STATOR INNER SHROUD TO DELIMIT A PRIMARY FLOW THROUGH AN AIRCRAFT TURBINE ENGINE

摘要

Stator shroud for an aircraft turbine engine module, intended radially toward the inside to delimit a primary flow passing through the turbine engine, this shroud having an overall U-shaped cross section of which the two branches of the U (26) extend substantially in an inward radial direction from the base of this U (32), the shroud having a number of perforations (36) each intended to accept the root of a stator vane, each perforation being made through the base of the U. Each perforation (36) is extended by shroud stiffening means (40) projecting from the base of the U (32) substantially in the inward radial direction.