Multi-objective optimization remodeling of eroded leading edge of supersonic fan blade
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摘要:
针对航空发动机风扇超声叶型前缘侵蚀造成的性能衰退问题，构建风扇前缘曲率控制点与总压损失系数、总压恢复系数和材料去除率3个优化目标之间的Kriging模型，采用第二代非劣排序遗传算法（NSGA-Ⅱ）对侵蚀叶型进行优化修型。结果显示：材料去除率与总压损失系数呈负相关，与总压恢复系数呈正相关，相比于侵蚀叶型，前缘修型后叶型总压损失系数降低8.74%，总压恢复系数提升2.31%，材料去除率为1.94%。优化叶型能够改善前缘流动，减弱唇形激波强度，缩小亚声速区域面积。侵蚀叶型的入射波与通道正激波相交于吸力面，与边界层的干扰作用严重，优化叶型使通道激波前移，激波提前在通道内交汇，从而抑制尾迹发展。
Abstract:To address the performance degradation caused by eroded leading edge of aero-engine supersonic fan blade, a Kriging model between the curvature control point of fan blade leading edge and three optimization objectives of total pressure loss coefficient, total pressure recovery coefficient and material removal rate was constructed, and the second Non-dominated Sorting Genetic Algorithm (NSGA-Ⅱ) was used to optimize the eroded leading edge. The results showed that the material removal rate was negatively correlated with the total pressure loss coefficient, and positively correlated with the total pressure recovery coefficient. Compared with the eroded cascade, the total pressure loss coefficient of the blade with trimmed leading edge decreased by 8.74%, the total pressure recovery coefficient increased by 2.31%, and the material removal rate was 1.94%. Optimized cascade was able to improve the flow around the leading edge, and reduce the intensity of the lip shock and the area of the subsonic region. The bow shock of the eroded cascade intersected the passage normal shock on the suction side, which intensified the interaction with the boundary layer. The optimized cascade made the passage shock move forward, and the shock waves met in advance within the passage, thus restraining the development of the wake.
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图 3 风扇90%叶高叶型及侵蚀前缘模型
Figure 3. 90% spanwise airfoil of fan blade and eroded leading edge model
图 6 ARL-SL19叶栅实验与仿真结果对比
Figure 6. Comparison of simulated and experimental results of ARL-SL19 cascade
图 8 前缘曲率半径和厚度控制点的分布
Figure 8. Distribution of leading edge radius of curvature and thickness control points
图 15 300代Pareto解集与前沿曲线
Figure 15. Pareto solution set and frontier curve after iteration for 300 generations
图 17 设计工况下静压系数沿相对弦长分布
Figure 17. Distribution of static pressure coefficient along relative chord length at designed point
图 18 非设计工况下静压系数沿相对弦长分布
Figure 18. Distribution of static pressure coefficient along relative chord length at non designed point
图 19 不同来流马赫数下的叶型总压损失系数
Figure 19. Total pressure loss coefficient at different inlet Mach numbers
图 22 非设计工况下相对马赫数分布云图
Figure 22. Contours of relative Mach number at non designed point
图 24 吸力面边界层厚度沿相对弦长分布
Figure 24. Distribution of boundary layer thickness on suction surface along relative chord length
图 25 吸力面形状因子沿相对弦长分布
Figure 25. Distribution of shape factor of suction surface along relative chord length
表 1 叶栅相关参数
Table 1. Related parameters of cascade
参数 数值 弦长/mm 232.19 稠度 1.31 安装角/（°） 34.6 进口几何角/（°） 58.7 最大厚度/mm 7.0 进口马赫数 1.2 
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表 2 优化变量取值范围
Table 2. Range of optimization variables
优化变量 上阙值/mm 下阙值/mm P1 0.157 0.324 P2 0.186 0.447 P3 0.201 0.534 P4 0.213 0.507
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