Sound propagation in a lined nozzle with shear and bias flows

Author:

Campos LMBC1,Legendre C2

Affiliation:

1. Center for Aeronautical and Space Science and Technology (CCTAE), Instituto Superior Técnico (IST), Technical University of Lisbon, Lisboa Codex, Portugal

2. Free Field Technologies S.A, Mont-Saint-Guibert, Belgium

Abstract

In this study, the propagation of waves in a two-dimensional parallel-sided nozzle is considered allowing for the combination of: (a) distinct impedances of the upper and lower walls; (b) upper and lower boundary layers with different thicknesses with linear shear velocity profiles matched to a uniform core flow; and (c) a uniform cross-flow as a bias flow out of one and into the other porous acoustic liner. The model involves an “acoustic triple deck” consisting of third-order non-sinusoidal non-plane acoustic-shear waves in the upper and lower boundary layers coupled to convected plane sinusoidal acoustic waves in the uniform core flow. The acoustic modes are determined from a dispersion relation corresponding to the vanishing of an 8 × 8 matrix determinant, and the waveforms are combinations of two acoustic and two sets of three acoustic-shear waves. The eigenvalues are calculated and the waveforms are plotted for a wide range of values of the four parameters of the problem, namely: (i/ii) the core and bias flow Mach numbers; (iii) the impedances at the two walls; and (iv) the thicknesses of the two boundary layers relative to each other and the core flow. It is shown that all three main physical phenomena considered in this model can have a significant effect on the wave field: (c) a bias or cross-flow even with small Mach number [Formula: see text] relative to the mean flow Mach number [Formula: see text] can modify the waveforms; (b) the possibly dissimilar impedances of the lined walls can absorb (or amplify) waves more or less depending on the reactance and inductance; (a) the exchange of the wave energy with the shear flow is also important, since for the same stream velocity, a thin boundary layer has higher vorticity, and lower vorticity corresponds to a thicker boundary layer. The combination of all these three effects (a–c) leads to a large set of different waveforms in the duct that are plotted for a wide range of the parameters (i–iv) of the problem.

Publisher

SAGE Publications

Subject

Acoustics and Ultrasonics,Aerospace Engineering

Reference43 articles.

1. On the fundamental acoustic mode in variable area, low Mach number nozzles

2. Goldstein ME. Aeroacoustics. New York: McGraw-Hill International Book Co., p.305, 1976.

3. On waves in gases. Part I: Acoustics of jets, turbulence, and ducts

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