公开(公告)号：US11952904B2

公开(公告)日：2024-04-09

申请号：US17905717

申请日：2021-03-04

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Romain Truco ,  Claire Marie Figeureu ,  Paul Ghislain Albert Levisse ,  Pierre-Alain Jean Philippe Reigner ,  Michel Gilbert Roland Brault

IPC: F01D15/10 ,  F01D21/04 ,  F02K3/06

CPC classification number: F01D15/10 ,  F01D21/045 ,  F02K3/06 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2220/76 ,  F05D2260/311 ,  F05D2270/09

Abstract: A fan module for an aircraft turbomachine includes a fan with a disc carrying fan blades and a rotor of an electric machine. The rotor has an annular shape and is mounted coaxially downstream of the fan. The module further includes an annular support for the rotor with a downstream end fixed to the rotor and with an upstream end fixed to the fan disc. The support is fixed to the disc by shear bolts configured to break when a torque transmitted by the disc to the support exceeds a predetermined threshold.

公开(公告)号：US11788931B2

公开(公告)日：2023-10-17

申请号：US17755984

申请日：2020-11-13

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Alméric Pierre Louis Garnier ,  Marion Cuny ,  Tony Alain Roger Joël Lhommeau ,  Claire Marie Figeureu

IPC: G01M15/14 ,  F01D21/00 ,  G01L3/10

CPC classification number: G01M15/14 ,  F01D21/003 ,  G01L3/109 ,  F05D2220/323 ,  F05D2260/83

Abstract: A method for monitoring the torsion of a rotary shaft on an aircraft turbomachine based on the measurements from at least three sensors distributed along the rotary shaft to divide the shaft into at least two shaft segments, the method comprising:
a step of measuring, for each sensor, a parameter dependent on the rotation of the shaft,
a step of calculating, for each achievable pair of sensors, a parameter related to the torsion of the shaft,
a step of comparing the different calculated parameters related to the torsion of the shaft with references,
a step of detecting damage on a shaft segment at the end of the comparison step, and
a step of indicating the localization of the damage on the shaft from the shaft segment for which damage has been detected.

公开(公告)号：US10655486B2

公开(公告)日：2020-05-19

申请号：US16109042

申请日：2018-08-22

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Benjamin Bulot ,  Claire Marie Figeureu

IPC: F01D9/04 ,  F01D11/00

Abstract: An assembly for a turbine engine or turbine engine test bed, including a hub defined about a longitudinal axis, a blade, including a blade root, extending in a radial direction to the longitudinal axis, the hub including a recess capable of receiving the blade root by insertion in the radial direction, wherein the recess includes a groove, the blade root including a groove, so that the two grooves are facing each other when the blade root is inserted into the recess, the assembly further includes a seal located in the two grooves.

公开(公告)号：US11460040B2

公开(公告)日：2022-10-04

申请号：US15548040

申请日：2016-02-04

Applicant: Safran Aircraft Engines

Inventor： Guillaume Olivier Vartan Martin ,  Alexandre Bernard Marie Boisson ,  Claire Marie Figeureu ,  Frederic Alain Edouard Allair ,  Thea Claire Lancien

IPC: F04D29/38 ,  F04D29/32 ,  F04D29/54 ,  F04D29/02 ,  F01D5/14 ,  F04D29/34 ,  F02K3/06

Abstract: A blade including at least one web and a vane having a leading edge and a trailing edge, wherein, for at least one aerofoil of the vane in the vicinity of the web, a maximum sweep angle associated with a position along a chord of the aerofoil extending from the leading edge to the trailing edge of the vane corresponding to a relative chord length of at least 50%.

公开(公告)号：US11105208B2

公开(公告)日：2021-08-31

申请号：US16516375

申请日：2019-07-19

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Claire Marie Figeureu ,  Thomas Alain De Gaillard ,  Oscar-Emmanuel Gnangnon

IPC: F01D5/14 ,  F02K3/06 ,  F04D19/00 ,  F04D29/32 ,  F04D29/38

Abstract: A platform for a fan of a turbomachine that will be mounted on a hub of the fan between two adjacent blades, the platform comprising a principal wall with a longitudinal principal orientation, that has a curved shape along the longitudinal direction, and a stiffener that is mounted on a lower face of the principal wall, of which the section of the stiffener, in a plane perpendicular to the longitudinal direction is globally in the form of a U open towards the principal wall. The stiffener comprises at least two straight segments inclined relative to each other and inclined relative to the longitudinal principal direction.

公开(公告)号：US10941667B2

公开(公告)日：2021-03-09

申请号：US16174553

申请日：2018-10-30

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Claire Marie Figeureu ,  Eric Pierre Georges Lemarechal ,  Benjamin Bulot ,  Mathieu Simon Paul Gruber ,  Raphael Barrier ,  Cyril Polacsek

IPC: F01D9/04 ,  F01D5/14 ,  F04D29/68 ,  F04D29/54 ,  F04D29/66 ,  F01D25/16 ,  F01D5/28

Abstract: A stator vane including a vane root, a vane tip, a leading edge extending between the root and the tip, the leading edge having a serrated profile having a succession of teeth and of troughs each having an amplitude and a thickness, wherein a series of at least three teeth and three consecutive troughs starting from the vane root and/or from the vane tip have a growing amplitude and/or thickness.

公开(公告)号：US10710704B2

公开(公告)日：2020-07-14

申请号：US16312582

申请日：2017-06-22

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Thomas Alain De Gaillard ,  Alexandre Bernard Marie Boisson ,  Claire Marie Figeureu

IPC: F04D29/32 ,  B64C11/14 ,  F01D5/06 ,  F01D11/00 ,  F04D29/02

Abstract: A fairing ring for a bladed wheel is disclosed. The fairing ring includes an annular wall extending axially, the wall presenting a plurality of notches extending axially, each notch being configured to receive a leading edge or a trailing edge of a blade.