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。
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.
作者
史磊
郭姝含
马鹏宇
熊杰
姜琪
SHI Lei;GUO Shuhan;MA Pengyu;XIONG Jie;JIANG Qi(Sino-European Institute of Aviation Engineering,Civil Aviation University of China,Tianjin 300300,China;Shanghai Aircraft Design and Research Institute,Commercial Aircraft Corporation of China Limitatetd,Shanghai 201210,China;Aircraft Maintenance Engineering Department,Xiamen Airlines Company Limited,Xiamen 361009,China)
出处
《航空动力学报》
北大核心
2025年第6期330-342,共13页
Journal of Aerospace Power
基金
翼型叶栅空气动力学国家重点实验室开放基金(6142201200509)
民航航空器适航审定技术重点实验室开放基金(SH2022070501)。
