Supersonic Jet Noise: an Investigation into Noise Generation Mechanisms using Large Eddy Simulation and High-Resolution PIV Data

Markesteijn, Anton P.; Semiletov, Vasily; Karabasov, Sergey A.; Tan, Dominic J.; Wong, Marcus; Honnery, Damon; Edgington-Mitchell, Daniel

doi:10.2514/6.2017-3029

Cited by 10 publications

(8 citation statements)

References 23 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…This, combined with a relatively coarse grid, may cause the simulation not to capture the screech tones. 79–81 Moreover, the location and the intensity of the shocks is sensitive to the grid fineness and affects the BBSAN levels. Hence, the OASPL difference between the numerical and experimental results at large angles is expected.…”

Section: Resultsmentioning

confidence: 99%

Noise reduction analysis of supersonic unheated jets with fluidic injection using large eddy simulations

Coderoni

Lyrintzis

Blaisdell

2018

International Journal of Aeroacoustics

View full text Add to dashboard Cite

A set of large eddy simulations is used to perform a numerical analysis of fluidic injection as a tool for noise reduction. This technique, developed at the Pennsylvania State University, allows one to turn on and off the air injectors in order to reduce the noise during takeoff and landing without penalizing performance in other flight regimes. Numerical simulations are performed on a military-style nozzle based on the GE F400-series engines, with a design Mach number of 1.65, for overexpanded jet conditions. The numerical results are compared and validated with the outcome of experiments performed at the Pennsylvania State University. For the case chosen, the fluidic injection shows the potential of breaking down shock cells into smaller structures with different orientation and strength. This directly reduces the intensity of broadband shock associated noise, with a positive effect of reducing the overall sound pressure level by more than 1:5 dB along the direction of maximum sound propagation of the baseline case. The maximum noise reduction was found to be almost 3 dB at 55 on the azimuthal plane in between two lines of injectors.

show abstract

Section: Resultsmentioning

confidence: 99%

Noise reduction analysis of supersonic unheated jets with fluidic injection using large eddy simulations

Coderoni

Lyrintzis

Blaisdell

2018

International Journal of Aeroacoustics

View full text Add to dashboard Cite

show abstract

“…The flow variables relevant for modelling the BBSAN and mixing noise sources are calculated directly from the spatial turbulence statistics of the PIV measurements. The measurements have been examined by Markesteijn et al [28], where it was demonstrated that the velocity correlations is consistent with the quasi-normality hypothesis. The integral length scales are evaluated with an upper limit of integration that is defined by…”

Section: Correlation Analysismentioning

confidence: 93%

“…In the same study, the correlation scales along the nozzle lip line were shown to be important for modelling the noise sources. Additional studies that examined the velocity correlations have shown that contributions of the 11,22,1111,2222,3333,1212,1313, and 2323 components dominate in axisymmetric jets [13,28].…”

Section: Correlation Scalesmentioning

confidence: 99%

“…(20) from the 2D PIV measurements yields proportionality coefficients for both the axial and transverse velocities. Only the symmetric tensor components are considered as they have the largest statistical significance in axisymmetric round unheated jets [13,28]. The RMSE associated with the proportionality coefficients is expressed as a percentage of the local integral length scale value such that…”

Section: Correlation Analysismentioning

confidence: 99%

See 1 more Smart Citation

Correlation Analysis of High-Resolution Particle Image Velocimetry Data of Screeching Jets

Tan¹,

Honnery²,

Kalyan

et al. 2019

AIAA Journal

View full text Add to dashboard Cite

The acoustic analogy provides a general framework for predicting broadband jet noise. The accuracy of the noise predictions are strongly dependent on the second-and fourth-order integral time and length scales of the turbulence quantities in the jet. Two low-order models for the second-and fourth-order integral length scales are examined. The low-order models are defined by locally isotropic scales estimated from 2D particle image velocimetry measurements. These measurements are of screeching underexpanded unheated round jets issuing from a purely converging nozzle at conditions, which corresponds to ideally expanded Mach numbers of 1.45 and 1.59. The jets are dominated by the helical C instability screech mode, which is associated with large-scale coherent periodic fluctuations. These fluctuations are filtered using a proper orthogonal decomposition method to assess low-order models that approximate the length scales associated with the broadband noise mechanisms. The length scale model parameters are shown to be insensitive for the two Mach numbers considered. The root-mean-square error associated with the low-order models indicates that either is sufficient for approximating the integral length scales required to model equivalent sources of broadband jet noise.

show abstract

“…With the caveat that the experimental results are for the Reynolds number of 680,000 (an order of magnitude higher than the condition of this simulation), the results are in good agreement with the experiment. The slight difference in the location of the Mach disk is considered to be due to the difference in the Reynolds number, and also the sensitivity of the mean field to inlet conditions as recently investigated by Markesteijn et al [46]. Now moving to the discussion of the first-and second-order statistics of the flow field, contour maps of ensemble-averaged streamwise and radial velocities, as well as pressure obtained from LES are shown in Figure 5.…”

Section: Characteristics Of the Flow-fieldmentioning

confidence: 95%

Analysis of Coherent Structures in an Under-Expanded Supersonic Impinging Jet Using Spectral Proper Orthogonal Decomposition (SPOD)

Karami

Soria

2018

Aerospace

View full text Add to dashboard Cite

The spatiotemporal dynamics of the coherent structures in an under-expanded supersonic impinging jet are studied using a spectral proper orthogonal decomposition technique. For this analysis, a large eddy simulation of an under-expanded supersonic impinging jet at a pressure ratio of 3.4 and a stand-off distance of 2 jet diameters at a Reynolds number of 50,000 is performed. The mean flow fields illustrate some striking features of this flow, such as an oblique shock, a stand-off shock, a Mach disk, and a recirculation bubble. The spectral proper orthogonal decomposition method is applied to time-resolved three-dimensional flow fields. The accumulative energy of modes within each azimuthal mode number reveals that the first three azimuthal modes contain most of the energy of the flow. The spectra of these azimuthal modes show that the flow exhibits a low-ranked behaviour with discrete frequencies at the optimal symmetric azimuthal mode while other two azimuthal modes have negligible contributions in this behaviour. Three peaks are observed in the spectra of the optimal symmetric azimuthal mode. The spatial fields of the streamwise velocity and pressure of these peaks show that the complex structures are consequences of the under-expansion, Mach disk, and the impingement. Strong hydrodynamic instabilities exist in the shear layer of the jet in the optimal azimuthal mode at each of these dominant frequencies. High-amplitude acoustic waves are also present in the near-field of the jet. These acoustic waves are strong at the nozzle lip, suggesting that a feedback loop linking these two processes exists for dominant frequencies in the optimal mode. High cross-spectrum density of near-field pressure fluctuations and streamwise velocity fluctuations near the nozzle lip at these frequencies confirms the hydro-acoustic coupling, which is necessary to close the feedback loop.

show abstract

Supersonic Jet Noise: an Investigation into Noise Generation Mechanisms using Large Eddy Simulation and High-Resolution PIV Data

Cited by 10 publications

References 23 publications

Noise reduction analysis of supersonic unheated jets with fluidic injection using large eddy simulations

Noise reduction analysis of supersonic unheated jets with fluidic injection using large eddy simulations

Correlation Analysis of High-Resolution Particle Image Velocimetry Data of Screeching Jets

Analysis of Coherent Structures in an Under-Expanded Supersonic Impinging Jet Using Spectral Proper Orthogonal Decomposition (SPOD)

Contact Info

Product

Resources

About