Granted Patent B1

US 12,486,775 · App. 18/877,899 · Granted Dec 2, 2025

Inventors: Nicolas Xavier Trappier (Moissy-Cramayel, FR); Didier René André Escure (Moissy-Cramayel, JP); Matthieu Arnaud Gimat (Moissy-Cramayel, FR); Sébastien Serge Francis Congratel (Moissy-Cramayel, FR); Patrick Joseph Marie Girard (Moissy-Cramayel, FR); Arthur De Castro (Moissy-Cramayel, FR); Patrice Jean-Marc Rosset (Moissy-Cramayel, FR); Baptiste Dorian Lawniczek (Moissy-Cramayel, FR)

Assignees: SAFRAN AIRCRAFT ENGINES; SAFRAN CERAMICS

F01D5/225F05D2240/80F05D2260/96

Abstract

Claims (11)

1 . A turbomachine bladed assembly extending around a main axis and including at least one first blade and one second blade circumferentially adjacent,

each of the first blade and the second blade including a vane extending according to a direction of radial extension with respect to said main axis and including a platform located at a free radial end of the vane,

wherein the platform of the first blade includes a lateral face which is located circumferentially opposite an associated lateral face of the platform of the second blade,

wherein the platform of the first blade is intended to come into contact with the platform of the second blade, during operation of the turbomachine, only via an excrescence which projects circumferentially with respect to the lateral face of the platform of the first blade in the direction of the platform of the second blade, and in that the excrescence is received in a groove formed in the platform of the second blade,

wherein each of the excrescence and the groove extends in a plane substantially perpendicular to a radial direction with respect to the main axis, the excrescence including a radially outer face which is oriented radially outward and which bears radially against a bottom face of the groove which is oriented radially inward, and

wherein the excrescence and the groove are axially located substantially at the middle of the platform that is associated therewith.

2 . The turbomachine bladed assembly according to claim 1 , wherein the groove formed in the second blade and which is associated with the excrescence of the first blade is circumferentially open into a lateral face of the platform of the second blade in the direction of the platform of the first blade.

3 . The turbomachine bladed assembly according to claim 1 , wherein the excrescence of the first blade includes at least one face which bears against an opposite face of the groove of the second blade.

4 . The turbomachine bladed assembly according to claim 1 , wherein the groove of the second blade is axially delimited by two lateral faces against which the excrescence of the first blade is able to axially bear.

5 . The turbomachine bladed assembly according to claim 1 , wherein each of the platform of the first blade and the platform of the second blade includes an excrescence at a circumferential end and a groove at its other circumferential end.

6 . The turbomachine bladed assembly according to claim 1 , wherein the excrescence is arranged at a circumferential end of the platform of the first blade or of the second blade, the circumferential end being located on the intrados side of the vane of said first or second blade.

Assignments (1)

Priority Claims (1)

References Cited (12)