公开(公告)号：US11788420B2

公开(公告)日：2023-10-17

申请号：US17909175

申请日：2021-03-03

Applicant: Safran Aircraft Engines

Inventor： Guillaume Pascal Jean-Charles Gondre ,  Thomas Alain De Gaillard

IPC: F01D5/28 ,  F01D5/14

CPC classification number: F01D5/282 ,  F01D5/147 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2300/6034

Abstract: The present invention relates to a fan blade (3) having a structure made from a composite material, comprising a fibrous reinforcement (5), which is obtained by three-dimensional weaving of warp strands and weft strands, and a matrix in which the fibrous reinforcement (5) is embedded, wherein—the fibrous reinforcement (5) comprises a first portion (14) forming the trailing edge (9) of the structure made from a composite material and a second portion (15) forming its leading edge (8), and wherein—the warp strands of the fibrous reinforcement (5) comprise first strands (12) having a predetermined stiffness and second strands (13) having a greater stiffness than that of the first strands (12), the first portion (14) comprising all or part of the first strands (12) and being devoid of second strands (13) while the second portion (15) comprises all or part of the second strands (13).

公开(公告)号：US11377973B2

公开(公告)日：2022-07-05

申请号：US17059147

申请日：2019-05-16

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Eddy Keomorakott Souryavongsa ,  Thomas Alain De Gaillard ,  Teddy Fixy ,  Gilles Pierre-Marie Notarianni

IPC: F01D11/02 ,  B64D29/00 ,  F02C7/28 ,  F16J15/447

Abstract: A sealing arrangement is provided between inner and outer coaxial ring-shaped walls of an aircraft engine. The outer wall has an axial end with a U-shaped cross-section parallel to axis, the opening therein being oriented axially in a first direction. The inner wall has an axial end with a U-shaped cross-section parallel to axis, the opening therein being oriented axially in the opposite direction. The U-shaped end of the outer wall includes a ring-shaped free edge axially engaged in the opening in the axial end of the inner wall. The U-shaped end of the inner wall includes a ring-shaped free edge axially engaged in the opening in the axial end of the outer wall. The walls define therebetween a ring-shaped gas channel having a substantially S-shaped axial cross-section.

公开(公告)号：US20210199018A1

公开(公告)日：2021-07-01

申请号：US17059147

申请日：2019-05-16

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Eddy Keomorakott Souryavongsa ,  Thomas Alain De Gaillard ,  Teddy Fixy ,  Gilles Pierre-Marie Notarianni

IPC: F01D11/02 ,  F02C7/28 ,  F16J15/447 ,  B64D29/00

Abstract: A sealing arrangement is provided between inner and outer coaxial ring-shaped walls of an aircraft engine. The outer wall has an axial end with a U-shaped cross-section parallel to axis, the opening therein being oriented axially in a first direction. The inner wall has an axial end with a U-shaped cross-section parallel to axis, the opening therein being oriented axially in the opposite direction. The U-shaped end of the outer wall includes a ring-shaped free edge axially engaged in the opening in the axial end of the inner wall. The U-shaped end of the inner wall includes a ring-shaped free edge axially engaged in the opening in the axial end of the outer wall. The walls define therebetween a ring-shaped gas channel having a substantially S-shaped axial cross-section.

公开(公告)号：US10670038B2

公开(公告)日：2020-06-02

申请号：US15982880

申请日：2018-05-17

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Thomas Alain De Gaillard ,  William Henri Joseph Riera ,  Guillaume Olivier Vartan Martin

IPC: F04D29/32 ,  F01D5/30 ,  F01D11/00

Abstract: Blade made of composite material, with an integrated platform, for an aircraft turbine engine, including a root connected to an aerofoil and having a connection platform between the root and the aerofoil, the root having a generally elongate shape along an axis (A) of elongation, the aerofoil having a curved cross-sectional shape and including a pressure face and a suction face, the platform including a first portion extending on the pressure-face side of the aerofoil and including a first longitudinal free edge and a second opposite longitudinal edge for connecting to the rest of the blade, the platform including a second portion extending on the suction-face side of the aerofoil and comprising a third longitudinal free edge and an opposite fourth longitudinal edge for connecting to the rest of the blade, wherein the first longitudinal free edge is concave and the third longitudinal free edge is convex, and, for any plane (P, P′) perpendicular to the axis of elongation and intersecting the platform, the distance (L1, L2; L1′, L2′) between the first and second edges, on the one hand, and the distance between said third and fourth edges, on the other hand, are identical in the plane considered.

公开(公告)号：US10556367B2

公开(公告)日：2020-02-11

申请号：US15522848

申请日：2015-10-28

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Sébastien Marin ,  Thomas Alain De Gaillard ,  Audrey Laguerre

IPC: B29B11/16 ,  F01D5/28 ,  B29C70/22 ,  B29D99/00 ,  D03D25/00 ,  F01D5/34 ,  B29L31/08

Abstract: A fiber preform for a turbine engine blade and also a single-piece blade suitable for being formed using such a preform, a rotor wheel, and a turbine engine including such a blade, the fiber preform being obtained by three-dimensional weaving and comprising a first longitudinal segment suitable for forming a blade root (21), a second longitudinal segment extending the first longitudinal segment upwards and suitable for forming an airfoil portion (22), a first transverse segment extending transversely from the junction between the first and second longitudinal segments and suitable for forming a first platform (23), and a first stiffener strip extending downwards from the distal edge of the first transverse portion and suitable for forming a first platform stiffener (25).