公开(公告)号：US20210254481A1

公开(公告)日：2021-08-19

申请号：US16973663

申请日：2019-06-06

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Nicolas Daniel DELAPORTE ,  Alain Dominique GENDRAUD ,  Emmanuel Bernard Marie CHARRIER

IPC: F01D5/30 ,  F01D25/28

Abstract: The present disclosure relates to a holding system for the dismantling of a blade wheel, the blade wheel comprising: a disc, a plurality of blades configured to be mounted circumferentially around the disc, the plurality of blades defining a plurality of inter-blade spaces, each of the inter-blade spaces being defined circumferentially between two adjacent blades of the plurality of blades, the holding system comprising a plurality of inserts, each of the inserts being configured to be inserted into each of the inter-blade spaces in a holding position so as to hold the relative position of the blades when the plurality of blades is dismantled from the disc.

公开(公告)号：US20200040735A1

公开(公告)日：2020-02-06

申请号：US16339801

申请日：2017-10-06

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Vincent Francois Georges MILLIER ,  Francois Pierre Michel COMTE ,  Fabien Stephane GARNIER ,  Alain Dominique GENDRAUD ,  Arnaud Lasantha GENILIER

IPC: F01D5/06 ,  F01D5/30 ,  F01D11/00

Abstract: A movable ring assembly (4) for a turbine engine turbine (10) that is mounted between two successive rotor discs (20a) and (20b) of said turbine (10), said rotor discs (20a) and (20b) being fixed to each other by bolting, characterised in that it comprises:—a fixing ferrule (44) fixed between the upstream (20a) and downstream (20b) discs by the bolting thereof; a part forming a movable ring (42), said part supporting radial sealing members (32) and being fixed between the upstream disc (20a) and the ferrule (44);—and a seal (46) interposed between said part forming the movable ring (42) and the ferrule (44).

公开(公告)号：US20220290579A1

公开(公告)日：2022-09-15

申请号：US17634159

申请日：2020-08-04

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Simon Nicolas MORLIERE ,  Stéphane Pierre Guillaume BLANCHARD ,  Nicolas Jean-Marc Marcel BEAUQUIN ,  Alain Dominique GENDRAUD ,  Olivier RENON

IPC: F01D25/14 ,  F01D25/12

Abstract: The invention relates to an assembly (25) for a turbomachine turbine comprising a casing (18) including an annular wall (26) extending about an axis, and means of cooling the casing (18), the said means of cooling comprising a collector housing (22) and at least one tube (23) extending circumferentially around the annular wall (26) of the casing (18) and connected to the housing (22), with the tube (23) comprising cooling-air ejection orifices.

公开(公告)号：US20230212953A1

公开(公告)日：2023-07-06

申请号：US17922288

申请日：2021-04-28

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Simon Nicolas MORLIERE ,  Nicolas Jean-Marc Marcel BEAUQUIN ,  Thierry FACHAT ,  Alain Dominique GENDRAUD

IPC: F01D11/00 ,  F01D9/04 ,  F01D11/12 ,  F01D25/24

CPC classification number: F01D11/005 ,  F01D9/042 ,  F01D11/122 ,  F01D25/243 ,  F05D2240/11

Abstract: The invention proposes an aeronautical turbine engine assembly comprising an upstream casing (55) to which guide blading (48a) is fastened, and a downstream casing (58) to which a sealing element (62) provided with an abradable material for rotor blading is fastened. This assembly further comprises a shroud ring (66) placed between the upstream casing and the downstream casing and fastening means (68) for detachably fastening the shroud ring. In order to be fastened to the upstream casing, the guide blading (48a) of the turbine engine is mounted on a downstream hook (480b) of the upstream casing, without being hooked onto the shroud ring (66), and the downstream casing (58) has an upstream hook with which the sealing element (62) is engaged in order to be fastened to the downstream casing, or the shroud ring has an upstream hook on which the sealing element (62) is mounted so as to be fastened to the downstream casing.

公开(公告)号：US20180209302A1

公开(公告)日：2018-07-26

申请号：US15745788

申请日：2016-07-19

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Alain Dominique GENDRAUD ,  Jean-Baptiste Vincent DESFORGES ,  Arnaud GENILIER ,  Reda OUDYI

IPC: F01D25/24 ,  F16B39/24 ,  F16B39/10

Abstract: An assembly including a securing stud held by a locking key that rotates with the stud and is provided with bearing surfaces for sitting on an edge of one of the parts to be assembled. Sufficient clamping torque can be introduced without risk of damage and at the same time avoiding excessive screwing of the stud.

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.