公开(公告)号：US12122529B2

公开(公告)日：2024-10-22

申请号：US17381360

申请日：2021-07-21

Applicant: General Electric Company Polska sp. z o.o.

Inventor： Mirosław Czarnik ,  Tomasz Edward Berdowski ,  Paweł Zdrojewski ,  Łukasz Maciej Janczak ,  Maciej Grunwald

IPC: F02K3/06 ,  B64D27/12 ,  B64D27/24 ,  B64D29/02 ,  B64D27/02 ,  B64F5/40

CPC classification number: B64D29/02 ,  B64D27/12 ,  B64D27/24 ,  B64D27/026 ,  B64F5/40

Abstract: Propulsion engines and methods of accessing components within propulsor cavities of propulsion engines are disclosed. A propulsion engine includes an outer engine housing that includes a propulsor cavity located therein. The propulsor cavity is axially located between a low-pressure compressor and a fan of the propulsion engine. An electric converter is disposed within the propulsor cavity.

公开(公告)号：US20240343409A1

公开(公告)日：2024-10-17

申请号：US18632361

申请日：2024-04-11

Applicant: Airbus Operations SAS

Inventor： Mathieu BELLEVILLE

IPC: B64D37/30 ,  B64C3/18 ,  B64D27/12

CPC classification number: B64D37/30 ,  B64D27/12 ,  B64C3/185

Abstract: An aircraft having a wing, a dihydrogen-powered engine, a supply pipe for the dihydrogen, in which each wing has a front spar, a first rear spar extending behind the front spar and a second rear spar extending behind the first rear spar, in which the two rear spars together define a corridor, and in which each supply pipe extends backwards from the related engine then into the corridor of the wing carrying the related engine.

公开(公告)号：US12104539B2

公开(公告)日：2024-10-01

申请号：US17972720

申请日：2022-10-25

Applicant: General Electric Company

Inventor： Daniel John Oehrle ,  Randy M. Vondrell

IPC: F02C7/32 ,  B64D27/12

CPC classification number: F02C7/32 ,  B64D27/12

Abstract: A gas turbine engine defines an axial direction and a radial direction and comprises a turbomachine having an unducted primary fan, a core engine a combustor casing enclosing a combustor and defining an outer surface, a core cowl surrounding at least a portion of the core engine. The outer surface of the core cowl defines a peak cowl diameter (D) in the radial direction, and the outer surface of the combustor casing defines a maximum combustor casing diameter (d) along the radial direction. The core engine defines an overall core axial length (L) along the axial direction and an under-core cowl axial length (L1) along the axial direction. The gas turbine engine defines a core cowl diameter ratio (CDR) equal to the peak cowl diameter (D) divided by the maximum combustor casing diameter (d) and a core cowl length ratio (CLR) equal to the under-core cowl axial length (L1) divided by the overall core axial length (L). The CDR is between 2.7 and 3.5 and the CLR is between 0.25 and 0.50.

公开(公告)号：US20240239504A1

公开(公告)日：2024-07-18

申请号：US18307172

申请日：2023-04-26

Applicant: General Electric Company ,  General Electric Company Polska sp. z o.o.

Inventor： William Joseph Bowden ,  Lukasz Ignacy Mazurkiewicz ,  Syed Arif Khalid ,  Trevor Howard Wood

IPC: B64D29/02 ,  B64D27/12 ,  B64D27/26

CPC classification number: B64D29/02 ,  B64D27/12 ,  B64D27/26

Abstract: An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft comprises a fuselage extending between the forward end of the aircraft and the aft end of the aircraft; a wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; an unducted turbofan engine; and a pylon fairing that connects the unducted turbofan engine to the wing assembly, the pylon fairing defining a lengthwise direction, a leading edge, a trailing edge, and a chord extending from the leading edge to the trailing edge, the pylon fairing including a maximum thickness portion along the lengthwise direction of the pylon fairing located between 10% and 60% of the chord.

公开(公告)号：US11999497B2

公开(公告)日：2024-06-04

申请号：US18353162

申请日：2023-07-17

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Pierre Bertrand ,  Jean Thomassin

IPC: B64D27/24 ,  B64D27/02 ,  B64D27/12 ,  B64D29/02

CPC classification number: B64D27/24 ,  B64D27/12 ,  B64D29/02 ,  B64D27/026

Abstract: The aircraft includes a fuselage and at least one wing extending from the fuselage. The wing includes first and second original portions and a plug portion positioned between the first and second original portions. A propulsion system is positioned on the at least one wing. The propulsion system includes at least one electric powerplant and at least one combustion powerplant. Each powerplant delivers power to a respective air mover for propelling the aircraft. The electric powerplant and/or the combustion powerplant is positioned outboard from the plug portion.

公开(公告)号：US20240150029A1

公开(公告)日：2024-05-09

申请号：US18378339

申请日：2023-10-10

Applicant: ROLLS-ROYCE PLC

Inventor： James G STARLEY

IPC: B64D29/06 ,  B64D27/12 ,  F02C7/04

CPC classification number: B64D29/06 ,  B64D27/12 ,  F02C7/04

Abstract: An inner cowl arrangement for a gas turbine engine includes a first hinge and a second hinge pivotally connecting a first cowl member and a second cowl member, respectively, to a mounting structure. The inner cowl arrangement further includes a latch detachably securing the first and second cowl members. At least one of the first hinge, the second hinge, and the latch includes a pressure relief component that deforms or breaks when an applied load on the pressure relief component due to a pressure within an engine core is greater a normal operating load, causing at least one of the first cowl member and the second cowl member to move relative to the engine core, and forming an opening.

公开(公告)号：US20240133345A1

公开(公告)日：2024-04-25

申请号：US17972720

申请日：2022-10-24

Applicant: General Electric Company

Inventor： Daniel John Oehrle ,  Randy M. Vondrell

IPC: F02C7/32 ,  B64D27/12

CPC classification number: F02C7/32 ,  B64D27/12

Abstract: A gas turbine engine defines an axial direction and a radial direction and comprises a turbomachine having an unducted primary fan, a core engine a combustor casing enclosing a combustor and defining an outer surface, a core cowl surrounding at least a portion of the core engine. The outer surface of the core cowl defines a peak cowl diameter (D) in the radial direction, and the outer surface of the combustor casing defines a maximum combustor casing diameter (d) along the radial direction. The core engine defines an overall core axial length (L) along the axial direction and an under-core cowl axial length (L1) along the axial direction. The gas turbine engine defines a core cowl diameter ratio (CDR) equal to the peak cowl diameter (D) divided by the maximum combustor casing diameter (d) and a core cowl length ratio (CLR) equal to the under-core cowl axial length (L1) divided by the overall core axial length (L). The CDR is between 2.7 and 3.5 and the CLR is between 0.25 and 0.50.

公开(公告)号：US20240124147A1

公开(公告)日：2024-04-18

申请号：US17964982

申请日：2022-10-13

Applicant: General Electric Company

Inventor： William Joseph Bowden ,  Jonathan Edward Coleman ,  Sharad Tiwari ,  Srinivas Addagatla ,  Sara Elizabeth Carle

IPC: B64D27/12 ,  B64D27/26 ,  F02C7/20

CPC classification number: B64D27/12 ,  B64D27/26 ,  F02C7/20 ,  F05D2220/323 ,  F05D2240/90

Abstract: A gas turbine engine includes an aft frame and a forward frame disposed upstream from the aft frame. The forward frame includes an outer ring. The outer ring includes an inner surface that is radially spaced from an outer surface. A first indention is defined in the outer surface, and a first engine mount flange protrudes radially outwardly from the first indention.

公开(公告)号：US20240092494A1

公开(公告)日：2024-03-21

申请号：US18513916

申请日：2023-11-20

Applicant: General Electric Company

Inventor： Randy M. Vondrell ,  Anthony Austin Bouvette ,  Glenn David Crabtree

IPC: B64D27/24 ,  B60L50/16 ,  B64C21/06 ,  B64D27/12 ,  B64D27/18 ,  F02C6/20 ,  F02K3/04 ,  H02G5/10 ,  H02K7/18

CPC classification number: B64D27/24 ,  B60L50/16 ,  B64C21/06 ,  B64D27/12 ,  B64D27/18 ,  F02C6/206 ,  F02K3/04 ,  H02G5/10 ,  H02K7/1823 ,  B64D2027/026

Abstract: A propulsion system for an aircraft can include an electric power source and an electric propulsion assembly having an electric motor and a propulsor. The propulsor can be powered by the electric motor. An electric power bus can electrically connect the electric power source to the electric propulsion assembly. The electric power source can be configured to provide electrical power to the electric power bus. An inverter converter controller can be positioned along the electric power bus and can be electrically connected to the electric power source at a location downstream of the electric power source and upstream of the electric propulsion assembly.

公开(公告)号：US11897622B2

公开(公告)日：2024-02-13

申请号：US16368305

申请日：2019-03-28

Applicant: Airbus Operations SAS

Inventor： Patrick Lieven ,  Jérôme Colmagro

IPC: B64D27/02 ,  B64D27/24 ,  F01D15/10 ,  F02C6/00 ,  B64D27/12

CPC classification number: B64D27/02 ,  B64D27/12 ,  B64D27/24 ,  F01D15/10 ,  F02C6/00 ,  B64D2027/026 ,  F05D2220/323 ,  F05D2220/76

Abstract: A propeller propulsion unit, comprising at least one kinematic system comprising at least: a heat engine, an electrical energy generator, an electric motor configured to generate a rotary movement as output from the electrical energy generated by the electrical energy generator, a drive and selection device configured to assume a first configuration, in which it is coupled to the output of the electric motor, and a second configuration, in which it is coupled to the main shaft of the heat engine, and a propeller rotated by the drive and selection device. Such a propeller propulsion unit with a hybrid engine allows more power to be provided and facilitates maintenance and ergonomics and is safer.