Effects of airflow on the acoustic attenuation performance of reactive muffler
Zhigang Chu^{1} , Fang Kuang^{2} , Runcheng Kang^{3} , Xiaoxin Gao^{4}
^{1, 4}The State Key Laboratory of Mechanical Transmission, College of Automotive Engineering, Chongqing University, Chongqing 400044, China
^{2}College of Mechanical Engineering, Chongqing University, Chongqing 400044, China
^{2, 3}National Automobile Quality Supervision Test Center, Xiangyang 441004, China
^{1}Corresponding author
Journal of Vibroengineering, Vol. 18, Issue 1, 2016, p. 637648.
Received 6 September 2015; received in revised form 17 December 2015; accepted 8 January 2016; published 15 February 2016
JVE Conferences
In order to study the effect of airflow on the acoustic attenuation performance of reactive muffler, firstly, the formulas of wavenumber, transfer matrix method and three point method were deduced in the case of uniform flow. Then, the differences between transfer matrix method and three point method were compared based on the results of finite element method (FEM), for the noflow, uniform flow and nonuniform flow three different cases. The results showed that both the transfer matrix method and three point method can accurately calculate the transmission loss (TL) of muffler under noflow and uniform flow conditions. But, for the nonuniform flow case, both the results calculated by the two methods above have deviations on account of the complexity of flow field and the limitations of calculation methods. In addition, negative values even appear in the low frequency range. Finally, comparative study about the effect of uniform flow and nonuniform flow on the acoustic attenuation performance of muffler was made. Results showed that the difference of the effect of uniform flow and nonuniform flow on the acoustic attenuation performances is little when the airflow regenerated noise is ignored and the existence of airflow has little effect on the acoustic attenuation performance of reactive muffler. Therefore, the effect of airflow on the acoustic attenuation performance can be neglected during the initial phase of muffler design.
Keywords: muffler, airflow velocity, TL, transfer matrix method, three point method.
1. Introduction
Mufflers are widely used in mechanical systems and obviously affect the comprehensive property of mechanical systems [14]. Its acoustic attenuation performance has been researched by many scholars. Early studies are mostly based on the assumption that the medium inside the muffler is static ideal gas [59]. But, this assumption is not consistent with the actual situation. In fact, mufflers are often used to attenuate the noise from fluid machines, the existence of high velocity airflow may affect the propagation and attenuation of sound wave. Therefore, some scholars discussed the acoustic attenuation performance of muffler under the nonstatic gas condition. The flow field was assumed to be uniform, that is, the fluid motion of every part has same effect on the propagation and attenuation of sound wave, and the wave equation was deduced in this case. Then, the effect of uniform flow on the acoustic attenuation performance of muffler was explored by experiment, theoretical analysis and numerical simulation [1017]. Though the assumption above simplified the flow field inside the muffler and the research, the effect of practical flow field on the propagation and attenuation of sound wave has not been truly reflected. Actually, flow field inside the muffler is very complex and the effects of airflow at all places are not consistent. Thus, the prediction method of acoustic attenuation performance for the muffler with nonuniform flow was discussed. Consequently, the results become closer to the truth [1821].
The above researches have obtained a lot of achievements and provided references for the muffler design. Whereas, in the case of uniform flow, negative values appear on the TL curves in Refs. [1618] on the condition that the airflow regenerated noise is not considered, which is not consistent with the truth. Furthermore, most of the references adopt transfer matrix method to calculate the TL values of muffler with flow, but two different boundary conditions must be set and need doublecalculation, which is complex and timeconsuming. What is more, the assumptions of uniform flow and nonuniform flow both have their advantages and disadvantages, but not much attention has been given to the differences between the two.
The present work aims at discussing the problems above. The remainder of this paper develops as follows: first, in Section 2, the calculation formulas of wavenumber, transfer matrix method and three point method were deduced under uniform flow condition. Thereafter, in Section 3, the differences between transfer matrix method and three point method were compared. Next, in Section 4, the effects of uniform flow and nonuniform flow on the acoustic attenuation performance of reactive muffler were studied by FEM. Finally, Section 5 concludes the paper.
2. Theory
2.1. Wavenumber under uniform flow condition
Along the x direction, the wave equation, which contains velocity gradient and temperature gradient, can be written as [22]:
$\mathrm{}\mathrm{}\mathrm{}\mathrm{}\mathrm{}\mathrm{}\frac{1}{{\rho}_{0}}\left(\frac{\partial {\rho}_{0}}{\partial y}\frac{\partial p}{\partial y}+\frac{\partial {\rho}_{0}}{\partial z}\frac{\partial p}{\partial z}\right)=0,$
where $u$, $v$, $w$ are the components of fluctuation velocity, $U$ is the velocity of uniform flow, ${c}_{0}$ and ${\rho}_{0}$ are the sound velocity and air density, respectively. $p$ is the sound pressure, $t$ is the time, $x$, $y$, $z$ are the three directions of coordinate axis, respectively.
When the flow field is uniform and isothermal, $\partial u/\partial y=\partial u/\partial z=\partial {\rho}_{0}/\partial y=\partial {\rho}_{0}/\partial z=0$, and the wave equation can be rewritten as:
The expression of sound pressure along the $x$ positive direction is:
where ${k}_{x}$, ${k}_{y}$, ${k}_{z}$ are the wavenumbers along $x$, $y$, $z$ directions, respectively; ${A}_{2}$, ${B}_{2}$ are the incident wave and reflected wave along the $y$ direction, respectively; ${A}_{3}$, ${B}_{3}$ are the incident wave and reflected wave along the $z$ direction, respectively.
Submitting Eq. (3) into Eq. (2) yields:
where, ${k}_{0}=\omega /{c}_{0}$ is the wavenumber in the case of noflow, $\omega $ is the angular frequency, $M=U/{c}_{0}$ is the Mach number, ${k}^{\mathrm{\text{'}}}$ is the wavenumber of the uniform flow. When the sound waves propagate along $x$ direction in the form of plane wave, ${k}_{y}=0$, ${k}_{z}=0$, ${k}_{x}={k}^{\mathrm{\text{'}}}$ Then, the axial wavenumbers ${k}_{x+}$ and ${k}_{x}$ can be written as: ${k}_{x+}=k/(1+M)$, ${k}_{x}=k/\left(1M\right)$, “–” represents direction.
2.2. Transfer matrix method
Fig. 1(a) shows the sketch map of TL measurement. In the case of uniform flow, the sound pressures of the four measuring points can be expressed as:
${p}_{3}={P}_{C}{e}^{j\frac{{k}_{0}}{1+M}{l}_{3}}+{P}_{D}{e}^{j\frac{{k}_{0}}{1M}{l}_{3}},{p}_{4}={P}_{C}{e}^{j\frac{{k}_{0}}{1+M}{l}_{4}}+{P}_{D}{e}^{j\frac{{k}_{0}}{1M}{l}_{4}},$
where, ${p}_{1}$, ${p}_{2}$ are the complex sound pressures of point 1 and point 2, respectively. ${p}_{3}$, ${p}_{4}$ are the complex sound pressures of point 3 and point 4, respectively. ${P}_{A}$, ${P}_{B}$ are the incident sound pressure and reflected sound pressure of crosssection ${i}_{1}$${i}_{2}$, respectively; ${P}_{C}$, ${P}_{D}$ are the incident sound pressure and reflected sound pressure of crosssection ${o}_{1}$${o}_{2}$, respectively; ${l}_{1}$, ${l}_{2}$ are the distances between point 1, point 2 and the crosssection ${i}_{1}$${i}_{2}$, respectively; ${l}_{3}$, ${l}_{4}$ are the distances between point 3, point 4 and the crosssection ${o}_{1}$${o}_{2}$, respectively.
By solving the Eq. (5), ${P}_{A}$, ${P}_{B}$, ${P}_{C}$ and ${P}_{D}$ can be written as:
${P}_{C}=\frac{\left({p}_{3}{p}_{4}{e}^{j\frac{{k}_{0}}{1M}{l}_{34}}\right){e}^{j\frac{{k}_{0}}{1M}{l}_{4}}}{{e}^{j\frac{{k}_{0}M}{1{M}^{2}}({l}_{34}+2{l}_{4})}\cdot 2j\mathrm{s}\mathrm{i}\mathrm{n}\left(\frac{{k}_{0}{l}_{34}}{1{M}^{2}}\right)},{P}_{D}=\frac{\left({p}_{4}{e}^{j\frac{{k}_{0}}{1+M}{l}_{34}}{p}_{3}\right){e}^{j\frac{{k}_{0}}{1+M}{l}_{4}}}{{e}^{j\frac{{k}_{0}M}{1{M}^{2}}({l}_{34}+2{l}_{4})}\cdot 2j\mathrm{s}\mathrm{i}\mathrm{n}\left(\frac{{k}_{0}{l}_{34}}{1{M}^{2}}\right)},$
where ${l}_{12}$ is the distance between measuring point 1 and measuring point 2; ${l}_{34}$ is the distance between measuring point 3 and measuring point 4.
The transfer matrix of muffler can be expressed as:
where ${P}_{i}$, ${V}_{i}$ are the sound pressure and particle velocity of crosssection ${i}_{1}$${i}_{2}$, respectively; ${P}_{o}$, ${V}_{o}$ are the sound pressure and particle velocity of crosssection ${o}_{1}$${o}_{2}$, respectively. $A$, $B$, $C$ and $D$ represent the fourpole parameters.
Assuming the sound waves in inlet and outlet pipes propagate in the form of plane wave, the sound pressures and particle velocities of crosssections ${i}_{1}$${i}_{2}$ and ${o}_{1}$${o}_{2}$ are given by:
In order to obtain the fourpole parameters, two boundary conditions must be set.
Boundary condition 1:
Boundary condition 2:
The fourpole parameters derived from Eqs. (9)(10) can be written as:
$C=\frac{{V}_{1i}{V}_{2o}{V}_{2i}{V}_{1o}}{{P}_{1o}{V}_{2o}{P}_{2o}{V}_{1o}},D=\frac{{V}_{1i}{P}_{2o}{V}_{2i}{P}_{1o}}{{V}_{1o}{P}_{2o}{V}_{2o}{P}_{1o}}.$
Fig. 1. Geometry of mufflers
a) Sketch map of transmission loss measurement
b) Coaxial expansion muffler
c) Noncoaxial expansion muffler
d) Reversing chamber muffler
Submitting Eq. (8) into Eq. (11) yields:
$B=\frac{\left({P}_{1A}+{P}_{1B}\right)\left({P}_{2C}+{P}_{2D}\right)\left({P}_{2A}+{P}_{2B}\right)\left({P}_{1C}+{P}_{1D}\right)}{\left({P}_{1C}{P}_{1D}\right)\left({P}_{2C}+{P}_{2D}\right)\left({P}_{2C}{P}_{2D}\right)\left({P}_{1C}+{P}_{1D}\right)}.\rho c,$
$C=\frac{\left({P}_{1A}{P}_{1B}\right)\left({P}_{2C}{P}_{2D}\right)\left({P}_{2A}{P}_{2B}\right)\left({P}_{1C}{P}_{1D}\right)}{\left({P}_{1C}+{P}_{1D}\right)\left({P}_{2C}{P}_{2D}\right)\left({P}_{2C}+{P}_{2D}\right)\left({P}_{1C}{P}_{1D}\right)}.\frac{1}{\rho c},$
$D=\frac{\left({P}_{1A}{P}_{1B}\right)\left({P}_{2C}+{P}_{2D}\right)\left({P}_{2A}{P}_{2B}\right)\left({P}_{1C}+{P}_{1D}\right)}{\left({P}_{1C}{P}_{1D}\right)\left({P}_{2C}+{P}_{2D}\right)\left({P}_{2C}{P}_{2D}\right)\left({P}_{1C}+{P}_{1D}\right)},$
where ${P}_{1A}$, ${P}_{1C}$ and ${P}_{1B}$, ${P}_{1D}$ are the incident sound pressures and reflected sound pressures of inlet and outlet pipes under boundary condition 1; ${P}_{2A}$, ${P}_{2C}$ and ${P}_{2B}$, ${P}_{2D}$ are the incident sound pressures and reflected sound pressures of inlet and outlet pipes under boundary condition 2.
The TL calculated by fourpole parameters can be written as:
Submitting Eq. (12) into Eq. (13) gives:
2.3. Three point method
Assuming the sound waves in inlet and outlet pipes propagate in the form of plane wave and the outlet pipe has an anechoic termination, that is the reflected wave ${P}_{D}=$0. Then, the sound wave in the outlet pipe only contains incident wave, that is ${p}_{3}={P}_{C}$; the sound wave in the inlet pipe contains incident wave as well as reflected wave. Hence, the sound pressures at point 1 and point 2 can be written as [23]:
${P}_{A}$ can be obtained by solving Eq. (15):
The TL is defined as the difference between the incoming sound power level and the outgoing sound power level, therefore, the TL calculated by three point method can be expressed as:
where ${A}_{i}$ and ${A}_{o}$ are the crosssectional areas of the inlet and outlet pipes, respectively. If ${A}_{i}={A}_{o}$, the formula of three point method can be rewritten as:
3. Comparison of transfer matrix method and three point method
Under the noflow, uniform flow and nonuniform flow three different conditions, the computational accuracy of transfer matrix method and three point method was compared. In addition, the uniform flow is modeled by applying a zero potential value to the nodes of outlet surface and a constant flow velocity on the inlet surface to provide a fixed flow rate through the model during the acoustic field calculation, so the turbulence was not considered. However, the nonuniform flow is modeled by mapping the flow field data calculated by CFD software Fluent^{®} to the nodes of acoustical mesh. In this case, the $k$$\epsilon $ twoequation turbulence model was chosen, so the turbulence was considered.
Fig. 2(a) and Fig. 2(b) are the FEM models of flow field calculation and acoustic field calculation, respectively. Both the two FEM models adopt hexahedron mesh and the mesh sizes of the two FEM models are 4 mm and 8 mm, respectively. In addition, the material is the air at normal pressure and temperature for all the calculations. For the flow field calculation, the inlet is set as velocity boundary condition, the outlet is set as pressure outlet and the pressure is zero relative to atmospheric pressure, the wall is smooth. For the acoustic field calculation, the inlet is set as unit vibration velocity, the outlet is set as anechoic termination for the three point method and the acoustic impedance of outlet is set as two different values for the transfer matrix method.
In order to calculate the TL, firstly, the sound pressures of measuring points should be obtained by FEM. Then, bringing the sound pressures into the formulas of three point method and transfer matrix method to calculate the TL. And the flowchart of TL calculation is shown in Fig. 3.
Fig. 2. FEM models
a)
b)
Fig. 3. Flowchart of TL calculation
Fig. 4(a) and 4(b) shows the TL curves of coaxial expansion muffler under noflow and uniform flow of $v=$90 m/s conditions, respectively. And the geometry of coaxial expansion muffler is shown in Fig. 1(b). It can be observed that the TL curves overlap completely for the two calculation methods no matter the airflow velocity is zero or uniform flow of 90 m/s, which explains that both the two methods above can accurately calculate the TL values of muffler under noflow and uniform flow conditions. In addition, it should be noted that negative values appear on the TL curves of mufflers with uniform flow in Refs. [1618] on the condition that airflow regenerated noise is ignored, which is not consistent with the theory. However, it can be seen that no negative values appear on the TL curves calculated by the transfer matrix method and three point method in this paper, as shown in Fig. 4(b), which fully shows that the calculation error of TL is eliminated and the computational accuracy of TL is improved in the case of uniform flow assumption.
In Fig. 4(c), the TL curves calculated by transfer matrix method and three point method were compared for the nonuniform flow case. Similar with the above cases, two curves almost coincide exactly, but negative values appear in the frequency region of 050 Hz.
In order to explore the reasons of the phenomenon mentioned above, the TL curves of the coaxial expansion muffler under uniform flow and nonuniform flow conditions were made a further comparison.
As shown in Fig. 5, no matter the results are calculated by transfer matrix method or three point method, differences between the uniform flow results and nonuniform flow results are always existing. Compared with the uniform flow results, nonuniform results significantly decrease at the peaks except the phenomenon mentioned above.
Fig. 4. Comparison of transfer matrix method and three point method
a)$v=$0
b) Uniform flow
c) Nonuniform flow
Fig. 5. Transmission loss comparison
a) Transfer matrix method
b) Three point method
For the above differences, the main reason is the limitation of algorithm, for example, for the transfer matrix method, ${P}_{i}$, ${P}_{o}$ and ${V}_{i}$, ${V}_{o}$ in the Eq. (7) are the average sound pressures and average particle velocities of crosssections ${i}_{1}$${i}_{2}$ and ${o}_{1}$${o}_{2}$, respectively. For the plane wave, the sound pressures and particle velocities of arbitrary two points in a same crosssection are the equal. So, the value of any point in the crosssection can be seen as the average value and selected to calculate the values of ${P}_{A}$, ${P}_{B}$, ${P}_{C}$ and ${P}_{D}$. At last, the results of ${P}_{i}$_{,}${V}_{i}$ and ${P}_{o}$, ${V}_{o}$ equal to the average values of crosssections ${i}_{1}$${i}_{2}$ and ${o}_{1}$${o}_{2}$, respectively. Therefore, the TL values calculated by transfer matrix method are accurate for the plane wave case. In Fig. 6(a), (b), (d), (e), the sound pressure contours at 5 Hz and 4000 Hz are presented for the coaxial expansion muffler under noflow and uniform flow conditions, respectively. It can be observed that the sound waves propagate in the form of plane wave in the inlet and outlet pipes, actually, in the whole analysis frequency region, the sound waves in the inlet and outlet pipes always propagate in the shape of plane wave. Hence, the transfer matrix method in this paper can be used to predict the TL values of muffler under noflow and uniform flow conditions.
Fig. 6. Sound pressure contours
a)
b)
c)
d)
e)
f)
Fig. 7. Velocity contours
However, for the nonuniform flow case, the sound waves in the inlet and outlet pipes are not strict plane wave, as shown in Fig. 6(c) and (f), which can be explained by the velocity contours in Fig. 7. It is observed that the airflow velocities in the inlet and outlet pipes are uniform and equal under uniform flow condition, so the effects of airflow at all places on the sound waves propagation are consistent and the sound waves propagate in the form of plane wave in the inlet and outlet pipes. But, for the nonuniform flow case, because the wall boundary condition was considered in the flow field calculation and the velocity fluctuation caused by the abrupt change of crosssection is large, the airflow velocities in the inlet and outlet pipes are not uniform and equal. Consequently, the sound waves in the inlet and outlet pipes are not strict plane wave.
Furthermore, the $M$ in Eq. (5) is the specific value of $U$ and ${c}_{0}$. As mentioned above, the airflow in the inlet and outlet pipes are not uniform for the nonuniform flow case, that is, the Mach numbers in all parts of the pipes are not entirely equal. Therefore, the TL values calculated by the $M$ which still equals to the specific value of $U$ and ${c}_{0}$ are not accurate.
Because of the existence of above reasons, the TL values calculated by transfer matrix method generate errors for the nonuniform flow case, negative values even appear in the low frequency. Similarly, three point method has the same problems, so they will not be mentioned in this article.
In conclusion, both the transfer matrix method and three point method can accurately calculate the TL of muffler under noflow and uniform flow conditions. Just for the nonuniform flow case, the errors of TL values still exist on account of the complexity of airflow and the limitation of algorithm. Synthetically consider the advantages and disadvantages of the two methods above, three point method was used for the following calculations for purpose of reducing the calculation and saving the computing time.
4. Effects of airflow
In order to study the effects of uniform flow and nonuniform flow on the acoustic attenuation performance of muffler, taking the expansion chamber muffler and reversing chamber muffler two kinds of simple reactive muffler and a complex car muffler as examples, comparative study was made when the airflow regenerated noise is ignored.
4.1. Simple reactive muffler
Fig. 8(a) shows the TL curves of noncoaxial expansion muffler under different airflow velocities conditions, and its geometry is shown in Fig. 1(c). It is observed that the TL curve almost has no change as the increase of airflow velocity for the muffler with uniform flow. While, for the nonuniform flow case, even though the TL curves nearly overlap completely in the frequency range of 01800 Hz and the difference of TL curves is small in the frequency range of 34004000 Hz, the change is still very obvious in the frequency range of 18003400 Hz, especially in the frequency ranges of 26002800 Hz and 30003400 Hz. The main reason is that the inlet and outlet pipes are not coaxial, the highspeed airflow ejected from inlet pipe strikes the opposite wall and forms strong reflow. Then the reflow air mixes with the low speed air in the muffler and forms strong turbulence which leads to large velocity fluctuation [24]. As a result, the propagation of sound wave were affected more largely.
Fig. 8. Transmission loss curves
a) Noncoaxial expansion muffler
b) Reversing chamber muffler
Because the higher order modes were suppressed effectively, the acoustic attenuation performance of muffler (${\beta}_{1}=$0, ${\beta}_{2}=$0.063$D$) had a significant enhancement in the mediumhigh frequency range [25]. Whereas, the effect of airflow has not been considered in Ref. [25]. It can be seen from the above analysis, the existence of airflow did not destroy the good acoustic attenuation performance of this type of muffler on the condition that the airflow regenerated noise is ignored, no matter the airflow is uniform or nonuniform.
In Fig. 8(b), the TL curves of reversing chamber muffler under different airflow velocities conditions are presented, and the geometry of the reversing chamber muffler is shown in Fig. 1(d). Similar with the expansion muffler, the airflow has little effect on the acoustic attenuation performance of reversing chamber muffler and the difference between uniform flow and nonuniform flow is little too.
4.2. Complex car muffler
In order to make the conclusion more universal, further study about the effect of airflow on the acoustic attenuation performance of complex car muffler was made. The geometry of the car muffler is shown in Fig. 9.
Fig. 10 presents the TL curves of the complex car muffler under different airflow velocities conditions. Similar conclusions have also been obtained, the acoustic attenuation performance of the complex car muffler was slightly affected by the airflow. The existence of airflow has not destroyed the good acoustic attenuation performance of the car muffler. Furthermore, it can be observed that the average TL of the car muffler gradually decreases with the increase of airflow velocity, but the reduction is tiny, as indicated in Table 1. When the inlet airflow velocity is 90 m/s, the TL values of the car muffler only reduce 0.56 dB and 2.48 dB for the uniform flow and nonuniform flow cases, respectively. In addition, the change rate of TL decreases as airflow velocity increases.
Fig. 9. Geometry of a complex car muffler
Fig. 10. Transmission loss curves of the complex car muffler
Table 1. Transmission loss variation of a car muffler with different airflow velocities
Flow velocity

Average transmission loss/dB
(uniform flow)

Average transmission loss/dB
(nonuniform flow)

0

38.75

38.75

30 m/s

38.35

37.59

45 m/s

38.36

37.22

60 m/s

38.28

36.93

75 m/s

38.20

36.51

90 m/s

38.19

36.27

Note: The inlet airflow velocity is 90 m/s

5. Conclusions
Both the transfer matrix method and three point method can accurately calculate the TL values of muffler under noflow and uniform flow conditions. While, for the nonuniform flow case, both the results calculated by the two methods above exist errors, negative values even appear in the low frequency, because of the complexity of airflow and the limitation of calculation method.
The difference of the effect of uniform flow and nonuniform flow on the acoustic attenuation performances is little when the airflow regenerated noise is ignored. Furthermore, both the acoustic attenuation performances of simple reactive muffler and complex car muffler are affected slightly by the airflow in the case of $M<$0.3. When the inlet airflow velocity is 90 m/s, the TL values of the complex car muffler only reduce 0.56 dB and 2.48 dB for the uniform flow and nonuniform flow cases, respectively. In addition, the change rate of TL decreases as the airflow velocity increases. Therefore, the effect of airflow on the acoustic attenuation performance can be ignored during the initial phase of muffler design when the airflow regenerated noise is ignored.
Acknowledgements
This work was supported by Chongqing Significant Application and Development Planning Project (No. cstc2015yykfc60003) and National Natural Science Foundation of China (51275540, 51275542).
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