飞行参数对旋翼桨-涡干扰噪声特性的影响机理研究
收稿日期: 2012-12-17
修回日期: 2013-04-26
网络出版日期: 2013-05-17
基金资助
江苏高校优势学科建设工程资助项目;中央高校基本科研业务费专项基金（NS2012035）
Research on the Influence of Flight Parameters on Helicopter Rotor BVI Noise Characteristics
Received date: 2012-12-17
Revised date: 2013-04-26
Online published: 2013-05-17
Supported by
Priority Academic Program Development of Jiangsu Higher Education Institutions(PAPD);Fundamental Research Funds for the Central Universities(NS2012035)
针对旋翼桨-涡干扰（BVI）现象的复杂特征，建立了一个耦合欧拉-拉格朗日数值方法用于干扰过程中脉冲气动载荷的计算。该方法将旋翼流场计算域分为两部分：在桨叶附近区域，通过求解Navier-Stokes方程来模拟流场中旋翼桨尖涡的形成;在尾迹输运区，采用自由尾迹模型表示尾迹涡的运动及其影响。噪声的计算采用基于声学类比法的FW-H方程。应用上述方法以AH-1/OLS旋翼为研究对象，分析了桨盘迎角、前进比和拉力系数3个飞行参数对BVI噪声特性的影响。计算结果表明：BVI噪声具有很强指向性，受桨盘上多处干扰的共同作用，噪声可能向直升机前下方多个方向传播;通过调整下降角度和前飞速度，增大平行干扰的垂直干扰距离，可有效地规避强BVI的出现;拉力系数变化会引起传播方向的改变，而对干扰噪声的强度影响不大。
史勇杰 , 徐国华 . 飞行参数对旋翼桨-涡干扰噪声特性的影响机理研究[J]. 航空学报, 2013 , 34(11) : 2520 -2528 . DOI: 10.7527/S1000-6893.2013.0226
Rotor blade-vortex interaction (BVI) is a complex aerodynamic phenomenon of the helicopter. In this paper, a coupled Eulerian-Lagrangian method is established for impulsive air-loading prediction during interaction. The flow field is divided into two zones. A Navier-Stokes code is used to model the tip vortex formation around the blade, while a free wake model is employed in the vortex transport area to account for the effect of the far wake. The noise prediction is based on the well-known FW-H equation for acoustic pressure. With this method, a parametric study is performed to examine the effects of the descent angle, advance ratio and thrust coefficient on the BVI noise of an AH-1/OLS rotor. BVI noise has the typical feature of impulsivity and strong directivity. It may propagate in multiple directions down and forward of the helicopter because several interaction events occur on the rotor. The BVI noise can be reduced by increasing the miss-distance of parallel interactions with proper descent angle and forward speed adjustment. However, decrease or increase in thrust coefficient changes only the direction of propagation, but not its magnitude.
[1] Yu Y H.Rotor blade-vortex interaction noise.Progress in Aerospace Sciences,2000,36(2): 97-115.
[2] Tung C,Yu Y H.Aerodynamic aspects of blade-vortex interaction (BVI).AIAA-1996-2010,1996.
[3] Yu Y H,Tung C,Gallman J,et al.Aerodynamics and acoustics of rotor blade-vortex interactions; analysis capability and its validation.AIAA-1993-4332,1993.
[4] Chung K.Numerical predictions of rotorcraft unsteady air-loadings and BVI noise by using a time-marching free-wake and acoustic analogy.31st European Rotorcraft Forum,2005.
[5] Strawn R C,Caradonna F X,Duque E P N.30 years rotorcraft computational fluid dynamics research and development.Journal of the American Helicopter Society,2006,51(1): 5-21.
[6] Kim J W,Park S H,Yu Y H.Euler and Navier-Stokes simulations of helicopter rotor blade in forward flight using an overlapped grid solver.AIAA-2009-4268,2009.
[7] Kang H J,Kwon O J.Unstructured mesh Navier-Stokes calculations of the flow field of a helicopter rotor in hover.Journal of the American Helicopter Society,2002,47(2): 90-99.
[8] Gennaretti M,Bernardini G.Novel boundary integral formulation for blade-vortex interaction aerodynamics of helicopter rotors.AIAA Journal,2007,45(6): 1169-1176.
[9] Hu H,Jordan L A,Bader J D.CFD investigation of double-swept blade in BVI noise reduction.AIAA-2003-3172,2003.
[10] McAlister K W,Tung C,Heineck J T.Forced diffusion of trailing vorticity from a hovering rotor.Proceedings of 57th Annual Forum of AHS,2001.
[11] van der Wall B G,Yin J P.Prediction of BVI noise radiation variation due to HHC using advanced prescribed wake methodology.Proceedings of 68th Annual Forum of AHS,2012.
[12] Fogarty D E,Wibur M L,Sekula M K,et al.Prediction of BVI noise for an active twist rotor using a loosely coupled CFD/CSD method and comparison to experimental data.Proceedings of 68th Annual Forum of AHS,2012.
[13] Schmitz F H,Sim B W.Radiation and directionality characteristics of helicopter blade-vortex interaction noise.Journal of the American Helicopter Society,2003,48(4): 253-269.
[14] Farassat F,Succi G P.The prediction of helicopter rotor discrete frequency noise.Vertica,1983,17(4): 309-320.
[15] Roe P L.Approximate Riemann solvers,parameter vectors,and difference schemes.Journal of Computational Physics,1981,43(2): 357-372.
[16] Luo H,Baum J D.A fast,matrix-free implicit method for computing low Mach number flows on unstructured grids.AIAA-1999-3315,1999.
[17] Xu G H,Newman S J.A full-span free-wake model using circular-arc vortex elements and incorporating rotor trim analysis.Proceeding of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering,2006,220(2): 145-153.
[18] Shi Y J,Zhao Q J,Xu G H.Numerical calculation and parametric study of aerodynamics of rotor blade-vortex interaction.Acta Aeronautica Astronautica Sinica,2010,31(6): 1106-1114.(in Chinese) 史勇杰,招启军,徐国华.旋翼桨-涡干扰气动特性计算及参数影响研究.航空学报,2010,31(6): 1106-1114.
[19] Boxwell D A,Schmitz F H,Splettstoesser W R,et al.Helicopter model rotor-blade vortex interaction impulsive noise: scalability and parametric variations.Journal of the American Helicopter Society,1987,32(1): 5-12.
[20] Shi Y J,Zhao Q J,Xu G H.An analytical study of parametric effects on rotor-vortex interaction noise.Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering,2011,225(3): 259- 268.
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