公开(公告)号：US20240151151A1

公开(公告)日：2024-05-09

申请号：US18278803

申请日：2022-02-23

Applicant: SAFRAN AIRCRAFT ENGINES ,  SAFRAN HELICOPTER ENGINES

Inventor： Bertrand Guillaume, Robin PELLATON ,  Thibaud Louis ZAIA

IPC: F01D9/04 ,  F01D25/24

CPC classification number: F01D9/041 ,  F01D25/24 ,  F05D2270/3062

Abstract: A turbine for a turbomachine of longitudinal axis including an alternating arrangement of annular rows of movable blades and of fixed blades and a radially inner annular cavity formed radially inside the movable and fixed blades, and a supply circuit for supplying cooling air to the inner annular cavity, the downstream end of the supply circuit comprising an inner annular row of orifices and an outer annular row of orifices opening into the radially inner annular cavity. The turbine may also include means for controlling the flow rate of supply air to the orifices of the inner and outer annular rows of orifices.

公开(公告)号：US20240133306A1

公开(公告)日：2024-04-25

申请号：US18546169

申请日：2022-02-08

Applicant: SAFRAN AIRCRAFT ENGINES ,  SAFRAN CERAMICS

Inventor： Sébastien Serge Francis CONGRATEL ,  Aurélien GAILLARD ,  Matthieu Arnaud GIMAT ,  Clément JARROSSAY ,  David René Pierre LE CAIR

IPC: F01D9/04

CPC classification number: F01D9/042 ,  F01D9/041 ,  F05D2250/71 ,  F05D2260/38 ,  F05D2300/6033

Abstract: A turbine engine nozzle extending about an axis and including a vane assembly mounted between an outer shroud and an inner shroud; and a position retaining device configured to be placed in an elastically prestressed state between the inner shroud and an inner platform of the vane assembly to apply a stress on the vane assembly towards the outer shroud. The contact between the inner shroud and the inner platform is obtained by one same surface of the position retaining device.

公开(公告)号：US20240102432A1

公开(公告)日：2024-03-28

申请号：US17950497

申请日：2022-09-22

Applicant: Safran Electrical & Power ,  Safran Power USA, LLC

Inventor： Sachin Aggarwal ,  Matthew Fallon ,  Nicodeme Faucher ,  Abdoulahad Thiam

IPC: F02K5/00 ,  B64D27/24 ,  B64D33/08

CPC classification number: F02K5/00 ,  B64D27/24 ,  B64D33/08

Abstract: Described is a fan assembly for an electrical aircraft motor having an axial fan with an inner hub of a first diameter and an outer hub of a second diameter. The outer hub may be concentrically aligned with the inner hub. A plurality of blades may extend between the inner hub and the outer hub. The fan assembly may also have a mounting plate connected to the inner hub. The mounting plate may attach to a component of the electrical aircraft motor.

公开(公告)号：US11932410B2

公开(公告)日：2024-03-19

申请号：US17767576

申请日：2020-10-12

Applicant: SAFRAN ,  SAFRAN HELICOPTER ENGINES

Inventor： Jean-Louis Robert Guy Besse ,  Ye-Bonne Karina Maldonado

IPC: B64D29/00 ,  F01D5/02 ,  F01D25/00 ,  F02K1/00

CPC classification number: B64D29/00 ,  F01D5/02 ,  F01D25/005 ,  F02K1/002 ,  F05D2220/90 ,  F05D2240/20 ,  F05D2300/505

Abstract: A propulsion system for an aircraft includes a rotor and a nacelle fairing that extends around the rotor in relation to an axis. The nacelle fairing includes an upstream portion forming an inlet section of the nacelle fairing as well as a downstream portion, a downstream end of which forms an outlet section of the nacelle fairing. The downstream portion includes radially inner and outer walls, both of which are made of a deformable shape memory material. The wall has independently actuatable piston actuator mechanisms, each actuator mechanism being actuatable independently of the others and being designed to cooperate with means built into an inner surface of the wall to deform the wall in a radial direction in relation to the axis under the effect of a predetermined displacement command.

公开(公告)号：US20240026962A1

公开(公告)日：2024-01-25

申请号：US18256827

申请日：2021-12-13

Applicant: SAFRAN ,  SAFRAN ELECTRONICS & DEFENSE

Inventor： Amadou ASSOUMANE ,  Mohammed EL BADAOUI ,  Badr MANSOURI ,  Audrey VENON

IPC: F16H57/01 ,  F16H25/22

CPC classification number: F16H57/01 ,  F16H25/2214

Abstract: A method includes for each of the portions of a guide of the actuator, obtaining an operating signal measured when a movable element of the actuator travels over the guide portion in question, upon each of a plurality of successive activations of the actuator; for each of the guide portions, seeking wear of the actuator from the operating signals obtained for this guide portion; and locating the wear on the guide or on the motor according to the guide portions from which the wear has been found.

公开(公告)号：US11845483B2

公开(公告)日：2023-12-19

申请号：US17216064

申请日：2021-03-29

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

Inventor： Andrew Michael Ellis ,  Graeme Peter Arthur Klim ,  Thibaud Mazoue

IPC: B61L3/00 ,  B61C11/00 ,  B61K13/00 ,  B61C1/00

CPC classification number: B61L3/006 ,  B61C1/00 ,  B61K13/00

Abstract: A disclosed controller is configured with logic that, when executed, performs actions to extend landing gear of a maglev vehicle. The actions include receiving a height control target value and transitioning between a standby control state and an active control state. The controller maintains the landing gear in a fixed position when the controller is in the standby control state, and the controller controls extension and retraction of the landing gear according to the height control target value when the controller is in the active control state.

公开(公告)号：US11834187B2

公开(公告)日：2023-12-05

申请号：US16998893

申请日：2020-08-20

Applicant: Safran Nacelles ,  Safran Aircraft Engines

Inventor： Patrick Boileau ,  Bruno Beutin

IPC: B64D29/06 ,  B64F5/50 ,  B64D27/26 ,  F02K1/70 ,  F02K1/76

CPC classification number: B64D29/06 ,  B64D27/26 ,  B64F5/50 ,  F02K1/70 ,  F02K1/763 ,  B64D2027/262 ,  F05D2220/323 ,  F05D2260/02

Abstract: A drive unit includes an engine such as a turbofan engine and a nacelle which includes, on the outside around an annular stream of fresh air, starting from upstream, an air inlet, front side covers, a thrust reverser having reversal gratings and movable rear covers. The front side covers surround the reversal gratings of the thrust reverser when it is closed, and the movable rear covers retreat with said gratings to open the reverser. The engine includes lifting points that form heavy-duty attachment points intended to receive handling clevis for lifting and transporting the drive unit. The lifting points are two upper lifting points arranged on the engine, each on one side of the engine radially behind the front side covers above the horizontal diameter (D) of the drive unit.

公开(公告)号：US11801941B2

公开(公告)日：2023-10-31

申请号：US18015529

申请日：2021-07-08

Applicant: Safran Seats ,  Safran Seats GB Limited

Inventor： Oscar Ruiz ,  Arthur Glain ,  Yann Cavereau ,  Paul Wills ,  Rachel James ,  James Woodington ,  Shaun Kilbane ,  Ryan Jones

IPC: B64D11/06

CPC classification number: B64D11/0605 ,  B64D11/0604

Abstract: The present invention relates to a suite, in particular for an aircraft cabin, comprising:



a seat,
an ottoman, and
a storage cupboard,
the suite further comprising a movable table capable of assuming:

a stowed state in


which the movable table extends in a vertical plane, in which the movable table is arranged between the cupboard and the ottoman, and

a deployed state in which the movable table extends in a horizontal plane.

公开(公告)号：US20230318416A1

公开(公告)日：2023-10-05

申请号：US18042157

申请日：2021-08-13

Applicant: SAFRAN HELICOPTER ENGINES ,  SAFRAN

Inventor： Camel SERGHINE ,  Thomas KLONOWSKI ,  Pierre Gabriel Marie QUINIO ,  Sabrina Siham AYAT ,  Eric ROULAND ,  Sébastien YON ,  Albert MUTABAZI

IPC: H02K15/12 ,  H02K3/34 ,  H02K15/02

CPC classification number: H02K15/12 ,  H02K3/345 ,  H02K15/02

Abstract: A method for protecting coils from excessive heating in an aircraft electrical machine comprising a stator (12) and a rotor (14) configured to be rotationally driven with respect to one another, the stator including a plurality of notches (120) receiving one and the same plurality or otherwise of coils, the method including the following successive steps:



inserting an electrical insulator (16) into the notches or onto the teeth of the stator,
installing the coils (18) in the notches or on the teeth of the stator, casting a phase change material (20) in the notches or on the teeth equipped with the coils, the electrical insulator forming a casting mold.

公开(公告)号：US11777370B2

公开(公告)日：2023-10-03

申请号：US17597786

申请日：2020-07-24

Applicant: SAFRAN HELICOPTER ENGINES ,  SAFRAN

Inventor： Loïs Pierre Denis Vive ,  Christophe Ludovic Jean-Claude Viguier

IPC: H02K7/18 ,  H02K21/14 ,  F02C6/20 ,  B64D27/24 ,  B64D27/10 ,  B64D27/02

CPC classification number: H02K7/1823 ,  B64D27/02 ,  B64D27/10 ,  B64D27/24 ,  F02C6/20 ,  H02K21/14 ,  B64D2027/026 ,  F05D2220/76

Abstract: An aeronautical turbogenerator for hybrid electric propulsion includes a heat engine and an electrical generator coupled mechanically to the heat engine and including a rotor and a stator, the rotor extending in an axial direction and including a common magnetized rotor yoke comprising a plurality of permanent magnets defining at least three axially distributed movable annular rings, the stator including a magnetic stator yoke comprising a plurality of electrical windings defining axially and/or circumferentially distributed stationary sectors, at least two stationary sectors, one of which covers axially at least two movable annular rings, being arranged angularly so as not to mutually coincide and thus deliver at least two distinct and independent voltage levels.