Noise mechanisms in a transonic high-pressure turbine stage

Wang, Gaofeng; Sanjosé, Marlène; Moreau, Stéphane; Papadogiannis, Dimitrios; Duchaine, Florent; Gicquel, Laurent

doi:10.1177/1475472x16630870

Cited by 17 publications

(12 citation statements)

References 43 publications

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“…These schemes are used in conjunction with Hermitian interpolation for the data exchange at the overlap zone, ensuring low dissipation and low dispersion of the rotor/stator interactions, while preserving the global order of accuracy of the employed numerical scheme. Initial flow solutions and grid studies were obtained with the Lax-Wendroff (LW) finite volume scheme [78] with second-order accuracy in time and space [73,75,79]. For the boundary conditions on the computational domain, Navier-Stokes Characterisitic Boundary Conditions (NSCBC) are crucially used to prevent any reflection that may corrupt the acoustic field [80].…”

Section: Methodsmentioning

confidence: 99%

Turbomachinery Noise Predictions: Present and Future

Moreau

2019

Acoustics

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In future Ultra-High By-Pass Ratio turboengines, the turbomachinery noise (fan and turbine stages mainly) is expected to increase significantly. A review of analytical models and numerical methods to yield both tonal and broadband contributions of such noise sources is presented. The former rely on hybrid methods coupling gust response over very thin flat plates of finite chord length, either isolated or in cascade, and acoustic analogies in free-field and in a duct. The latter yields tonal noise with unsteady Reynolds-Averaged Navier–Stokes (u-RANS) simulations, and broadband noise with Large Eddy Simulations (LES). The analytical models are shown to provide good and fast first sound estimates at pre-design stages, and to easily separate the different noise sources. The u-RANS simulations are now able to give accurate estimates of tonal noise of the most complex asymmetric, heterogeneous fan-Outlet Guiding Vane (OGV) configurations. Wall-modeled LES on rescaled stage configurations have now been achieved on all components: a low-pressure compressor stage, a transonic high-pressure turbine stage and a fan-OGV configuration with good overall sound power level predictions for the latter. In this case, hybrid Lattice–Boltzmann/very large-eddy simulations also appear to be an excellent alternative to yield both contributions accurately at once.

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Section: Methodsmentioning

confidence: 99%

Turbomachinery Noise Predictions: Present and Future

Moreau

2019

Acoustics

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“…The code AVBP [21] is used for the compressible LES. It has been extensively validated against multiple turbomachinery cases, including both aerodynamic and aeroacoustic ones [6,7,20,22]. The Taylor-Galerkin scheme TTG4A [23] that is 3rd order accurate in space and 4th order in time is used.…”

Section: Numerical Modelmentioning

confidence: 99%

“…Despite a number of remaining uncertainties, the numerical simulation allows studying these noise sources in realistic configurations [6][7][8] by resolving the flow field numerically and either computing directly or modeling the corresponding noise contributions [4]. Only a few numerical studies are devoted to the fan broadband noise.…”

Section: Introductionmentioning

confidence: 99%

Identification of Noise Sources in a Realistic Turbofan Rotor Using Large Eddy Simulation

Kholodov

Moreau

2020

Acoustics

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Large Eddy Simulation is performed using the NASA Source Diagnostic Test turbofan at approach conditions (62% of the design speed). The simulation is performed in a periodic domain containing one fan blade (rotor-alone configuration). The aerodynamic and acoustic results are compared with experimental data. The dilatation field and the dynamic mode decomposition (DMD) are employed to reveal the noise sources around the rotor. The trailing-edge radiation is effective starting from 50% of span. The strongest DMD modes come from the tip region. Two major noise contributors are shown, the first being the tip noise and the second being the trailing-edge noise. The Ffowcs Williams and Hawkings’ (FWH) analogy is used to compute the far-field noise from the solid surface of the blade. The analogy is computed for the full blade, for its tip region (outer 20% of span) and for lower 80% of span to see the contribution of the latter. The acoustics spectrum below 6 kHz is dominated by the tip part (tip noise), whereas the rest of the blade (trailing-edge noise) contributes more beyond that frequency.

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“…The ratio seems to be reverted at higher frequencies, as shown by Duran and Moreau [6]. Wang et al [7] studied the indirect noise generated by plane entropy waves in a realistic high-pressure turbine stage using large-eddy simulations. Strong acoustic waves were found at the excitation frequency and the frequencies scattered around the blade passing frequency and its harmonics.…”

Section: Introductionmentioning

confidence: 87%

CFD-Based Investigation of Turbine Tonal Noise Induced by Steady Hot Streaks †

Holewa

Lesnik

Ashcroft

et al. 2017

IJTPP

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Abstract:The interaction of steady hot streaks from an annular ring of combustion chambers with turbine rotating blades can potentially generate tonal noise. The relevance of this source mechanism in aeroengine noise is controversially discussed in the literature. In the present paper, the streak-turbine interaction is investigated using the computational fluid dynamics (CFD) method called harmonic balance (HB)-a truncated non-linear frequency domain approach with a high potential of reducing the computational effort. The investigated high-pressure turbine is composed of a single stator-rotor stage. The first part of the present paper compares the results obtained with the HB method to those obtained with the more established time-accurate unsteady Reynolds-averaged Navier-Stokes (URANS) approach and investigates their sensitivity with respect to the computational mesh density. Thereby, no streaks are simulated, and only the turbine alone tones are considered. Convincing results are obtained on aerodynamics and acoustics. The second part of the paper deals with a parametric study on the acoustical impact of steady hot streaks. The streaks are prescribed at the inlet of the stage using a boundary condition as an attempt to simulate a ring of combustor nozzles. No vorticity is coupled into the computational domain, as the objective is to measure the effect of temperature inhomogeneity only. Overall, the turbine appears to be slightly quieter with hot streaks. The streak-to-stator-vane ratio of 1-to-2 explains the generation of new acoustic modes with distinct azimuthal orders. The acoustic power amplitude of those additional modes scales roughly with the square of the temperature difference, the fourth-power of the diameter, and the square of the entropy difference. This last result agrees well with the 1D theory of Marble and Candel. The acoustic contribution of the unsteady force on the rotor blades due to the overspeed measured in the wakes of the streaks-resulting from the flow acceleration through the stator-remains an open question.

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Noise mechanisms in a transonic high-pressure turbine stage

Cited by 17 publications

References 43 publications

Turbomachinery Noise Predictions: Present and Future

Turbomachinery Noise Predictions: Present and Future

Identification of Noise Sources in a Realistic Turbofan Rotor Using Large Eddy Simulation

CFD-Based Investigation of Turbine Tonal Noise Induced by Steady Hot Streaks †

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