Outer shell sector forming assembly for bladed ring sector of turbine or compressor stator in turbojet engine of aircraft, has vibration-damping block supported against two friction surfaces respectively provided on two elementary sectors

摘要

The assembly (28) has elementary sectors (30) spaced with respect to each other along a tangential direction (22) of the assembly, and vibration-damping blocks (34) e.g. annular section tubes, where each block is interposed between two of the elementary sectors. The blocks are positioned in a directly consecutive manner along the tangential direction. The block is supported against two friction surfaces (38) that are placed opposite to each other along the tangential direction and respectively provided on the two elementary sectors associated to the block. Independent claims are also included for the following: (1) a bladed ring sector of a turbine or compressor stator in a turbomachine of an aircraft, comprising blades (2) a method for manufacturing an outer shell sector forming assembly.