TY - GEN
T1 - Calculation model for sound propagation in duct with circumferentially non-uniform liner
AU - Wang, Xuli
AU - Wang, Xiaoyu
AU - Huang, Lixi
AU - Sun, Xiaofeng
N1 - Publisher Copyright:
© 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2017
Y1 - 2017
N2 - Ill this paper, an efficient method is described for modeling the wave propagation in a circumferentiaUy non-uniform lined annular duct with mean flow. The cross-section space is discretized by Chebyshev spectral method, through which the equation matrix for physical field and the influence matrix of boundary condition are established. Then the issue is converted to an eigenvalue problem in terms of the acoustic propagation, where the eigenvalues stand for axial wave numbers, the eigenvectors display wave mode profiles. The sound pressure and axial velocity continuity equation is applied at the interface between different segments of the duct, through which the sound field in duct is constructed. It is shown that by using present method, which requires quite less quantity of CPU time compared with 3D numerical method, the superiority in broadband noise reduction of circumferential non-uniform liners is revealed. When sound propagates through the duct lined by circumferential non- uniform liner, the energy is scattered into modes of different orders. What is more, this method is expected to serve as an efficient approach for the optimization of non-uniform liner in the future.
AB - Ill this paper, an efficient method is described for modeling the wave propagation in a circumferentiaUy non-uniform lined annular duct with mean flow. The cross-section space is discretized by Chebyshev spectral method, through which the equation matrix for physical field and the influence matrix of boundary condition are established. Then the issue is converted to an eigenvalue problem in terms of the acoustic propagation, where the eigenvalues stand for axial wave numbers, the eigenvectors display wave mode profiles. The sound pressure and axial velocity continuity equation is applied at the interface between different segments of the duct, through which the sound field in duct is constructed. It is shown that by using present method, which requires quite less quantity of CPU time compared with 3D numerical method, the superiority in broadband noise reduction of circumferential non-uniform liners is revealed. When sound propagates through the duct lined by circumferential non- uniform liner, the energy is scattered into modes of different orders. What is more, this method is expected to serve as an efficient approach for the optimization of non-uniform liner in the future.
UR - https://www.scopus.com/pages/publications/85088072157
U2 - 10.2514/6.2017-3374
DO - 10.2514/6.2017-3374
M3 - 会议稿件
AN - SCOPUS:85088072157
SN - 9781624105043
T3 - 23rd AIAA/CEAS Aeroacoustics Conference, 2017
BT - 23rd AIAA/CEAS Aeroacoustics Conference, 2017
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 23rd AIAA/CEAS Aeroacoustics Conference, 2017
Y2 - 5 June 2017 through 9 June 2017
ER -