公开(公告)号：US10689996B2

公开(公告)日：2020-06-23

申请号：US15625211

申请日：2017-06-16

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Gilles Pierre-Marie Notarianni ,  Audrey Laguerre ,  Stephane Roger Mahias

IPC: F01D11/00 ,  F04D29/32 ,  F04D29/08 ,  F01D5/28

Abstract: A turbomachine blade (10) comprising a body (11) and an elastomer gasket (12) fastened to said body (11).

公开(公告)号：US10267164B2

公开(公告)日：2019-04-23

申请号：US15569161

申请日：2016-04-26

Applicant: Safran Aircraft Engines

Inventor： Caroline Jacqueline Denise Berdou ,  Alexandre Bernard Marie Boisson ,  Matthieu Arnaud Gimat ,  Audrey Laguerre

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

Abstract: A fiber preform for a turbine engine blade and a single-piece blade suitable for being made by means of such a preform, a bladed wheel, and a turbine engine including such a blade; the fiber preform obtained by three-dimensional weaving comprises a first longitudinal segment (41) suitable for forming a blade root, a second longitudinal segment (42) extending the first longitudinal segment (41) upwards and suitable for forming an airfoil portion, a first transverse segment (51) extending transversely from the junction between the first and second longitudinal segments (41, 42), and suitable for forming a first platform; the first transverse segment (51) includes at least one non-interlinked portion comprising a top strip (51b) and a bottom strip (51a), and at least one insert (61) is arranged between the top and bottom strips (51b, 51a) of the non-interlinked portion of the first transverse segment (51).

公开(公告)号：US10233939B2

公开(公告)日：2019-03-19

申请号：US15205265

申请日：2016-07-08

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Thomas Alain De Gaillard ,  Alexandre Bernard Marie Boisson ,  Audrey Laguerre

IPC: F04D29/34 ,  F04D19/00 ,  F04D29/64 ,  F04D29/02 ,  F02K3/06 ,  F01D11/00 ,  F01D5/30 ,  F01D5/32

Abstract: A fan assembly for an aviation turbine engine, the assembly including a fan disk having at least one tooth and at least one platform mounted on the tooth of the fan disk, the platform including a box of composite material made from fiber reinforcement densified by a matrix, the box having a flow passage wall, a bottom wall, and two side walls extending radially between the bottom wall and the flow passage wall. The box of the platform includes an upstream opening at an upstream end of the platform and a downstream opening, and the assembly also includes a locking key housed in the box and passing through the upstream and downstream openings of the box, the locking key being blocked at each of its ends by a blocking element.

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).