor(s) and configured to generate a feedback signal indicative of the blade pitch angle in response to the sensor signal(s) received from the sensor(s).

公开(公告)号：US11814164B1

公开(公告)日：2023-11-14

申请号：US17729646

申请日：2022-04-26

申请人： Textron Innovations Inc.

发明人： John Robert Wittmaak ,  Alan Hisashi Steinert

IPC分类号： B64C29/00 ,  B64C11/30 ,  B64D27/24

CPC分类号： B64C29/0033 ,  B64C11/301 ,  B64C11/305 ,  B64D27/24

摘要： A method of verifying operation of an aircraft in a pre-defined flight mode includes operating the aircraft in a first flight mode, commanding the aircraft to transition to a second flight mode, evaluating a plurality of motor performance parameters, and based on values of the plurality of motor performance parameters, determining whether the aircraft has successfully transitioned to the second flight mode.

公开(公告)号：US11772778B2

公开(公告)日：2023-10-03

申请号：US17766047

申请日：2020-10-02

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Tewfik Boudebiza ,  Julien Michel Patrick Christian Austruy ,  Gilles Alain Marie Charier ,  Cedrik Djelassi

IPC分类号： B64C11/40 ,  B64C11/30 ,  F01D7/00

CPC分类号： B64C11/40 ,  B64C11/30 ,  F01D7/00 ,  F05D2220/30 ,  F05D2240/30 ,  F05D2260/941

摘要： The invention describes a system for controlling the cyclic setting of blades (1) of a turbine engine propeller, the blades (1) being arranged in a plane normal to the axis of rotation (r) of the propeller, the system comprising: —a plate assembly (40) that can be tilted relative to the normal plane (P), —an articulation system (50) articulating the plate assembly (40) relative to the blades (1) such that tilting the plate assembly (40) modifies the setting of the blades (1), —a force sensor (5) designed to measure a force applied in the normal plane (P) by an air flow at the inlet of the propeller blades (1), —a cylinder (60) suitable for tilting the plate assembly (40) in response to a force measured by the force sensor (5).

公开(公告)号：US20230286644A1

公开(公告)日：2023-09-14

申请号：US18006128

申请日：2021-07-15

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Clément COTTET ,  Vivien Mickaël COURTIER ,  Vincent JOUDON ,  Arnaud LANGLOIS ,  Régis Eugène Henri SERVANT ,  Laurent JABLONSKI

IPC分类号： B64C11/30 ,  F01D7/00 ,  F01D5/30 ,  B64C11/06

CPC分类号： B64C11/30 ,  F01D7/00 ,  F01D5/30 ,  B64C11/06 ,  F05D2260/70

摘要： An assembly including a propeller blade and a pitch adjustment system for setting the pitch of the blade. A root of the blade has a bulb and the pitch adjustment system for setting the pitch of the blade includes a cup having an upper opening; a retaining ring, which extends around the bulb, is restricted at least in terms of axial movement towards the opening relative to the cup and has a bearing face to inhibit axial movement of the root towards the opening The pitch adjustment system being further includes a lower seat for the root to engage the cup, the seat and/or the retaining ring being mounted so as to be capable of axial translation relative to the cup by at least one clamping mechanism.