公开(公告)号：US20210054752A1

公开(公告)日：2021-02-25

申请号：US16965433

申请日：2019-01-25

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Sébastien Jean Laurent PRESTEL ,  Simon Jean-Marie Bernard COUSSEAU ,  Alice PAGES ,  Cyril VERBRUGGE

IPC: F01D9/04 ,  F01D25/24

Abstract: The invention relates to an inter-turbine casing (1) comprising: an inner shell (10), an outer shell (20), and an assembly of arms (2) extending radially between the timer (10) and outer (20) shells; and an assembly of splitter blades (30) positioned between the arms (2), each splitter blade (30) comprising an inner platform (33) and an outer platform (36). The inner shell (10) comprises at least one inner groove (11) for slidably receiving one or more inter platforms (33). The outer shell (20) comprises at least one outer groove (21) for slidably receiving one or more outer platforms (36). The inter-turbine casing further comprises locking means (4, 5) for locking the splitter blades (30) in the inner (11) and outer (21) grooves. The splitter blades are arranged using multiple tenons (39) that extend in corresponding ribs (12, 22).

公开(公告)号：US20230125862A1

公开(公告)日：2023-04-27

申请号：US17906248

申请日：2021-03-19

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Simon Jean-Marie Bernard COUSSEAU ,  Nicolas Xavier TRAPPIER ,  Maxime Aurelien ROTENBERG

IPC: F01D11/12 ,  F01D9/04 ,  F01D11/02

Abstract: A rotary assembly for a turbomachine including a rotor including at least two consecutive rotor stages provided with a plurality of blades and an annular rotor shroud connecting the two consecutive rotor stages, a stator including: at least one stator stage provided between the two consecutive rotor stages including a plurality of vanes, a turbomachine stator vane root, an annular clamping part and an annular support of abradable material, the root extending radially and being clamped axially between the annular support of abradable material and the annular clamping part, A space separates a radially internal end of the root and the annular support of abradable material. A turbojet engine including a rotary assembly as previously.

公开(公告)号：US20250043687A1

公开(公告)日：2025-02-06

申请号：US18720412

申请日：2022-12-14

Applicant: Safran Aircraft Engines

Inventor： Simon Jean-Marie Bernard COUSSEAU ,  Patrice Jean-Marc ROSSET ,  Nicolas Xavier TRAPPIER ,  Julian Nicolas GIRARDEAU ,  Patrick Joseph Marie GIRARD ,  Baptiste Dorian LAWNICZEK

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

Abstract: The present invention relates to a turbine rotor of a turbine engine of an aircraft, the rotor comprising a rotor disc provided at its periphery with a plurality of cavities for receiving the root of a blade. This rotor is characterised in that each blade comprises a circumferential coupling rib, in that it comprises a plurality of platforms, which comprise a main wall that is extended at its two ends by an upstream radial wall and by a downstream radial wall, the two longitudinal edges of each platform comprising a groove for receiving part of said coupling rib of one of the two blades between which this platform is assembled, and in that the height of each upstream radial wall is such that said wall extends radially inwards beyond the bottom of the cavity, until it is in front of the upstream face of the rotor disc.

公开(公告)号：US20240093638A1

公开(公告)日：2024-03-21

申请号：US17754858

申请日：2020-10-08

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Simon Jean-Marie Bernard COUSSEAU ,  Mathieu Patrick Henri DELALANDRE ,  Patrick Jean Laurent SULTANA ,  Laurent Cédric ZAMAI

IPC: F02C3/067

CPC classification number: F02C3/067 ,  F05D2240/24 ,  F05D2250/44

Abstract: A counter-rotating turbine for a turbine engine comprising an inner rotor having an inner drum to which is attached a plurality of inner impellers rotatably supported by a first shaft, an outer rotor comprising an outer drum to which is fastened a plurality of outer impellers rotatably supported by a second shaft coaxial with the first shaft, the outer rotor comprising a downstream impeller having a plurality of downstream moving blades extending between an outer shroud and an inner shroud, one upstream end of the outer shroud being attached downstream of said outer drum, the inner shroud being attached to the second shaft, at least one of the inner shroud and of the outer shroud comprising at least one flexible transition part configured to allow elastic deformation of said shroud in the radial direction.