基于IBC方法的旋翼BVI噪声主动控制机理

doi:10.7527/S1000-6893.2016.0284

Abstract

Abstract:

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.

Key words: rotor, blade-vortex interaction (BVI) noise, noise active control, Navier-Stokes equations, FW-H_pds method, CFD/CSD coupling method, individual blade control (IBC)

CLC Number:

V211.52

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.

References

[1] YANG C, AOYAMA T, CHAE S. Blade planform optimization to reduce HSI noise of helicopter in hover[C]// 64th Annual Forum of the American Helicopter Society. Fairfax, VA: American Helicopter Society (AHS) International, Inc., 2008.
[2] JOHNSON C, BARAKOS G N. A framework for the optimization of a BERP-like blade[C]//51st AIAA Aerospace Science Meeting. Reston: AIAA, 2013.
[3] MEGAN S M. Helicopter blade-vortex interaction noise with comparisons to CFD calculations: NASA-TM-110423[R]. Washington,D.C.: NASA, 1996.
[4] YU Y H. Rotor blade-vortex interaction noise[J]. Progress in Aerospace Science, 2000, 36(2): 97-115.
[5] TANGLER J L, WOBLFELD R M, MILEY S J. An experimental investigation of vortex stability, tip shapes, compressibility and noise for hovering model rotors: NASA-CR-2305[R]. Washington, D.C.: NASA, 1973.
[6] 史勇杰,苏大成,徐国华. 桨叶气动外形对直升机桨-涡干扰噪声影响研究[J]. 南京航空航天大学学报, 2015, 47(2): 235-242. SHI Y J, SU D C, XU G H. Research on influence of shape parameters on blade-vortex interaction noise of helicopter rotor[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2015, 47(2): 235-242 (in Chinese).
[7] POLYCHRONIADIS M, ACHACHE M. Higher harmonic control: Flight tests of an experimental system on SA349 research gazelle[C]//42nd Annual Forum of the American Helicopter Society, 1986.
[8] SPLETTSTOESSER W R, SCHULTZ K J, KUBE R, et al. A higher harmonic control test in the DNW to reduce impulsive BVI noise[J]. Journal of the American Helicopter Society, 1994, 39(4):3-13.
[9] SPLETTSTOESSER W R, KUBE R, WAGNER W, et al. Key results from a higher harmonic control aeroacoustic rotor test (HART) in the German-Dutch wind tunnel[J]. Journal of the American Helicopter Society, 1997, 42(1):58-78.
[10] NIESL G, SWANSON S M, JACKLIN S A, et al. Effect of individual blade control on noise radiation[C]//75th AGARD Fluid Dynamics Panel Meeting and Symposium on Aerodynamics and Aeroacoustics of Rotorcraft. Paris:AGARD, 1994.
[11] SWANSON S M, JACKLIN S A, BLAAS A, et al. Individual blade control effects on blade-vortex interaction noise[C]//50th Annual Forum of the American Helicopter Society. Fairfax, VA: American Helicopter Society (AHS) International, Inc., 1994.
[12] YEO H, ROMANDER E A, NORMAN T R. Investigation of rotor performance and loads of a UH-60A individual blade control system[J]. Journal of the American Helicopter Society, 2011, 56(4):1-18.
[13] SPLETTSTÖ ßER W R, SCHULTZ K J, VAN DER WALL B G, et al. Helicopter noise reduction by individual blade control (IBC)-selected flight test and simulation results[C]//RTO/AVT Symposium on Active Control Technology for Enhanced Performance Operational Capabilities of Military Aircraft, Land Vehicles and Sea Vehicles, 2000.
[14] 冯剑波, 陆洋, 徐锦法, 等. 旋翼桨涡干扰噪声开环桨距主动控制研究[J]. 航空学报, 2014, 35(11): 2901-2909. FENG J B, LU Y, XU J F, et al. Research on the effect of open-loop active blade-pitch control on rotor BVI noise alleviation[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(11): 2901-2909 (in Chinese).
[15] ROE P L. Approximate riemann solvers, parameters vectors, and difference schemes[J]. Journal of Computational Physics, 1981, 43(2): 357-372.
[16] WANG B, ZHAO Q J, XU G H, et al. Numerical analysis on noise of rotor with unconventional blade tips based on CFD/Kirchhoff method[J]. Chinese Journal of Aeronautics, 2013, 26(3): 572-582.
[17] BLAZEK J. Computational fluid dynamics: Principles and applications[M]. Netherlands: Elsevier, 2001: 204-208.
[18] SPALART P R, ALLMARAS S R. A one-equation turbulence model for aerodynamic flows: AIAA-1992-0439[R]. Reston: AIAA, 1992.
[19] YUAN K A, FRIEDMANN P P. Aeroelasticity and structural optimization of composite helicopter rotor blades with swept tips: NASA-CR-4665[R]. Washington, D.C.: NASA, 1995.
[20] BRENTNER K S, FARASSAT F. Analytical comparison of the acoustic analogy and Kirchhoff formulation for moving surfaces[J]. AIAA Journal, 1998, 36(8): 1379-1386.
[21] POTSDAM M, YEO H, JOHNSON W. Rotor airloads prediction using loose aerodynamic/structural coupling[J]. Journal of Aircraft, 2004, 43(3): 732-742.
[22] YU Y H, TUNG C, GALLMAN J, et al. Aerodynamics and acoustics of rotor blade-vortex interactions[J]. Journal of Aircraft, 1995, 32(5): 970-977.

Active control mechanism of rotor BVI noise based on IBC method

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