Numerical Study of Free Supersonic Hot Jet on Unstructured Grids with Emphasis on Aerodynamics and Resulting Radiated Noise

Troyes, Julien; Vincent, François; Lambaré, Hadrien; Ramos, Amaya Espinosa

doi:10.2514/6.2016-2734

Cited by 6 publications

(13 citation statements)

References 31 publications

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“…A resolution of PPW = 20 has been found to be required for a proper acoustic propagation in the near field with the CEDRE code. 45 The associated numerical damping reaches its maximum value of 0.5 dB/λ c at the cut-off.…”

Section: Flow Computationmentioning

confidence: 95%

“…x and radial u ′ r velocities, axial velocity skewness S(u x ) and kurtosis K(u x ), along the jet axis and along four radii positioned at x * = x/D j = 1, 3, 3.67 and 6. A microphone arc of ra- 45 The acoustic far field was computed with the Ffowcs Williams & Hawkings method. 31 More recently, Langenais et al 44 have adapted the case by using an identical near field mesh and computing the far field with the full Euler equations.…”

Section: Experimental and Numerical Databasementioning

confidence: 99%

“…Troyes et al have simulated jet cases corresponding to experiments con-ducted at the MARTEL test bench. 45 Major grid effects have been investigated. A sufficiently refined unstructured mesh has been found to be required on the jet axis to accurately capture shock cell locations.…”

Section: Past Effortsmentioning

confidence: 99%

“…The azimuthal resolution at the nozzle lips has been found to significantly influence the early shear layer development. More recently, the far field mesh of a same free jet case 45 has been adapted by Langenais et al 44 to perform a Navier-Stokes−Euler coupled computation following the procedure described in section II B 3. Since the near field mesh and flow solution were unchanged, it has allowed to specifically study the impact of the nonlinearities on the acoustic far field.…”

Section: Past Effortsmentioning

confidence: 99%

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Accurate simulation of the noise generated by a hot supersonic jet including turbulence tripping and nonlinear acoustic propagation

et al. 2019

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A procedure to accurately simulate a free hot supersonic jet and its associated noise, which uses simultaneously a turbulence tripping method and a two-way coupling between a flow solver and a nonlinear acoustic solver, is proposed in this study. A Mach 3.1 overexpanded hot jet is computed via a large-eddy simulation by solving the filtered Navier-Stokes equations with a finite volume method on unstructured grids. The resulting noise is propagated in the far field by solving the full Euler equations with a high-order discontinuous Galerkin method on unstructured grids. The full convergent-divergent nozzle is explicitly included in the computational domain thanks to the unstructured flow solver. Both a refined grid and a geometrical boundary layer tripping in the convergent are used to get highly disturbed turbulent conditions at the nozzle lips. The flow field appears to agree with the expected turbulence behavior and the available experimental data. The jet development shows significant improvement compared to similar past simulations. The far field acoustic levels are finely recovered at most of observation angles. An analysis of the acoustic near and far fields is then performed. The studied conditions lead to strong shock-associated noise and Mach wave emission. The spatio-frequency and azimuthal content of the acoustic field is described in order to identify the main noise properties. A particular noise component, different from screech tones and radiating upstream like Mach waves, is highlighted. Nonlinear propagation effects are finally quantified through specific metrics. They are found significant in both the near and the far fields which justifies the use of a nonlinear acoustic solver.

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Section: Flow Computationmentioning

confidence: 95%

Section: Experimental and Numerical Databasementioning

confidence: 99%

Section: Past Effortsmentioning

confidence: 99%

Section: Past Effortsmentioning

confidence: 99%

See 2 more Smart Citations

Accurate simulation of the noise generated by a hot supersonic jet including turbulence tripping and nonlinear acoustic propagation

et al. 2019

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“…In addition to various experimental studies [5] which have led to significant noise reduction on launch pads [6], semi-empirical jet noise models based on the Lighthill's theory have been formulated [7] and improved [8][9][10] but they are often unsuitable to deal with such realistic space applications. More recently, the development of large-eddy simulation (LES) allowed accurate simulations of hot supersonic jets [11][12][13][14][15], even for increasingly complex configurations as performed with realistic launch pad geometries by Fujii et al [16] or Tsutsumi et al [17]. The computational cost of such simulations remains however heavy for current industrial practices, especially when the acoustic propagation is directly calculated by the flow solver.…”

Section: Introductionmentioning

confidence: 99%

Assessment of a Two-Way Coupling Methodology Between a Flow and a High-Order Nonlinear Acoustic Unstructured Solvers

Langenais

Vincent

Peyret

et al. 2018

Flow Turbulence Combust

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A two-way coupling on unstructured meshes between a flow and a high-order acoustic solvers for jet noise prediction is considered. The flow simulation aims at generating acoustic sources in the near field while the acoustic simulation solves the full Euler equations, thanks to a discontinuous Galerkin method, in order to take into account nonlinear acoustic propagation effects. This methodology is firstly validated on academic cases involving nonlinear sound propagation, shock waves and convection of aerodynamic perturbations. The results are compared to analytical solutions and direct computations. A good behaviour of the coupling is found regarding the targeted space applications. An application on a launch pad model is then simulated to demonstrate the robustness and reliability of the present approach.

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Computation of the noise radiated by a hot supersonic jet deflected in a flame trench

Langenais

Vincent

Troyes

et al. 2021

The Journal of the Acoustical Society of America

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This study aims to numerically investigate the noise radiated by a reduced-scale rocket engine jet at lift-off conditions including a flame trench. An over-expanded Mach 3.1 hot jet entering a flame duct where it impinges on a deflector before being guided in a horizontal duct, is considered. The computation is performed with a two-way coupled approach on unstructured grids. This methodology relies on a large-eddy simulation of the jet and the acoustic near field, associated with a full Euler simulation of the acoustic far field. The aerodynamic and acoustic results are compared to a previous computation involving the Ffowcs Williams and Hawkings approach and show a better agreement with the measurements conducted at the MARTEL facility. A more careful analysis of the pressure field suggests that the noise is strongly influenced by the flame trench geometry. Nonlinear propagation effects, natively taken into account by the full Euler solver, are finally highlighted and discussed. Based on appropriate metrics, a good agreement with the experiment is obtained.

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Numerical Study of Free Supersonic Hot Jet on Unstructured Grids with Emphasis on Aerodynamics and Resulting Radiated Noise

Cited by 6 publications

References 31 publications

Accurate simulation of the noise generated by a hot supersonic jet including turbulence tripping and nonlinear acoustic propagation

Accurate simulation of the noise generated by a hot supersonic jet including turbulence tripping and nonlinear acoustic propagation

Assessment of a Two-Way Coupling Methodology Between a Flow and a High-Order Nonlinear Acoustic Unstructured Solvers

Computation of the noise radiated by a hot supersonic jet deflected in a flame trench

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