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An inlet of an aircraft nacelle having an acoustic barrel configured to reduce engine fan flutter by attenuating various frequencies. The acoustic barrel may comprise an acoustic panel of a honeycomb configuration sandwiched between a first back sheet and a face sheet and extending from a forward bu

An inlet of an aircraft nacelle having an acoustic barrel configured to reduce engine fan flutter by attenuating various frequencies. The acoustic barrel may comprise an acoustic panel of a honeycomb configuration sandwiched between a first back sheet and a face sheet and extending from a forward bulkhead to an aft bulkhead of the inlet. The acoustic barrel may further comprise a deep liner section bonded to and sandwiched between the first back sheet and a second back sheet. The deep liner section may have a narrower width than the acoustic panel and may be located proximate the aft bulkhead. The sections of the first back sheet, the face sheet, and a septum of the acoustic panel may be perforated and may contain additional holes formed in portions aligned radially inward of the deep liner section.

대표청구항 ▼

Having thus described an embodiment of the invention, what is claimed as new and desired to be protected by Letters Patent includes the following: 1. An acoustic barrel of an aircraft nacelle, the acoustic barrel comprising: an acoustic panel having a honeycomb configuration with a plurality of hon

Having thus described an embodiment of the invention, what is claimed as new and desired to be protected by Letters Patent includes the following: 1. An acoustic barrel of an aircraft nacelle, the acoustic barrel comprising: an acoustic panel having a honeycomb configuration with a plurality of honeycomb cells, an outer face, and an inner face; a deep liner section having a honeycomb configuration, an outer face, and an inner face, and positioned outward of the acoustic panel and substantially narrower in width than the acoustic panel; a first back sheet substantially covering the outer face of the acoustic panel, positioned between and bonded to both the acoustic panel and the deep liner section, wherein the first back sheet comprises a plurality of holes formed into a portion of the first back sheet radially inward of and adjacent to the deep liner section, wherein the spacing of the holes coordinates with the spacing of the honeycomb cells of the acoustic panel; and a second back sheet bonded to and covering the outer face of the deep liner section. 2. The acoustic barrel of claim 1, wherein at least one of the acoustic panel and the deep liner section form a complete 360-degree ring. 3. The acoustic barrel of claim 1, wherein the acoustic panel is a sandwich honeycomb core comprising the plurality of honeycomb cells and an acoustic septum, wherein the septum is buried within the acoustic panel and traverses at least a portion of the plurality of honeycomb cells, wherein the septum does not traverse the honeycomb cells located within an area radially inward of the deep liner section. 4. The acoustic barrel of claim 1, further comprising a face sheet substantially covering the inner face of the acoustic panel. 5. The acoustic barrel of claim 4, wherein the face sheet is substantially perforated, with perforations located radially inward of the deep liner section being larger in size than perforations formed over the rest of the face sheet. 6. The acoustic barrel of claim 1, wherein the deep liner section is located proximate an aft end of the acoustic barrel. 7. The acoustic barrel of claim 1, wherein the second back sheet is impervious. 8. The acoustic barrel of claim 1, wherein a portion of the first back sheet not located between the deep liner section and the acoustic panel is impervious. 9. The acoustic barrel of claim 1, wherein the acoustic panel and the deep liner section each comprise a plurality of honeycomb cells, each having a diameter of between approximately 0.1 inches and 1 inch. 10. The acoustic barrel of claim 1, wherein the acoustic panel and the deep liner section each comprise a plurality of honeycomb cells, each having a diameter of between approximately 0.2 inches and 0.5 inches. 11. The acoustic barrel of claim 1, wherein the depth of the deep liner section from an inner face of the deep liner section proximate the acoustic panel to an outer face of the deep liner section is between approximately 0.5 inches and 10 inches. 12. The acoustic barrel of claim 1, wherein the depth of the deep liner section from an inner face of the deep liner section proximate the acoustic panel to an outer face of the deep liner section is between approximately 1 inch and 4 inches. 13. The acoustic barrel of claim 1, wherein the width of the deep liner section from a first surface of the deep liner section facing a forward end of the acoustic barrel to a second surface of the deep liner section facing an aft end of the acoustic barrel is between approximately 0.5 inches and 6 inches. 14. The acoustic barrel of claim 1, wherein the width of the deep liner section from a first surface of the deep liner section facing a forward end of the acoustic barrel to a second surface of the deep liner section facing an aft end of the acoustic barrel is between approximately 1 inch and 3 inches. 15. An inlet of an aircraft nacelle, the inlet comprising: a forward bulkhead; an aft bulkhead; and an acoustic barrel, comprising: an acoustic panel having a honeycomb configuration with a plurality of honeycomb cells, an inner face, and an outer face, and extending from the forward bulkhead to the aft bulkhead of the inlet, a deep liner section positioned outward of the acoustic panel and substantially narrower in width than the acoustic panel, the deep liner section having a honeycomb configuration, an inner face, and an outer face, a first back sheet substantially covering the outer face of the acoustic panel, positioned between and bonded to both the acoustic panel and the deep liner section, wherein the first back sheet comprises a plurality of holes or perforations formed into a portion of the first back sheet radially inward of and adjacent to the deep liner section, wherein the holes or perforations are slightly smaller in diameter than the honeycomb cells of the acoustic panel and are spaced to coordinate with a spacing of the honeycomb cells of the acoustic panel, and a second back sheet bonded to and covering the outer face of the deep liner section. 16. The inlet of claim 15, wherein at least one of the inlet, the acoustic panel, and the deep liner section form a complete 360-degree ring. 17. The inlet of claim 15, wherein the acoustic panel is a sandwich honeycomb core comprising the plurality of honeycomb cells and an acoustic septum, wherein the septum is buried within the acoustic panel and traverses the plurality of honeycomb cells, wherein the septum does not traverse the honeycomb cells located within an area radially inward of the deep liner section. 18. The inlet of claim 15, further comprising a face sheet substantially covering at least one surface of the acoustic panel, opposite of the surface covered by the first back sheet, wherein the face sheet is substantially perforated, with perforations or holes located radially inward of the deep liner section being larger than perforations or holes positioned at other locations in the face sheet. 19. The inlet of claim 18, wherein: the deep liner section is located closer to the aft bulkhead than to the forward bulkhead; the second back sheet is impervious; and a portion of the first back sheet not located between the deep liner section and the acoustic panel is impervious. 20. The inlet of claim 15, wherein the acoustic panel and the deep liner section each comprise a plurality of honeycomb cells, each having a diameter of between approximately 0.1 inches and 1 inch. 21. The inlet of claim 15, wherein the depth of the deep liner section from an inner face of the deep liner section proximate the acoustic panel to an outer face of the deep liner section is between approximately 0.5 inches and 10 inches. 22. The inlet of claim 15, wherein the width of the deep liner section from a first surface of the deep liner section facing the forward bulkhead to a second surface of the deep liner section facing the aft bulkhead is between approximately 0.5 inches and 6 inches. 23. A method of attenuating frequencies in a nacelle, the method comprising: bonding a first back sheet to an outer face of an acoustic panel comprised of a plurality of honeycomb cells; bonding a deep liner section comprised of a plurality of honeycomb cells to the first back sheet, wherein the acoustic panel is wider than the deep liner section; forming holes in the first back sheet throughout a portion of the first back sheet that is disposed between the deep liner section and the acoustic panel; forming holes into a portion of a face sheet radially inward of the deep liner section, wherein the face sheet is bonded to an inner face of the acoustic panel; and attaching the acoustic panel to the nacelle. 24. The method of claim 23, wherein the acoustic panel is a sandwich honeycomb core having a perforated septum traversing a plurality of honeycomb cells, wherein the septum is configured to not traverse the honeycomb cells of the acoustic panel that are radially inward of the deep liner section.