Advanced turbofan duct liner concepts [microform] / Gerald W. Bielak and John W. Premo, Alan S. Hersh.
"The Advanced Subsonic Technology Noise Reduction Program goal is to reduce aircraft noise by 10 EPNdB by the year 2000 relative, to 1992 technology. The improvement goal for nacelle attenuation is 25% relative to 1992 technology by 1997 and 50% by 2000. The Advanced Turbofan Duct Liner Concept...
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| Online Access: |
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| Main Author: | |
| Corporate Authors: | , |
| Other Authors: | , |
| Format: | Government Document Microfilm Book |
| Language: | English |
| Published: |
Hampton, Va. : [Springfield, Va.] :
National Aeronautics and Space Administration, Langley Research Center ; [National Technical Information Service, distributor],
[1999]
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| Series: | NASA contractor report ;
NASA CR-209002. |
| Subjects: |
| Summary: | "The Advanced Subsonic Technology Noise Reduction Program goal is to reduce aircraft noise by 10 EPNdB by the year 2000 relative, to 1992 technology. The improvement goal for nacelle attenuation is 25% relative to 1992 technology by 1997 and 50% by 2000. The Advanced Turbofan Duct Liner Concepts Task work by Boeing presented in this document was in support of these goals. The basis for the technical approach was a Boeing study conducted in 1993-94 under NASA/FAA contract NAS1-19349, Task 6, investigating broadband acoustic liner concepts. As a result of this work, it was recommended that linear double layer, linear and perforate triple layer, parallel element, and bulk absorber liners be further investigated to improve nacelle attenuations. NASA LaRC also suggested that 'adaptive' liner concepts that would allow 'in-situ' acoustic impedance control also be considered. As a result, bias flow and high-temperature liner concepts were also added to the investigation. The major conclusion from the above studies is that improvements in nacelle liner average acoustic impedance characteristics alone will not result in 25% increased nacelle noise reduction relative to 1992 technology. Nacelle design advancements currently being developed by Boeing are expected to add 20-40% more acoustic lining to hardwall regions in current inlets, which is predicted to result in and additional 40-80% attenuation improvement. Similar advancements are expected to allow 10-30% more acoustic lining in current fan ducts with 10-30% more attenuation expected. In addition, Boeing is currently developing a scarf inlet concept which is expected to give an additional 40-80% attenuation improvement for equivalent lining areas.''--NASA Technical Reports Server web site. |
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| Physical Description: | 1 volume. Available in microfiches and via the Internet. |
| Additional Physical Form available Note: | Available in microfiches and via the Internet. |