论文:2012,Vol:30,Issue(1):73-79
引用本文:
郭旺柳, 宋文萍, 许建华, 许瑞飞. 旋翼桨尖气动/降噪综合优化设计研究[J]. 西北工业大学
Guo Wangliu, Song Wenping, Xu Jianhua, Xu Ruifei. An Effective Aerodynamics/Acoustic Optimization of Blade Tip Planform for Helicopter Rotors[J]. Northwestern polytechnical university

旋翼桨尖气动/降噪综合优化设计研究
郭旺柳, 宋文萍, 许建华, 许瑞飞
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
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。
关键词:    旋翼    噪声    优化设计    雷诺平均 NS 方程    Kriging 模型   
An Effective Aerodynamics/Acoustic Optimization of Blade Tip Planform for Helicopter Rotors
Guo Wangliu, Song Wenping, Xu Jianhua, Xu Ruifei
National Key Laboratory of Science and Technology on Aerodynamic Design and Research,Northwestern Polytechnical University,Xi'an 710072,China
Abstract:
Sections 1, 2 and 3 of the full paper explain the optimization mentioned in the title,which we believe ismore effective than previous ones.Their core consists of: "The aerodynamic/acoustic optimization of rotor blade tipshape is studied with the genetic algorithm based on the Kriging model.To obtain accurately aerodynamic perform-ance and acoustic pressure,the flow around helicopter rotor in forward flight is simulated by solving URANS (Un-steady Reynolds-Averaged Navier-Stokes) equations on a chimera grid system,then the solution on the intermeadialgrid is used to solve FW-Hpds (Ffowcs Williams-Hawkings equation with Penetrable Data Surface) equation.Krig-ing model,which is built by using LHS (Latin Hypercube Sampling) to produce sample points,is used to improvecomputational efficiency,thus making it possible to accomplish the optimization process successfully".Optimizationbased on AH-1/OLS rotor in forward flight is accomplished with the aerodynamic performance as a constraint andwith the minimization of the absolute sound pressure peak value taken as an objective function.The optimized simu-lation results, presented in Figs.7 through 14 and Tables 1 through 4, and their analysis show preliminarily that ouroptimization method is indeed effective.
Key words:    aerodynamics    algorithm    analysis    calculations    compressible flow    computational fluid dynamics    design    efficiency    errors    helicopter rotors    improvement    models    Navier-Stokes equations    numeri-cal methods    optimization    pressure distribution    Reynolds number    sampling    shock waves    simula-tion    unsteady flow    Kriging model   
收稿日期: 2011-04-06     修回日期:
DOI:
基金项目: 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
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作者简介: 郭旺柳(1985-),西北工业大学硕士研究生,主要从事旋翼气动噪声的计算及优化设计的研究。
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