Patent ID: 9017022
Filing Date: 2015-04-28
Classification: F01D,F04D,F05D,Y02T

Abstract:
1. A shell for a stator of an aircraft turbo-engine module, comprising: a plurality of through openings each configured to house a stator blade, each stator blade having a trailing edge and a leading edge, each opening forming a skeleton extending between a first end configured to house the trailing edge of the blade and a second end configured to house the leading edge of the blade, a mechanical load transfer slit passing through the shell, said slit being associated with one of said openings and arranged facing and at a distance from the first end of the opening along the direction of the skeleton, wherein the slit has a generally horseshoe shape with a bottom portion and two branches extending from said bottom portion, wherein the first end of the opening is located between said branches of said slit, and wherein the slit is separated from said opening by a portion of said shell.