The Response of Supersonic Jet Noise Components to Fluidic Injection Parameters

Cuppoletti, Daniel R.; Malla, Bhupatindra; Gutmark, Ephraim; Hafsteinsson, Haukur; Eriksson, Lars‐Erik; Prisell, Erik

doi:10.2514/6.2013-2196

Cited by 11 publications

(14 citation statements)

References 15 publications

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“…The presented Large Eddy Simulations (LES) have shown to be in good agreement with previous experiments in terms of far-field acoustics, mean flow velocity and even turbulence kinetic energy [16,17,18,19]. However, in the experiments it proves to be difficult to obtain the instantaneous flow quantities within the supersonic region.…”

Section: Introductionsupporting

confidence: 76%

“…The time-averaged axial velocity obtained from the LES, for both the no-injection case and the steady injection case, has previously been shown to compare well with PIV, see Cuppoletti et al [16]. It was shown that the injection penetrates through the shear layer and introduces a pair of stream-wise vortices into the main jet flow downstream of each injector and these stream-wise vortices interrupts the roll up of the shear layer into Kelvin-Helmholtz instabilities.…”

Section: Flow Resultsmentioning

confidence: 87%

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Near-Field and Far-Field Spectral Analysis of Supersonic Jet with and without Fluidic Injection

Hafsteinsson

Eriksson

Andersson

et al. 2014

52nd Aerospace Sciences Meeting

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In the presented study the time-dependent flow features of a supersonic jet with and without steady microjet injection are investigated. The flow field is sampled at various axial and radial locations in the supersonic region and its near surroundings. The jet is emitted from a sharp-throat converging diverging nozzle operated at a nozzle pressure ratio (NPR) of 4.0, which gives a jet exit Mach number of M = 1.56 and a Reynolds number of Re = 2.46 × 10 6 based on the jet exit diameter. Large Eddy Simulation (LES) is used to obtain the fully three dimensional instantenous turbulent flow field and the Kirchhoff surface integral method is applied to obtain the far-field radiated noise. Both the near-field flow dynamics and the far-field noise obtained from the LES are in good agreement with experimental data. The noise components in the far-field noise are identified and compared with the spectra obtained from the probe-locations within the jet. The effect of micro-jet injection on the spectral characteristics within the jet and the far-field noise is analyzed. The screech tone appearing in the far-field noise is clearly established also in the jet-plume. Two point cross-correlations within and outside the supersonic region of the jet-plume revealed two types of moving phenomenon. These where found to be turbulent structures and acoustic waves. The odd thing at first sight was that the acoustic waves appeared to be traveling upstream within the supersonic region, which sounds contradictory. However, it was showed that the acoustic wave was traveling in the form of a helical mode which allows the phase velocity of the pressure wave to be higher than the flow velocity, even at supersonic flow speeds. The fluidic injection was shown to disrupt and weaken the helical pattern which resulted in a lower far-field screech tone noise. Upon sufficient dissipation of the injection, a few nozzle diameters downstream of the nozzle exit, the helical pattern picks up strength again. However, the feed-back loop mechanism associated with the screech tone is still disabled.

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Section: Introductionsupporting

confidence: 76%

Section: Flow Resultsmentioning

confidence: 87%

Near-Field and Far-Field Spectral Analysis of Supersonic Jet with and without Fluidic Injection

Hafsteinsson

Eriksson

Andersson

et al. 2014

52nd Aerospace Sciences Meeting

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“…PIV measurements by Cuppoletti et. al 3 are available without injection, which are compared to the numerical data in Fig. 2 for p 0,n /p ∞ = 4.0.…”

Section: Nozzle-outsidementioning

confidence: 99%

“…Comparison of the numerical results with PIV measurements,3 where the experimental flow visualisation is shown on the top and the numerical data on the bottom. The streamwise velocity normalised by the nozzle mean exit velocity, u e,x , is shown in (a) and the normalised turbulence kinetic energy, √ T KE/u e,x , in (b).…”

mentioning

confidence: 99%

Fluidic Injection Scenarios for Shock Pattern Manipulation in Exhausts

Semlitsch

Mihăescu

2018

AIAA Journal

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Screening numerically internal fluidic injection scenarios for the manipulation of the double diamond shock pattern in convergent-divergent nozzle exhausts, we demonstrate the individual importance of design parameters. We find that the evolving shock pattern is sensitive to the injection location, while the persistence of the induced counterrotating vortex pairs is primarily governed by the injection pressure. Injection close to the nozzle exit generates secondary vortical structures amplifying the fluctuations in the nozzle vicinity.

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“…Fluidic injection was found especially efficient to reduce shock associated noise [10]. Nonetheless, the design of fluidic injection systems requires parametric studies, because the interaction of the injected flow with complex shock patterns involves non-linear interactions that are difficult to predict [11,12].…”

Section: Introductionmentioning

confidence: 99%

Transforming the Shock Pattern of Supersonic Jets Using Fluidic Injection

et al. 2019

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Double shock diamonds establish in the exhaust of modular convergent-divergent nozzles. These consist of two shock structures; one originating from the nozzle throat and another from its exit. Analyzing the shock pattern developing for different fluidic injection operating conditions, it is shown that fluidic injection allows the rearrangement of the shock structures relative to each other. Overlapping the two structures caused large pressure oscillations in the exhaust and high amplitudes of shock associated noise, whereas staggering the shock structures mitigated these effects. The screech tone frequency did not change for all injection operating configurations, although the shock diamonds had been shifted drastically with respect to each other. Hence, the screech phenomenon is dominated by the primary shock spacing originating from the nozzle throat.

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The Response of Supersonic Jet Noise Components to Fluidic Injection Parameters

Cited by 11 publications

References 15 publications

Near-Field and Far-Field Spectral Analysis of Supersonic Jet with and without Fluidic Injection

Near-Field and Far-Field Spectral Analysis of Supersonic Jet with and without Fluidic Injection

Fluidic Injection Scenarios for Shock Pattern Manipulation in Exhausts

Transforming the Shock Pattern of Supersonic Jets Using Fluidic Injection

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