Towards Prediction of Dual-Stream Jet Noise: Database Generation

Viswanathan, K.; Caech, Michael; Lee, In-Cheol

doi:10.2514/6.2011-1030

Cited by 7 publications

(11 citation statements)

References 21 publications

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“…Both bypass and core flows were held constant at NPR b = NPR c = 1.8 simulating a "dual-stream configuration" with a free jet M ∞ = 0.10. Figure 9 shows the computational results when the tertiary power settings are varied resulting in decreased peak TKE consistent with a previously noted dual-stream study 4 . Figure 10 shows the axial locations of the cross-stream non-dimensional velocity and non-dimensional TKE to be plotted and analyzed for the previous design point.…”

Section: B Tertiary Npr Variationsupporting

confidence: 79%

Flow Field and Acoustic Predictions for Three-Stream Jets

Simmons¹,

Henderson

Khavaran

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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Computational fluid dynamics was used to analyze a three-stream nozzle parametric design space. The study varied bypass-to-core area ratio, tertiary-to-core area ratio and jet operating conditions. The flowfield solutions from the Reynolds-Averaged Navier-Stokes (RANS) code Overflow 2.2e were used to pre-screen experimental models for a future test in the Aero-Acoustic Propulsion Laboratory (AAPL) at the NASA Glenn Research Center (GRC). Flowfield solutions were considered in conjunction with the jet-noise-prediction code JeNo to screen the design concepts. A two-stream versus three-stream computation based on equal mass flow rates showed a reduction in peak turbulent kinetic energy (TKE) for the three-stream jet relative to that for the two-stream jet which resulted in reduced acoustic emission. Additional three-stream solutions were analyzed for salient flowfield features expected to impact farfield noise. As tertiary power settings were increased there was a corresponding near nozzle increase in shear rate that resulted in an increase in high frequency noise and a reduction in peak TKE. As tertiary-to-core area ratio was increased the tertiary potential core elongated and the peak TKE was reduced. The most noticeable change occurred as secondary-to-core area ratio was increased thickening the secondary potential core, elongating the primary potential core and reducing peak TKE. As forward flight Mach number was increased the jet plume region decreased and reduced peak TKE. Nomenclaturex,z = axial and radial dimensions M ∞ = freestream Mach number T ∞ = freestream static temperature A c = core nozzle exit area A b = bypass nozzle exit area A t = tertiary nozzle exit area NPR c = core stagnation pressure to freestream total pressure ratio NPR b = bypass stagnation pressure to freestream total pressure ratio NPR t = tertiary stagnation pressure to freestream total pressure ratio NTR c = core stagnation temperature to freestream total temperature ratio NTR b = bypass stagnation temperature to freestream total temperature ratio NTR t = tertiary stagnation temperature to freestream total temperature ratio U = axial jet velocity U jet = core jet axial peak velocity TKE = turbulent kinetic energy D core = effective core exit area diameter 1 Researcher, Inlet and Nozzle Branch, MS VPL-3, 21000 Brookpark Rd., Cleveland OH 44135. AIAA Fellow. 2 Researcher, Acoustic Branch, MS 54-3, 21000 Brookpark Rd., Cleveland OH 44135. AIAA member. 3 Researcher, Acoustic Branch, MS VPL-3, 21000 Brookpark Rd., Cleveland OH 44135. AIAA member. Downloaded by UNIVERSITY OF TENNESSEE on August 13, 2015 | http://arc.aiaa.org |

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Section: B Tertiary Npr Variationsupporting

confidence: 79%

Flow Field and Acoustic Predictions for Three-Stream Jets

Simmons¹,

Henderson

Khavaran

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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“…17(b) at z/D ≈ ±0. 2 Due to the large magnitude of the primary and secondary shear layer turbulence, the upstream turbulence effect does not appear pronounced. However, figures 18(a) shows an earlier and greater peak in the primary shear layer at y/D ≈ −0.2 for x/D =1,1.5 and 2.…”

Section: Axial Variation Of Mean Velocity and Reynolds Stressesmentioning

confidence: 97%

LES of jet flow and noise with internal and external geometry features

Tyacke

Tucker

2015

53rd AIAA Aerospace Sciences Meeting

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The noise produced by aeroengines is a critical topic in engine design. Large-Eddy Simulation (LES) and hybrid Reynolds-Averaged Navier-Stokes (RANS)-LES, provides a method to increase understanding of influences on the noise produced and could lead to improved models for use in design. Use of Immersed Boundary (IB) and Body Force Methods (BFM) allows arbitrary geometry to be added rapidly and so this is explored to model internal geometry effects on jet flow and noise. This reduces grid complexity and broadens the accessible design space by reducing setup time and computational cost. Using LES and BFM/IB, many effects that are difficult to test experimentally can be assessed within useful time-frames. The introduction of internal geometry produces complex bypass duct exit flow and a more rapid development of the shear layers which may influence noise produced. Nomenclature u, v = Axial, radial velocity x, y, z = Cartesian coordinates d = True wall distancẽ d = Modified wall distance U 0 = Bypass exit velocity (≈ 300) P 0 = Total pressure T 0 = Total temperaturė m = Mass flow rate h b = Blade thickness F = Cell face i, j = Cells adjacent to cell face K n = Body force model constant normal to blade surface K p = Body force model constant parallel to blade surface

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“…The constant increase in by-pass ratio and the new regulatory terms that were agreed by the community on noise reduction led to the industry to focus again on the noise generated by the turbofans. An extensive experimental campaign on subsonic and supersonic dual stream jets was initiated by Viswanathan 18,19 and Viswanathan et al 20 in order to carry out a parametric study on the effect of the primary and secondary nozzle pressure ratios, the secondary-to-primary jet velocity ratio and the secondary-to-primary nozzle area ratio. The main conclusions are summarized in the following.…”

Section: Introductionmentioning

confidence: 99%

Large Eddy Simulation of Shock-Cell Noise From a Dual Stream Jet

Arroyo

Puigt

Airiau

et al. 2016

22nd AIAA/CEAS Aeroacoustics Conference

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This study presents the shock-cell noise results obtained with a large eddy aeroacoustic simulation from a dual stream jet. The primary stream is cold and subsonic with an exit Mach number of Mp = 0.89 and a Reynolds number of Rep = 0.57 × 10 6. The secondary stream is cold supersonic and under-expanded with a perfectly expanded Mach number of Ms = 1.20 and Res = 1.66 × 10 6. The computations are performed with the structured multiblock solver elsA. The aerodynamics and aeroacoustics of the flow are studied and analyzed in detail showing good agreement with experimental fits for the lengthscale and shear layer development. An acoustic-hydrodynamic filtering is used in order to compute the characteristic wavelengths of each component and estimate the shock-cell noise frequency. Moreover, the broadband shock-cell noise is captured in the near and far fields.

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Towards Prediction of Dual-Stream Jet Noise: Database Generation

Cited by 7 publications

References 21 publications

Flow Field and Acoustic Predictions for Three-Stream Jets

Flow Field and Acoustic Predictions for Three-Stream Jets

LES of jet flow and noise with internal and external geometry features

Large Eddy Simulation of Shock-Cell Noise From a Dual Stream Jet

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