ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Active control mechanism of rotor BVI noise based on IBC method
Received date: 2016-09-01
Revised date: 2016-09-21
Online published: 2016-11-21
Supported by
National Natural Science Foundation of China (11572156);A Project Funded by the Priority Academic Program Development of Jiangsu Higher Education Institutions
A CFD/CSD/FW-H_pds coupling method is established to investigate the mechanism for rotor blade-vortex interaction (BVI) noise reduction based upon individual blade control (IBC) technique. The rotor aeroacoustics is closely related to the blade deformation, the airload characteristic and the blade-tip vortex structure. In order to simulate the blade airload characteristic and blade-tip vortex structure effectively and have better capture ability for separated flows, the Navier-Stokes equations with Spalart-Allmaras turbulence model are adopted as the governing equations for the forward flight flowfield. The third-order MUSCL interpolation scheme and flux-difference splitting Roe scheme are used in spatial discretization, and the dual-time stepping method is employed in temporal discretization while the implicit LU-SGS scheme is used to march in the pseudo time step. In order to improve the calculation accuracy of elastic deformation of blade, a CSD module is developed based on Hamilton's variational principles. Combined with high-accuracy CFD solver, a CFD/CSD coupling strategy is developed to adapt for elastic deformation and load characteristics simulation of blades. Based upon the simulated flowfield by CFD/CSD coupling method, calculations on aeroacoustic characteristics of the rotor are conducted based on the FW-H_pds equations with the penetrable integral surface. The numerical verifications of flowfield and noise analysis methods are first completed. The aeroacoustic characteristics of the UH-60A rotor in oblique descending flight are then calculated with and without IBC. Comparisons of the effects of different control parameters such as phase angle, amplitude and frequency on rotor aeroacoustic characteristics show that with IBC active control, the negative pressure peak of the blade surface (especially the blade-tip surface) in the advancing side decreases, resulting in decrease of the blade airloads where the BVI phenomenon occurs. In addition, with IBC, the blade-tip vortex concentration decreases, and the distance between the blade and the blade-tip vortex increases, resulting in significant reduction of the blade vortex interaction noise. The BVI noise can be reduced about 5-7 dB with reasonable parameter combination of phase angle, amplitude and frequency.
NI Tongbing , ZHAO Qijun , MA Li . Active control mechanism of rotor BVI noise based on IBC method[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017 , 38(7) : 120744 -120744 . DOI: 10.7527/S1000-6893.2016.0284
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