公开(公告)号：US20240263560A1

公开(公告)日：2024-08-08

申请号：US18699150

申请日：2022-09-30

Applicant: SAFRAN AIRCRAFT ENGINES ,  SAFRAN CERAMICS

Inventor： Patrick Joseph Marie GIRARD ,  Didier René André ESCURE ,  Matthieu Arnaud GIMAT ,  Sébastien Serge Francis CONGRATEL ,  Arthur DE CASTRO

IPC: F01D5/30 ,  F01D5/14 ,  F01D9/04

CPC classification number: F01D5/3084 ,  F01D5/141 ,  F01D9/041 ,  F05D2300/6033

Abstract: Blade of a turbomachine turbine including a airfoil extending along a first direction between an internal end and an external end, a base secured to said internal end, and a root secured to said external end and extending, along a second direction perpendicular to said first direction, between an upstream edge, and a downstream edge and, along a third direction orthogonal to the first and second directions, between first and second lateral edges, the first side edge having, in a plane including the second and third directions, a shape complementary to that of the second lateral edge. The first lateral edge includes a first portion extending from the upstream edge, and a second portion externally protruding along the third direction at an acute angle with the first portion.

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.