公开(公告)号：US20230007929A1

公开(公告)日：2023-01-12

申请号：US17783950

申请日：2020-12-11

Applicant: SAFRAN AIRCRAFT ENGINES ,  SAFRAN TRANSMISSION SYSTEMS

Inventor： Caroline Marie FRANTZ ,  Gilles Alain Marie CHARIER ,  Adrien Louis SIMON

IPC: F02C7/36

Abstract: A propulsion system includes a drive shaft movable about an axis of rotation, a fan, a fan shaft that drives the fan, and a reduction device coupling the drive shaft and the fan shaft. The reduction device has first and second reduction stages and includes a sun gear, centered on the axis and driven by the drive shaft, a ring gear that is coaxial with the sun gear and that drives the fan shaft about the axis, and planet gears distributed circumferentially about the axis between the sun gear and the ring gear. Each planet gear includes a first portion meshed with the sun gear and a second portion meshed with the ring gear. A diameter of the first portion is different from a diameter of the second portion, and the first portion of the planet gears extend between the second portion of the planet gears and the fan.

公开(公告)号：US20220411095A1

公开(公告)日：2022-12-29

申请号：US17779935

申请日：2020-12-08

Applicant: SAFRAN ELECTRICAL & POWER ,  SAFRAN ELECTRONICS & DEFENSE

Inventor： François GUILLOT ,  Serge Thierry ROQUES ,  Nicolas FANTON

IPC: B64D45/00

Abstract: An impact detection device includes an impact detector, a wireless communication device, an energy storage device, an autonomous electrical energy generation device, a device for receiving energy by radio frequency, the device being configured to adopt the following two modes: a first mode, referred to as autonomous mode, in which the autonomous electrical energy generation device is configured to supply the impact detector and the wireless communication device; a second mode, referred to as external mode, in which the device for receiving energy by radio frequency is configured to supply the impact detector and the wireless communication device.

公开(公告)号：US11518417B2

公开(公告)日：2022-12-06

申请号：US16791903

申请日：2020-02-14

Applicant: SAFRAN LANDING SYSTEMS ,  SAFRAN LANDING SYSTEMS CANADA INC.

Inventor： Graeme Peter Arthur Klim ,  Andrew Michael Ellis ,  Justin Guang Yuang Cheng

IPC: B61B1/02 ,  B61B1/00 ,  B61B13/10 ,  B61B13/12 ,  B61F13/00

Abstract: A method is disclosed for docking and undocking a hyperloop vehicle in a station. The method includes the step of extending a support system to a first position, wherein the support system engages a surface to support the hyperloop vehicle at a first elevation. The method further includes the steps of moving the hyperloop vehicle to a predetermined docking position and engaging a coupler to fixedly position the hyperloop vehicle relative to a docking platform.

公开(公告)号：US20220372912A1

公开(公告)日：2022-11-24

申请号：US17775423

申请日：2020-11-06

Applicant: SAFRAN AIRCRAFT ENGINES ,  SAFRAN TRANSMISSION SYSTEMS

Inventor： Guillaume Patrice Kubiak ,  Julien Fabien Patrick Becoulet ,  Romain Guillaume Cuvillier ,  Simon Loïc Clément Lefebvre ,  Emmanuel Pierre Dimitri Patsouris ,  Didier Jean-Louis Yvon

IPC: F02C7/06 ,  F01D25/18 ,  F16H57/04 ,  F02C7/36

Abstract: An impeller (230) for a planet carrier of a planetary gear speed reducer of a turbomachine, is configured intended to be rotatably secured to the planet carrier and to be rotated about an axis A of the speed reducer. The impeller has an annular shape about the axis and includes lubrication means (43, 45, 238), in particular for lubricating bearings of planet gears of the speed reducer. The lubrication means include an annular cavity (238) situated at the inner periphery of the impeller. The impeller includes an inner peripheral wall (246) closing the cavity (238) in the radial direction, and the impeller includes an annular port (248) that extends around the axis and that opens in the axial direction into the cavity in order to supply it with lubricating oil.

公开(公告)号：US20220219813A1

公开(公告)日：2022-07-14

申请号：US17147337

申请日：2021-01-12

Applicant: Safran Landing Systems ,  Safran Landing Systems Canada Inc.

Inventor： Robert Kyle Schmidt ,  Steve Amberg ,  Didier Brun

IPC: B64C25/40 ,  F16H1/28 ,  F16D11/14

Abstract: A landing gear system includes wheel rotatably coupled to an axle. A driveshaft extends through a cavity formed in the axle and is rotatable about an axis. A planetary gear includes a sun gear operably coupled to the drive shaft and a planet gear operably engaging the sun gear. The planetary gear further includes a ring gear that surrounds and is operably coupled to the planet gear so that rotation of the drive shaft rotates the ring gear. A clutch assembly is selectively moveable between an engaged state and a disengaged state. The clutch assembly transfers rotation of the ring gear to the wheel when the clutch assembly is in the engaged state, and the clutch assembly does not transfer rotation of the wheel to the ring gear when the clutch assembly is in the disengaged state.

公开(公告)号：US20220213842A1

公开(公告)日：2022-07-07

申请号：US17608685

申请日：2020-07-03

Applicant: SAFRAN HELICOPTER ENGINES ,  SAFRAN POWER UNITS

Inventor： Fabien MERCIER-CALVAIRAC ,  Patrick MARCONI ,  Denis Antoine Julien REAL

IPC: F02C9/28 ,  B64D27/24 ,  B64F5/60 ,  B64D31/06 ,  F02C6/00

Abstract: A propulsion assembly for aircraft includes a single-shaft engine turbomachine including a combustion chamber and a rotatably mounted shaft that turns at a turbomachine rating; an electrical generator coupled to the shaft; and a control system. The control system includes a fuel pump that brings fuel into the combustion chamber at a fuel flow rate which is a direct function of an ambient pressure and of the turbomachine rating, and power electronics that are coupled to the electrical generator and that control an electrical power drawn off the electrical generator so as to attain a target turbomachine rating.

公开(公告)号：US20220205365A1

公开(公告)日：2022-06-30

申请号：US17595008

申请日：2020-04-24

Applicant: SAFRAN ,  SAFRAN AIRCRAFT ENGINES

Inventor： Léandre OSTINO ,  Pierre Guillaume AUZILLON ,  Michel SLUSARZ ,  Patrice ENEAU ,  Thomas Olivier Michel Pierre DE ROCQUIGNY ,  Romain Pierre CARIOU ,  Ba-Phuc TANG ,  Adrien Bernard Vincent ROLLINGER ,  Vianney SIMON

IPC: F01D5/18 ,  B22C9/10

Abstract: A turbine vane includes a root carrying a blade terminated by a squealer tip, the blade having intrados and extrados walls, a leading edge, a trailing edge, and a tip wall delimiting a bottom of the squealer tip, by which the intrados wall is connected to the extrados wall. The blade also includes: a serpentine median circuit, including a first radial pipe that collects air at the root and is connected by a first bend to a second radial pipe that is connected by a second bend to a third radial pipe; a cavity under the squealer tip running along the extrados wall and extending from a central region of the squealer tip to the trailing edge; and a central radial pipe collecting air at the root and extending between at least two of the three pipes of the median circuit and directly supplying the cavity under the squealer tip.

公开(公告)号：US20220190686A1

公开(公告)日：2022-06-16

申请号：US17432245

申请日：2020-02-19

Applicant: SAFRAN ,  SAFRAN HELICOPTER ENGINES

Inventor： Sabrina AYAT ,  Camel SERGHINE ,  Thomas KLONOWSKI

IPC: H02K9/22 ,  H02K9/20

Abstract: An assembly including a winding and a cooler in contact with conductors of the winding, the cooler including a container forming a heat dissipator and including a phase change material having the ability to absorb a surplus quantity of heat when the conductors of the winding are subject to an increase in their current density and the heat dissipator is composed of at least two hollow parts separate and nestable with one another and intended to house the phase change material.

公开(公告)号：US20220082064A1

公开(公告)日：2022-03-17

申请号：US17536480

申请日：2021-11-29

Applicant: Safran Nacelles ,  SAFRAN AIRCRAFT ENGINES

Inventor： Patrick BOILEAU ,  Pierre CARUEL ,  Gina FERRIER ,  Quentin GARNAUD ,  Guillaume GLEMAREC

IPC: F02K1/68 ,  F02K1/70

Abstract: An aircraft propulsion unit including a nacelle and a turbojet engine. The aircraft propulsion unit includes an external envelope, at least one fan casing, at least one actuator, and at least one support structure. The external envelope includes fan cowls. The fan casing cooperates with the fan cowls to define an interior space configured to house a thrust reverser configured to be displaced between a first position and a second position. The actuator configured to move the thrust reverser between the first position and the second position The support structure connects the fan cowls and the fan. The support structure includes at least one aperture configured to allow passage of part of the actuator.

公开(公告)号：US11235867B2

公开(公告)日：2022-02-01

申请号：US16511579

申请日：2019-07-15

Applicant: Safran Landing Systems UK LTD ,  Safran Landing Systems

Inventor： Neil Price ,  Marie Coq

IPC: B64C25/42 ,  G01L5/28

Abstract: An aircraft landing gear assembly comprising: an axle having an axis, a wheel rotatably mounted on the axle to rotate about the axis, a brake arranged to selectively exert a braking torque on the wheel about the axis, a brake anchor structure having a substantially fixed position relative to the axle, a brake reaction linkage that mechanically couples the brake to the brake anchor structure, and a sensor comprising a sensor element arranged to detect a change in one or more physical properties of a component of the brake reaction linkage in order to determine a stress in the component due to the braking torque, wherein the sensor element does not contact the component.