Interaction of axisymmetric supersonic twin jets

Moustafa, Gamal H.

doi:10.2514/3.12508

Cited by 17 publications

(2 citation statements)

References 12 publications

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“…Screech phenomenon suppression is then the main effort with lots of experimental studies [6] [11], of which Raman presents a synthesis [12]. In parallel, nozzle spacing effects on the three regions (converging, merging, and combining) of the flowfield are investigated by Mustapha [13], or on shielding and interaction by Bozak [14] or Osawa [15] (on a shock free jet for the latter). In the last 5 years, twin jets screech is still a research field.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of the Noise Radiated by Free Hot Supersonic Twin Jets

Troyes

Vincent

2022

28th AIAA/CEAS Aeroacoustics 2022 Conference

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Numerical simulation of the noise radiated by free hot supersonic twin jets is conducted by combining different numerical tools. These are based on the one hand on a high fidelity LES (Large Eddy Simulation) computation with geometric triggering of the turbulence in the nozzle convergents and on the other hand on the use of a CAA code, coupled with the CFD code, to properly propagate at a lower cost the high level acoustic waves from the jet near field towards the far field microphones. This methodology has demonstrated its benefits by producing very satisfactory results. Numerical velocity profiles are shown in very good agreement with the experimental measurements for several diameters downstream of the nozzle outlets. These results show that marked interactions between the two jets only occurs several diameters after the nozzle outlets. Regarding acoustics, the results are very encouraging. Considering the far field OASPL, the numerical vs. experimental deviation ranges from 0 to 3 dB. Higher levels in the azimuths perpendicular to the two jets with respect to the levels in the azimuths coplanar to the two jets are well recovered by the computation. These higher levels do not exactly reach the theoretical addition of two single jets noise, which suggests that acoustics source efficiency is reduced by interaction effects while lower levels in the coplanar plane traduce a probable masking effect.

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Section: Introductionmentioning

confidence: 99%

Numerical Simulation of the Noise Radiated by Free Hot Supersonic Twin Jets

Troyes

Vincent

2022

28th AIAA/CEAS Aeroacoustics 2022 Conference

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“…[13] experimentally studied the spreading rate of two supersonic coaxial jets for rectangular and circular cross sections. Moustafa [14] investigated the interaction between multiple supersonic jets in two, three and four nozzle configurations. Though, the investigations deal with a lot many flow features of coaxial jets, it seems the effect of jet cross-section shape on the co-flow features has not been sufficiently explored.…”

Section: Introductionmentioning

confidence: 99%

Numerical and Experimental Studies on the Supersonic Coaxial Jet Mixing

Karthikeyan

Sridhar

2011

AMR

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Coaxial nozzles are an integral part of many engineering systems where mixing of different fluid streams is required. Single noncircular nozzles have been shown to have better mixing characteristics than their axisymmetric counterparts. Therefore, a combination of such nozzles into coaxial configurations is promising. The aim of the present study is to quantitatively determine the effects of the geometry of the primary supersonic jet on the mixing characteristics with the secondary high speed subsonic jet. Measurements of pressure profiles at several positions along central axis of jets using identical facilities and nominally identical experimental conditions were done. The mixing is dominated by the vortex structures that are present in the inner shear layers. The interaction of the vortex structures govern the growth, and entrainment, and mixing of the jet. Also, the experimental results show that the radial and centerline pressure profiles through various coaxial jets has good correlation with the CFD simulation.

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A study of the impulse wave discharged from the exits of two parallel tubes

et al. 2003

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The twin impulse wave leads to very complicated flow fields, such as Mach stem, spherical waves, and vortex ring. The twin impulse wave discharged from the exits of the two tubes placed in parallel is investigated to understand the detailed flow physics associated with the twin impulse wave, compared with those in a single impulse wave. In the current study, the merging phenomena and propagation characteristics of the impulse waves are investigated using a shock tube experiment and by numerical computations. The Harten-Yee's total variation diminishing (TVD) scheme is used to solve the unsteady two-dimensional compressible Euler equations. The Mach number Ms of incident shock wave is changed below 1.5 and the distance between two-parallel tubes, L/d, is changed from 1.2 to 4.0. In the shock tube experiment, the twin impulse waves are visualized by a Schlieren optical system for the purpose of validation of computational work. The results obtained show that on the symmetric axis between two-parallel tubes, the peak pressure produced by the twin impulse waves and its location strongly depend upon the distance between two-parallel tubes, L/d and the incident shock Mach number, Ms. The predicted Schlieren images represent the measured twin-impulse wave with a good accuracy.

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Interaction of axisymmetric supersonic twin jets

Cited by 17 publications

References 12 publications

Numerical Simulation of the Noise Radiated by Free Hot Supersonic Twin Jets

Numerical Simulation of the Noise Radiated by Free Hot Supersonic Twin Jets

Numerical and Experimental Studies on the Supersonic Coaxial Jet Mixing

A study of the impulse wave discharged from the exits of two parallel tubes

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