低HSI噪声旋翼桨尖外形优化设计方法
收稿日期: 2014-06-05
修回日期: 2014-09-02
网络出版日期: 2014-09-17
基金资助
国家自然科学基金(11272150); 江苏高校优势学科建设工程资助项目
Optimization design method for rotor blade-tip shape with low HSI noise characteristics
Received date: 2014-06-05
Revised date: 2014-09-02
Online published: 2014-09-17
Supported by
National Natural Science Foundation of China (11272150); Project Funded by the Priority Academic Development of Jiangsu Higher Education Institutions
建立了一套基于计算流体力学(CFD)/FW-H_pds方程(Ffowcs Williams-Hawkings equations with penetrable data surface)的气动噪声预估技术和组合优化算法的低噪声旋翼桨尖平面外形设计方法。首先,采用积分形式的可压雷诺平均Navier-Stokes(RANS)方程作为旋翼流场求解控制方程,围绕旋翼流场的网格采用嵌套网格方法生成。在优化过程中,桨叶网格生成采用提出的高效参数化的网格自动生成方法。在建立的CFD方法求解基础上,采用基于可穿透旋转积分面的鲁棒性较好的FW-H_pds方程来求解旋翼高速脉冲(HSI)噪声。然后,以降低旋翼HSI噪声为目标,以旋翼悬停气动性能为约束,提出具备前掠-后掠-尖削等组合特征的桨尖外形方案并进行优化分析。将基于拉丁超立方(LHS)方法和径向基函数(RBF)的代理模型方法耦合到遗传算法过程中,建立了一种高效的组合优化算法。在当前的计算状态下,优化后的桨尖外形的负压峰值相比于矩形桨叶降低了58.4%,优化后的桨叶有效地减弱了旋翼桨尖区域的跨声速"离域化"现象,因此可以降低旋翼HSI噪声特性,同时可以减弱旋翼桨尖涡强度达30%,旋翼悬停性能提高了2%~3%。
朱正 , 招启军 . 低HSI噪声旋翼桨尖外形优化设计方法[J]. 航空学报, 2015 , 36(5) : 1442 -1452 . DOI: 10.7527/S1000-6893.2014.0208
Based on computational fluid dynamics (CFD)/FW-H_pds methods (Ffowcs Williams-Hawkings equations with penetrable data surface) and hybrid optimization technique, an optimization design procedure for rotor planform with low HSI noise characteristics is established. In this solver, based on the moving-embedded grid methodology, a CFD simulation method for the aerodynamic characteristics of rotor is developed by solving the compressible Reynolds-averaged Navier-Stokes (RANS) equations. During the optimization process, the high-qualified blade grids are generated by a high-efficient parameterized method. Additionally, the high-speed impulsive (HSI) noise characteristics generated by transonic helicopter rotor are analyzed through a robust prediction method based on FW-H_pds equations. Aimed at the minimization of the absolute sound pressure peak value, optimization analyses based on the rotor blade with double-swept and tapered tip have been accomplished with the aerodynamic performance in hover as constraints. The genetic algorithm and surrogated model based on Latin hypercube sampling (LHS) design and radial basis function (RBF) are combined as a hybrid optimization technique. Compared with rectangular blades, it shows that the minimum acoustics pressure of rotor with optimized blade-tip shape is decreased by 58.4% at the present calculating condition. For the rotor with optimized blade-tip, the HSI noise level can be reduced effectively due to its weaker transonic "delocalization" phenomenon in the region of blade-tip and the blade-tip vortex strength is decreased by 30% which results in the improvement of the FM about 2%-3%.
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