Prediction of Noise Sources in Axial Compressor from URANS Simulation

Laborderie, Jerome de; Soulat, Laurent; Moreau, Stéphane

doi:10.2514/1.b35000

Cited by 12 publications

(12 citation statements)

References 27 publications

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“…The original grid distribution of 20 points per wavelength used in a previous study [26] has not been found to be enough for the plate response at 3 BPF, the levels of which are very sensitive to this numerical parameter (30-40 points needed). For the viscous flow calculations, the dimensionless distance to the plate y is found to be below 5 for most of the streamwise positions, with a maximum around 9 near the leading edge, which is consistent with the parallel simulation on the CME2 stage [15,16]. The grids at midspan for the thick and thin-plate cascades are shown in Figs.…”

Section: A Geometry Of the Annular Flat-plate Cascade And Simulationsupporting

confidence: 53%

“…7a. The mean compressor flowfield has been validated against experimental and other numerical data [15,16]. The boundary layers on the rotor blades develop in wakes downstream of the trailing edge and are convected with the mean flow.…”

Section: Cme2 Compressor-stage Unsteady Reynolds-averaged Navierstmentioning

confidence: 99%

“…A URANS simulation of the CME2 compressor stage performed by Soulat et al [15] and de Laborderie et al [16] is used within this study. This subsonic low-pressure axial compressor stage is composed of a 30-blade rotor and a 40-vane stator mounted in a R H ∕R T 0.77 hub-to-tip ratio annular duct.…”

Section: Cme2 Compressor-stage Unsteady Reynolds-averaged Navierstmentioning

confidence: 99%

“…III.B). The second step consists of using a simulation of a realistic compressor stage [15,16]. The so-called CME2 compressor has been the object of several investigations [31,32], and its main flow characteristics are presented in Sec.…”

Section: Unsteady Simulationsmentioning

confidence: 99%

“…As a first step, three successive aerodynamic simulations of an annular flat-plate cascade allow the evaluation of the vane-thickness effect and the flow viscosity effect on the acoustic sources located on the vane surfaces. Then, the effects of the real vane geometry and flow conditions are assessed on an axial compressorstage simulation performed and validated by Soulat et al [15] and de Laborderie et al [16]. The influence of the 3-D gusts on the acoustic model are also surveyed on this realistic test case.…”

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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 Geometry Of the Annular Flat-plate Cascade And Simulationsupporting

confidence: 53%

Section: Cme2 Compressor-stage Unsteady Reynolds-averaged Navierstmentioning

confidence: 99%