公开(公告)号：US12209554B2

公开(公告)日：2025-01-28

申请号：US18002445

申请日：2021-06-02

Applicant: SAFRAN NACELLES

Inventor： Romain Gardel ,  Thomas Marlay ,  Matthieu Menielle ,  Ophélie Schmitter

IPC: F02K1/76 ,  B64D29/00 ,  F02K1/60

Abstract: A thrust reverser for an aircraft propulsion unit. The thrust reverser includes three gates that can be deployed downstream of an outlet section of the propulsion unit. The device increases the possibilities for installation of the reverser, in particular when a tail assembly extends in line with the propulsion unit.

公开(公告)号：US20240429786A1

公开(公告)日：2024-12-26

申请号：US18828901

申请日：2024-09-09

Applicant: DENSO CORPORATION

Inventor： YOSHIYASU INOUE ,  YOHEI KONNO

IPC: H02K11/00 ,  B64D27/30 ,  B64D29/00 ,  H02K1/22 ,  H02K7/00

Abstract: An apparatus for removing magnetic foreign matter includes a magnetic force generator and a magnetic material. The magnetic material is configured to be magnetized by the magnetic force generator and be brought into contact with fluid in a flow path that allows the fluid to flow therethrough.

公开(公告)号：US12104526B2

公开(公告)日：2024-10-01

申请号：US17166826

申请日：2021-02-03

Applicant: Safran Nacelles

Inventor： Audrey Riquet

IPC: F02C7/047 ,  B23K26/00 ,  B23K26/0622 ,  B23K26/352 ,  B23K103/16 ,  B29C59/16 ,  B64D15/04 ,  B64D29/00 ,  B64D33/02

CPC classification number: F02C7/047 ,  B23K26/0006 ,  B23K26/0624 ,  B23K26/355 ,  B23K26/3584 ,  B29C59/16 ,  B64D15/04 ,  B64D33/02 ,  B23K2103/16 ,  B29C59/165 ,  B64D29/00 ,  B64D2033/0233 ,  F05D2300/512 ,  Y02T50/60

Abstract: A method for the anti-icing treatment of a surface of an aircraft part made of an organic matrix composites includes a texturing step in which the surface is irradiated with femtosecond laser pulses so as to render the surface superhydrophobic.

公开(公告)号：US12071232B2

公开(公告)日：2024-08-27

申请号：US17786194

申请日：2020-12-17

Applicant: LEONARDO S.P.A.

Inventor： Riccardo Bianco Mengotti ,  Paolo Brughera ,  Luca Sampugnaro ,  Carlo Cassinelli

IPC: B64C29/00 ,  B64C1/20 ,  B64C1/22 ,  B64C3/52 ,  B64C27/22 ,  B64D27/02 ,  B64D27/24 ,  B64D29/00 ,  B64D35/04 ,  B64D35/08 ,  H02K7/18

CPC classification number: B64C29/0033 ,  B64C1/20 ,  B64C1/22 ,  B64C3/52 ,  B64C27/22 ,  B64D27/24 ,  B64D29/00 ,  B64D35/04 ,  B64D35/08 ,  H02K7/1861 ,  B64D27/026

Abstract: A convertiplane is described that comprises: a fuselage, having a first longitudinal axis and, in turn, comprising a nose and a tail portion; a pair of wings arranged on respective opposite sides of the fuselage, carrying respective rotors and generating a lift value; and a pair of engines operatively connected to respective rotors; each rotor comprising a mast rotatable about a second axis between a helicopter configuration and an aeroplane configuration; each rotor is interposed between the fuselage and the relative rotor along the direction of extension of the relative wing.

公开(公告)号：US20240253773A1

公开(公告)日：2024-08-01

申请号：US18375540

申请日：2023-10-01

Applicant: JETZERO, INC.

Inventor： Mark Allan Page

IPC: B64C21/01 ,  B64C21/06 ,  B64C39/10 ,  B64D29/00

CPC classification number: B64C21/01 ,  B64C21/06 ,  B64C39/10 ,  B64D29/00

Abstract: An apparatus for ingesting boundary layer flow on an aircraft, the apparatus includes a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and main body of the aircraft, wherein the blended wing body includes a nacelle located aft of a leading edge of the blended wing body, wherein the nacelle includes a propulsor configured to propel the aircraft, a primary duct, and a flow augmentation arrangement, wherein the flow augmentation arrangement is configured to accelerate a boundary layer flow in the airflow, wherein the flow augmentation arrangement further includes a secondary duct, wherein the secondary duct configured to ingest the boundary layer flow in the airflow from an inlet proximal to a forward portion of the nacelle to an outlet proximal to a rear portion of the nacelle and a tertiary duct between the primary duct and the secondary duct.

公开(公告)号：US20240208663A1

公开(公告)日：2024-06-27

申请号：US18088221

申请日：2022-12-23

Applicant: Pratt & Whitney Canada Corp.

Inventor： Paul Weaver ,  Bruno Chatelois

IPC: B64D27/24 ,  B64C3/00 ,  B64D27/10 ,  B64D29/00 ,  B64D35/08 ,  F02K5/00 ,  H02K7/116 ,  H02K7/18

CPC classification number: B64D27/24 ,  B64C3/00 ,  B64D27/10 ,  B64D29/00 ,  B64D35/08 ,  F02K5/00 ,  H02K7/116 ,  H02K7/1823 ,  B64D2027/026

Abstract: An aircraft system is provided that includes a propulsor rotor, a geartrain, a thermal engine, a drivetrain and an electric machine. The geartrain includes a power output, a first power input and a second power input. The power output is coupled to the propulsor rotor. The thermal engine is configured to drive rotation of the propulsor rotor through the geartrain. The thermal engine is coupled to the first power input. The drivetrain includes a first driveshaft and a second driveshaft. The first driveshaft is coupled to and between the second power input and the second driveshaft. The second driveshaft is angularly offset from the first driveshaft. The electric machine is configured to drive rotation of the propulsor rotor through the drivetrain and the geartrain. The second driveshaft is coupled to and between the first driveshaft and the electric machine.

公开(公告)号：US11913378B2

公开(公告)日：2024-02-27

申请号：US17768933

申请日：2020-10-15

Applicant: INSTITUT SUPERIEUR DE L AERONAUTIQUE ET DE L ESPACE ,  SAFRAN AIRCRAFT ENGINES

Inventor： Nicolas Jérôme Jean Tantot ,  Xavier Carbonneau ,  Philippe Gérard Chanez ,  Nicolas Garcia Rosa ,  Alejandro Martin Pleguezuelo ,  Nicolas Joseph Sirvin

IPC: F02C7/04 ,  B64D29/00 ,  B64D33/02 ,  F02C7/042

CPC classification number: F02C7/042 ,  B64D29/00 ,  B64D33/02 ,  B64D2033/0233 ,  B64D2033/0286

Abstract: The invention relates to an assembly for a turbomachine, comprising: —a nacelle comprising an inlet lip which defines an air inlet, and—a device for modifying the geometry of the air inlet, comprising: —a first spout, and—a second spout, the first spout and the second spout being translatably movable in relation the nacelle between: —a first configuration, in which the first spout forms the inlet lip and the second spout extends inside the nacelle, and—a second configuration, in which the first spout extends away from the inlet lip, and the second spout forms the inlet lip so as to define an air flow channel between a downstream surface of the first spout and an upstream surface of the second spout.

公开(公告)号：US11827339B1

公开(公告)日：2023-11-28

申请号：US18102342

申请日：2023-01-27

Applicant: JETZERO, INC.

Inventor： Mark Allan Page

IPC: B64C21/01 ,  B64C39/10 ,  B64C21/06 ,  B64D29/00

CPC classification number: B64C21/01 ,  B64C21/06 ,  B64C39/10 ,  B64D29/00

Abstract: An apparatus for ingesting boundary layer flow on an aircraft, the apparatus includes a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and main body of the aircraft, wherein the blended wing body includes a nacelle located aft of a leading edge of the blended wing body, wherein the nacelle includes a propulsor configured to propel the aircraft, a primary duct, and a flow augmentation arrangement, wherein the flow augmentation arrangement is configured to accelerate a boundary layer flow in the airflow, wherein the flow augmentation arrangement further includes a secondary duct, wherein the secondary duct configured to ingest the boundary layer flow in the airflow from an inlet proximal to a forward portion of the nacelle to an outlet proximal to a rear portion of the nacelle and a tertiary duct between the primary duct and the secondary duct.

公开(公告)号：US11814184B2

公开(公告)日：2023-11-14

申请号：US17532813

申请日：2021-11-22

Applicant: Airbus Operations SAS

Inventor： José Goncalves

IPC: B64D29/06 ,  B64D29/08 ,  F16B5/02 ,  B64D29/00 ,  B64D7/02 ,  B64D29/02

CPC classification number: B64D29/06 ,  B64D29/08 ,  F16B5/0208 ,  F16B5/0266 ,  B64D7/02 ,  B64D29/00 ,  B64D29/02

Abstract: An assembly of a pylon and of a nacelle of an aircraft, wherein the nacelle has a structure, a visor, two centering systems and two tensioning systems. Each tensioning system comprises a first fitting, which is attached to the structure and has an engagement wall through which an orifice passes, a second fitting, which is attached to the visor, a threaded rod that is articulated on the second fitting and passes through the orifice, a spring element fitted on the threaded rod against the opposite face of the engagement wall from the second fitting, and an arresting means that blocks the spring element. Each centering system comprises a first fitting, which is attached to the structure and has a bore, and a second fitting, which is attached to the visor and bears a shaft that is accommodated in the bore.

公开(公告)号：US11798524B2

公开(公告)日：2023-10-24

申请号：US16998578

申请日：2020-08-20

Applicant: THE BOARD OF REGENTS FOR THE OKLAHOMA AGRICULTURAL AND MECHANICAL COLLEGES

Inventor： James Mathew Manimala

IPC: G10K11/16 ,  F24F13/24 ,  B64D29/00 ,  B64D33/02

CPC classification number: G10K11/161 ,  B64D29/00 ,  F24F13/24 ,  B64D2033/0206 ,  F24F2013/242

Abstract: An acoustic damper has a sound pickup unit defining a plurality of pickup unit passageways. Hollow flexible tubes are connected to exit openings of the pickup unit passageways and extend outwardly therefrom. The hollow flexible tubes and pickup unit passageways define acoustic paths.