Experimental Investigation of an In-Duct Orifice with Bias Flow under Medium and High Level Acoustic Excitation

Zhou, Lin; Bodén, Hans

doi:10.1260/1756-8277.6.3.267

Cited by 14 publications

(9 citation statements)

References 38 publications

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“…Scarpato et al (2012) and Scarpato, Ducruix & Schuller (2013) performed extensive work on modelling the acoustic properties of perforate backed by a cavity with bias flow at low Strouhal number. Zhou & Bodén (2014) investigated the bias flow under medium and high-level acoustic excitation and found more complex acoustic properties compared with the no-bias flow case.…”

Section: Literature Reviewmentioning

confidence: 99%

Numerical investigation of a honeycomb liner grazed by laminar and turbulent boundary layers

Zhang

Bodony

2016

J. Fluid Mech.

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Direct numerical simulations are used to study the interaction of a cavity-backed circular orifice with grazing laminar and turbulent boundary layers and incident sound waves. The flow conditions and geometry are representative of single degree-of-freedom acoustic liners applied in the inlet and exhaust ducts of aircraft engines and are the same as those from experiments conducted at NASA Langley. The simulations identify the fluid mechanics of how the sound field and state of the grazing boundary layer impact the in-orifice flow and suggest a simple flow analogy that enables scaling estimates. From the scaling estimates the simulations are then used to develop reduced-order models for the in-orifice flow and a time-domain impedance model is constructed. The liner is found to increase drag at all conditions studied by an amount that increases with the incident sound pressure amplitude.

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Section: Literature Reviewmentioning

confidence: 99%

Numerical investigation of a honeycomb liner grazed by laminar and turbulent boundary layers

Zhang

Bodony

2016

J. Fluid Mech.

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“…The curves show a maximum around u ^ normalac / U s ≈ 1, where, after the maximum, one finds a transition zone where the EF decreases with increasing velocity ratios. Jing and Sun 13 and Zhou and Bodèn 14 found a similar transition range for an orifice in the presence of a bias flow ( 0.3 < u ^ normalac / U s < 4). In this range, they observe a dip in the resistance.…”

Section: Enhancement Of the Resistancementioning

confidence: 78%

“…10 In the literature, most of the works focus on circular perforations in the presence of a mean flow. 11–15 Salikuddin et al 11 find that the effect of acoustic excitation amplitude is similar to that of a bias flow. Jing and Sun 13 compare a discrete vortex model and a quasi-steady method to study high-intensity sound absorption at an orifice with a bias flow.…”

Section: Introductionmentioning

confidence: 96%

“…15,[20][21][22][23] Fabre et al 24,25 focus on the impact of flow through a thin circular aperture. Zhou and Bodèn 14,16 find that a bias flow makes the acoustic properties more complex compared to the no bias flow case, especially when the velocity ratio between acoustic velocity and mean flow velocity is close to unity. In recent works, Guzmàn-Iñigo et al, 26 Hirschberg et al 27 and Burgmayer et al 15,28 discuss the effect of the geometry of the perforations on the acoustic response in the presence of flow.…”

Section: Introductionmentioning

confidence: 99%

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Experimental study of a slit in the presence of a bias flow under medium- and high-level acoustic excitations

Aulitto

Hirschberg

Arteaga

et al. 2023

International Journal of Spray and Combustion Dynamics

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This work presents an experimental investigation of the acoustic properties of a slit in the presence of a bias flow under moderate- and high-acoustic excitations. Impedance tube experiments are discussed for a geometry inspired by deep punching resulting in a cut in the plate. The acoustic transfer impedance of the plate is discussed for several bias flow velocities, acoustic excitation, and different frequencies. In the range considered for this study, a bias flow appears to have two main effects, globally enhancing the sound absorption of the plate and creating a protective layer downstream of the plate due to the interaction between the slits. A maximum of the enhancement factor is found at a specific ratio between the acoustic velocity and the bias flow velocity. Two simple asymptotic behaviors are found, dominated by the flow or by the acoustic excitation, respectively. The behavior of the inertance is complex. Globally the inertance decreases with decreasing flow Strouhal number while its dependency on the amplitude of the acoustic velocity is less obvious.

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“…At higher levels of acoustic excitation, the unsteady high acoustic particle velocity through the orifice combines with the steady mean flow and the resulting net effect is a combination of linear bias flow and non-linear orifice jet flow effects. 35,36 To investigate this effect, the LBM simulations have been repeated at 1800 Hz for SPL of 140 dB, 150 dB, and 160 dB. The results for the predicted resistance are shown in Figure 22(a), whereas Figure 22(b) shows the corresponding predictions using the non-linear impedance model given by equations (3) and (4) and the linear bias flow model given by equation (8).…”

Section: High-fidelity Liner Simulationsmentioning

confidence: 99%

High fidelity modeling tools for engine liner design and screening of advanced concepts

Winkler

Mendoza

Reimann

et al. 2021

International Journal of Aeroacoustics

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With aircraft engines trending toward ultra-high bypass ratios, resulting in lower fan pressure ratios, lower fan RPM, and therefore lower blade pass frequency, the aircraft engine liner design space has been dramatically altered. This result is also due to the associated reduction in both the available acoustic treatment area (axial extent) as well as thickness (liner depth). As a consequence, there is current need for novel acoustic liner technologies that are able to meet multiple physical constraints and simultaneously provide enhanced noise attenuation capabilities. In addition, recent advances in additive manufacturing have enabled the consideration of complex liner backing structures that would traditionally be limited to honeycomb cores. This paper provides an overview of engine liner modeling and a description of the key physical mechanisms, with some emphasis on the use of low to high-fidelity tools such as empirical models and commercially available software such as COMSOL, Actran, and PowerFLOW. It is shown that the higher fidelity tools are a critical enabler for the evaluation and construction of future complex liner structures. A systematic study is conducted to predict the acoustic performance of traditional single degree of freedom liners and comparisons are made to experimental data. The effects of grazing flow and bias flow are briefly addressed. Finally, a more advanced structure, a metamaterial, is modeled and the acoustic performance is discussed.

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Experimental Investigation of an In-Duct Orifice with Bias Flow under Medium and High Level Acoustic Excitation

Cited by 14 publications

References 38 publications

Numerical investigation of a honeycomb liner grazed by laminar and turbulent boundary layers

Numerical investigation of a honeycomb liner grazed by laminar and turbulent boundary layers

Experimental study of a slit in the presence of a bias flow under medium- and high-level acoustic excitations

High fidelity modeling tools for engine liner design and screening of advanced concepts

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