过渡状态倾转旋翼气动力模拟的高效CFD方法  

Highly-Efficient CFD Method for Predicting Aerodynamic Force of Tiltrotor in Conversion Mode

作　　者：李鹏[1] 招启军[1] 汪正中 王博[1] 

机构地区：[1]南京航空航天大学直升机旋翼动力学国家级重点实验室,南京210016 [2]中航工业直升机设计研究所,景德镇333001

出　　处：《南京航空航天大学学报》2015年第2期189-197,共9页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：国家高技术研究发展计划("八六三"计划)(2012AA112201)资助项目

摘　　要：为显著减少倾转旋翼过渡飞行时气动力CFD模拟的计算代价,提出并建立了适合倾转旋翼过渡状态气动特性分析的高效混合CFD方法。首先,提出了适合于过渡状态模拟的嵌套网格系统,并发展了相应的挖洞和贡献单元搜寻方法。在此基础上,结合叶素理论和动量理论建立了旋翼气动力模拟的简化虚拟桨盘模拟方法(Virtual rotor model,VBM)。为了能够分析倾转旋翼气动力的细节特性,多层运动嵌套网格系统和单指令多数据流(Single program multiple data,SPMD)并行技术被引入来建立精确的旋翼模拟方法(Real blade model,RBM)。然后,通过将VBM和RBM方法结合,构建了适合倾转旋翼过渡状态气动特性分析的高效(Hybrid blade model,HBM)方法。最后,通过对有试验值对比的悬停状态典型旋翼和7A旋翼分别验证了VBM和RBM方法的有效性。分别采用3种方法预测了过渡状态不同倾转角下旋翼的气动特性,VBM表现出最优的计算效率,能用于倾转旋翼总体气动性能的分析。HBM方法在保证流场求解精度的基础上,相对于高精度的RBM方法节省了1/3的计算时间。Aiming at reducing the calculation amount of the CFD simulation on aerodynamic force of til- trotor in transition flight, a new highly-effective hybrid CFD method is proposed. An embedded grid system with the corresponding digging-hole and donor element searching method is presented. By com- bination of blade element theory and momentum theory, a simplified momentum source technology, i.e. virtual rotor model （VBM） is established. In order to analyze the details of aerodynamic force of the tiltrotor in transition flight, the multi-layer embedded grid system and the single program multiple data （SPMD） model parallel acceleration technology are adopted in the real blade model （RBM）. Then, a highly-efficient hybrid blade model （HBM） is established by combining VBM and RBM methods. Final- ly, a typical rotor and 7A rotor are taken as numerical examples to verify the validity of VBM and RBM respectively, and the aerodynamic force of tiltrotor in transition flight with different tilt-angles is analyzed by three methods also. It is demonstrated that VBM shows the most optimal efficiency in the sireulation of the aerodynamic saved by the HBM method solver. characteristics of the tiltrotor in conversion. compared with the RBM method with the One-third computation time is guaranteed accuracy of the flow

关 键 词：倾转旋翼 过渡状态 气动力 N-S方程 混合CFD方法 并行计算 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程] V211.3