A numerical comparison between multiple-scales and FEM solution for sound propagation in lined flow ducts

Sjoerd W. Rienstra; Walter Eversman

doi:10.2514/6.1999-1821

A numerical comparison between multiple-scales and FEM solution for sound propagation in lined flow ducts

Sjoerd W. Rienstra, Walter Eversman

Center for Analysis, Scientific Computing and Applications

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › Academic › peer-review

3 Citations (Scopus)

1 Downloads (Pure)

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
Title of host publication	5th AIAA/CEAS Aeroacoustics Conference and Exhibit
Publisher	American Institute of Aeronautics and Astronautics Inc. (AIAA)
Pages	140-150
Number of pages	11
DOIs	https://doi.org/10.2514/6.1999-1821
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.

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10.2514/6.1999-1821

pdfFinal author version , 1.4 MB

Cite this

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title = "A numerical comparison between multiple-scales and FEM solution for sound propagation in lined flow ducts",

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.",

author = "Rienstra, \{Sjoerd W.\} and Walter Eversman",

year = "1999",

doi = "10.2514/6.1999-1821",

language = "English",

pages = "140--150",

booktitle = "5th AIAA/CEAS Aeroacoustics Conference and Exhibit",

publisher = "American Institute of Aeronautics and Astronautics Inc. (AIAA)",

address = "United States",

note = "Aeroacoustics Conference and Exhibit, AIAA/CEAS 1999 ; Conference date: 10-05-1999 Through 12-05-1999",

}

Rienstra, SW & Eversman, W 1999, A numerical comparison between multiple-scales and FEM solution for sound propagation in lined flow ducts. in 5th AIAA/CEAS Aeroacoustics Conference and Exhibit., AIAA 99-1821 / A99-27815, American Institute of Aeronautics and Astronautics Inc. (AIAA), pp. 140-150, Aeroacoustics Conference and Exhibit, AIAA/CEAS 1999, Bellevue, United States, 10/05/99. https://doi.org/10.2514/6.1999-1821

A numerical comparison between multiple-scales and FEM solution for sound propagation in lined flow ducts. / Rienstra, Sjoerd W.; Eversman, Walter.
5th AIAA/CEAS Aeroacoustics Conference and Exhibit. American Institute of Aeronautics and Astronautics Inc. (AIAA), 1999. p. 140-150 AIAA 99-1821 / A99-27815.

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › Academic › peer-review

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AU - Eversman, Walter

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N2 - 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.

AB - 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.

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BT - 5th AIAA/CEAS Aeroacoustics Conference and Exhibit

PB - American Institute of Aeronautics and Astronautics Inc. (AIAA)

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Y2 - 10 May 1999 through 12 May 1999

ER -

A numerical comparison between multiple-scales and FEM solution for sound propagation in lined flow ducts

Abstract

Conference

Funding

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