公开(公告)号：US20180195416A1

公开(公告)日：2018-07-12

申请号：US15746375

申请日：2016-07-20

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Baptiste Marie Aubin Pierre JOUY ,  Bertrand Guillaume Robin PELLATON ,  Sebastien Jean Laurent PRESTEL

IPC: F01D25/30 ,  F02C9/18 ,  F02C3/13 ,  F01D9/06

CPC classification number: F01D25/30 ,  F01D9/065 ,  F02C3/13 ,  F02C9/18 ,  F05D2220/323 ,  F05D2250/314 ,  F05D2260/20 ,  F05D2260/941 ,  F05D2270/101 ,  F05D2270/114 ,  F05D2300/50212 ,  Y02T50/675

Abstract: The invention relates to an exhaust casing for a turbine engine of an aircraft, including: a collar (4), a hub (5), hollow arms (63) connecting said collar (4) to said hub (5), and an opening piece (3) which is located on the collar (4) and is suitable for being connected to an outlet tube (30) of a transient-operation valve of the turbine engine. In said exhaust casing, said opening piece (3) is attached onto the collar (4) and forms an extension of a hollow arm (63) such that an air flow (7) leaving the outlet tube (30) of the transient-operation valve penetrates the hollow arm (63) and flows into the hub (5).

公开(公告)号：US20210108526A1

公开(公告)日：2021-04-15

申请号：US16496368

申请日：2018-03-23

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Patrick Jean Laurent SULTANA ,  Sebastien Jean Laurent PRESTEL ,  Olivier RENON

IPC: F01D9/06 ,  F01D25/04 ,  F16L3/13

Abstract: The invention relates to a turbomachine assembly comprising: —a casing comprising: —an internal hub (10), —an external ferrule (20) extending around and at a distance from the internal hub (10), —a hollow arm (30), provided with a longitudinal cavity (40) and connecting the internal hub (10) and the external ferrule (20), —a tube (50) configured to extend in the interior of the longitudinal cavity (40) of the hollow arm (30) of the casing and comprising a central support (60) comprising two elastic blades (61) and configured to exert a pressure on the wall (42) of the longitudinal cavity (40) when the tube (50) is extended in the interior of the longitudinal cavity (40); characterized in that the material(s) of the elastic blades (61) is (are) such that said elastic blades (61) have a stress curve between the minimum and maximum stress curves of table A.

公开(公告)号：US20170218785A1

公开(公告)日：2017-08-03

申请号：US15501161

申请日：2015-08-04

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Cyril LOISEAU ,  Alain Dominique GENDRAUD ,  Sebastien Jean Laurent PRESTEL

IPC: F01D11/00 ,  F01D25/24

CPC classification number: F01D11/005 ,  F01D25/246 ,  F05D2240/11

Abstract: A turbomachine module, comprising a mobile wheel rotatably mounted inside a housing of the module and surrounded by a sectorised sealing ring (18) that comprises an annular row of sectors, each ring sector comprising at least one circumferential hook that is configured to engage with an annular hooking rail of the housing, the module further comprising a sectorised protective annular shim (50) that is interposed between the hooks of the ring sectors and the rail of the housing and that comprises an annular row of sectors of shim, characterised in that the edges (60) of the circumferential ends of the sectors of shim are not aligned with the edges (58) of the circumferential ends of the ring sectors along the longitudinal axis of the module.