公开(公告)号：US20230160313A1

公开(公告)日：2023-05-25

申请号：US17917151

申请日：2021-03-29

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Patrice Jean-Marc ROSSET

IPC: F01D5/30 ,  F01D5/32

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

Abstract: A turbine rotor includes a disc with cavities, a plurality of blades, each with a root received in one of the cavities, and an axial retention system including a first series and a second series of strips circumferentially distributed around an axis of the rotor, the first and the second series being axially superimposed and arranged such that at least two strips circumferentially adjacent to the first series are axially superimposed on a strip of the second series and each strip of the first and second series is arranged opposite a cavity of the disc so as to axially block the root of a blade.

公开(公告)号：US20230117756A1

公开(公告)日：2023-04-20

申请号：US17906930

申请日：2021-03-26

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Michel Gilbert Roland BRAULT ,  Julien Fabien Patrick BECOULET ,  Olivier FORMICA ,  Patrice Jean-Marc ROSSET ,  Alexandre Jean-Marie TAN-KIM

IPC: F16C33/58 ,  F16C19/06 ,  F01D25/16

Abstract: An enclosure for a turbomachine includes a turbomachine drive shaft rotating about a longitudinal axis (X) by means of two roller bearings, an upstream bearing and a downstream bearing, each having an inner ring carried by the drive shaft. The two bearings share a single integral outer ring that has an upstream end and a downstream end connected to one another by a section of studs. The single outer ring is carried by an upstream base plate and a downstream base plate of a bearing support configured to be attached to a stationary structure of the turbomachine.

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：US20240337201A1

公开(公告)日：2024-10-10

申请号：US18580890

申请日：2022-07-20

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Vianney SIMON ,  Patrice Jean-Marc ROSSET ,  Patrick Jean Laurent SULTANA ,  Jean-Claude Christian TAILLANT

IPC: F01D25/18 ,  F02C7/36

CPC classification number: F01D25/183 ,  F02C7/36 ,  F05D2260/31

Abstract: The present invention relates to a rotating assembly of a turbomachine, comprising:—a shaft configured to drive a propeller of the turbo machine around an axis and comprising a first flange radially extending from the shaft, the first flange being monolithic with the shaft;—a sleeve fitted onto the shaft and comprising a second flange radially extending from the sleeve, the sleeve being attached to the first flange of the shaft by means of the second flange; and—at least one component connected to the shaft by means of the sleeve so as to be rigidly connected to the shaft to move therewith, the component comprising at least one sealing element.