Abstract
An explicit, analytical, multiple-scales solution for modal sound transmission through slowly varying ducts with mean flow and acoustic lining, is tested against a numerically "exact" finite element solution. The test geometry taken is representative of a high-bypass turbo fan aircraft engine, with typical Mach numbers of 0.5-0.7, circumferential mode numbers m of 10-40, dimensionless-wave numbers of 10-50, and both hard and acoustically treated inlet walls of impedance Z = 2 - i. Of special interest is the presence of the spinner, which incorporates a geometrical complexity which could previously only be handled by fully numerical solutions. The results in predicted power attenuation loss show in general a very good agreement. The results in iso-pressure contour plots show good comparison in the cases where scattering into many higher radial modes can occur easily (high frequency, low angular mode), and again a very good agreement in the other cases.
| Original language | English |
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| Pages | 140-150 |
| Number of pages | 11 |
| Publication status | Published - 1999 |
| Event | Aeroacoustics Conference and Exhibit, AIAA/CEAS 1999 - Bellevue, United States Duration: 10 May 1999 → 12 May 1999 |
Conference
| Conference | Aeroacoustics Conference and Exhibit, AIAA/CEAS 1999 |
|---|---|
| Country/Territory | United States |
| City | Bellevue |
| Period | 10/05/99 → 12/05/99 |
Funding
Acknowledgement contribution of Professor Eversman was supported by NASA Lewis Research under Grant NAG 3-2109.