Investigation of rotor–stator interaction broadband noise using a RANS-informed analytical method

Tong, Hang; Li, Lin; Wang, Liangfeng; Mao, Luqin; Qiao, Weiyang

doi:10.1016/j.cja.2021.02.003

Cited by 8 publications

(11 citation statements)

References 23 publications

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“…The source region is modeled with the Unsteady Reynolds Averaged Navier-Stokes equations (URANS). 41 The grid size in the source region is imposed by the smallest aerodynamic length scale and the simulation of this region is the most time-consuming part of the HCAA method. In the acoustic near-field, the acoustic waves propagate in non-uniform mean flow, and linearized Euler equations are used.…”

Section: Computational Methods For the Acoustic Source Region And Aco...mentioning

confidence: 99%

Numerical study on the noise propagation characteristics of rotor in non-uniform downwash flowfield Based on Linearized Euler Equations

Yang

Chen

Zhao

et al. 2022

International Journal of Aeroacoustics

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To study the influence of non-uniform flowfield on the propagation characteristics of helicopter rotor noise, a Hybrid Computational Aeroacoustics (HCAA) method is developed. The acoustic source region is simulated by Computational Fluid Dynamics (CFD) technique with the Unsteady Reynolds Averaged Navier-Stokes equations (URANS) as the governing equations. Acoustic near-field is simulated by Computational Aeroacoustics (CAA) technique with the Linearized Euler Equations (LEE) as the governing equations, and the numerical discretization of the LEE is accomplished by Runge-Kutta Discontinuous Galerkin (RKDG) method. A novel acoustic source extraction method based on pressure and pressure gradient is proposed to accomplish the one-way CFD-CAA weak coupling. The HCAA method is validated through comparisons with noise experimental data of the UH-1H model rotor and the BO-105 model rotor. Based on the proposed HCAA method, the convection and refraction effects of rotor noise under different collective pitch angles are analyzed. The results show that the distortion effect of the rotor noise is most affected by the non-uniformly distributed downwash velocity field, resulting in an increment of acoustic energy below the rotor plane. The effect of non-uniformly distributed downwash velocity on noise propagation increases with the increase of the collective pitch angle. For the UH-1H model rotor, the maximum change of the sound pressure level is 0.8 dB (about 10% change of the effective sound pressure).

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Section: Computational Methods For the Acoustic Source Region And Aco...mentioning

confidence: 99%

Numerical study on the noise propagation characteristics of rotor in non-uniform downwash flowfield Based on Linearized Euler Equations

Yang

Chen

Zhao

et al. 2022

International Journal of Aeroacoustics

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“…The broadband noise prediction method is based on the results of the RANS method that was introduced by Tong [16]. (c) The unsteady load of the vane surface at different radial positions is combined with the basic theory of duct acoustics, and the acoustic power in the duct is solved by integrating the whole annular duct.…”

Section: Broadband Noise Prediction Modelmentioning

confidence: 99%

“…They pointed out that the maximum noise reduction that can achieved is 8.6 dB and 3.7 dB in the frequency bands of 315~4000 Hz and 6300~16,000 Hz, respectively. A Reynolds-averaged Navier-Stokes (RANS) information analytical method for predicting Rotor-Stator Interaction (RSI) broadband noise was established by Tong et al [16]. And based on the RANS-informed analytical method, they studied the effect of wavy leading edges on RSI broadband noise.…”

Section: Introductionmentioning

confidence: 99%

Broadband Noise Reduction of a Two-Stage Fan with Wavy Trailing-Edge Blades

Gao,

Chen,

Tong

et al. 2024

Aerospace

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In this paper, a numerical investigation is performed to study the broadband noise of a fan stage with wavy trailing-edge blades. A study of the wavelength and ratio of amplitude to wavelength (H/L) is conducted to better understand the noise reduction effect of wavy trailing-edge blades. A rotor–stator interaction broadband noise prediction method based on the result of a Reynolds-averaged Navier–Stokes equation is used. The results show that all wavy trailing-edge configurations reduce the sound power level of the fan stage. The noise reduction effect of H20L10 is the best among all the wavy trailing-edge configurations, and the sound power level is reduced by 2.4 dB at 1000 Hz. When the H/L remains unchanged, the noise reduction effect of the wavy trailing-edge configuration increases with the increase in wavelength. When the wavelength remains unchanged, the noise reduction effect of the wavy trailing-edge configuration with an H/L of 2 is the best. The use of wavy trailing-edge configurations reduces the turbulent kinetic energy and turbulent integral length scale upstream of the stator by changing the wake of the rotor, thereby reducing the rotor–stator interaction broadband noise of the fan stage.

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“…However, the turbulence information as input in most traditional analytical models is empirical. To resolve this issue, the RANS-informed analytical method [19][20][21][22][23] has been the focus of many studies. Its time-and-resourcesaving ability compared with numerical methods, and higher-robustness compared with traditional analytical models, improves the RANS-informed analytical method's prospects.…”

Section: Introductionmentioning

confidence: 99%

“…In 1973, Smith [33] proposed a fundamental and groundbreaking method called LINSUB to calculate unsteady blade lift, moment and acoustic waves for unsteady, subsonic flow through an infinite, two-dimensional cascade of flat plate blades at zero mean incidence. Many following works, like Hanson [37,38], Cheong [39], Ju [19,20] and Tong [23], were all built on the basis of LINSUB.…”

Section: Introductionmentioning

confidence: 99%

A Rapid RI-TP Model for Predicting Turbine Wake Interaction Broadband Noise

Xiang,

Chen,

Aneeb

et al. 2024

Aerospace

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Future UHBR (Ultra-High Bypass-Ratio) engines might cause serious ‘turbine noise storms’ but, at present, turbine noise prediction capability is lacking. The large turning angle of the turbine blade is the first major factor deserving special attention. The RANS (Reynold Averaged Navier–Stokes equation)-informed (here called RI) method and LINSUB (the bound vorticity 2D model LINearized SUBsonic flow in cascade), developed to predict fan broadband noise, coupled with a two-flat-plates (here called TP) assumption for the turbine blade, is applied here, and one autonomous rapid RI-TP model for predicting turbine wake interaction broadband noise has been developed. Firstly, taking the single axial turbine test rig NPU-Turb as the object, both the experimental data and the DDES/AA (delayed Detached Eddy Simulation/Acoustic Analogy) hybrid model have been used to validate the RI-TP model. High consistency in the medium and high frequencies among the three designed and off-designed rotation speeds indicates that the RI-TP model has the ability to predict turbine broadband noise rapidly. And compared with the original RANS-informed method, with one thin-flat-plate assumption on the blade, the RI-TP model can enhance the PWL (sound power level) in almost the whole spectral range below 10 KHz, which, in turn, is closer to the experimental data and the DDES/AA prediction results. The PWL trend with a ‘dividing point’ position is also studied. The spectrum would move up or down if the location is away from true value. In addition, the extraction location for turbulence as an input for the RI-TP model is negligible. In the future, multi-stage characteristics and the blade thickness effect should be further considered when predicting turbine noise.

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Investigation of rotor–stator interaction broadband noise using a RANS-informed analytical method

Cited by 8 publications

References 23 publications

Numerical study on the noise propagation characteristics of rotor in non-uniform downwash flowfield Based on Linearized Euler Equations

Numerical study on the noise propagation characteristics of rotor in non-uniform downwash flowfield Based on Linearized Euler Equations

Broadband Noise Reduction of a Two-Stage Fan with Wavy Trailing-Edge Blades

A Rapid RI-TP Model for Predicting Turbine Wake Interaction Broadband Noise

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