共轴刚性旋翼流场测量试验研究
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摘要
利用粒子图像测速(Particle image velocimetry,PIV)试验技术,开展了共轴刚性旋翼桨尖涡尾迹以及桨叶周围流场的测量试验,获得了单/双旋翼桨尖涡的运动轨迹以及桨尖诱导速度分布,研究了旋翼前进比对尾迹边界倾斜角的影响规律,进行了大前进比下强径向流对桨叶周围流场的影响机理研究。结果表明:强径向流具有增强气流附着性、减缓气流分离以及延迟失速的特性,前进比μ=0.64比μ=0.53后缘分离点延迟了约18%;后行侧反流区前进比越大反流强度越强;悬停状态双/上旋翼涡收缩性最快,单旋翼尾迹涡收缩性次之,下旋翼尾迹涡收缩性最慢。测量结果合理可信,为开展旋翼流动机理理论研究及提高CFD分析精度奠定了基础。
The particle image velocimetry(PIV)experimental technology is used in the experiments to measure the co-axial rigid rotor blade vortex wake and flow field around the blade. From these experiments,the blade vortex trajectory and the blade tip induction velocity distribution of the single/dual rotor are obtained. The influence rule of the rotor forward ratio on the offset angle of trail boundary is revealed. The influence mechanism of the strong radial flow on the flow field around the blade is researched. The results show that the strong radial flow can enhance airflow adhesion,delay airflow separation and stalling. Besides,the trailing edge separation piont is dalayed about 18% at the 0.64 forward ratio compared to 0.53.The greater the forward ratio of the rear side reverse flow region is,the stronger the reflow intensity is. In hover,the upper-rotor vortex of the dual rotor vortex contract fastest,the single rotor vortex contract second,and the lower-rotor vortex of the dual rotor contract slowest. The measurement result is reasonable and reliable,which lays the foundation for theoretical research of rotor flow mechanism and improvement of CFD analysis accuracy.
The particle image velocimetry(PIV)experimental technology is used in the experiments to measure the co-axial rigid rotor blade vortex wake and flow field around the blade. From these experiments,the blade vortex trajectory and the blade tip induction velocity distribution of the single/dual rotor are obtained. The influence rule of the rotor forward ratio on the offset angle of trail boundary is revealed. The influence mechanism of the strong radial flow on the flow field around the blade is researched. The results show that the strong radial flow can enhance airflow adhesion,delay airflow separation and stalling. Besides,the trailing edge separation piont is dalayed about 18% at the 0.64 forward ratio compared to 0.53.The greater the forward ratio of the rear side reverse flow region is,the stronger the reflow intensity is. In hover,the upper-rotor vortex of the dual rotor vortex contract fastest,the single rotor vortex contract second,and the lower-rotor vortex of the dual rotor contract slowest. The measurement result is reasonable and reliable,which lays the foundation for theoretical research of rotor flow mechanism and improvement of CFD analysis accuracy.
引文
[1]BURGESS R K.The ABC? rotor-A historical perspective[C]//American Helicopter Society 60th Annual Forum.Baltimore,MD:AHS,2004:7-10.
[2]CHENEY M C.The ABC helicopter[J].Journal of the American Helicopter Society,1969,14(4):10-19.
[3]PAGLINO V M,BENO E A.Full-scale wind tunnel investigation of the advancing blade concept rotor system[R].SER-50705,1971.
[4]BURGESS R K.Development of the ABC Rotor[C]//Proceedings of the 27th American Helicopter Society Forum.Washington,D C:AHS,1971:15-18.
[5]ARENTS D N.An assessment of the hover performance of the XH-59A advancing blade concept demonstration helicopter[R].USAAMRDL-TN-25,1977.
[6]PHELPS III A E,MINECK R E.Aerodynamic characteristics of a counter-rotating coaxial hingeless rotor helicopter model with auxiliary propulsion[R].NASA-TM-78705,1978.
[7]RUDDELL A J,GROTH W,MCCUTCHEON R.Advancing blade concept(ABC)technology demonstrator[R].USAAVR ADCOM-TR-81-D-5,1981.
[8]COLEMAN C P.A survey of theoretical and experimental coaxial rotor aerodynamic research[R].NASA TP 3675,1997.
[9]LIM J W,MCALISTER K W,JOHNSON W.Hover performance correlation for full-scale and modelscale coaxial rotors[J].Journal of the American Helicopter Society,2009,54(3):32005.
[10]HIRSCHBERG M.Sikorsky pushes forward with X2technology demonstrator[J].Vertiflite,2005,51(3):12-14.
[11]李建波.复合式直升机技术发展分析[J].南京航空航天大学学报,2016,48(2):149-158.LI Jianbo.Progress of compound helicopter technology[J].Journal of Nanjing University of Aeronautics&Astronautics,2016,48(2):149-158.
[12]邓景辉.高速直升机前行桨叶概念旋翼技术[J].航空科学技术,2012(3):9-14.DENG Jinghui.The ABC rotor technology for high speed helicopter[J].Aeronautical science&Technology,2012(3):9-14.
[13]吴希明.高速直升机发展现状、趋势与对策[J].南京航空航天大学学报,2015,47(2):173-179.WU Ximing.Current status,development trend and countermeasure for high-speed rotorcraft[J].Journal of Nanjing University of Aeronautics&Astronautics,2015,47(2):173-179.
[14]邓彦敏,陶然,胡继忠.共轴式直升机上下旋翼之间气动干扰的风洞实验研究[J].航空学报,2003,24(1):10-14.DENG Yanmin,TAO Ran,HU Jizhong.Experimental investigation of the aerodynamic interaction between upper and lower rotors of a coaxial helicopter[J].Acta Aeronautica et Astronautica Sinica,2003,24(1):10-14.
[15]马杨超,于世美,邓彦敏.共轴式双旋翼悬停诱导速度场的PIV试验研究[J].实验流体力学,2012,26(1):16-20.MA Yangchao,YU Shimei,DENG Yanmin.PIV experimental investigation of coaxial rotor induced velocity field in hover[J].Journal of Experimental in Fluid Mechanics,2012,26(1):16-20.
[2]CHENEY M C.The ABC helicopter[J].Journal of the American Helicopter Society,1969,14(4):10-19.
[3]PAGLINO V M,BENO E A.Full-scale wind tunnel investigation of the advancing blade concept rotor system[R].SER-50705,1971.
[4]BURGESS R K.Development of the ABC Rotor[C]//Proceedings of the 27th American Helicopter Society Forum.Washington,D C:AHS,1971:15-18.
[5]ARENTS D N.An assessment of the hover performance of the XH-59A advancing blade concept demonstration helicopter[R].USAAMRDL-TN-25,1977.
[6]PHELPS III A E,MINECK R E.Aerodynamic characteristics of a counter-rotating coaxial hingeless rotor helicopter model with auxiliary propulsion[R].NASA-TM-78705,1978.
[7]RUDDELL A J,GROTH W,MCCUTCHEON R.Advancing blade concept(ABC)technology demonstrator[R].USAAVR ADCOM-TR-81-D-5,1981.
[8]COLEMAN C P.A survey of theoretical and experimental coaxial rotor aerodynamic research[R].NASA TP 3675,1997.
[9]LIM J W,MCALISTER K W,JOHNSON W.Hover performance correlation for full-scale and modelscale coaxial rotors[J].Journal of the American Helicopter Society,2009,54(3):32005.
[10]HIRSCHBERG M.Sikorsky pushes forward with X2technology demonstrator[J].Vertiflite,2005,51(3):12-14.
[11]李建波.复合式直升机技术发展分析[J].南京航空航天大学学报,2016,48(2):149-158.LI Jianbo.Progress of compound helicopter technology[J].Journal of Nanjing University of Aeronautics&Astronautics,2016,48(2):149-158.
[12]邓景辉.高速直升机前行桨叶概念旋翼技术[J].航空科学技术,2012(3):9-14.DENG Jinghui.The ABC rotor technology for high speed helicopter[J].Aeronautical science&Technology,2012(3):9-14.
[13]吴希明.高速直升机发展现状、趋势与对策[J].南京航空航天大学学报,2015,47(2):173-179.WU Ximing.Current status,development trend and countermeasure for high-speed rotorcraft[J].Journal of Nanjing University of Aeronautics&Astronautics,2015,47(2):173-179.
[14]邓彦敏,陶然,胡继忠.共轴式直升机上下旋翼之间气动干扰的风洞实验研究[J].航空学报,2003,24(1):10-14.DENG Yanmin,TAO Ran,HU Jizhong.Experimental investigation of the aerodynamic interaction between upper and lower rotors of a coaxial helicopter[J].Acta Aeronautica et Astronautica Sinica,2003,24(1):10-14.
[15]马杨超,于世美,邓彦敏.共轴式双旋翼悬停诱导速度场的PIV试验研究[J].实验流体力学,2012,26(1):16-20.MA Yangchao,YU Shimei,DENG Yanmin.PIV experimental investigation of coaxial rotor induced velocity field in hover[J].Journal of Experimental in Fluid Mechanics,2012,26(1):16-20.