Design and optimization research of swirl recovery vane on a propfan
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摘要:
桨扇-恢复旋流叶片（swirl recovery vane, SRV）结构因其相对对转桨扇结构较为简单的传动机构、较弱的叶尖干涉以及能够为推进系统带来推进效率增益而重新受到关注。基于叶素理论设计思想，以提供推进系统推力、带来推进效率增益为目的，采用跨声速高升阻比翼型，为跨声速桨扇恢复旋流叶片进行了气动外形设计，并将恢复旋流叶片的直径、后掠角以及沿展向叶型截面的扭转角、弦长作为优化设计变量，基于本征正交分解（POD）的降维优化设计方法对恢复旋流叶片进行了优化设计。结果表明：经过设计与优化后的恢复旋流叶片能够为推进系统带来4.83%的推进效率增益，并且使得桨扇后方流场速度分布均匀，具有良好的旋流恢复作用，可以作为高效、低碳排放航空动力系统备选方案。
Abstract:Propfan-Swirl recovery vane (SRV) structure has received renewed attention because of its relatively simple transmission mechanism, weak blade tip interference, and its ability to bring propulsion efficiency gains to the propulsion system. Based on the design idea of blade element theory, the aerodynamic shape design of the transonic propfan-SRV was carried out by using the transonic high lift drag ratio airfoil. The twist angle and chord length of the transverse section blade of the SRV, as well as the diameter and sweep angle of the SRV, were taken as the optimization design variables. A dimensionality reduction optimization design method based on proper orthogonal decomposition (POD) was used to optimize the SRV. The results showed that the optimized SRV can bring 4.83% propulsive efficiency gain to the propulsion system, and make the velocity distribution of the flow field behind the propfan more uniform, which had a good swirl recovery effect and can be used as an efficient and low-carbon aviation power system alternative.
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图 3 计算域边界条件设置及网格
Figure 3. Size of computational zone and boundary conditions and grid
图 4 起飞工况下前进比-功率系数特性
Figure 4. Characteristics of propfan’s advance ratio and power coefficient at take-off condition
图 5 巡航工况下前进比-功率系数及效率特性
Figure 5. Characteristics of propfan’s advance ratio, power coefficient and efficiency at cruise condition
图 6 恢复旋流叶片所采用叶型的气动特性
Figure 6. Aerodynamic characteristics of airfoil used in swirl recovery vane
图 8 恢复旋流叶片弦长与扭转角沿展向分布
Figure 8. Spanwise distribution of chord length and twist angle of swirl recovery vane
图 10 桨扇恢复旋流叶片总推进效率
Figure 10. Total propulsive efficiency of propfan and swirl recovery vane
图 11 恢复旋流叶片推力系数展向分布
Figure 11. Spanwise distribution of thrust coefficient of swirl recovery vane
图 12 恢复旋流叶片叶型截面压力系数弦向分布
Figure 12. Chordwise distribution of section airfoil’s pressure coefficient of swirl recovery vane
图 13 桨扇恢复旋流叶片两轴向位置截面旋向动能分布
Figure 13. Distribution of swirl kinetic energy in the two axial positions of swirl recovery vane
图 14 各阶基模态能量以及前d阶基模态能量占比示意图
Figure 14. Proportion of each order fundamental mode energy and the first d order fundamental mode energy
图 15 种群目标函数值最优解变化示意图
Figure 15. Change of optimal solution of population objective function value
图 16 恢复旋流叶片扭转角展向分布变化示意图
Figure 16. Spanwise distribution of twist angle of swirl recovery vane before and after optimization
图 17 恢复旋流叶片优化前后相对位置关系及几何变化
Figure 17. Relative position and geometric change of swirl recovery vane before and after optimization
图 18 优化前后桨扇恢复旋流叶片结构总推进效率
Figure 18. Total propulsive efficiency of propfan and swirl recovery vane before and after optimization
图 19 优化前后恢复旋流叶片推力系数展向分布
Figure 19. Spanwise distribution of thrust coefficient of swirl recovery vane before and after optimization
图 20 恢复旋流叶片叶型截面优化前后压力系数弦向分布
Figure 20. Chordwise distribution of pressure coefficient of swirl recovery vane’s section airfoil before and after optimization
图 21 优化前后恢复旋流叶片两轴向位置截面旋向动能分布
Figure 21. Distribution of swirl kinetic energy in two axial positions of swirl recovery vane before and after optimization
表 1 采用不同网格量得到的计算结果
Table 1. Results of different numbers of grid
网格数量/万 CT_pf 推力系数
相对误差/%CP_pf 功率系数
相对误差/%290 0.6588 0.98 3.1139 0.37 453 0.6517 3.1271 836 0.6511 0.11 3.1273 0.05 
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表 2 优化前后恢复旋流叶片推力及推进效率增益对比
Table 2. Thrust and propulsive efficiency of swirl recovery vane before and after optimization
参数 初始设计
构型优化设计
构型变化量 相对
变化率/%推力/N 3.59 5.17 1.58 44$（\uparrow ） $ 推进效率增益/% +3.53 +4.83 +1.30
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