公开(公告)号：US20250042538A1

公开(公告)日：2025-02-06

申请号：US18797158

申请日：2024-08-07

Applicant: General Electric Company

Inventor： Sara Elizabeth Carle ,  Daniel L. Tweedt ,  Syed Arif Khalid ,  Andrew Breeze-Stringfellow ,  William Bowden

IPC: B64C11/48 ,  B64C3/14

Abstract: The present disclosure is generally related to aircraft having one or more unducted fan propulsors at locations within specific regions relative to an airfoil, such as a wing or horizontal stabilizer. More specifically, the specific regions are located where there is a relatively higher pressure air flow beneath the wings or above a horizontal stabilizer. That higher pressure air flow can be utilized to provide increased thrust from the unducted fan propulsor.

公开(公告)号：US20250033761A1

公开(公告)日：2025-01-30

申请号：US18910473

申请日：2024-10-09

Applicant: Kubota Corporation

Inventor： Mitsuru ISHIKAWA ,  Masakazu YAMAZAKI

IPC: B64C11/48

Abstract: A flight device in which vibrations and anti-torque generated during flight can be effectively reduced includes a first engine, a second engine, a first transmission shaft rotated by the first engine, a second transmission shaft rotated by the second engine, a first rotor rotated by the first transmission shaft, and a second rotor rotated by the second transmission shaft. The first transmission shaft has a hollow structure, and the second transmission shaft is located inside the first transmission shaft.

公开(公告)号：US20240317386A1

公开(公告)日：2024-09-26

申请号：US18577131

申请日：2022-07-04

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Norman Bruno André JODET ,  Anthony BINDER ,  Adrien Clément Marcel DUBOIS ,  Fernando GEA AGUILERA, ,  Anthony Bernard Germain LAFITTE ,  Eva Julie LEBEAULT ,  Josselin David Florian REGNARD

IPC: B64C11/48 ,  F01D5/02

CPC classification number: B64C11/48 ,  F01D5/02

Abstract: An aeronautical thruster having a longitudinal axis and having a hub, an upstream annular row and a downstream annular row which are spaced apart from each another along the longitudinal axis, the upstream annular row being rotatable around the longitudinal axis, and the downstream annular row having a first blade and a second blade each extending in a radial direction to define a radial dimension between the hub and a radially outer end of the corresponding blade. When observed angularly around the longitudinal axis, the second blade can be positioned closer to an angular position at 3 o'clock or an angular position at 9 o'clock than the first blade, and the radial dimension of the first blade can be greater than the radial dimension of the second blade.

公开(公告)号：US12097940B2

公开(公告)日：2024-09-24

申请号：US17706204

申请日：2022-03-28

Applicant: VAM CO., LTD.

Inventor： Dohyun Kang

IPC: B63H1/16 ,  B63H5/10 ,  B63H21/17 ,  B64C11/00 ,  B64C11/48 ,  B64D27/24 ,  B63H23/00

CPC classification number: B63H1/16 ,  B63H5/10 ,  B63H21/17 ,  B64C11/001 ,  B64C11/48 ,  B64D27/24 ,  B63H2001/165 ,  B63H2023/005

Abstract: The present invention relates to rotating equipment, and more specifically, to high efficiency rotating equipment which generates thrust through contra-rotating or produces electricity. The rotating equipment includes: a plurality of propeller modules (10, 20) including a plurality of blades (11, 21) installed inside along a circumferential direction; and a rotary module (40) which rotates the plurality of propeller modules (10, 20) or is rotated.

公开(公告)号：US20240254924A1

公开(公告)日：2024-08-01

申请号：US18427543

申请日：2024-01-30

Applicant: SAFRAN TRANSMISSION SYSTEMS

Inventor： Maxime FERNANDEZ ,  Yohan DOUY ,  Boris Pierre Marcel MORELLI ,  Jordane Emile André PELTIER

IPC: F02C7/36 ,  B64C11/48 ,  B64C27/12

CPC classification number: F02C7/36 ,  B64C11/48 ,  B64C27/12

Abstract: The disclosure relates to an assembly for an aircraft turbomachine, having a speed reduction gear comprising an input pinion connected to a power shaft of the turbomachine and an output pinion connected to a propeller shaft of the turbomachine. According to the disclosure, the assembly includes two electric machines which are each configured to provide electrical power to the propeller shaft or to draw mechanical power from the propeller shaft, each electric machine comprising a rotor and a stator, the stator configured to be connected to a casing of the turbomachine. The speed reduction gear can include two substantially parallel intermediate transmission lines configured to transmit the torque from the input pinion to the output pinion, each rotor being driven in rotation respectively by a pinion of an intermediate line.

公开(公告)号：US12049297B2

公开(公告)日：2024-07-30

申请号：US18030982

申请日：2021-10-11

Applicant: Greenjets Limited

Inventor： Anmol Manohar ,  Guido Monterzino

IPC: B64C11/48 ,  B64C11/00 ,  B64D15/00 ,  B64D27/24 ,  B64D35/06 ,  F02K3/072 ,  F02K3/08 ,  F02K5/00

CPC classification number: B64C11/001 ,  B64C11/48 ,  B64D15/00 ,  B64D27/24 ,  B64D35/06 ,  F02K3/072 ,  F02K3/08 ,  F02K5/00

Abstract: A propulsion system for an aircraft having a two stage contra-rotating fan system to generate thrust. The contra-rotating fan system is surrounded by an aerodynamic duct, having the power train within the duct.

公开(公告)号：US11987369B2

公开(公告)日：2024-05-21

申请号：US17288206

申请日：2019-10-25

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Nicolas Jérôme Jean Tantot ,  Anthony Binder ,  Mario Antoine Lambey

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

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

Abstract: 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：US11977394B2

公开(公告)日：2024-05-07

申请号：US17603190

申请日：2021-10-12

Applicant: Aergility Corporation

Inventor： James E. Vander Mey ,  Lawrence Winston Yonge, III

IPC: B64C27/10 ,  B64C11/50 ,  B64C27/00 ,  B64C27/02 ,  B64C27/12 ,  B64C27/14 ,  B64C27/22 ,  B64C27/26 ,  B64D31/00 ,  G05D1/00 ,  B64C11/48 ,  B64C27/82 ,  B64D27/24 ,  H02K1/27

CPC classification number: G05D1/0858 ,  B64C11/50 ,  B64C27/006 ,  B64C27/02 ,  B64C27/021 ,  B64C27/025 ,  B64C27/027 ,  B64C27/028 ,  B64C27/10 ,  B64C27/12 ,  B64C27/14 ,  B64C27/22 ,  B64C27/26 ,  B64D31/00 ,  B64C11/48 ,  B64C2027/8236 ,  B64D27/24 ,  H02K1/27

Abstract: A multi-rotor aircraft includes a fuselage, a propulsion engine coupled to the fuselage that generates thrust to propel the aircraft along a first vector during forward flight, and rotors coupled to the fuselage, each rotor comprising blades, each rotor coupled to a motor, and each motor configured to supply power to and draw power from the coupled rotor. The aircraft includes a flight control system configured to control the motors coupled to the rotors in a power managed regime in which a net electrical power, consisting of a sum of the power being supplied to or drawn from each rotor by its motor, is maintained within a range determined by a feedback control system of the flight control system. The flight control system can also be leveraged to adjust rotor control inputs to modify at least one of thrust, roll, pitch, or yaw of the multi-rotor aircraft.

公开(公告)号：US20240124128A1

公开(公告)日：2024-04-18

申请号：US18555961

申请日：2022-04-18

Applicant: Emilio MARTIN ALEXANDRE

Inventor： Emilio MARTIN ALEXANDRE

IPC: B64C11/48 ,  B64D27/02

CPC classification number: B64C11/48 ,  B64D27/02 ,  B64C9/00

Abstract: Consisting of a flap-type aerodynamic surface on the wing(s) (2) above the fuselage (1) of an aircraft with control surfaces (5) of the wing (2), the length of the device in the wing span direction being greater than or equal to the mid-chord of the flap, and comprising a thrust propeller engine (4), converting it into a propulsive flapper (3).

公开(公告)号：US20240010332A1

公开(公告)日：2024-01-11

申请号：US18165659

申请日：2023-02-07

Applicant: Joby Aero, Inc.

Inventor： Mark MOORE ,  John Conway BADALAMENTI ,  Ian Andreas VILLA ,  Adam Shaw WARMOTH ,  David Lane JOSEPHSON

IPC: B64C29/00 ,  B64C9/02 ,  G05D1/08 ,  B64C11/48 ,  B64C3/10 ,  B64D27/24 ,  B64D35/06

CPC classification number: B64C29/0033 ,  B64C9/02 ,  G05D1/0858 ,  B64C11/48 ,  B64C3/10 ,  B64D27/24 ,  B64D35/06

Abstract: A vertical landing and take-off aircraft VTOL transitions from a vertical takeoff state to a cruise state where the vertical takeoff state uses propellers to generate lift and the cruise state uses wings to generate lift. The aircraft has an M-wing configuration with propellers located on the wingtip nacelles, wing booms, and tail boom. The wing boom and/or the tail boom can include boom control effectors. Hinged control surfaces on the wings, tail boom, and tail tilt during takeoff and landing to yaw the vehicle. The boom control effectors, cruise propellers, stacked propellers, and control surfaces can have different positions during different modes of operation in order to control aircraft movement and mitigate noise generated by the aircraft.