Claims
- 1. An extended reaction acoustic liner for use in jet engine noise mitigation, the liner comprising:
- a) a substantially non-porous outer layer; and
- b) a plurality of alternating layers of honeycomb core and porous inner layers disposed in laminar juxtaposition to the outer layer, each layer of honeycomb core comprising a plurality of cells, each of the cell walls having a plurality of microporous openings sized and configured to channel laminar airflow therethrough, the mircroporous openings each having a frictional inner surface, some of the cells being in fluid communication with one another via the openings formed in the cell walls thereof;
- c) wherein the opening in the cell walls cause viscous acoustic losses, resulting in acoustic energy dissipation and enhanced noise attenuation.
- 2. The extended reaction acoustic liner as recited in claim 1, wherein substantially all of the cells are in fluid communication with one another.
- 3. The extended reaction acoustic liner as recited in claim 1, wherein the size and number of openings in the cell walls are configured to provide a desired acoustic resistance.
- 4. The extended reaction acoustic liner as recited in claim 1, wherein the honeycomb core is comprised of metal.
- 5. The extended reaction acoustic liner as recited in claim 1, wherein the honeycomb core is comprised of a composite material.
- 6. The extended reaction acoustic liner as recited in claim 1, wherein each porous inner layer comprises a linear inner layer.
- 7. The extended reaction acoustic liner as recited in claim 1, wherein each porous inner layer comprises a non-linear inner layer.
- 8. The extended reaction acoustic liner as recited in claim 1, wherein each of the layers of honeycomb core comprise openings formed in the cell walls thereof.
Parent Case Info
This patent application is a divisional patent application of U.S. Ser. No. 08/982,710, filed Dec. 2, 1997, now U.S. Pat. No. 5,923,003, entitled EXTENDED REACTION ACOUSTIC LINER FOR JET ENGINES AND THE LIKE, the contents of which are hereby incorporated by reference, which is a continuation in part patent application of U.S. Ser. No. 08/709,893 filed Sep. 9, 1996, now U.S. Pat. No. 5,721,402, and entitled NOISE SUPPRESSION SYSTEM FOR A JET ENGINE, the contents of which are hereby incorporated by reference.
US Referenced Citations (41)
Divisions (1)
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982710 |
Dec 1997 |
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Continuation in Parts (1)
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709893 |
Sep 1996 |
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