Bulletin of the American Physical Society
68th Annual Meeting of the APS Division of Fluid Dynamics
Volume 60, Number 21
Sunday–Tuesday, November 22–24, 2015; Boston, Massachusetts
Session H38: Acoustics IV: Aero-Acoustics |
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Chair: Joseph Nichols, University of Minnesota Room: Sheraton Back Bay B |
Monday, November 23, 2015 10:35AM - 10:48AM |
H38.00001: Acoustic source analysis of supersonic jets from complex nozzles Joseph W. Nichols, Jordan Kreitzman We compute acoustic source terms corresponding to Goldstein’s generalized acoustic analogy from an unstructured high-fidelity large eddy simulation of a supersonic jet issuing from a rectangular nozzle with chevrons. The simulation data are validated against experimental measurements of mean and turbulence flow statistics as well as far-field noise. We evaluate fourth-order correlations from the simulation data to assess assumptions of quasi-normality and statistical axisymmetry that underpin reduced-order acoustic source models originally developed for round jets. A spatial analysis of these correlations in relation to the complex geometry of the nozzle reveals locations where the validity of these assumptions begins to break down. Using two point two-time correlations of the simulation data, we also directly evaluate and compare the accuracy of four different acoustic source models, including the Gaussian, moving-frame, fixed-frame, and modified distance models. [Preview Abstract] |
Monday, November 23, 2015 10:48AM - 11:01AM |
H38.00002: Input-output analysis of high-speed turbulent jet noise Jinah Jeun, Joseph W. Nichols We apply input-output analysis to predict and understand the aeroacoustics of high-speed isothermal turbulent jets. We consider axisymmetric linear perturbations about Reynolds-averaged Navier-Stokes solutions of ideally expanded turbulent jets with Mach numbers $0.6 < M_j < 1.8$. For each base flow, we compute the optimal harmonic forcing function and its linear response by singular value decomposition of the resolvent operator. In addition to the optimal mode, input-output analysis also yields suboptimal modes associated with a spectrum of lesser singular values. For supersonic jets, the optimal response closely resembles a wavepacket in both the nearfield and the farfield such as those obtained by the parabolized stability equations (PSE), and this mode dominates the response. For subsonic jets, however, the singular values indicate that the contributions of suboptimal modes to noise generation are nearly equal to that of the optimal mode, explaining why PSE misses some of the farfield sound in this case. Finally, high-fidelity large eddy simulation (LES) is used to assess the prevalence of suboptimal modes in the unsteady data. By projecting LES data onto the corresponding input modes, the weighted gain of each mode is examined. [Preview Abstract] |
Monday, November 23, 2015 11:01AM - 11:14AM |
H38.00003: Global mode decomposition of supersonic impinging jet noise Nathaniel Hildebrand, Joseph W. Nichols We apply global stability analysis to an ideally expanded, Mach 1.5, turbulent jet that impinges on a flat surface. The analysis extracts axisymmetric and helical instability modes, involving coherent vortices, shocks, and acoustic feedback, which we use to help explain and predict the effectiveness of microjet control. High-fidelity large eddy simulations (LES) were performed at nozzle-to-wall distances of 4 and 4.5 throat diameters with and without sixteen microjets positioned uniformly around the nozzle lip. These flow configurations conform exactly to experiments performed at Florida State University. Stability analysis about LES mean fields predicted the least stable global mode with a frequency that matched the impingement tone observed in experiments at a nozzle-to-wall distance of 4 throat diameters. The Reynolds-averaged Navier-Stokes (RANS) equations were solved at five nozzle-to-wall distances to create base flows that were used to investigate the influence of this parameter. A comparison of the eigenvalue spectra computed from the stability analysis about LES and RANS base flows resulted in good agreement. We also investigate the effect of the boundary layer state as it emerges from the nozzle using a multi-block global mode solver. [Preview Abstract] |
Monday, November 23, 2015 11:14AM - 11:27AM |
H38.00004: Global Mode-Based Control of Supersonic Jet Noise Mahesh Natarajan, Jonathan Freund, Daniel Bodony The loudest source of high-speed jet noise appears to be describable by unsteady wavepackets that resemble instabilities. We seek to reduce their acoustic impact by developing a novel control strategy that uses global modes to model their dynamics and structural sensitivity of the linearized compressible Navier-Stokes operator to determine effective linear feedback control. Using co-located actuators and sensors we demonstrate the method on an axisymmetric Mach 1.5 fitted with a nozzle. Direct numerical simulations using this control show significant noise reduction, with additional reduction with increase in control gain. Eigenanalysis of the uncontrolled and controlled mean flows reveal fundamental changes in the spectrum at frequencies lower than that used by the control. The non-normality of the global modes is shown to enable this control to affect a wide range of frequencies. The low-frequency wavepacket components are made less acoustically efficient, which is reflected in the far-field noise spectrum. Mean flow alterations are minor near the nozzle and only become apparent further downstream. [Preview Abstract] |
Monday, November 23, 2015 11:27AM - 11:40AM |
H38.00005: Mode Decomposition of a Supersonic Jet Using Momentum Potential Theory Unnikrishnan Sasidharan Nair, Datta Gaitonde We adopt Doak’s momentum potential theory to investigate the acoustic, thermal and hydrodynamic modes in a Mach 1.3 cold jet. A statistically stationary LES of the jet is subjected to Helmholtz decomposition to yield the solenoidal and irrotational components of the momentum density. The irrotational component is further decomposed into acoustic and thermal modes. The data confirms the quantitative radial decay rates of the hydrodynamic and acoustic fields as well as the experimentally observed universal spectrum specific to the downstream and sideline directions. The irrotational field in the core exhibits an axially coherent jittering wave-packet with an internal frequency of St~0.4, yielding the highly directional downstream radiation at St~0.2. The intrusion of rolled up vortices from the expanding shear layer into the core induces a coherent perturbation zone in the irrotational component, which persists and propagates into the nearfield resulting in intermittent noise events. The interaction of the fluctuating solenoidal field with the fluctuating Lamb vector in the core of the jet is found to be the most prominent source, while its interaction with the fluctuating entropy gradient is found to be a sink in this cold jet. [Preview Abstract] |
Monday, November 23, 2015 11:40AM - 11:53AM |
H38.00006: Extracting Near-Field Structures Related to Noise Production in High Speed Jet Pinqing Kan, Jacques Lewalle Jet noise research started with Lighthill's seminal work on aerodynamic sound in 1952. The current consensus is that jet noise has two main kinds of sources, the large turbulent structures and the fine-scale turbulence. Coherent structures and the noise they produce are the focus of this paper because they offer better odds for control and they are associated with the most energetic part of the acoustic spectrum. We develop an algorithm using cross-correlation, continuous wavelet and pattern recognition techniques to search for near-field (NF) structures associated with far-field (FF) acoustic noise at aft angles. An experimental data is analyzed which measured a cold circular jet of Mach 0.6 (Low et al. 2013). The events identified are short wave packets in the time-frequency domain, distorted by ambient perturbations. The statistics of the event properties, including intermittency, frequency and magnitude are consistent with observations from other researchers. We investigate the localization and time sequencing of the events and use ensemble average to bring out the distinct structures associated to noise production. The filtered signals including / excluding the events are compared and the results are further tested using synthetic and randomized signals. [Preview Abstract] |
Monday, November 23, 2015 11:53AM - 12:06PM |
H38.00007: How non-parallel flow affects the low frequency sound of supersonic heated jets Mohammed Afsar, Adrian Sescu Experiements show that the peak noise of heated supersonic jets is lower than the peak noise associated with isothermal jets at all observation angles. Attempts to explain this reduction via acoustic analogy approaches were based on theories in which the enthalpy or momentum flux co-variance (coupling term) reduces the acoustic spectrum at small observation angles. These results, that were derived using a parallel flow assumption and determined using a low frequency asymptotic analysis, indicate that the propagator in the coupling term possesses an odd power of inverse Doppler factors that change sign at small observation angles to the jet axis for supersonic jets. This result, however, does not take into account mean flow spreading. In this study, we extend a previously developed asymptotic theory for the propagator in non-parallel flows, to heated jets. Our calculations show that, non-parallelism re-distributes the spatial structure of the propagator at small observation angles for supersonic jets. Rather than introducing cancellation in the acoustic spectrum, as parallel flow asymptotics predict, the non-parallel flow asymptotic analysis suggests that heating shifts the propagator's peak much further downstream, into regions where turbulence becomes weak. [Preview Abstract] |
Monday, November 23, 2015 12:06PM - 12:19PM |
H38.00008: Coupling dynamic of twin supersonic jets Ching-Wen Kuo, Jordan Cluts, Mo Samimy In a supersonic shock-containing jet, the interaction of large-scale structures in the jet's shear layer with the shock waves generates acoustic waves. The waves propagate upstream, excite the jet initial shear layer instability, establish a feedback loop at certain conditions, and generate screech noise. The screech normally contains different modes of various strengths. Similarly, twin-jet plumes contain screech tones. If the dynamics of the two jet plumes are synchronized, the screech amplitude could be significantly amplified. There is a proposed analytical model in the literature for screech synchronization in twin rectangular jets. This model shows that with no phase difference in acoustic waves arriving at neighboring nozzle lips, twin-jet plumes feature a strong coupling with a significant level of screech tones. In this work the maximum nozzle separation distance for sustained screech synchronization and strong coupling is analytically derived. This model is used with our round twin-jet experiments and the predicted coupling level agrees well with the experimental results. Near-field microphone measurements and schlieren visualization along with the analytical model are used to investigate the coupling mechanisms of twin supersonic jets. [Preview Abstract] |
Monday, November 23, 2015 12:19PM - 12:32PM |
H38.00009: Mean Flow Perturbation Analysis of an Underexpanded Jet Swagata Bhaumik, Datta Gaitonde, Hao Shen Here, we illustrate a novel method to predict sound generated by imperfectly expanded jets where the resulting shock-cells can yield significant broadband noise in the far-field. We describe continued development of mean flow perturbation method to analyze the response of an underexpanded jet to small perturbations. This method originates from the work of Touber \& Sandham (Theor. Comput. Fluid. Dyn., 2009) for nominally 2D shock-wave turbulent-boundary layer interactions. This method is an initial boundary value problem and is equally applicable to flows with sharp gradients. It degenerates into the LST, global and PSE analysis under suitable conditions. We use this method to study finer details of the noise generation mechanisms of an under-expanded round jet at $M=1.0$. Preliminary results on time-averaged mean turbulent flow-field perturbed by an annular multi-periodic excitation close to the nozzle-exit plane show interaction of downstream propagating disturbances with the feet of the shock-cells. This causes significant amplification of disturbances resulting in the formation of toroidal vortical structures. This further destabilize the shock-cells, finally resulting in acoustic wave propagation in two distinct downstream and upstream directions. [Preview Abstract] |
Monday, November 23, 2015 12:32PM - 12:45PM |
H38.00010: Hybrid Analysis of Engine Core Noise Jeffrey O'Brien, Jeonglae Kim, Matthias Ihme Core noise, or the noise generated within an aircraft engine, is becoming an increasing concern for the aviation industry as other noise sources are progressively reduced. The prediction of core noise generation and propagation is especially challenging for computationalists since it involves extensive multiphysics including chemical reaction and moving blades in addition to the aerothermochemical effects of heated jets. In this work, a representative engine flow path is constructed using experimentally verified geometries to simulate the physics of core noise. A combustor, single-stage turbine, nozzle and jet are modeled in separate calculations using appropriate high fidelity techniques including LES, actuator disk theory and Ffowcs-Williams Hawkings surfaces. A one way coupling procedure is developed for passing fluctuations downstream through the flowpath. This method effectively isolates the core noise from other acoustic sources, enables straightforward study of the interaction between core noise and jet exhaust, and allows for simple distinction between direct and indirect noise. The impact of core noise on the farfield jet acoustics is studied extensively and the relative efficiency of different disturbance types and shapes is examined in detail. [Preview Abstract] |
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