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Acoustic scattering by cascades with complex boundary conditions: compliance, porosity and impedance

Published online by Cambridge University Press:  03 July 2020

Peter J. Baddoo*
Affiliation:
Department of Applied Mathematics and Theoretical Physics, Centre for Mathematical Sciences, University of Cambridge, UK
Lorna J. Ayton
Affiliation:
Department of Applied Mathematics and Theoretical Physics, Centre for Mathematical Sciences, University of Cambridge, UK
*
Present address: Department of Mathematics, Huxley Building, South Kensington Campus, Imperial College London, London SW7 2AZ, UK. Email address for correspondence: p.baddoo@imperial.ac.uk

Abstract

We present a solution for the scattered field caused by an incident wave interacting with an infinite cascade of blades with complex boundary conditions. This extends previous studies by allowing the blades to be compliant, porous or satisfy a generalised impedance condition. Beginning with the convected wave equation, we employ Fourier transforms to obtain an integral equation amenable to the Wiener–Hopf method. This Wiener–Hopf system is solved using a method that avoids the factorisation of matrix functions. The Fourier transform is inverted to obtain an expression for the acoustic potential function that is valid throughout the entire domain. We observe that the principal effect of complex boundary conditions is to perturb the zeros of the Wiener–Hopf kernel, which correspond to the duct modes in the inter-blade region. We focus efforts on understanding the role of porosity, and present a range of results on sound transmission and generation. The behaviour of the duct modes is discussed in detail in order to explain the physical mechanisms behind the associated noise reductions. In particular, we show that cut-on duct modes do not exist for arbitrary porosity coefficients. Conversely, the acoustic far-field modes are unchanged by modifications to the boundary conditions. We apply our solution to a cascade of perforated plates and see that a fractional open area of 1 % is sufficient to significantly attenuate backscattering. The solution is essentially analytic (the only numerical requirements are matrix inversion and root finding) and is therefore extremely rapid to compute.

Information

Type
JFM Papers
Creative Commons
Creative Common License - CCCreative Common License - BY
This is an Open Access article, distributed under the terms of the Creative Commons Attribution licence (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted re-use, distribution, and reproduction in any medium, provided the original work is properly cited.
Copyright
© The Author(s), 2020. Published by Cambridge University Press
Figure 0

Figure 1. An infinite, rectilinear cascade of flat plates with complex boundary conditions subjected to an unsteady perturbation. The plates have dimensional length $2b^{\ast }$ and are inclined at a stagger angle of $\unicode[STIX]{x1D712}^{\ast }$. The plates produce an unsteady wake in the case where there is a non-zero chordwise background flow $U_{0}^{\ast }$.

Figure 1

Figure 2. A three-dimensional view of the cascade in the rotated, dimensional $(x^{\ast },y^{\ast },z^{\ast })$ coordinate system. The background velocities may have a spanwise component $W_{0}^{\ast }$. The complex boundaries are illustrated by the holes on each blade, which may represent compliance, porosity or impedance.

Figure 2

Table 1. Summary of possible boundary conditions and corresponding $\unicode[STIX]{x1D707}_{0}$, $\unicode[STIX]{x1D707}_{1}$ and $\unicode[STIX]{x1D707}_{2}$ values for (2.17). The references highlight relevant papers, although only [1,2] consider cascade geometries and are restricted to impermeable and rigid boundaries. The reference numbers correspond to [1] (Glegg 1999), [2] (Posson et al.2010), [3] (Leppington 1977), [4] (Howe 1998), [5] (Jaworski & Peake 2013), [6] (Kisil & Ayton 2018), [7] (Howe et al.1996), [8] (Myers 1980) and [9] (Brambley 2009).

Figure 3

Figure 3. Schematic illustrating where each boundary condition is applied.

Figure 4

Figure 4. Schematic diagram illustrating the solution method. The abbreviations ‘FT’ and ‘IFT’ stand for ‘Fourier transform’ and ‘Inverse Fourier transform’ respectively.

Figure 5

Figure 5. Diagram indicating the different regions in the $(x,y)$-plane which require different areas of contour integration in the Fourier inversion.

Figure 6

Figure 6. Comparisons of surface pressure jump for flat plates for case 0 boundary conditions and geometries defined in table 2. The real and imaginary parts (blue and red respectively) of the pressure jump are compared to three alternative solutions: a Wiener–Hopf method (Posson et al.2010), a mode-matching technique (Bouley et al.2017) and a numerical method (Hall 1997).

Figure 7

Figure 7. The trajectories of the duct modes for a range of (complex) porosity coefficients for case C described in table 2, with $k_{x}=4$. Along each line, the phase of $C_{II}$ is held constant while its magnitude is increased from $0$ to $\infty$. For example, the duct modes corresponding to real and positive values of $C_{II}$ are illustrated in red. The duct modes for case 0 blades (i.e. $C_{II}=0$) are denoted by ●, the acoustic modes, $\unicode[STIX]{x1D706}_{m}$, are labelled denoted by ▪ and the convected mode ($-\unicode[STIX]{x1D714}/\unicode[STIX]{x1D6FD}^{2}$) is denoted by ▴. Accordingly, each trajectory begins at a ● and ends at either a ▪ or a ▴. The upper half-plane ${\mathcal{L}}^{+}$ is shaded in red and the lower half-plane ${\mathcal{L}}^{-}$ is shaded in blue.

Figure 8

Figure 8. The imaginary parts of the duct modes as a function of (real) porosity coefficient $C_{II}$. The asymptotic approximations for small porosity coefficients (4.3) as illustrated by the dashed blue lines and the asymptotic approximations for large porosity coefficients ((4.4a), (4.4b)) are denoted by the dashed red lines. The cascade parameters are defined in case C in table 2 with $\unicode[STIX]{x1D714}=5$ and $k_{x}=4$.

Figure 9

Figure 9. The trajectories of a pair of duct modes as the frequency is increased for a range of porosity constants. The duct modes for $\unicode[STIX]{x1D714}=0$ are denoted by ●. The complex trajectories are plotted in (a), and the imaginary part of the modes in the upper and lower half planes are plotted in (b,c) respectively. The colours correspond to different porosity parameters with black representing rigid and impermeable blades. The upper half-plane ${\mathcal{L}}^{+}$ is shaded in red and the lower half-plane ${\mathcal{L}}^{-}$ is shaded in blue. The relevant parameters correspond to case D in table 2 with $k_{x}=2$.

Figure 10

Table 2. Summary of parameters used in results section. All other parameters are taken to be zero, unless otherwise stated.

Figure 11

Figure 10. Unsteady lift for a range of frequencies and porosities. The aerodynamic and aeroacoustic parameters are defined in table 2 and correspond to those in figure 3 of Glegg (1999). The colours correspond to different porosity parameters with black representing rigid and impermeable blades.

Figure 12

Figure 11. Modal downstream sound power output for a cascade of porous blades at a range of frequencies for (a) the first mode ($m=0$) and (b) the second mode ($m=1$). The aerodynamic and aeroacoustic parameters are defined in table 2 and correspond to those in figure 9 of Glegg (1999). The colours correspond to different porosity parameters with black representing rigid and impermeable blades.

Figure 13

Figure 12. Modal downstream sound power levels for a cascade of porous blades at a range of frequencies for (a) the first mode ($m=0$) and (b) the second mode ($m=1$). The aerodynamic and aeroacoustic parameters are defined in table 2 and correspond to those in figure 9 of Glegg (1999). The colours correspond to different porosity parameters.

Figure 14

Figure 13. (ai–ci) The total (incident and scattered), normalised pressure field. (aii–cii) The amplitudes of the normalised reflection (blue) and transmission (orange) coefficients. The open area fraction values are $\unicode[STIX]{x1D6FC}_{H}=0,0.01$ and $0.05$ respectively. The darker bars indicate modes that are cut-on whereas the lighter bars are cut-off. The parameters in this case are defined in case E of table 2. The arrow indicates the direction of the incident wave.

Figure 15

Figure 14. Illustration of the locations of poles in the complex $\unicode[STIX]{x1D6FE}$-plane, and the relevant contours of integration.