Outer shell sector for a bladed ring for an aircraft turbomachine stator, including vibration damping shims

Abstract

An assembly forming an outer shell sector, for a bladed ring sector configured to be used on a compressor or turbine stator in an aircraft turbomachine, including a plurality of elementary sectors and vibration damping shims each of them being inserted between two elementary sectors associated with it. A profile of each vibration damping shim is approximately the same as a profile of the elementary sectors.

1 - 7 . (canceled) 
     
     
         8 . A bladed ring sector configured to be installed on a compressor stator of an aircraft turbomachine, comprising:
 an assembly forming an outer shell sector;   an inner shell sector;   a plurality of blades at a tangential spacing from each other and inserted between the assembly forming the outer shell sector and the inner shell sector, the blades being fixed to each assembly forming the outer shell sector and the inner shell sector; and   the assembly forming an outer shell sector comprising firstly a plurality of elementary sectors at a spacing from each other along a tangential direction of the assembly, and secondly vibration damping shims each of them being inserted between two elementary sectors associated with it, placed directly consecutively along the tangential direction,   wherein a profile of each vibration damping shim is approximately a same as a profile of the elementary sectors.   
     
     
         9 . A sector according to  claim 8 , wherein the shim is forced in contact with two parallel plane friction surfaces facing each other along the tangential direction and provided respectively on the two elementary sectors associated with the shim, and wherein the shim has two complementary plane friction surfaces, parallel to each other and cooperating with the two corresponding friction surfaces of the elementary sectors. 
     
     
         10 . A sector according to  claim 8 , wherein the shim includes hooks to hold it in place on the compressor or turbine stator. 
     
     
         11 . A sector according to  claim 8 , wherein the elementary sectors are separated from each other by radial slits completely filled in by the vibration damping shims. 
     
     
         12 . A sector according to  claim 8 , wherein the vibration damping shims extend approximately along an axial or oblique direction of the assembly. 
     
     
         13 . An aircraft turbomachine comprising:
 a compressor stator including at least one bladed ring sector according to  claim 8 .