公开(公告)号：US12060811B2

公开(公告)日：2024-08-13

申请号：US17441619

申请日：2020-03-19

Applicant: SAFRAN ,  SAFRAN AIRCRAFT ENGINES

Inventor： Jeremy Philippe Pierre Edynak ,  Jeremy Guivarc'h ,  Lola Auliac ,  Thibaut Dominique Augustin Girard ,  Pierre Jean Faivre D'Arcier

IPC: F01D11/00 ,  F01D5/30

CPC classification number: F01D5/3007 ,  F01D11/003 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/30 ,  F05D2240/55

Abstract: The invention relates to a fan rotor for a turbomachine, including a fan disk, fan blades with a leading edge and a trailing edge, platforms inserted between the blades and fixed to the periphery of the disk, each including an aerodynamic surface extending from the leading edges to the trailing edges of the blades. The aerodynamic surface includes an upstream longitudinal portion on the side of the leading edges and a downstream longitudinal portion on the side of the trailing edges, the upstream longitudinal portion being supported by a first member of the platform fixed to the disk in a pivotable manner, and the downstream longitudinal portion being independent of the upstream longitudinal portion and supported by a second member of the platform which is independent of the first member and fixed to the disk in a pivotable manner.

公开(公告)号：US11143047B2

公开(公告)日：2021-10-12

申请号：US16446669

申请日：2019-06-20

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Jeremy Guivarc'h ,  Fabrice Michel Francois Rene Aubert ,  Pierre Martin Michelsen

IPC: F01D11/00 ,  F01D5/32 ,  F04D19/00

Abstract: A fan includes: a fan disc; an inter-blade platform including a base and a radial tab, a second orifice being formed in the tab of the platform; and a lock having a downstream edge configured to bear against the tab of the platform. The one among the downstream edge and the yoke of the fan disc includes a pin, the other includes a first orifice, the pin being configured to enter the first orifice and the second orifice so as to block the platform relative to the fan disc.

公开(公告)号：US11254067B2

公开(公告)日：2022-02-22

申请号：US16590273

申请日：2019-10-01

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Jeremy Guivarc'h ,  Pierre Antoine Bossan ,  Michael Patrick Gramzow ,  Sebastien Marin

IPC: B29C65/00 ,  B29C65/48 ,  F16B4/00 ,  C09J5/06 ,  B29L31/00

Abstract: A method for producing a part. This part including a surface portion whereon is positioned an element to be assembled via an adhesive on the surface portion. The method includes the steps of: mounting a sleeve of heat-shrinkable material around at least one portion of the element on the part, heating of the sleeve in order to shrink it and thus to apply an application force of the element on the surface portion, hardening of the adhesive, and removing the sleeve.

公开(公告)号：US10436036B2

公开(公告)日：2019-10-08

申请号：US15201979

申请日：2016-07-05

Applicant: Safran Aircraft Engines

Inventor： Jeremy Guivarc'h ,  Francois Charleux

IPC: F01D5/14 ,  F01D5/28 ,  F01D11/00 ,  B29B11/16 ,  B29C45/02 ,  B29C45/14 ,  D03D1/00 ,  D03D13/00 ,  D03D25/00 ,  B29L31/08

Abstract: A fitted platform for positioning between two adjacent blades of an aviation turbine engine fan includes a flow passage wall made of composite material having a central portion, and first and second margins each extending in a longitudinal direction of the wall. Each margin extends over a determined distance from the central portion in a transverse direction of the wall. The flow passage wall includes a fiber reinforcement densified by a matrix. The fiber reinforcement present in the central portion presents three-dimensional weaving, and the fiber reinforcement present in the first and second margins presents two-dimensional weaving, at least in part.