STATORSTUFE EINES VERDICHTERS EINES LUFTFAHRZEUG-TURBOTRIEBWERKS

摘要

This document presents an invention relating to a stator stage (1) of a compressor of an aircraft turbomachine. The stator stage (1) comprises an internal ferrule (2) comprising at least one segment (21) made of a composite material, an external ferrule, stator vanes (3) extending radially from the internal ferrule (2) to the outer shell, and at least one auxiliary blade (4) comprising a foot (42) embedded at least partially in said composite material, and extending radially from this foot (42), parallel to and between two of the stator vanes (3).