Large-Scale Simulations for Turbine Engine Core Noise

Zante, Dale Van

doi:10.1260/1475-472x.10.1.75

Cited by 6 publications

(2 citation statements)

References 10 publications

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“…In the unsteady simulations, the time marching is performed with an explicit second-order Runge-Kutta scheme using five steps. These numerical parameters are similar to the ones used by Rumsey et al [17] and Van Zante [19], who numerically studied ducted tonal noise.…”

Section: A Unsteady Reynolds-averaged Navier-stokes Noise-source Modelmentioning

confidence: 84%

“…The deterministic noise sources in both configurations considered here are provided by URANS simulations following an existing methodology (e.g., [17][18][19]). The computational fluid dynamics (CFD) solver Turb'Flow developed at École Centrale de Lyon in France solves the 3-D compressible Navier-Stokes equations on multiblock structured grids.…”

Section: A Unsteady Reynolds-averaged Navier-stokes Noise-source Modelmentioning

confidence: 99%

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Evaluation of a Cascade-Based Acoustic Model for Fan Tonal Noise Prediction

Laborderie

Moreau

2014

AIAA Journal

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This study aims at evaluating an analytical model for the prediction of tonal fan noise created by the rotor-stator interaction. The methodology consists of comparing unsteady flow simulations with the cascade-based acoustic model to quantify the influence of some technological effects not included in the model. The simulations are performed with a dedicated turbomachinery flow solver Turb'Flow on a simplified stator vane cascade. They allow discussing the effects of both model assumptions of no vane thickness and inviscid flow on the predictions of the acoustic sources as well as on the modal acoustic powers radiated within the duct. The Kutta condition is found to be efficient to locally represent the viscosity effects, and the vane thickness tends to moderately modify the distributions of the sources and the amplitudes of the duct modes. Moreover, a three-dimensional decomposition of the aerodynamic excitation is proposed and coupled with the three-dimensional analytical cascade response. This fully three-dimensional acoustic model is evaluated by comparisons with an unsteady simulation of a realistic axial compressor stage. An improvement in the prediction of the acoustic sources and powers is clearly shown with respect to the previously used twodimensional version of the model. Nomenclature a = index of intervane channel acoustic mode B = number of rotor blades C = chord, m c 0 = speed of sound, m · s −1 d = nonoverlapping distance of the cascade, m E m;μ = duct radial function of the mode m; μ e = thickness, m f = force per surface unity, N · m −2 G = Green's function h = normal intervane distance, m j = index of the harmonic of the blade-passing frequency k = index of rectilinear cascade acoustic mode k r = spanwise aerodynamic wave number, m −1 M = Mach number m = order of azimuthal duct mode p = acoustic pressure, Pa p = order of the spanwise aerodynamic wave number S = surface, m 2 s= intervane distance, m T r = duct span, m t = time, s U xc = axial velocity in the rectilinear cascade reference frame, m · s −1 U xd = axial velocity in the duct reference frame, m · s −1 V = number of stator vaneŝ W j = azimuthal Fourier coefficient of w, m · s −1 W j;p = azimuthal and radial Fourier coefficient of w, m · s −1 w = upwash velocity (aerodynamic excitation), m · s −1 x, r, θ = cylindrical coordinates y = dimensionless wall distance ΔP = pressure jump across a flat plate (vane response), Pa μ = order of radial duct mode Π j = tonal acoustic power, W σ = intervane phase angle, rad χ m;μ = duct eigenvalue of the duct mode m; μ, m −1 χ s = vane stagger angle, rad Ω = rotational velocity, rad · s −1 Subscripts c = relative to the cascade reference frame d = relative to the duct reference frame H = relative to hub T = relative to tip

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Section: A Unsteady Reynolds-averaged Navier-stokes Noise-source Modelmentioning

confidence: 84%

Section: A Unsteady Reynolds-averaged Navier-stokes Noise-source Modelmentioning

confidence: 99%

Evaluation of a Cascade-Based Acoustic Model for Fan Tonal Noise Prediction

Laborderie

Moreau

2014

AIAA Journal

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Turbine Tone Noise Prediction Using a Linearized Computational Fluid Dynamics Solver: Comparison With Measurements

González¹,

Aparicio²

2016

Journal of Turbomachinery

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The capability of a linearized computational fluid dynamics (CFD) method for predicting turbine tone noise is investigated through comparison with measurements. To start with, a benchmark problem on flat plates is presented, and results are put together with those published by other authors. Then, numerical predictions are compared with measurements from two low-pressure turbines (LPTs), which have been tested in different facilities. The first specimen is a three-stage cold flow rig, noise tested in the Centro de Tecnologías Aeronáuticas (CTA) facility (Bilbao, Spain) in 2012 and funded by the Clean Sky EU Program. The second is the advanced near-term low emissions (ANTLE) LPT rig, full-scale, cold flow, noise tested in the twin shaft test facility (TSTF) in Rolls-Royce (Derby, UK) in 2005 and funded by the SILENCE(R) EU Funded Program. The comparison includes multistage effects, clocking sensitivities, and acoustic scattering through outlet guide vanes (OGVs).

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