旋翼桨尖气动/降噪综合优化设计研究  

An Effective Aerodynamics/Acoustic Optimization of Blade Tip Planform for Helicopter Rotors

作　　者：郭旺柳[1] 宋文萍[1] 许建华[1] 许瑞飞[1] 

机构地区：[1]西北工业大学翼型/叶栅空气动力学国家重点实验室,陕西西安710072

出　　处：《西北工业大学学报》2012年第1期73-79,共7页Journal of Northwestern Polytechnical University

基　　金：西北工业大学翼型叶栅空气动力学国家重点实验室基金(9140C4201020802)资助

摘　　要：采用Kriging模型和遗传算法开展了针对桨尖形状的气动/声学综合优化设计研究。为了获得精确的气动及声压特性,得到基于声类比混合方法计算气动噪声需要的声源数据,采用非定常雷诺平均NS方程(URANS)数值模拟旋翼前飞粘性绕流。为了提高遗传算法的优化效率,采用一种基于EI方法的Kriging模型代替费时的数值模拟过程。以AH-1G/OLS旋翼为基准,并以气动性能为约束,噪声峰值最小为目标,进行了旋翼桨尖的降噪优化设计。优化结果表明,文中多发展的优化方法是可行的。Sections 1,2 and 3 of the full paper explain the optimization mentioned in the title, which we believe is more effective than previous ones. Their core consists of： ＂The aerodynamic/acoustic optimization of rotor blade tip shape is studied with the genetic algorithm based on the Kriging model. To obtain accurately aerodynamic performance and acoustic pressure, the flow around helicopter rotor in forward flight is simulated by solving URANS（ unsteady Reynolds-Averaged Navier-Stokes） equations on a chimera grid system, then the solution on the intermeadial grid is used to solve FW-Hpds （Ffowcs Williams-Hawkings ing model, which is built by using LHS （Latin Hypercube equation with Penetrable Data Surface） equation. Krig- Sampling） to produce sample points, is used to improve computational efficiency, thus making it possible to accomplish the optimization process successfully＂. Optimization based on AH-1/OLS rotor in forward flight is accomplished with the aerodynamic performance as a constraint and with the minimization of the absolute sound pressure peak value taken as an objective function. The optimized simulation results, presented in Figs. 7 through 14 and Tables 1 through 4, and their analysis show preliminarily that our optimization method is indeed effective.

关 键 词：旋翼 噪声 优化设计 雷诺平均NS方程 KRIGING模型 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]