# US 2008/0185215 A2 · Integrated inlet attachment > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2008/0185215 A2 - Document ID: US20080185215A2 - Status: Published application - Kind: A2 - Application number: 11/537,764 - Filed: 2006-10-02 - Published: 2008-08-07 - Earliest claimed: 2006-10-02 - Assignees: Spirit AeroSystems, Inc. - Inventors: John Strunk - Web page: https://patentgrep.com/patent/US20080185215A2 ## CPC - B64D 33/02: of combustion air intakes - B64D 2033/0206: {comprising noise reduction means, e.g. acoustic liners} - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT ## Abstract An acoustic panel for integration in a nacelle of an aircraft engine assembly for absorbing noise generated by an engine or a fan assembly of the aircraft engine assembly. The acoustic panel comprises a generally annular section integrated into or attached to an inner wall of the inlet section, and a flange extending generally perpendicularly from the annular section. The flange attaches the acoustic panel to a bulkhead without requiring the use of fasteners extending through the annular section of the acoustic panel, thus eliminating any unwanted air passages through the annular section of the acoustic panel. ## Claims ### Claim 1 A nacelle for partially enclosing an aircraft engine and fan assembly, the nacelle comprising: an inlet section for directing air toward the fan assembly; a main section coupled with the inlet section for supporting the engine; and an acoustic panel for absorbing noise generated by the engine or the fan assembly, the acoustic panel including- a generally annular section integrated into or attached to an inner wall of the inlet section, and a flange extending generally perpendicularly from the annular section for attaching the acoustic panel to a bulkhead without requiring the use of fasteners extending through the annular section. ### Claim 2 (depends on 1) The nacelle as set forth in claim 1, wherein the acoustic panel annular section includes a structural honeycomb core layer connected to the flange, an acoustical honeycomb core layer on top of the structural honeycomb core layer, and a perforated skin layer on top of the acoustical honeycomb core layer. ### Claim 3 (depends on 1) The nacelle as set forth in claim 1, further including an annular support ring for attachment between the flange and the bulkhead. ### Claim 4 (depends on 3) The nacelle as set forth in claim 3, the annular support ring including a plurality of spaced-apart bolt holes, and the flange including a plurality of spaced-apart bolt holes aligned with the bolt holes of the annular support ring for receiving a plurality of bolts for bolting the acoustic panel to the annular support ring and therefore to the bulkhead. ### Claim 5 (depends on 4) The nacelle as set forth in claim 4, the annular support ring further including a plurality of raised bosses aligned with the bolt holes for receiving and holding barrel nuts in place so the bolts can be screwed through the bolt holes and into the barrel nuts to securely fasten the acoustic panel to the annular support ring and therefore to the bulkhead. ### Claim 6 (depends on 5) The nacelle as set forth in claim 5, the main section including an engine casing for containing parts which may break from the engine or fan assembly. ### Claim 7 (depends on 6) The nacelle as set forth in claim 6, the engine casing including a generally annular section integrated into or attached to an inner wall of main section and a flange extending generally perpendicularly from the annular section. ### Claim 8 (depends on 7) The nacelle as set forth in claim 7, the engine casing flange including a plurality of spaced-apart bolt holes aligned with the bolt holes of the annular support ring and the bolt holes of the inlet section flange so the bolts may be screwed through the engine casing flange, acoustic panel flange, and the annular support ring. ### Claim 9 An acoustic panel for integration in a nacelle of an aircraft engine assembly for absorbing noise generated by an engine or a fan assembly of the aircraft engine assembly, the acoustic panel comprising: a generally annular section integrated into or attached to an inner wall of the nacelle, and a flange extending generally perpendicularly from the annular section for attaching the acoustic panel to a bulkhead without requiring the use of fasteners extending through the annular section. ### Claim 10 (depends on 9) The acoustic panel as set forth in claim 9, wherein the acoustic panel annular section includes a structural honeycomb core layer connected to the flange, an acoustical honeycomb core layer on top of the structural honeycomb core layer, and a perforated skin layer on top of the acoustical honeycomb core layer. ### Claim 11 (depends on 9) The acoustic panel as set forth in claim 9, further including an annular support ring for attachment between the flange and the bulkhead. ### Claim 12 (depends on 11) The acoustic panel as set forth in claim 11, the annular support ring including a plurality of spaced-apart bolt holes, and the flange including a plurality of spaced-apart bolt holes aligned with the bolt holes of the annular support ring for receiving a plurality of bolts for bolting the acoustic panel to the annular support ring and therefore to the bulkhead. ### Claim 13 (depends on 12) The acoustic panel as set forth in claim 12, the annular support ring further including a plurality of raised bosses aligned with the bolt holes for receiving and holding barrel nuts in place so the bolts can be screwed through the bolt holes and into the barrel nuts to securely fasten the acoustic panel to the annular support ring and therefore to the bulkhead. ### Claim 14 An aircraft engine assembly comprising: an engine coupled with a fan assembly; and a nacelle for partially enclosing the engine and fan assembly, the nacelle comprising: an inlet section for directing air toward the fan assembly; a main section coupled with the inlet section for supporting the engine; and an acoustic panel for absorbing noise generated by the engine or the fan assembly, the acoustic panel including- a generally annular section integrated into or attached to an inner wall of the inlet section, and a flange extending generally perpendicularly from the annular section for attaching the acoustic panel to a bulkhead without requiring the use of fasteners extending through the annular section. ### Claim 15 (depends on 14) The aircraft engine assembly as set forth in claim 14, wherein the acoustic panel annular section includes a structural honeycomb core layer connected to the flange, an acoustical honeycomb core layer on top of the structural honeycomb core layer, and a perforated skin layer on top of the acoustical honeycomb core layer. ### Claim 16 (depends on 14) The aircraft engine assembly as set forth in claim 14, further including an annular support ring for attachment between the flange and the bulkhead. ### Claim 17 (depends on 16) The aircraft engine assembly as set forth in claim 16, the annular support ring including a plurality of spaced-apart bolt holes, and the flange including a plurality of spaced-apart bolt holes aligned with the bolt holes of the annular support ring for receiving a plurality of bolts for bolting the acoustic panel to the annular support ring and therefore to the bulkhead. ### Claim 18 (depends on 17) The aircraft engine assembly as set forth in claim 17, the annular support ring further including a plurality of raised bosses aligned with the bolt holes for receiving and holding barrel nuts in place so the bolts can be screwed through the bolt holes and into the barrel nuts to securely fasten the acoustic panel to the annular support ring and therefore to the bulkhead.