BLADE AND SHROUD WITH SOCKET FOR A COMPRESSOR OF AN AXIAL TURBOMACHINE

摘要

A blading structure of a compressor of an axial turbomachine for an aircraft has a wall, such as a composite internal shroud with an organic matrix, which is intended to radially delimit a primary annular flow of the turbomachine and includes a fastening socket. The structure additionally has a blade fastened in the fastening socket and extending radially with respect to the wall, and a fastening layer at the interface between the blade and the socket. The interface has asperities hugging the fastening layer so as to ensure anchoring by engagement of material in order to fasten the blade in the socket by bonding. A low-pressure compressor has an internal shroud with sockets bonded to blades.