# US 11,905,839 B2 · Attachment of an acoustic shroud to a housing shell for an aircraft turbine engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,905,839 B2 - Document ID: US11905839B2 - Status: Granted - Kind: B2 - Application number: 17/753,547 - Filed: 2020-09-09 - Published: 2022-10-20 - Granted: 2024-02-20 - Earliest claimed: 2019-09-10 - Assignees: Safran Aircraft Engines - Applicants: Safran Aircraft Engines - Inventors: Thomas Dupays; Clement Bourolleau; Coline Poulenc; Anwer Siraj - Web page: https://patentgrep.com/patent/US11905839B2 ## CPC - F01D 11/122: {with erodable or abradable material (blades having cutting or grinding tips F01D5/20)} - F05D 2240/11: Shroud seal segments - F05D 2260/96: Preventing, counteracting or reducing vibration or noise - F05D 2300/603: Composites; e.g. fibre-reinforced - F05D 2300/614: Fibres or filaments - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract The invention relates to a method for manufacturing an aircraft turbine engine housing, the housing (23) comprising: —an annular shell (29) with axis A; —an annular element (24; 253, 254) attached to the inside of the shell (29), the annular element comprising a body (25) made of NIDA-type cellular material and comprising a downstream portion (252) covered with an abradable material (26), and an upstream portion (251) without abradable material, the body (25) extending in a continuous manner from the upstream portion (251) to the downstream portion (252), the method comprising: —manufacturing the annular element in the form of a continuous annular body, —cutting the annular body into segments (253, 254), —attaching the segments to the shell, and —depositing the abradable material (26) onto the inside surface (25a) of the downstream portion (252). ## Claims ### Claim 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. ### Claim 2 (depends on 1) The manufacturing method according to claim 1, wherein the abradable material of the abradable material layer is a resin comprising a filler in the form of hollow beads. ### Claim 3 (depends on 1) The manufacturing method according to claim 1, wherein the step of attaching the body segments on the inside surface of the shell comprises a step of filling gaps between the body segments with an abradable filling material. ### Claim 4 (depends on 3) The manufacturing method according to claim 3, wherein the filling material is a resin comprising a filler in the form of hollow beads. ### Claim 5 (depends on 3) The manufacturing method according to claim 3, wherein the abradable filling gaps material is the same abradable material as the material making up the abradable material layer. ### Claim 6 (depends on 5) The manufacturing method according to claim 5, wherein at the downstream portion the abradable material layer is integral with the filling material. ### Claim 7 (depends on 3) The manufacturing method according to claim 3, wherein the filling material is a resin comprising a filler in the form of hollow glass beads. ### Claim 8 (depends on 3) The manufacturing method according to claim 3, wherein the filling material is an epoxy resin filled with hollow glass microspheres. ### Claim 9 (depends on 1) A housing for an aircraft turbine engine manufactured by the method of claim 1. ### Claim 10 (depends on 9) The housing according to claim 9, wherein the annular element is attached by adhesion to the inside surface of the shell. ### Claim 11 (depends on 9) The housing according to claim 9, wherein the abradable material layer is disposed in a recess of the downstream portion of the body. ### Claim 12 (depends on 9) The housing according to claim 9, wherein the abradable layer has an inside surface which extends in the axial extension of the second inside surface. ### Claim 13 (depends on 9) The housing according to claim 9, wherein a film based on fibres covers the first and second inside surfaces of the body made of cellular material, the film itself being covered by the abradable material layer at the first inside surface. ### Claim 14 (depends on 9) The housing according to claim 9, wherein the downstream portion of the body has a greater axial dimension than the upstream portion. ### Claim 15 (depends on 9) The housing according to claim 9, wherein the abradable layer has a radial thickness measured with respect to said axis A which is between 2 and 20% of the radial thickness of said body. ### Claim 16 (depends on 9) The housing according to claim 9, wherein the shell is made of a composite material comprising woven fibres embedded in a resin. ### Claim 17 (depends on 9) The housing according to claim 9, wherein the number of segments of the body is between two and ten. ### Claim 18 (depends on 1) The manufacturing method according to claim 1, wherein the abradable material of the abradable material layer is a resin comprising a filler in the form of hollow glass beads. ### Claim 19 (depends on 1) The manufacturing method according to claim 1, wherein the abradable material of the abradable material layer is an epoxy resin filled with hollow glass microspheres.