Patent ID: 8133011

Claim:
An aircraft engine, comprising: a decoupling device; and a turbomachine including a stator including at least one internal ferrule, at least one external ferrule, at least one blade stage of a plurality of fixed blades X, each of the fixed blades arranged between the at least one internal ferrule and at least one external ferrule, and a plurality of profiled members P, where P<X, the plurality of profiled members being stiffeners arranged on the at least one blade stage while being distributed at a periphery thereof, each of the stiffeners being disposed individually between two consecutive blades, and the stiffeners being fixed to the at least one internal ferrule and at least one external ferrule in order to increase axial and radial stiffness of the stator in normal operation of the turbomachine and to enable the at least one internal ferrule to have a limited displacement during normal functioning of the turbomachine, and a rotor arranged internally to the stator, wherein the stiffeners are fixed with a fusible fixing to the at least one external ferrule in order to reduce the radial stiffness of the stator in case of contact between the rotor and the at least one internal ferrule once the decoupling device is triggered.