Patent ID: 11905839
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
1. A method for manufacturing an aircraft turbine engine housing, the housing comprising:
an annular shell extending about an axis A;
an annular element, attached to an inside surface of the shell, the annular element comprising a body which is made of a honeycomb-type cellular material and which comprises a downstream portion having a first inside surface covered with a layer of abradable material, and an upstream portion having a second inside surface without abradable material, the body extending continuously from the upstream portion to the downstream portion,
the manufacturing method comprising:
a step of manufacturing the annular element as a continuous annular body,
a step of cutting the continuous annular body into body segments,
a step of attaching the body segments to the inside surface of the shell, and
a step of depositing a layer of abradable material on the inside surface of the downstream portion of the body.